CN215944856U - Fixed wing scouting and hitting integrated unmanned aerial vehicle model - Google Patents
Fixed wing scouting and hitting integrated unmanned aerial vehicle model Download PDFInfo
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Abstract
The utility model discloses a fixed wing scouting and printing integrated unmanned aerial vehicle model, which comprises a body, wings and an empennage, wherein the wings are of a single-beam structure and comprise wing spars and wing ribs which are connected with each other; meanwhile, the overall design parameters and the design indexes of the low-cost fixed-wing scouting and printing integrated unmanned reconnaissance plane with the maximum takeoff weight of 2.5 kilograms are determined by the fixed-wing scouting and printing integrated unmanned plane model design method, and meanwhile, a specific model of the fixed-wing scouting and printing integrated unmanned reconnaissance plane is designed.
Description
Technical Field
The utility model relates to the technical field of aviation reconnaissance and detection equipment, in particular to a fixed-wing reconnaissance and beating integrated unmanned aerial vehicle model.
Background
An Unmanned Aerial Vehicle (Unmanned Aerial Vehicle), which is a self-powered Unmanned Aerial Vehicle capable of carrying various electronic devices, performing various tasks, being operated by an operator through a radio remote control device or being operated by an automatic remote control program device of the Unmanned Aerial Vehicle; the unmanned aerial vehicle has the greatest characteristic that a pilot does not need to drive and operate in the fuselage, and almost all functions of the manned aircraft can be completed; therefore, the unmanned aerial vehicle does not need to be provided with a device which can enable a pilot to complete the airplane operation function, such as a pilot seat, an operation rod and the like, and also does not need to be provided with a device which is necessary for the manned aircraft to maintain the life of the pilot, such as a cabin pressurization system and the like, and has the characteristics of light structure, simple structure, easy operation, low use cost, safety and high efficiency in use and the like;
in recent years, with rapid development of relevant technologies of unmanned aerial vehicles, research on military unmanned reconnaissance aircraft and civil surveying and mapping unmanned aerial vehicles in China has breakthrough progress, and in the aspect of part of key unmanned aerial vehicle technologies, researchers in China have gone the front of the world; but current unmanned aerial vehicle is complicated to the structure that goes man-machine design because the operation requirement, leads to the maintenance difficulty, also leads to aircraft self weight to be difficult to control simultaneously because the chooseing for use of external material, influences unmanned aerial vehicle's performance.
SUMMERY OF THE UTILITY MODEL
Aiming at the existing problems, the utility model aims to provide a fixed-wing scouting and hitting integrated unmanned aerial vehicle model which has the characteristics of obtaining good low-speed aerodynamic performance, reducing the influence of wing wake flow and effectively utilizing propeller slipstream to improve the aerodynamic efficiency of an empennage.
In order to achieve the purpose, the technical scheme adopted by the model is as follows:
a fixed wing scouting and hitting integrated unmanned aerial vehicle model comprises a vehicle body, wings and a tail wing;
the aircraft body is a truss girder type aircraft body and comprises stringers, main stringers and wing body connecting pieces, wherein the main stringers are symmetrically arranged, the stringers are horizontally arranged on the two main stringers, the wing body connecting pieces are symmetrically arranged at the upper ends of the middle parts of the top stringers and connected with the wings, and an aircraft body mask is arranged on the outer side of the integral aircraft body;
the wing is of a single-beam structure and comprises a wing spar and a wing rib which are mutually connected, and the wing is connected with the fuselage through a wing body connecting piece;
the empennage is a symmetrical wing type and is connected with the tail end of the machine body through an empennage carbon tube.
Preferably, the fuselage still include third baffle, first baffle, motor mounting bracket, second baffle and bulkhead, the bulkhead vertically sets up on the rectangle fuselage, and mutually contact and mutually perpendicular with the stringer, first baffle, second baffle and third baffle are all set up in the frame that stringer and bulkhead formed.
Preferably, the bulkhead comprises a common bulkhead, a first reinforcing bulkhead and a second reinforcing bulkhead, the second reinforcing bulkhead is arranged at the tail end of the machine body, and the second reinforcing bulkhead is provided with a lightening hole and a first through hole; the first reinforced partition frames are arranged on two sides of the installation position of the middle wing of the fuselage, a common partition frame is arranged between the two first reinforced partition frames, and the second partition plates are symmetrically arranged on purlins on the lower side of the installation position of the middle wing; the front end of the machine body is also provided with a common partition frame and a first reinforced partition frame, and the third partition plate is arranged on a stringer on the upper side of the first partition plate; the motor mounting bracket is installed and is strengthened between bulkhead and the first bulkhead of strengthening at the second, and strengthens the bulkhead at the second and still be provided with ordinary bulkhead with the first bulkhead of strengthening, be provided with the second fixed orifices on the ordinary bulkhead, the second fixed orifices uses with the cooperation of first cross-under hole, fixes fin carbon tube.
Preferably, the wing spar is arranged at 30% chord of the wing, and comprises a main wing section spar and an outer wing section spar, the outer wing section spar is symmetrically arranged at two sides of the main wing section spar, the main wing section spar and the outer wing section spar respectively comprise a symmetrically arranged auxiliary wing spar and a beam web plate, and the beam web plate is arranged at one side of the auxiliary wing spar; a main wing beam is further arranged between the two symmetrically arranged auxiliary wing beams of the main wing section wing beam, an outer wing beam and a trailing edge wing beam are further arranged at the 65% chord position of the rear part of the main wing section wing beam wing, and the outer wing beams are symmetrically arranged; the leading edge of main wing section spar and the leading edge of outer wing section spar all are provided with the leading edge bead, and are provided with the leading edge balsa wood mask at leading edge bead leading edge, the front edge balsa wood mask wraps up the preceding 30% chord range part of wing, forms D type wing box structure with main spar, secondary spar, web, wing outer spar, trailing edge spar and leading edge bead.
Preferably, the wing ribs comprise a first reinforced rib, a second reinforced rib, a common rib and a half rib, the first reinforced rib is arranged at two sides of the wing installation position of the main wing section, the first reinforced rib is provided with an installation hole which is matched with a connecting hole arranged on the wing body connecting piece for use, and the common rib is arranged between the two first reinforced ribs; the second reinforcing rib is arranged at the joint of the main wing panel and the outer wing panel; the half rib is arranged between the second reinforcing rib of the outer panel and the normal rib.
Preferably, the wing is further provided with a wing connecting mechanism, and the wing connecting mechanism is arranged between the main wing section and the outer wing section and comprises a wing upper part connecting assembly and a wing lower part connecting assembly.
Preferably, wing upper portion coupling assembling set up on the aileron roof beam of main wing section and outer wing section upside, including setting up the inserted bar on main wing section aileron roof beam, set up slot and locating part on outer wing section aileron roof beam, the inserted bar uses with the slot cooperation, just be provided with a plurality of spacing grooves on the inserted bar, spacing groove uses with the spacing dop cooperation of locating part lower extreme, the locating part passes through the clamp plate and installs on outer wing section aileron roof beam, just clamp plate and locating part swing joint still are provided with spacing spring between clamp plate and locating part.
Preferably, the lower wing part connecting assembly is arranged on the lower surface of the wing and comprises a hinge mechanism, the hinge mechanism is connected with a second reinforcing wing rib at the joint of the wing and arranged on the lower side of the second reinforcing wing rib, the hinge mechanism comprises a first turning page, a second turning page and a rotating shaft, the first turning page is arranged between two second reinforcing wing ribs close to the main wing section, a rotating shaft mounting groove is formed in the first turning page, the rotating shaft is mounted in the rotating shaft mounting groove through a bearing, a plurality of spline grooves are equidistantly formed in the rotating shaft and connected with a hoop, an inserting groove is formed in the hoop, the inserting groove is matched with an inserting block arranged on the second turning page for use, and the second turning page is arranged between two second reinforcing wing ribs close to the outer wing section; and a gear shaft section is also arranged on the rotating shaft, the gear shaft section is meshed with the gear, the gear is arranged at the power output end of the motor, the motor is arranged on the first turnover page, and the second turnover page is driven to rotate by the motor.
Preferably, the empennage is a symmetrical wing type and comprises a horizontal empennage and a vertical empennage, the vertical empennage is symmetrically arranged at two ends of the horizontal empennage, the horizontal empennage comprises wing spars, wing walls, a connecting ring, common horizontal tail wing ribs and reinforced horizontal tail wing ribs, the wing spars are arranged at the front edge of the wing, the wing walls are arranged at the rear edge of the wing, the common horizontal tail wing ribs and the reinforced horizontal tail wing ribs are arranged between the wing walls and the wing spars, the connecting ring is arranged between the wing walls and the wing spars and is matched with an empennage carbon tube for use, and the reinforced horizontal tail wing ribs are arranged at two sides of the connecting ring; the vertical tail wing is rotatably arranged at two ends of the horizontal tail wing through a reinforced horizontal tail wing rib, and lightening holes are formed in the vertical tail wing.
The model has the beneficial effects that the utility model discloses a fixed-wing scouting and batting integrated unmanned aerial vehicle model, and compared with the prior art, the model has the improvement that:
the utility model obtains a fixed wing scouting and batting integrated unmanned aerial vehicle model through a fixed wing scouting and batting integrated unmanned aerial vehicle model design method, wherein in the model: (1) the Clark Y airfoil type with high lift-drag ratio and high incidence angle flight performance is selected as the wing, and the geometrical shape of the plane of the wing is a rectangular wing plus an elliptical wing tip with high aspect ratio, so that good low-speed aerodynamic performance can be obtained; (2) in order to accommodate various equipment and task loads, the size of the machine body is large, and a power system adopts a waist pushing mode; (3) the airplane adopts a low-mounted common empennage and a double-vertical-tail structure, thereby effectively utilizing the slipstream of the propeller to improve the aerodynamic efficiency of the empennage while avoiding the slipstream impact of the propeller and reducing the influence of the wake flow of the wings; (4) the aircraft adopts a hand-throwing take-off mode, so that an aircraft landing gear is further omitted, and unnecessary structural weight is reduced; through the arrangement, the model has the advantages that the good low-speed aerodynamic performance can be obtained, the influence of wing wake flow is reduced, meanwhile, propeller slipstream is effectively utilized to improve the aerodynamic efficiency of the empennage, and a research basis is provided for further designing the fixed-wing unmanned aerial vehicle for observing and driving the whole unmanned aerial vehicle.
Drawings
FIG. 1 is a schematic structural diagram of a fixed-wing scouting-beating integrated unmanned aerial vehicle model according to the present invention.
Fig. 2 is a schematic structural view of the fuselage of the present invention.
Fig. 3 is a schematic structural view of the wing of the present invention.
FIG. 4 is a schematic structural view of a main wing section spar of the present invention.
FIG. 5 is a schematic view of the structure of the main and outer panels of the present invention.
FIG. 6 is a schematic view of the structure of the junction of the main wing panel and the outer wing panel of the present invention.
FIG. 7 is a front view of the junction of the main panel and the outer panel of the present invention.
FIG. 8 is an enlarged, fragmentary view of the junction of the main panel and the outer panel of the present invention taken from the front view A.
FIG. 9 is a top view of the junction of the main panel and the outer panel of the present invention.
Figure 10 is an exploded view of the hinge mechanism of the present invention.
Figure 11 is a schematic diagram of the structure of a hoop according to the present invention.
Fig. 12 is a schematic view of the structure of the tail wing of the present invention.
In fig. 1-12: 1. the wing comprises a fuselage, 11, stringers, 12, main trusses, 13, wing body connectors, 14, a common bulkhead, 15, a first reinforcing bulkhead, 16, a second reinforcing bulkhead, 161, a first through hole, 17, a third partition, 18, a first partition, 19, a motor mounting bracket, 10, a second partition, 2, a wing, 21, a main spar, 22, a secondary spar, 221, an insert rod, 2211, a limiting groove, 222, an insert groove, 223, a pressing plate, 224, a limiting member, 225, a limiting spring, 23, a beam web, 24, an outer wing spar, 25, a rear wing spar edge, 26, a leading edge strip, 27, a leading edge balsa panel, 28, a first reinforcing rib, 29, a common rib, 20, a second reinforcing rib, 201, a spring bolt, 202, a carbon buckle, 203, a hinge mechanism, 2031, a first turned page, 20311, a shaft mounting groove, 2032, a second turned page, 21, a second turned page, 3, 20331. spline groove, 20332 gear shaft section, 2034 motor, 2035 gear, 2036 hoop, 20361 plug groove, 2037 bearing, 3 tail wing, 31 wing wall, 32 wing beam, 33 connecting ring, 34 common flat tail wing rib, 35 strengthening flat tail wing rib, 36 vertical tail wing.
Detailed Description
In order to make those skilled in the art better understand the technical solution of the present model, the following describes the technical solution of the present model with reference to the drawings and the embodiments.
Example 1: referring to the attached figures 1-12, a fixed-wing scouting and batting integrated unmanned aerial vehicle model design method comprises
The method comprises the following steps: appearance and power design stage of fixed wing scouting and batting integrated unmanned aerial vehicle model
S10, determining the overall performance parameters and the electrical system of the airplane according to preset design requirements, wherein the overall performance parameters comprise basic performance indexes, design parameters and pneumatic layout, the electrical system comprises a motor, a propeller, a battery, an electronic speed regulator and the like, and the electrical system specifically comprises:
s101, basic performance index design process
The 2.5 kilogram-level fixed wing unmanned reconnaissance aircraft designed by the model can select different electronic equipment according to different task requirements, carries various task loads to perform tasks such as close-range reconnaissance, striking, aerial photography, search and rescue and the like, and requires that the whole aircraft has the characteristics of light weight, strong structure, simplicity in manufacture, convenience in maintenance and the like; the system can fly according to a preset navigation point based on a GPS satellite positioning system, and realizes automatic return flight and manual landing under the control of a ground station;
according to the preset design requirements of the model, the basic performance indexes of the airplane are determined as shown in the following table 1:
table 1: basic performance index of unmanned aerial vehicle
By referring to design experience of the fixed-wing unmanned aerial vehicle and relevant data such as model airplane flight principle, the maximum weight of the target unmanned aerial vehicle during takeoff is M02.5kg, the maximum thrust is selected to be Fmax2kg motor, wing area S0.26 m2；
(1) Taking-off wing load:
(2) takeoff thrust-weight ratio P0：
From the above type can get the plane to get upThe wing load during flying is 11.54kg/m2The maximum takeoff thrust-weight ratio is 0.8;
s102, designing parameters of main unmanned aerial vehicle
(1) Maximum flying speed Vmax
When the airplane flies at a constant speed at a certain height h, the maximum thrust is equal to the drag, and the maximum flat flying speed V exists at the momentmaxThe basic equation is:
in the formula: rhohIs the air density over h height, CxThe total drag coefficient of the airplane is related to the rotating speed of a propeller and the flying speed of the airplane and is difficult to directly calculate, so that the maximum flat flying speed of the airplane is estimated to be 25m/s according to experience;
(2) lift-drag ratio of unmanned aerial vehicle
Lift and lift coefficient: according to the Bernoulli equation, the magnitude of the wing lift force can be calculated by using a formula through a wind tunnel test or a software simulation result, wherein the formula is as follows:
in the formula: l is the lift force, and the unit is 'N'; rho is air density, and the unit is' kg/m3", taking 1.226kg/m for the value of ρ to be calculated for convenience3(ii) a V is the airflow relative to the aircraft speed in units of "m/s"; s is the wing area of the unmanned plane, and the unit is m2”；CLIs the wing lift coefficient of the unmanned aerial vehicle;
resistance and coefficient of resistance: the calculation of the resistance is similar to that of the lift force, and can also be calculated by a calculation formula, wherein the formula is as follows:
in the formula: d is the resistance, in "N"; rho is air density, and the unit is' kg/m3", the value of ρ is taken to be 1.226kg/m for easy calculation3(ii) a V is the airflow relative to the aircraft speed in units of "m/s"; s is the wing area of the unmanned plane, and the unit is m2”；CDIs the unmanned aerial vehicle resistance coefficient;
through the above calculation formula, the general fixed wing unmanned aerial vehicle overall design experience and the design requirement of the model unmanned aerial vehicle are combined, and the basic main design parameters of the model unmanned aerial vehicle are determined, as shown in the following table 2:
table 2: main design parameters of unmanned aerial vehicle
S103. pneumatic layout
The aerodynamic layout of the airplane directly influences the performance of the airplane and has great influence on the overall structural design of the airplane, the aerodynamic layout of the fixed-wing unmanned aerial vehicle has various forms, wherein the normal layout with the front main wing and the horizontal tail at the back is the aerodynamic layout which is most widely applied and has the most mature technology at present, and common passenger planes and freight planes mostly adopt the aerodynamic layout design, the control performance of the aerodynamic layout is stable, the aerodynamic layout is suitable for the task requirements of the unmanned aerial vehicle designed by the model, so the unmanned aerial vehicle designed by the model adopts the normal aerodynamic layout;
s104. design of power system
The power sources adopted during the design of the fixed-wing unmanned aerial vehicle are mainly divided into two power sources, namely an oil power source and an electric power source, and in order to simplify the internal structure of the unmanned aerial vehicle and reduce the weight of the unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle designed by the model adopts the electric power source; the power system mainly comprises an electronic speed regulator, a motor, a battery and a propeller; the electric speed regulator is used for controlling the current flowing through the motor, and the motor converts the electric energy into mechanical energy to drive the propeller to rotate so as to generate thrust meeting the flight requirement of the airplane;
(1) design of a motor and a propeller:
the electric fixed wing unmanned aerial vehicle mainly adopts a permanent magnet type direct current motor as a power source, the motor mainly comprises a brush motor and a brushless motor, the two motors have the same structure and are composed of a rotor and a stator, but the brushless motor adopts a permanent magnet as the rotor and an electronic switch to replace a commutator and an electric brush, so that the internal mechanical friction is reduced, the efficiency is improved, and compared with the brush motor, the electric fixed wing unmanned aerial vehicle has longer service life, higher reliability and smaller electromagnetic interference, so the brushless motor is selected as the power device of the designed fixed wing unmanned aerial vehicle;
the wingspan of the unmanned aerial vehicle designed by the model is 1.3m, the maximum takeoff weight is 2.5kg, and the endurance time is designed to be 20 min; the required thrust of the unmanned aerial vehicle in a cruising state is about 1kg through the use and design experience of the same type of unmanned aerial vehicle, but in order to ensure that the aircraft realizes hand throwing take-off and has enough maneuverability to ensure the safe flight of the aircraft when encountering sudden wind, the margin of a power device is set to be 2, and the maximum thrust required by the fixed wing unmanned aerial vehicle designed by the model is about 2 kg; the motor must select the propeller matched with the motor, and when the diameter of the propeller is too large, the rotating speed of the motor during working cannot reach the optimal rotating speed required by the cruise flight of the airplane; when the diameter of the propeller is too small, the rotating speed of the propeller passes through the block, the motor efficiency is too low, the energy consumption is large, the maximum endurance time is reduced, and after various motors are analyzed by comparison, in order to meet the requirement of the unmanned aerial vehicle on the hand-throwing takeoff thrust and meet the thrust and power required by cruise, the scheme of matching the Langyu X2814(1250kv) motor with the APC11 5.5 paddle is determined to be used as the power configuration of the unmanned aerial vehicle;
(2) design of battery
The battery provides electric energy for an electric unmanned aerial vehicle power device and other onboard electronic equipment, the type of the battery used by the existing electric unmanned aerial vehicle is basically a lithium polymer battery, and compared with other types of batteries, the battery has the advantages of light weight, high energy density and the like, no redundant electrolyte exists in the lithium polymer in the battery, and the battery has stable performance, so that the lithium polymer battery is selected as a power supply for designing the fixed wing unmanned aerial vehicle;
according to preliminary calculation and use experience, in order to ensure that the performance of the airplane does not obviously decline in the 20-minute endurance time period, a format 5300mah/3S/11.1v 30C lithium polymer battery is selected as a power supply of the fixed wing unmanned aerial vehicle and a power supply of flight control equipment, and a format 2200mah/3S/11.1v 25C lithium polymer battery is selected as a power supply of image transmission equipment and a matched camera;
(3) electronic governor design
An electronic governor (ESC) is a speed regulation system of a motor equipped for an electric unmanned aerial vehicle, and the electronic governor can be divided into a brush-type governor and a brushless governor according to the type of the matched motor, wherein the brushless governor is responsible for converting direct current input by a battery and outputting the direct current into three-phase alternating current to drive the brushless motor; meanwhile, receiving a pulse modulation signal output by flight control to change the power of the motor; meanwhile, the model supplies power to electronic equipment such as a receiver, a steering engine, a flight control and the like, and selects a series of good heaven-person 60A brushless electric regulators according to the model of the brushless motor and the matched battery selected above;
s102, determining the geometrical shape of the plane of the wing and the wing profile parameters of the wing, and specifically comprising the following steps:
s1021, selecting a large-aspect-ratio rectangular wing with a root-tip ratio of 1, designing an inclined wing rib at the wing tip of the airplane to further reduce induced resistance, enabling the profile of the wing tip to be arc-shaped, enabling the plane shape of the wing of the airplane to be the rectangular wing plus an arc wing tip, and selecting a wing section with a relative thickness of about 12% and a maximum relative camber of about 2% -4% to enable the wing of the airplane to have good large attack angle performance;
screening in a profile library of Profili software according to the preset conditions to obtain 5 main alternative profiles, namely CLARKY, CLARKZ, NACA 2412, NACA 3412 and GOE 389;
s1022, the Reynolds number represents the state of the boundary layer of the surface of the wing, the larger the Reynolds number is, the easier the boundary layer of the surface of the wing becomes into a turbulent boundary layer, and the formula for calculating the Reynolds number is as follows:
in the formula: ρ is the air density; v is the relative air flow velocity; b is the wing chord length; mu is air viscosity, and the unit is 'Pa.s';
the cruise speed of the fixed wing unmanned aerial vehicle designed by the model is 18m/s, the cruise height is about 100m, and the Reynolds number Re is approximately equal to 24000 at the moment; when the speed is 8m/s, the Reynolds number Re is approximately equal to 108000, so that a polar curve of the airfoil polar curve chart is selected when the Reynolds number is 80000-250000; as can be known from the graphs of the lift coefficient and the drag coefficient of the last 5 candidate airfoils, the changes of the drag coefficient and the lift coefficient of the 5 candidate airfoils are related to the change of the attack angle; within a certain attack angle range, the lift coefficient is increased along with the increase of the attack angle, and after the critical attack angle, the lift coefficient is decreased along with the increase of the attack angle; the resistance coefficient is firstly reduced along with the increase of the attack angle and then increased along with the increase of the attack angle;
in order to ensure that the airplane has good high-incidence-angle flight performance, the position of a wing transition point at a high incidence angle needs to be checked, 5 wings are respectively created by using 5 wings in XFLR5 software, and 5 wing transition point diagrams at an incidence angle of 11 degrees and an incoming flow relative speed of 18m/s are obtained through analysis;
from the position diagrams of transition points at 11 ° angles of attack of 5 different airfoil profiles in fig. 2, it can be known that the transition point at the large angle of attack of the CLARK Y airfoil profile is closest to the trailing edge and most nonvolatile;
s1023, the CLAR Y, CLARK Z and NACA 3412 wing profiles have the maximum lift-drag ratio within the range of 2-4 degrees of attack angle as can be known from the figure 2; comprehensively considering that the CLAR Y airfoil is not easy to stall at a large attack angle, the lift coefficient is higher than that of an NACA 3412 airfoil at a small attack angle, the CLARK Z airfoil has the highest lift coefficient at a small attack angle but a lower lift-drag ratio, and compared with the CLAR Y airfoil, the CLAR Y airfoil is easy to stall at a large attack angle and does not meet the design requirement, so that the wing of the unmanned aerial vehicle designed by the method adopts the CLAR Y airfoil;
s103. design unmanned aerial vehicle fuselage
Different types of airplanes often have different emphasis points when the aerodynamic appearance design is carried out, for a high-speed airplane, the aerodynamic performance of the airplane is mainly considered in priority when the airplane body design is carried out, and on the premise of having good aerodynamic performance, the coordination design is carried out on the connection problem of each part and the loading problem of internal equipment; for a low-speed airplane, the convenience of connection between the airplane body and parts such as wings and horizontal tails and the convenience of loading electronic equipment in the airplane body are mainly considered when the airplane body is designed;
s1031, the common freight transport aircrafts and surveying and mapping unmanned aerial vehicles mostly adopt an upper single wing layout, namely a wing layout mode that wings are arranged at the top of a fuselage; the single wing has a single structure, and the wings can be designed into a whole; the fuselage with the upper single wing layout can be regarded as a large part hung below the wings, the structural design of the fuselage is simpler, the layout of the truss girder and the partition frame of the fuselage is flexible and convenient, the layout of the missile throwing cabin is convenient, and the fuselage can be easily arranged at the gravity center position of the aircraft fuselage; in the aspect of aerodynamics, the upper surface of the upper single wing is basically flush with the upper surface of the airplane body, mutual interference does not exist between low-pressure areas of an airplane flow field basically, and airflow separation is not easy to occur; the upper single wing and the wing body of the fuselage are high in fusion degree, and a configuration with a high lift-drag ratio is easily formed; the gravity center of the upper single-wing aircraft is suspended below the wings, the distance between the gravity center and the perpendicular line of the lift center is the farthest, the natural rolling stability is the best, the aircraft has stronger flight attitude stability, and the capability of automatically recovering the stability is high. The advantages show that the single-wing layout is suitable for the airplane with a simpler control system design or a remote flight task. Therefore, the fixed wing unmanned aerial vehicle designed by the model adopts an upper single wing layout, and the rear part of the upper surface of the vehicle body is opened so as to be convenient for mounting wings;
s1032, after the far-front incoming flow enters the propeller from the front of the rotating surface of the propeller, the speed is increased, and the far-front incoming flow flows out through the rotating surface of the propeller to form a tubular air flow with a cross section slightly smaller than the rotating surface and a speed larger than that of the front incoming flow, namely the propeller slipstream; when the wing is arranged behind the propeller, the slipstream flow field can be influenced by the wing to change, and then the side washing phenomenon and the blocking phenomenon can be generated, and the flow field can be uneven; in order to achieve the design target of the model, a camera needs to be installed right in front of the aircraft body for a flyer to use so as to realize first visual angle flight control, and the lower half part in front of the aircraft body is provided with an opening so as to arrange a retractable ground reconnaissance cloud deck in the cabin; if a motor base is arranged on the machine head, the propeller rotating at high speed can shield the visual angle of a camera of a flying hand of the machine head of the unmanned aerial vehicle, so that flying control is influenced, and under the condition that equipment such as a tripod head is arranged on the lower half part of the machine head of the unmanned aerial vehicle, the motor base is structurally difficult to install, so that the unmanned aerial vehicle adopts a waist push mode, and the motor base is arranged behind the wings and is higher than the rear part of the machine body;
s1033, compared with a fixed-wing airplane with a front-mounted motor, the airplane with the waist pushing layout is arranged on the rear side of the motor, thrust loss is smaller, propulsion efficiency is higher, and the airplane is suitable for hand throwing takeoff; in order to ensure the normal rotation of the propeller, the motor shaft is positioned at a vertical distance of more than 5.5 inches (about 13.97cm) from the rear fuselage tail carbon rod. The motor is arranged high, the thrust line passes over the center of gravity of the airplane, and the thrust generated by the propeller forms a low-head moment on the center of gravity of the airplane, so that the flying stability of the airplane is improved;
s1034, arranging an aircraft missile bay at an opening of a fuselage right below the aircraft wing, setting the gravity center of the whole aircraft at the chord position with the horizontal distance of 1/5 primarily, and setting the vertical distance at about 147mm, namely the position of the missile bay, so as to ensure that the gravity center of the whole aircraft does not change greatly after the aircraft is launched and maintain the stable flight performance of the aircraft;
s104, determining empennage wing section parameters, wherein the specific process comprises the following steps:
s1041, horizontal tail parameter setting: the horizontal tail is an important component for ensuring the pitching operation capability and stability of the airplane, the parameter representing the strength of the horizontal tail to the pitching operation capability of the airplane is the capacity of the horizontal tail, and the calculation formula is as follows:
(1) setting the volume A of the horizontal tailHorizontal tailComprises the following steps:
in the formula (7), AHorizontal tailThe tail capacity is the tail capacity, which is a ratio and has the unit of 1; sHorizontal tailIs the area of the horizontal tail, and the unit is m2”；LHorizontal tailThe horizontal tail force arm is a horizontal tail force arm, the unit is m, and the value of the horizontal tail force arm is the distance from the average aerodynamic chord length 1/4 of the wing to the average aerodynamic chord length 1/4 of the horizontal tail;s is the wing area, and the unit is m2"; b is the average aerodynamic chord length of the wing, and the unit is m;
(2) the horizontal tail area is large, the tail force arm is short, the horizontal tail control efficiency is high, but the generated resistance is large, so that the overall aerodynamic performance of the airplane is reduced; on the contrary, the horizontal tail area is small, and the tail force arm is long, so that the horizontal tail control efficiency is low; the larger the tail capacity is, the better the flight performance of the airplane is not necessarily, so that in the initial design of the airplane, the design value of the tail capacity is selected according to the design experience of the general airplane or the design experience of the airplane of the same type under the normal condition; the approximate range of the tail capacity of the fixed wing unmanned aerial vehicle designed by the model is 0.45-0.5; through software pneumatic design, the selected tail volume value is 0.49, and the wing area is 0.26m2The average aerodynamic chord length of the wing is 0.2m, the tail force arm is 0.62m, and the area of the horizontal tail obtained by a tail capacity calculation formula is about 0.0384m2(ii) a According to the design experience of the same type of airplane, the aspect ratio of the horizontal tail is about 2.5-3, the average aerodynamic chord length of the horizontal tail is 0.12m, and the aspect ratio is temporarily 2.67. In order to facilitate the manufacturing of the airplane and simplify the manufacturing process, the horizontal tail wing adopts a rectangular wing; therefore, an HQ-00-09 symmetrical wing section with the relative thickness of 8.11 percent is selected as a horizontal tail wing, and the horizontal tail wing is a rectangular wing with a thin front edge;
s1042. vertical tail parameter setting:
(1) the fixed wing aircraft designed by the method adopts straight wings with a high aspect ratio, the aileron has strong control capability, enough lateral control capability can be ensured to offset lateral rolling torque generated during vertical tail course control, and a vertical tail capacity calculation formula is as follows:
in the formula, AVertical finThe volume of the vertical tail is the volume of the vertical tail; sVertical finIs the area of the vertical tail; l isVertical finIs the vertical tail moment arm, and the value of the vertical tail moment arm is the distance from the average aerodynamic chord length 1/4 of the wing to the average aerodynamic chord length 1/4 of the vertical tail; s is the wing area; l is the wing mean aerodynamic chord length; the volume of the vertical tail is determined to be 0.29 by combining the design experience of the same type of airplane, and the double vertical tail total surface is obtained by the calculation formula of the volume of the vertical tailProduct of 0.024m2The area of the single-side vertical tail is 0.012m2；
(2) If the vertical fin is rectangular in geometric shape, when the rudder deflects to carry out course control, the air acting force at the wing tip of the vertical fin is larger, so that larger induced resistance is easily generated, and meanwhile, the unmanned aerial vehicle generates larger rolling torque; therefore, the fixed wing drone designed herein employs a trapezoidal vertical tail with a leading edge sweep angle of 18.43 °;
s105. undercarriage design
The landing gear is suitable for supporting an aircraft body when the aircraft is parked, glided, takes off or landed on the ground, reducing the impact force on the structure of the unmanned aerial vehicle body when the aircraft lands, and preventing the structure of the unmanned aerial vehicle body from being damaged; the unmanned aerial vehicle designed by the model does not adopt a landing gear, and only a wear-resistant sponge lining layer with the thickness of 5mm is laid on the lower surface of the body of the unmanned aerial vehicle to meet the landing requirement of the unmanned aerial vehicle; by adopting the design, the unmanned aerial vehicle can take off and land on various complex terrains, the sliding distance is short when the unmanned aerial vehicle lands, the requirement on the taking off and landing field is low, meanwhile, the unmanned aerial vehicle designed by the model can also be recovered by adopting the blocking net under special conditions, and the landing gear is also not needed;
s106. pneumatic appearance design of whole machine
After the pneumatic appearance design of each part of the unmanned aerial vehicle is finished, the unmanned aerial vehicle can be assembled in XFLR5 software and subjected to pneumatic analysis, the initial pneumatic appearance design conflict part of each part of the unmanned aerial vehicle can be found in the assembling process, the coordination design is carried out aiming at the conflict part, the pneumatic analysis is carried out on the whole unmanned aerial vehicle after the assembly is finished, the reasonability and the feasibility of the pneumatic appearance design of the whole unmanned aerial vehicle are examined, whether the design target is achieved is analyzed, and the pneumatic appearance design of the whole unmanned aerial vehicle is further optimized;
s1061, setting the installation angle of the wing to be 2 degrees, defining and analyzing in software, setting the incoming flow speed to be 18m/s, setting the gravity center position of the unmanned aerial vehicle to be 1/4 chord lengths away from the leading edge of the wing, setting the lift coefficient to be 0.375 when the attack angle is 0 degrees, setting the drag coefficient to be 0.021 and setting the lift-drag ratio to be 17.682, and setting the lift center of the unmanned aerial vehicle to be at the chord length away from the leading edge 3/5 of the wing to know that the tail wing flow field is hardly influenced by the tail flow of the wing;
s1062, when the attack angle is 1.5 degrees, the lift coefficient of the unmanned aerial vehicle is 0.489, the drag coefficient is 0.027, the lift-drag ratio is 18.06, the lift is about 25.25N at the moment obtained by a lift formula, and the aircraft can normally fly at the attack angle; the unmanned aerial vehicle is static and stable, when the attack angle is 1.5, the total pitching moment coefficient is negative, the whole machine has a low head moment, in order to simulate the horizontal flight of a pull rod of the unmanned aerial vehicle, the rear part of the horizontal tail is provided with a flap which is tilted up by 6 degrees to simulate the operation of the pull rod, and the analysis is carried out;
s1063, when the attack angle is 1.75 degrees and the elevator tilts upwards by 6 degrees, the lift coefficient of the unmanned aerial vehicle is 0.477, the drag coefficient is 0.028, the lift-drag ratio is 16.85, the total pitching moment coefficient of the unmanned aerial vehicle is 0.002, and the unmanned aerial vehicle basically keeps flat flight;
in conclusion, unmanned aerial vehicle pneumatic design is better, reaches the design objective basically.
Step two: internal structure design stage of fixed wing scouting and hitting integrated unmanned aerial vehicle model
S201. wing structural design
The wing of the unmanned aerial vehicle designed by the model adopts a single-beam structure, the wing beam is arranged at the position with the maximum structural height on the wing section, namely the position with 30 percent of wing chord of the wing, so as to improve the bearing efficiency of the wing beam and reduce the structural weight of the wing beam, the wing is internally provided with common wing ribs with lower strength for maintaining the shape of the wing section, the reinforced wing ribs are used for transmitting concentrated load, the edge strips of the wing beam bear bending axial force, the web plates of the wing beam bear and transmit wing shearing force, and the whole main load of the unmanned aerial vehicle is transmitted by the crossbeam;
s2011 wing spar design
The wing is mainly divided into a middle main wing section and two outer wing sections at two sides, the main wing section wing beam consists of a carbon rod with the outer diameter of 5mm and the inner diameter of 3mm, two 5mm tung wood flanges and a 1mm light wood beam web plate, the thickness of the light wood beam web plate is 1mm, and small holes are formed at the positions, close to the tung wood strips of the wing beam, of the two sides so as to be convenient for glue dripping fixation during assembly;
two stringers are arranged at 65% chord of the rear part of the wing to support a wing skin and assist the spars in maintaining a wing structure, and the material of the stringers is 3mm tung wood strips; the outer wing section wing beam is similar to the main wing section in structure and consists of an upper 5mm tung wood edge strip, a lower 5mm tung wood edge strip and a 1mm light wood beam web plate, and a 5mm carbon rod is not arranged in the middle; the main wing section trailing edge strip is cut by a 3mm balsa board to maintain the shape of the wing trailing edge and facilitate the attachment of a skin;
the front edge of the main wing section and the front edge of the outer wing section are provided with a front edge strip made of 5mm balsa wood, the front edge of the wing is provided with a 1mm balsa wood mask which wraps the range part of 30 percent of the chord in front of the wing, and the wing beam, the beam web, the front edge balsa wood mask and the front edge strip of the wing jointly form a D-shaped wing box structure which jointly bears the torque and the bending moment of the wing;
s2012, design of wing ribs of wings
The wing inner rib of the designed wing of the model is mainly divided into two types, namely a common rib and a reinforced rib; the common wing rib is mainly used for maintaining the shape of the section of the wing, and transmitting local aerodynamic force transmitted to the wing rib by a skin and a stringer to a wing beam web, and except for the strength requirement, the common wing rib has smaller lightening holes and the other common wing ribs have larger lightening holes, so that a 2mm light wood board is adopted as a manufacturing material; the reinforced wing rib is made of composite materials, has high strength requirement and smaller lightening holes, and is divided into two types according to the application, wherein one type is a special composite material reinforced wing rib used at the joint of the wing and the fuselage, the thickness of the wing rib is 3mm, the wing rib is made of 3mm glass fiber laminates, the strength is higher, and the wing rib can effectively bear the load of the fuselage;
the manufacturing method of the 3mm glass fiber laminate comprises the following steps: paving and pasting glass fiber cloth on two sides of the 3mm laminated board, dipping the prepared epoxy resin with a brush, uniformly coating the epoxy resin on the two sides of the laminated board so that the glass fiber cloth is tightly paved and pasted on the two sides of the laminated board, scraping off redundant glue, and naturally drying the laminated board in a dark place to obtain the required 3mm glass fiber laminated board. The other reinforcing wing rib is mainly used at the joint of the main wing panel and the outer wing panel, is used for fixing a wing connecting mechanism, is used at the position of an aileron steering engine of the outer wing panel and is used for installing an aileron steering engine; the thickness of the reinforced wing rib is 2mm, the reinforced wing rib is made of 2mm glass fiber light wood boards, and the manufacturing process of the 2mm glass fiber light wood boards is basically the same as that of 3mm glass fiber laminated boards;
common wing ribs and reinforcing wing ribs of a main wing section of the wing are distributed, 3 wing ribs at the joint of the center of the main wing section and a fuselage are completely coated by a 1mm balsa wood mask, a front edge mask, a rear edge mask, wing ribs, wing spars, rear stringers and front edge strips jointly form a central wing box structure which has higher strength and penetrates through the fuselage so as to bear larger stress at the joint of a wing body, the main wing section is loaded more, and therefore gaps among the wing ribs are smaller;
the common wing ribs and the reinforced wing ribs of the outer wing section are distributed, and in order to install an aileron steering engine, a 2mm glass fiber light wood reinforced wing rib is arranged at the rudder angle installation position of the aileron except the connection position with the main wing section; a common wing rib is obliquely arranged at the wing tip, so that the wing tip is in an arc shape, and the induced resistance of the wing is effectively reduced; the outer wing sections are under small load, so that gaps among the wing ribs are large, and half wing ribs are arranged among the wing ribs to enhance the torsion resistance of the wing boxes of the outer wing sections and reduce the deformation of the front edge mask of the outer wing sections when the front edge mask is pressed;
s2013. design of wing connecting mechanism
The wing connecting mechanism mainly comprises two parts: (1) an upper wing part connecting assembly on the upper surface of the wing; (2) a metal hinge mechanism on the lower surface of the wing;
by utilizing the connecting mechanism, the outer wing sections can be folded and folded downwards during airplane transportation, so that the size of the airplane is reduced; during taking off, the outer wing sections are quickly unfolded by using the hinge mechanism, and the airplane can be unfolded after the connecting components on the upper parts of the wings are self-locked, so that the airplane can take off by throwing by hands;
the rear edge of the outer wing section is provided with a rear wall so that the ailerons can be hinged with the wings, and in order to ensure stable connection, the rear wall is made of a 2mm glass fiber light wood board; the length of the aileron is 261mm, the width is 60mm, the aileron mainly comprises an aileron rib, an aileron front edge upper cover plate, an aileron front edge lower cover plate and an aileron mask, and a light wood block is arranged inside the aileron for installing a rudder angle;
s202 fuselage structural design, the unmanned plane model adopts a truss girder type fuselage
S2021. truss structure design
The fuselage truss girder of the model unmanned aerial vehicle is formed by cutting a 5mm balsawood fiberglass board through a laser cutting machine, the whole unmanned aerial vehicle is provided with 8 truss girders penetrating through the fuselage, four main girders with higher strength are arranged at four right-angle positions of the cross section of the rectangular fuselage, the cross section of the main girders changes along with the change of the position of the fuselage, the loading at the nose is smaller, the size of the cross section of the main truss girder is 5 x 6, the loading at the middle part and the rear part of the fuselage is larger, the size of the cross section of the main truss girder is 5 x 8, and the shape of the lower part of an airfoil is cut out from the main truss girder at the upper part so as to facilitate the subsequent assembly of wings; 4 stringers with smaller strength are additionally arranged between the upper girder and the lower girder of the machine body to strengthen the structural strength of the machine body, the materials of the stringers are 5mm glass fiber balsawood, and the size of the cross section is 5 x 5;
s2022. spacer frame structure design
The model body bulkhead mainly comprises two types, namely a common bulkhead and a reinforced bulkhead, wherein the reinforced bulkhead can be divided into a 3mm glass fiber laminate reinforced bulkhead and a 2mm glass fiber laminate reinforced bulkhead according to the manufacturing materials of the reinforced bulkhead, and the manufacturing material of the common bulkhead is a 2mm laminate;
the first bulkhead is arranged from the rear part of the machine body to the front, a motor base mounting hole position needs to be arranged at the upper part of the first bulkhead, a tail fin carbon tube mounting hole needs to be arranged at the lower part of the first bulkhead, the requirement on structural strength is high, therefore, the first bulkhead is made by cutting a 3mm glass fiber laminate, and a corresponding lightening hole is arranged in the middle of the first bulkhead for lightening the weight; the motor thrust is large, so 4 pieces of 2mm laminated plates which are vertical in pairs are arranged at the rear part of a motor seat mounting hole of the 3mm glass fiber laminated plate reinforced bulkhead, and the motor thrust is transmitted into the machine body structure; the bulkhead frames at the front side and the rear side of the wing installation position are 2mm glass fiber laminate reinforced bulkhead frames with higher strength so as to bear larger stress at the connection part of the wing body and the opening of the missile bay at the lower part of the body, and the two common bulkhead frames are arranged in the middle so as to reinforce the structural strength of the body; the aircraft nose is provided with an opening for arranging the first visual angle camera and the reconnaissance cloud deck, so that a common partition frame and a reinforced partition frame are arranged to reinforce the structural strength of the aircraft nose;
s2023, design of partition board and connecting piece of fuselage and wing
In order to place various electronic equipment in the machine body and simultaneously strengthen the structural strength of the machine body, 3 partition plates are arranged in the machine body, and the space in the machine body is roughly divided into 5 parts by matching with a machine body partition frame, and the 5 parts are used for installing flight control, a GPS antenna, an airspeed tube, a barometer, a battery, an image transmission device, a camera, a holder, a projectile shooting cabin and the like;
the flight control is arranged in a cabin below the wing, a 5200mah lithium polymer battery for supplying power to equipment such as a motor and the flight control is arranged above the nose, the area of the partition plate is larger than that of the battery, and the battery can be freely adjusted in position to adjust the gravity center of the airplane; first visual angle camera is installed in the aircraft nose middle part, and the cloud platform is reconnoitered in the installation of lower part, and first visual angle camera rear portion passes the mounted position promptly for the picture, and is serious because of high-power picture passes the long-time work of equipment and generates heat, needs the forced air cooling, and for guaranteeing the image transmission effect, the picture passes the antenna and need stretch out outside the fuselage, so fuselage mask opening is in order to satisfy equipment work demand here. The image transmission rear cabin is provided with equipment required by flight control work such as a GPS antenna, an airspeed meter and a barometer, and a 2200mah lithium polymer battery for supplying power to the image transmission. The lower part of the rear part of the body is the projectile shooting cabin; wing body connecting pieces are arranged on two sides of the flight control cabin, and the manufacturing materials of the wing body connecting pieces are glass fiber laminates with the thickness of 3 mm;
s203 empennage structure design
The empennage provides pitching control and course control capabilities for the airplane, the structural strength of the empennage meets the flight use requirements, and meanwhile, the weight of the empennage directly influences the gravity center position of the airplane and the trim of the airplane before taking off and in flight; therefore, when the structure of the tail wing is designed, whether the structural strength meets the use requirement or not is considered, and meanwhile, the moderate weight of the tail wing is ensured as much as possible;
s2031. horizontal tail wing design
The horizontal tail wing of the unmanned aerial vehicle designed by the model adopts HQ-00-09 symmetrical wing type with a thin front edge and a relative thickness of 8.11%, in order to reduce the weight of the horizontal tail structure, the horizontal tail wing also adopts single-beam type wing, a wing beam is made of 2mm glass fiber laminates, in order to enhance the structural strength of the wing, a front edge strip of the wing is a 3mm solid carbon rod, a rear edge is provided with a wing wall so as to be hinged and installed with a lifting rudder, and the material used for manufacturing the wing wall is 2mm glass fiber balsawood;
the middle parts of the wing beams and the wing walls are provided with circular rings for installing tail fin carbon tubes, and the tail fins are connected with the machine body through carbon tubes with the outer diameter of 15mm and the inner diameter of 14 mm; the flat tail wing ribs near the carbon tubes have higher strength requirements, so the flat tail wing ribs are all made of 2mm glass fiber light wood plates; a steering engine is arranged on the right side of the tail wing from back to front so as to control the elevator, a steering engine mounting seat is arranged between the two reinforcing wing ribs, and the manufacturing material is a light wood board with the thickness of 2 mm; the vertical tails are arranged at two ends of the horizontal tail and are arranged on the vertical tail reinforcing wing ribs at two ends of the horizontal tail, the rectangular hole is formed in the middle of each vertical tail reinforcing wing rib to install a vertical tail steering engine, and the requirement on strength is high, so that the vertical tail reinforcing wing ribs are made of 5mm glass fiber light wood boards. The strength requirements of other common horizontal tail wing ribs are not high, the section shape of the horizontal tail wing surface is only required to be kept, and the manufacturing material is a 2mm light wood board. The front edge of the horizontal tail wing is coated by a 1mm balsa wood mask, and the balsa wood mask, the wing beam and the wing front edge strip jointly form a D-shaped wing box structure, so that the torsion resistance and bending resistance of the wing are enhanced. A1 mm mask is arranged between the vertical fin reinforced rib and the adjacent common rib, so that subsequent skin attachment is facilitated. In order to simplify the manufacturing process, the elevator is integrally cut from a 5mm light wood plate, lightening holes are formed in the elevator, the mounting position of the steering engine is not provided with the lightening holes so as to mount a steering angle, and the elevator is directly hinged on the rear wing wall through a plastic hinge;
s2032. vertical tail wing design
In order to simplify the manufacturing process and reduce the structural weight, the whole vertical tail wing is formed by splicing materials cut by a 5mm light wood board, the manufacturing method of the rudder is similar to that of an elevator, the rudder is directly manufactured by integrally cutting the 5mm light wood board, and a lightening hole is arranged in the middle;
the fixed-wing scouting and hitting integrated unmanned aerial vehicle model obtained by the method comprises the following steps: the model comprises a fuselage 1, wings 2 and a tail wing 3;
the fuselage 1 is a truss type fuselage and comprises stringers 11, main stringers 12, wing body connecting pieces 13, third partition plates 17, first partition plates 18, a motor mounting rack 19, second partition plates 10 and partition frames, wherein the main stringers 12 are symmetrically arranged main stress beams, most bending moments of the fuselage are borne by the stringers, the stringers 11 are horizontally arranged on the two main stringers 12 and are less stressed than the main stringers 12, the wing body connecting pieces 13 are symmetrically arranged at the upper ends of the middle parts of the top stringers 11 and are provided with bolt connecting holes to be matched with the empennage carbon tubes 4 for use, the partition frames are longitudinally arranged on the rectangular fuselage, are in mutual contact with and vertical to the stringers 11, a plurality of small frames are formed between the partition frames and the stringers 11, and the first partition plates 18, the second partition plates 10 and the third partition plates 17 are all erected in the frames formed by the stringers 11 and the partition frames, a body mask is arranged on the outer side of the integral body 1;
the wing 2 is of a single-beam structure and comprises a wing spar and wing ribs which are connected with each other, the wing spar is arranged at the position with the largest structural height on a wing section, namely the position with 30% chord of the wing, so that the bearing efficiency of the wing spar is improved, the structural weight of the wing spar is reduced, the wing ribs are used for maintaining the shape of the wing section in the wing, the wing ribs comprise a first reinforced rib 28, a second reinforced rib 20, a common rib 29 and half ribs, the first reinforced rib 28 is used for transmitting concentrated load, the common rib 29 is mainly used for maintaining the shape of the wing section, a flange strip bears bending axial force, a web plate of the wing beam bears and transmits shear force to the wing, the whole main load of the unmanned aerial vehicle is transmitted by a girder, and the wing 2 is detachably connected with the fuselage 1 through a wing body connecting piece 13 and a fastening bolt;
the empennage 3 is a symmetrical wing type and is detachably connected with the tail end of the machine body 1 through an empennage carbon tube 4.
Preferably, in order to ensure the strength of the fuselage, the bulkhead includes a common bulkhead 14, a first reinforced bulkhead 15 and a second reinforced bulkhead 16, the second reinforced bulkhead 16 is arranged at the tail end of the fuselage 1, and the second reinforced bulkhead 16 is provided with a lightening hole, a motor base mounting hole and a first through hole 161, wherein the first through hole 161 is matched with the tail carbon tube 4 for use; the first reinforcing partition frames 15 are symmetrically arranged on two sides of a wing mounting position in the middle of the fuselage 1, namely two ends of a wing body connecting piece, so as to bear larger stress at a wing body connection position and an opening of a missile cabin at the lower part of the fuselage, two common partition frames 14 are arranged between the two first reinforcing partition frames 15, so that the structural strength of the fuselage is enhanced, the two second partition plates 10 are arranged on two layers of stringers 11 on the lower side of the wing mounting position in the middle, a flight control mounting position is formed on the upper layer of second partition plate 10, a pattern transmission rear cabin is formed on the lower layer of second partition plate 10, and is used for mounting equipment required by flight control work such as a GPS antenna, an airspeed meter, a barometer, a 2200mah lithium battery and the like, and a missile cabin is formed on the lower side of the pattern transmission rear cabin; the front end of the machine body 1 is also provided with a common partition frame 14 and a first reinforcing partition frame 15, the third partition plate 17 is arranged on a stringer 11 on the upper side of the first partition plate 18, a 5200mah lithium battery installation position is formed on the third partition plate 17 for installing a lithium battery, a drawing transmission installation cabin is formed on the first partition plate 18 for installing a first visual angle camera, and a reconnaissance cloud deck is arranged on the lower side of the first partition plate 18; motor mounting bracket 19 is installed and is strengthened between bulkhead 16 and the first bulkhead 15 of strengthening at the second, and strengthens bulkhead 16 and first bulkhead 15 of strengthening at the second and still be provided with ordinary bulkhead 14, be provided with the second fixed orifices on the ordinary bulkhead 14, the second fixed orifices uses with the cooperation of first cross-under hole 161, is convenient for fix fin carbon tube 4, realizes fuselage 1 and fin carbon tube 4's being connected.
Preferably, for the intensity of guaranteeing the fuselage when flying, guarantee performance:
(1) the stringer 11 is arranged between the upper part of the machine body and the lower main beam, 4 stringers with smaller strength are additionally arranged to strengthen the structural strength of the machine body, the material of the stringer is 5mm glass fiber balsa wood, and the size of the cross section is 5mm by 5 mm;
(2) the main truss girder 12 is formed by cutting a 5mm balsa wood glass fiber board by a laser cutting machine, the whole machine is provided with 8 truss girders penetrating through the machine body, four main girders with higher strength are arranged at four right angles of the cross section of the rectangular machine body, and the cross section of the main girders changes along with the position change of the machine body; the loading at the nose is small, the size of the cross section of the main truss is 5mm x 6mm, the loading at the middle part and the rear part of the fuselage is large, the size of the cross section of the main truss is 5mm x 8mm, and the shape of the lower part of the wing section is cut out from the upper main truss so as to facilitate the subsequent assembly of the wing;
(3) the first reinforcing partition frame 15 is supported by a 3mm glass fiber laminate so as to bear larger stress at the joint of the wing and the fuselage and at the opening of the missile bay at the lower part of the fuselage;
(4) the second reinforced bulkhead 16 is made by cutting a 3mm glass fiber laminate because of the large thrust of the motor, the lower part of the second reinforced bulkhead needs to be provided with an empennage carbon tube mounting hole and the high structural strength requirement;
(5) the common partition frame 14 is made of 2mm glass fiber laminates and is used for enhancing the structural strength of the machine body;
(6) the wing body connecting piece 13 is made of a 3mm glass fiber laminate.
Preferably, the wing spars arranged on the wing 2 comprise a main wing section spar and an outer wing section spar, wherein the outer wing section spar is symmetrically arranged on two sides of the main wing section spar (the main wing section spar is arranged in the middle), the main wing section spar and the outer wing section spar respectively comprise a symmetrically arranged auxiliary wing spar 22 and a beam web plate 23, and the beam web plate 23 is arranged on one side of the auxiliary wing spar 22 and is used for bearing and transmitting wing shearing force; the cutting position ensures the strength of the main wing section wing beam, and a main wing beam 21 is also arranged between two sub wing beams 22 of the main wing section wing beam; an outer wing spar 24 and a trailing edge wing spar 25 are further arranged at the 65% chord position of the rear part of the wing of the main wing section wing spar, and the outer wing spar 24 is symmetrically arranged to support a wing skin and assist the wing spars in maintaining a wing structure; the front edge of the main wing section wing beam and the front edge of the outer wing section wing beam are both provided with a front edge strip 26, and the front edge of the front edge strip 26 is provided with a front edge balsa wood cover plate 27; the front edge balsa wood mask 27 wraps the front 30% chord range part of the wing, and forms a D-shaped wing box structure together with the main wing beam 21, the auxiliary wing beam 22, the web plate 23, the outer wing beam 24, the trailing edge wing beam 25 and the front edge strip 26 to bear the torque and the bending moment of the wing together.
Preferably, to ensure the strength of the wing 2:
(1) the main wing beam 21 is made of carbon rods with the outer diameter of 5mm and the inner diameter of 3 mm;
(2) the auxiliary wing beam 22 is made of 5mm tung wood edge strips;
(3) the beam web plate 23 is made of 1mm balsa wood, and small holes are formed in the positions, close to the tung wood strips of the wing spars, of the two sides so as to be convenient for glue dripping fixation during assembly;
(4) the outer wing beam 24 is made of 3mm tung wood strips and is arranged at 65% chord of the rear part of the wing to support the wing skin;
(5) the trailing edge wing beam 25 is cut by a 3mm balsa board and is used for maintaining the shape of the trailing edge of the wing and facilitating the attachment of a skin;
(6) the leading edge strip 26 is made of 5mm balsa wood strips;
(7) the leading edge balsa panel 27 is made of 1mm balsa panel.
Preferably, the wing ribs include a first reinforcing rib 28, a second reinforcing rib 20, a common rib 29 and a half rib, the first reinforcing rib 28 is disposed on both sides of the wing installation position of the main wing section, the first reinforcing rib 28 is provided with an installation hole 281 and a connection hole disposed on the wing body connection member 13 for matching use, and a common rib 29 is disposed between the two first reinforcing ribs 28, the two first reinforcing ribs 28 and the common rib 29 are completely covered by a 1mm balsa panel, the leading edge panel, the trailing edge panel, the wing ribs, the wing spars, the rear stringers and the leading edge strips together form a central box structure with high strength penetrating through the wing body connection part to bear large stress at the wing body connection part, the main wing section bears large load, and therefore, the gap between the ribs is small; the second reinforcing rib 20 is arranged at the joint of the main wing panel and the outer wing panel; besides the connection with the main wing section, a second reinforced wing rib 20 is arranged at the rudder angle installation position of the aileron, a common wing rib 29 is obliquely arranged at the wing tip, so that the wing tip is in an arc shape, the induced resistance of the wing is effectively reduced, the load of the outer wing section is small, the gap between the wing ribs is large, and half wing ribs are arranged among the wing ribs to enhance the torsion resistance of a wing box of the outer wing section and reduce the deformation of a front edge mask of the outer wing section when the front edge mask is pressed.
Preferably, to ensure the rib support:
(1) the common wing rib 29 is mainly used for maintaining the shape of the section of the wing, and transmitting local aerodynamic force transmitted to the wing rib by skins and stringers to a wing web, and except for the strength requirement, the common wing rib has smaller lightening holes and the other common wing ribs have larger lightening holes, so that a 2mm light wood plate is adopted as a manufacturing material of the common wing rib;
(2) the first reinforced rib 28 is used for reinforcing the rib of a specially-made composite material at the joint of the wing and the fuselage, has the thickness of 3mm, is made of a 3mm glass fiber laminate, has higher strength, and can effectively bear the load of the fuselage, and the manufacturing method of the 3mm glass fiber laminate is as follows: paving glass fiber cloth on two sides of the 3mm laminated board, dipping the prepared epoxy resin with a brush, uniformly coating the epoxy resin on the two sides of the laminated board so that the glass fiber cloth is tightly paved on the two sides of the laminated board, scraping off redundant glue, and naturally drying in a dark place to obtain the required 3mm glass fiber laminated board;
(3) the second reinforced wing rib 20 is mainly used at the joint of the main wing section and the outer wing section, is used for fixing a wing connecting mechanism, is used at the position of an aileron steering engine of the outer wing section and is used for installing an aileron steering engine, the thickness of the reinforced wing rib is 2mm, and the reinforced wing rib is made of a 2mm glass fiber light wood plate, and the making process of the 2mm glass fiber light wood plate is basically the same as that of a 3mm glass fiber laminate.
Preferably, the wing 2 further comprises a wing connecting mechanism, the wing connecting mechanism is arranged between the main wing section and the outer wing section, and comprises a wing upper part connecting assembly and a wing lower part connecting assembly; the connecting assembly for the upper part of the wing is arranged on the wing spar 22 on the upper side of the main wing section and the outer wing section, and comprises an inserting rod 221 arranged on the wing spar 22 of the main wing section, and a slot 222 and a limiting piece 224 arranged on the wing spar 22 of the outer wing section, wherein the inserting rod 221 is matched with the slot 222 for use, namely when the outer wing section is unfolded, the inserting rod 221 is inserted into the slot 222, a plurality of limiting grooves 2211 are arranged on the inserting rod 221, the limiting grooves 2211 are matched with limiting chucks at the lower end of the limiting piece 224 for use, namely when the inserting rod 221 is inserted into the slot 222, the limiting piece 224 is tightly pressed in the limiting grooves 2211 to limit the inserting rod 221, the limiting piece 224 is arranged on the wing spar 22 of the outer wing section through a pressing plate 223 and is fixed by screws, and the pressing plate 223 is movably connected with the limiting piece 224, namely in the use process, the limiting piece 224 can move up and down due to the extrusion effect of the side wall of the inserting rod 221, meanwhile, in order to enable the limiting part 224 to automatically reset and achieve a limiting effect, a limiting spring 225 is further arranged between the pressing plate 223 and the limiting part 224, and when the outer wing section is horizontal by using the upper part connecting assembly of the wing, the auxiliary wing beam 22 on the upper side of the outer wing section is restrained and prevented from turning downwards under the action of gravity.
Preferably, the under-wing part connecting assembly is arranged on the lower surface of the wing, and includes a hinge mechanism 203, the outer wing section wing is driven to turn and fold by the turning of the hinge mechanism 203, the hinge mechanism 203 is connected with the second reinforcing wing rib 20 at the wing joint and is arranged at the lower side of the second reinforcing wing rib 20, the hinge mechanism 203 includes a first turning page 2031, a second turning page 2032 and a rotating shaft 2033, the first turning page 2031 is arranged between two second reinforcing wing ribs 20 close to the main wing section, a rotating shaft mounting groove 11 is arranged on the first turning page 2031, the rotating shaft 2033 is rotatably mounted in the rotating shaft mounting groove 20311 through a bearing 2037, a plurality of spline grooves 20331 are equidistantly arranged on the rotating shaft 2033, the spline grooves 20331 are connected with the hoop 2036 (by a latch snap connection), a splicing groove 20361 is arranged on the hoop 2036, the splicing groove 20361 is used in cooperation with a plug 21 arranged on the second turning page 2032, namely, when in use, the inserting block 20321 is tightly inserted into the inserting groove 20361 to realize the connection between the rotating shaft 2033 and the second turning page 2032, and the second turning page 2032 is arranged between the two second reinforcing ribs 20 close to the outer wing section; a gear shaft section 20332 is further arranged on the rotating shaft 2033, the gear shaft section 20332 is meshed with a gear 2035, the gear 2035 (with a larger gear and arranged by penetrating through the first turning page 2031) is arranged at the power output end of the motor 2034, the motor 2034 is arranged on the first turning page 2031, and when the aircraft is used, the motor 2034 drives the second turning page 2032 to rotate, so that the outer wing section can be folded downwards during aircraft transportation, and the volume of the aircraft is reduced; during takeoff, the outer wing sections are rapidly unfolded by the hinge mechanism 203, and the airplane can be unfolded after the connecting components on the upper parts of the wings are self-locked, so that the airplane can take off by throwing.
Preferably, the tail wing 3 is a symmetrical wing type wing with a thin front edge and a relative thickness of 8.11%, in order to reduce the weight of the horizontal tail structure, the horizontal tail wing is also a single-beam wing, the wing 3 comprises a horizontal tail wing and a vertical tail wing 36, the vertical tail wing 36 is symmetrically arranged at two ends of the horizontal tail wing, the horizontal tail wing comprises a wing beam 32, a wing wall 31, a connecting ring 33, a common horizontal tail wing rib 34 and a reinforced horizontal tail wing rib 35, the wing beam 32 is arranged at the front edge of the wing, the wing wall 31 is arranged at the rear edge of the wing so as to be hinged with the elevator, the common horizontal tail wing rib 34 and the reinforced horizontal tail wing rib 35 are arranged between the wing wall 31 and the wing beam 32, the connecting ring 33 is arranged between the wing wall 31 and the wing beam 32 and is used in cooperation with the tail carbon tube 4, and the reinforced horizontal tail wing ribs 35 are arranged at two sides of the connecting ring 33; the vertical rear wing 36 is rotatably provided at both ends of the horizontal rear wing by reinforcing horizontal rear wing ribs 35 so as to realize the conversion of the double vertical tail wing and the horizontal rear wing, and lightening holes are provided on the vertical rear wing 36 for weight reduction.
Preferably, to ensure tail strength:
(1) the wing beam is made of 2mm glass fiber laminates;
(2) in order to enhance the structural strength of the wing, a flange strip is arranged at the front edge of the wing, and the flange strip is a 3mm solid carbon rod;
(3) the empennage carbon tube 4 is made of a carbon tube with the outer diameter of 15mm and the inner diameter of 14 mm;
(4) the strength requirement of the common horizontal tail wing rib 34 is not high, the section shape of the horizontal tail wing surface is only required to be kept, and the manufacturing material is a 2mm light wood board;
(5) the reinforced horizontal tail wing rib 35 has higher strength requirement, so the reinforced horizontal tail wing rib is made of 2mm glass fiber light wood plates;
(6) a steering engine is arranged on the right side of the tail wing from back to front so as to control the elevator, a steering engine mounting seat is arranged between the two reinforcing wing ribs, and the manufacturing material is a light wood board with the thickness of 2 mm;
(7) the front edge of the horizontal tail wing is coated by a 1mm balsa wood mask, and the balsa wood mask, the wing beam and the wing front edge strip jointly form a D-shaped wing box structure to strengthen the torsion resistance and bending resistance of the wing;
(8) a 1mm mask is arranged between the vertical fin reinforced rib and the adjacent common rib, so that subsequent skin attachment is facilitated;
(9) the vertical tail 36 is integrally formed by splicing materials cut from a 5mm light wood board.
The foregoing illustrates and describes the principles, essential features, and advantages of the utility model. It will be understood by those skilled in the art that the present model is not limited to the embodiments described above, which are merely illustrative of the principles of the model, and that various changes and modifications may be made to the model without departing from the spirit and scope of the model, and these changes and modifications are within the scope of the claimed model. The scope of protection sought by the present model is defined by the claims appended hereto and their equivalents.
Claims (7)
1. The utility model provides a fixed wing is examined and is beated integrative unmanned aerial vehicle model which characterized in that: comprises a fuselage (1), wings (2) and a tail wing (3);
the aircraft body (1) is a truss girder type aircraft body and comprises stringers (11), main stringers (12) and wing body connecting pieces (13), the main stringers (12) are symmetrically arranged, the stringers (11) are horizontally arranged on the two main stringers (12), the wing body connecting pieces (13) are symmetrically arranged at the upper end of the middle part of the top stringers (11) and are connected with the wings (2), and an aircraft body mask is arranged on the outer side of the integral aircraft body (1);
the wing (2) is of a single-beam structure and comprises a wing spar and a wing rib which are mutually connected, and the wing (2) is connected with the fuselage (1) through a wing body connecting piece (13);
the empennage (3) is a symmetrical wing type and is connected with the tail end of the machine body (1) through an empennage carbon tube (4).
2. The fixed-wing scouting-beating integrated unmanned aerial vehicle model according to claim 1, characterized in that: the wing spars are arranged at 30% chord of the wing (2) and comprise main wing section spars and outer wing section spars, the outer wing section spars are symmetrically arranged on two sides of the main wing section spars, the main wing section spars and the outer wing section spars respectively comprise symmetrically arranged auxiliary spars (22) and beam webs (23), and the beam webs (23) are arranged on one sides of the auxiliary spars (22); a main wing beam (21) is further arranged between the two symmetrically arranged auxiliary wing beams (22) of the main wing section wing beam, an outer wing beam (24) and a trailing edge wing beam (25) are further arranged at 65% of the chord of the rear part of the main wing section wing beam, and the outer wing beams (24) are symmetrically arranged; the leading edge of main wing section spar all is provided with leading edge bead (26) with the leading edge of outer wing section spar, and is provided with leading edge balsa wood mask (27) at leading edge bead (26) leading edge, 30% chord scope part before leading edge balsa wood mask (27) parcel wing, and main spar (21), secondary spar (22), web (23), wing outer spar (24), trailing edge spar (25) and leading edge bead (26) form D type wing box structure.
3. The fixed-wing scouting-beating integrated unmanned aerial vehicle model according to claim 2, characterized in that: the wing ribs comprise a first reinforced rib (28), a second reinforced rib (20), a common rib (29) and a half rib, wherein the first reinforced rib (28) is arranged on two sides of the wing installation position of the main wing section, the first reinforced rib (28) is provided with an installation hole (281) which is matched with a connection hole arranged on the wing body connecting piece (13) for use, and the common rib (29) is arranged between the two first reinforced ribs (28); the second reinforcing rib (20) is arranged at the joint of the main wing panel and the outer wing panel; the half-ribs are arranged between the second reinforcing rib (20) of the outer panel and the normal rib (29).
4. The fixed-wing scouting and batting integrated unmanned aerial vehicle model according to claim 3, characterized in that: the wing (2) is also provided with a wing connecting mechanism, and the wing connecting mechanism is arranged between the main wing section and the outer wing section and comprises a wing upper part connecting assembly and a wing lower part connecting assembly.
5. The fixed-wing scouting and batting integrated unmanned aerial vehicle model according to claim 4, characterized in that: wing upper portion coupling assembling set up on vice wing spar (22) of main wing panel and outer wing panel upside, including setting up inserted bar (221) on main wing panel vice wing spar (22), slot (222) and locating part (224) of setting on outer wing panel vice wing spar (22), inserted bar (221) and slot (222) cooperation are used, and be provided with a plurality of spacing grooves (2211) on inserted bar (221), spacing dop cooperation use of spacing groove (2211) and locating part (224) lower extreme, locating part (224) are installed on outer wing panel vice wing spar (22) through clamp plate (223), just clamp plate (223) and locating part (224) swing joint still are provided with spacing spring (225) between clamp plate (223) and locating part (224).
6. The fixed-wing scouting and batting integrated unmanned aerial vehicle model according to claim 5, characterized in that: the wing lower part connecting assembly is arranged on the lower surface of a wing and comprises a hinge mechanism (203), the hinge mechanism (203) is connected with a second reinforcing wing rib (20) at the joint of the wing and is arranged on the lower side of the second reinforcing wing rib (20), the hinge mechanism (203) comprises a first turning page (2031), a second turning page (2032) and a rotating shaft (2033), the first turning page (2031) is arranged between two second reinforcing wing ribs (20) close to a main wing section, a rotating shaft installation groove (20311) is arranged on the first turning page (2031), the rotating shaft (2033) is installed in the rotating shaft installation groove (20311) through a bearing (2037), a plurality of spline grooves (20331) are equidistantly arranged on the rotating shaft (2033), the spline grooves (20331) are connected with a hoop (2036), a splicing groove (20361) is arranged on the 2036), and the splicing groove (61) is matched with a splicing block (21) arranged on the second turning page (2) for use, the second turned leaf (2032) is arranged between two second reinforcing ribs (20) of the near outer panel; and a gear shaft section (20332) is further arranged on the rotating shaft (2033), the gear shaft section (20332) is meshed with the gear (2035), the gear (2035) is arranged at the power output end of the motor (2034), the motor (2034) is arranged on the first turning page (2031), and the motor (2034) drives the second turning page (2032) to rotate.
7. The fixed-wing scouting-beating integrated unmanned aerial vehicle model according to claim 1, characterized in that: the tail wing (3) is a symmetrical wing type and comprises a horizontal tail wing and a vertical tail wing (36), the vertical tail wing (36) is symmetrically arranged at two ends of the horizontal tail wing, the horizontal tail wing comprises a wing beam (32), a wing wall (31), a connecting ring (33), a common horizontal tail wing rib (34) and a reinforced horizontal tail wing rib (35), the wing beam (32) is arranged at the front edge of the wing, the wing wall (31) is arranged at the rear edge of the wing, the common horizontal tail wing rib (34) and the reinforced horizontal tail wing rib (35) are arranged between the wing wall (31) and the wing beam (32), the connecting ring (33) is arranged between the wing wall (31) and the wing beam (32) and is matched with the carbon tube (4) for use, and the reinforced horizontal tail wing rib (35) is arranged at two sides of the connecting ring (33); the vertical tail wing (36) is rotatably arranged at two ends of the horizontal tail wing through a reinforced horizontal tail wing rib (35), and lightening holes are formed in the vertical tail wing (36).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121431729.6U CN215944856U (en) | 2021-06-26 | 2021-06-26 | Fixed wing scouting and hitting integrated unmanned aerial vehicle model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121431729.6U CN215944856U (en) | 2021-06-26 | 2021-06-26 | Fixed wing scouting and hitting integrated unmanned aerial vehicle model |
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| Publication Number | Publication Date |
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| CN215944856U true CN215944856U (en) | 2022-03-04 |
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| CN202121431729.6U Expired - Fee Related CN215944856U (en) | 2021-06-26 | 2021-06-26 | Fixed wing scouting and hitting integrated unmanned aerial vehicle model |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113371175A (en) * | 2021-06-26 | 2021-09-10 | 中国民用航空飞行学院 | Fixed wing scouting and hitting integrated unmanned aerial vehicle model and design method thereof |
| CN115180117A (en) * | 2022-08-01 | 2022-10-14 | 燕山大学 | Deformation wing framework mechanism of double-side triangular pyramid modularized aircraft |
| CN117799817A (en) * | 2024-02-26 | 2024-04-02 | 中国科学院工程热物理研究所 | Truss type wing structure, assembly method and preparation method of truss type girder |
-
2021
- 2021-06-26 CN CN202121431729.6U patent/CN215944856U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113371175A (en) * | 2021-06-26 | 2021-09-10 | 中国民用航空飞行学院 | Fixed wing scouting and hitting integrated unmanned aerial vehicle model and design method thereof |
| CN115180117A (en) * | 2022-08-01 | 2022-10-14 | 燕山大学 | Deformation wing framework mechanism of double-side triangular pyramid modularized aircraft |
| CN117799817A (en) * | 2024-02-26 | 2024-04-02 | 中国科学院工程热物理研究所 | Truss type wing structure, assembly method and preparation method of truss type girder |
| CN117799817B (en) * | 2024-02-26 | 2024-05-07 | 中国科学院工程热物理研究所 | Truss type wing structure, assembly method and preparation method of truss type girder |
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