CN110775273A - Unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle Download PDFInfo
- Publication number
- CN110775273A CN110775273A CN201911200236.9A CN201911200236A CN110775273A CN 110775273 A CN110775273 A CN 110775273A CN 201911200236 A CN201911200236 A CN 201911200236A CN 110775273 A CN110775273 A CN 110775273A
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- Prior art keywords
- wing
- fuselage
- tail
- cover
- carbon tube
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Remote Sensing (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides an unmanned aerial vehicle, which belongs to the technical field of aircrafts and comprises a fuselage, a horizontal tail, an undercarriage, two wings, a vertical tail and tail supports, wherein the undercarriage is arranged at the bottom of the fuselage, the two wings are symmetrically arranged at two sides of the fuselage, the two vertical tails are arranged at the rear of the fuselage in parallel, the horizontal tail is arranged at the tops of the two vertical tails and is fixedly connected with the vertical tail, and the bottoms of the two vertical tails are respectively connected with two ends of the rear side of the fuselage through the two tail supports; the fuselage includes fuselage frame and aircraft bonnet, be provided with power equipment on the fuselage frame, the fuselage frame sets up in the aircraft bonnet to support the aircraft bonnet, the aircraft bonnet is provided with the central line from top to bottom. This unmanned aerial vehicle can satisfy great loading space requirement, adopts the design of high lift-drag ratio overall appearance, can dismantle fast, assemble, and the big angle of attack performance is promoted to aircraft nose and high horizontal tail, and winglet and vertical fin promote anti crosswind performance.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to an unmanned aerial vehicle.
Background
The unmanned aerial vehicle is flexible, convenient and reliable, can complete technical equipment with various task requirements, and obtains great attention and application in military and civil fields. At present, development and application of unmanned aerial vehicles are paid great attention to all countries, all units, all fields and all companies. Although there are a number of mature and reliable drone products in the prior art, these products still suffer from the following problems:
1) the fuselage region does not generate lift and is only used as a loading space for equipment and task loads;
2) each part of the machine body is fixedly connected together, and the occupied space for transportation and storage is large;
3) the flight stability and the large attack angle flight capability are weak.
Aiming at the problems, the invention provides a novel unmanned aerial vehicle design scheme.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides an unmanned aerial vehicle.
In order to achieve the above purpose, the invention provides the following technical scheme:
an unmanned aerial vehicle comprises a fuselage, horizontal tails, landing gears, two wings, vertical tails and tail braces, wherein the landing gears are arranged at the bottom of the fuselage, the two wings are symmetrically arranged at two sides of the fuselage, the two vertical tails are arranged at the rear of the fuselage in parallel, the horizontal tails are arranged at the tops of the two vertical tails and are fixedly connected with the vertical tails, and the bottoms of the two vertical tails are respectively connected with two ends of the rear side of the fuselage through the two tail braces;
the aircraft body comprises an aircraft body frame and an aircraft bonnet, a central line is arranged above and below the aircraft bonnet, power equipment is arranged on the aircraft body frame, and the aircraft body frame is arranged in the aircraft bonnet and supports the aircraft bonnet;
the top of the hood is of an upwardly arched curved surface structure, the nose part on the front side of the hood is inwardly contracted and downwardly bent, the middle of the rear side of the hood is bulged towards the periphery to form a columnar empennage, wing mounting holes are formed in two sides of the hood respectively, wing mounting sleeves are arranged on the outer sides of the wing mounting holes, tail strut connecting pieces are arranged behind the two wing mounting sleeves, an observation window is formed in the top of the hood, and a cover plate is arranged on the observation window;
the two wings are respectively matched with the two wing mounting sleeves and detachably connected with the fuselage frame, and the two tail braces are respectively detachably connected with the two tail brace rod connecting pieces.
Preferably, the fuselage frame comprises a front-mounted carbon tube of the fuselage, a rear-mounted carbon tube of the fuselage, two support beams arranged side by side and a group of oil tank partition frames arranged perpendicular to the support beams, the support beams penetrate through the bottom of the oil tank partition frames, the support beams on two sides of the oil tank partition frames are provided with equipment mounting plates, and the power equipment is mounted on the equipment mounting plates;
an oil tank is arranged between the two oil tank partition frames, two sides of the two oil tank partition frames are respectively opposite to the wing mounting hole, and the front installation carbon tube of the fuselage and the rear installation carbon tube of the fuselage are respectively arranged at the outer sides of the two oil tank partition frames;
a front side machine body bulkhead is arranged at the front end of the support beam, a photoelectric pod mounting plate is arranged on the outer wall of the front side machine body bulkhead, a photoelectric pod is mounted on the photoelectric pod mounting plate, and a front landing gear rotating shaft is arranged on the photoelectric pod mounting plate and close to the front side machine body bulkhead; the rear end of the supporting beam is provided with a tail partition frame, and the tail partition frame is connected with the oil tank partition frame on the rear side through an auxiliary beam; the columnar empennage is matched with the positions of the tail partition frame and the auxiliary beam, and the lower end of the photoelectric pod penetrates through a front side bottom plate of the hood.
Preferably, the wing includes a main wing, an aileron and a winglet, the main wing includes a main wing cover and a main wing frame arranged in the main wing cover and supporting the main wing cover, the main wing frame includes a wing forward-mounted carbon tube, a wing backward-mounted carbon tube, a front rib, a rear rib arranged side by side, a plurality of middle ribs between the front rib and the rear rib, and two wing beams arranged side by side, both of the two wing beams pass through the front rib, the middle rib and the rear rib, and both of the wing forward-mounted carbon tube and the wing backward-mounted carbon tube pass through the front rib; the front wing rib is matched with the wing installation sleeve, the wing preposed installation carbon tube is detachably connected with the fuselage preposed installation carbon tube, and the wing postposed installation carbon tube is detachably connected with the fuselage postposed installation carbon tube;
the aileron comprises an aileron cover and an aileron frame which is arranged in the aileron cover and drives the aileron cover to rotate, the aileron frame comprises a rotating shaft and a plurality of supporting sheets which are uniformly arranged on the rotating shaft, two ends of the rotating shaft are respectively and rotatably connected with the rear rib and one middle rib, and the bottom of the aileron cover is hinged with the bottom of the main wing cover through a hinge component;
the wingtip winglet comprises a small wing cover and two small wing beams fixed on the inner side of the small wing cover, the two small wing beams penetrate through the rear wing rib and are fixedly connected with the rear wing rib, and the tail part of the small wing cover tilts upwards.
Preferably, the bottom of the main wing cover is provided with a hinge hole, the hinge hole is provided with a hole cover, the hinge part comprises a hinge block, a hinge seat and a connecting rod, the hinge block is arranged inside the hole cover, the hinge seat is fixed at the bottom of the auxiliary wing cover, one end of the connecting rod is rotatably connected with the hinge seat, and the other end of the connecting rod penetrates through the hole cover to be rotatably connected with the hinge block.
Preferably, the undercarriage comprises a U-shaped support and two rollers, an undercarriage mounting hole is formed in the bottom of the hood, the top of the U-shaped support penetrates through the undercarriage mounting hole and is fixedly connected with the two support beams, and the two rollers are respectively fixed at two ends of the U-shaped support.
The unmanned aerial vehicle provided by the invention can meet the requirement of a larger loading space, adopts the overall appearance design with a high lift-drag ratio, and can be quickly disassembled and assembled; the design of a wing body fusion body is adopted totally, and the wings and the fuselage are naturally fused to form the wing body fusion body, so that the flight resistance is reduced; meanwhile, wings with fused wing bodies naturally extend in the body to form strake wings, so that the lift force and the large attack angle performance are improved; the flat and streamline fuselage is subjected to pneumatic optimization design to generate considerable lift force; the middle lines above and below the hood play a role in guiding airflow, so that the whole flow field of the machine body is optimized, and the asymmetric separation of the airflow is avoided; the nose of the lower bay reduces the local attack angle of the nose accessory, simultaneously starts the washing effect to the incoming flow, and improves the large attack angle performance of the whole machine; the high tail support design improves the operation performance of the aircraft under the condition of a large angle of attack and improves the flight performance under the condition of the large angle of attack.
Drawings
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle according to embodiment 1 of the present invention;
fig. 2 is a schematic view of an aerial view structure of the unmanned aerial vehicle according to embodiment 1 of the present invention;
FIG. 3 is a schematic view of the fuselage construction;
FIG. 4 is a schematic view of a wing configuration;
FIG. 5 is a schematic view of a wing in an overhead configuration;
FIG. 6 is a schematic view of a wing skeleton;
FIG. 7 is a schematic structural view of a winglet;
FIG. 8 is a first schematic structural view of a fuselage skeleton;
FIG. 9 is a second schematic structural view of the airframe frame;
fig. 10 is a schematic structural diagram three of the fuselage skeleton.
Description of reference numerals:
the device comprises a fuselage 1, a hood 11, a columnar empennage 12, wing mounting holes 13, wing mounting sleeves 14, tail stay connecting pieces 15, a cover plate 16, a front-mounted carbon tube 17 of the fuselage, a rear-mounted carbon tube 18 of the fuselage, a support beam 19, an oil tank bulkhead 110, an equipment mounting plate 111, an oil tank 112, a front-side fuselage bulkhead 113, a photoelectric pod mounting plate 114, a photoelectric pod 115, a front landing gear rotating shaft 116, a tail bulkhead 117 and an auxiliary beam 118;
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention and can practice the same, the present invention will be described in detail with reference to the accompanying drawings and specific examples. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing technical solutions of the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. In the description of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the terms "connected" and "connected" are to be interpreted broadly, e.g., as a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations. In the description of the present invention, unless otherwise specified, "a plurality" means two or more, and will not be described in detail herein.
Example 1
The invention provides an unmanned aerial vehicle, which is modularized in design for convenient use and transportation, and the modules can be assembled into an aircraft capable of executing specific functions through simple plugging. Specifically, as shown in fig. 1 and 2, the aircraft is divided into four major parts, namely a fuselage 1, two wings 4, an undercarriage 3 and a tail part according to modules, wherein the tail part consists of a horizontal tail 2, two vertical tails 5 and a tail support 6. The undercarriage 3 is arranged at the bottom of the fuselage 1, the two wings 4 are symmetrically arranged at two sides of the fuselage 1, the two vertical tails 5 are arranged behind the fuselage 1 in parallel, the horizontal tails 2 are arranged at the tops of the two vertical tails 5 and fixedly connected with the vertical tails 5, and the bottoms of the two vertical tails 5 are respectively connected with two ends of the rear side of the fuselage 1 through two tail braces 6; the aircraft body 1 comprises an aircraft body frame and an aircraft bonnet 11, a midline is arranged above and below the aircraft bonnet 11, the aircraft body frame is provided with power equipment 7, and the aircraft body frame is arranged in the aircraft bonnet 11 and supports the aircraft bonnet 11; the front end of the whole body shape is similar to the head shape of the dolphin.
Specifically, as shown in fig. 3 to 10, the top of the hood 11 is an upwardly arched curved surface structure, the nose portion on the front side of the hood 11 is inwardly contracted and downwardly bent, the middle of the rear side of the hood 11 is bulged to the periphery to form a columnar empennage 12, wing mounting holes 13 are respectively formed in two sides of the hood 11, wing mounting sleeves 14 are arranged on the outer sides of the wing mounting holes 13, tail stay connecting pieces 15 are respectively arranged behind the two wing mounting sleeves 14, an observation window is formed in the top of the hood 11, and a cover plate 16 is arranged on the observation window;
the two wings 4 are respectively matched with the two wing mounting sleeves 14 and detachably connected with the fuselage airframe, and the two tail braces 6 are respectively detachably connected with the two tail brace rod connecting pieces 15.
Specifically, in this embodiment, the body frame includes a front-mounted carbon tube 17 of the body, a rear-mounted carbon tube 18 of the body, two support beams 19 arranged side by side, and a group of oil tank partition frames 110 arranged perpendicular to the support beams 19, the support beams 19 penetrate through the bottom of the oil tank partition frames 110, the support beams 19 on both sides of the oil tank partition frames 110 are both provided with equipment mounting plates 111, and the power equipment 7 is mounted on the equipment mounting plates 111;
an oil tank 112 is arranged between the two oil tank partition frames 110, two sides of the two oil tank partition frames 110 are respectively opposite to one wing mounting hole 13, and a front-mounted carbon tube 17 of the fuselage and a rear-mounted carbon tube 18 of the fuselage are respectively arranged at the outer sides of the two oil tank partition frames 110;
a front side body bulkhead 113 is arranged at the front end of the support beam 19, a photoelectric pod mounting plate 114 is arranged on the outer wall of the front side body bulkhead 113, a photoelectric pod 115 is mounted on the photoelectric pod mounting plate 114, and a nose landing gear rotating shaft 116 is arranged on the photoelectric pod mounting plate 114 and close to the front side body bulkhead 113; the rear end of the support beam 19 is provided with a tail bulkhead 117, and the tail bulkhead 117 is connected with the oil tank bulkhead 110 at the rear side through a secondary beam 118; the columnar empennage 12 is matched with the positions of the tail bulkhead 117 and the auxiliary beam 118, and the lower end of the photoelectric pod 115 penetrates through the front side bottom plate of the hood 11.
As shown in fig. 4 to 7, the wing 4 includes a main wing 41, an aileron 42 and a winglet 43, the main wing 41 includes a main wing cover 411 and a main wing frame arranged in the main wing cover 411 to support the main wing cover 411, the main wing frame includes a wing forward-mounting carbon tube 412, a wing backward-mounting carbon tube 413, a front wing rib 414 and a rear wing rib 415 arranged side by side, a plurality of middle wing ribs 416 between the front wing rib 414 and the rear wing rib 415, and two wing beams 417 arranged side by side, the two wing beams 417 pass through the front wing rib 414, the middle wing rib 416 and the rear wing rib 415, and the wing forward-mounting carbon tube 412 and the wing backward-mounting carbon tube 413 pass through the front wing rib 414; the front wing rib 414 is matched with the wing installation sleeve 14, the wing prepositive installation carbon tube 412 is detachably connected with the fuselage prepositive installation carbon tube 17, and the wing postpositive installation carbon tube 413 is detachably connected with the fuselage postpositive installation carbon tube 18;
the aileron 42 comprises an aileron cover 421 and an aileron frame which is arranged in the aileron cover 421 and drives the aileron cover 421 to rotate, the aileron frame comprises a rotating shaft 422 and a plurality of supporting pieces 423 which are uniformly arranged on the rotating shaft 422, two ends of the rotating shaft 422 are respectively connected with the rear rib 415 and one middle rib 416 in a rotating way, and the bottom of the aileron cover 421 is hinged with the bottom of the main wing cover 411 through a hinge component 8;
the winglet 43 comprises a winglet cap 431 and two small spars 432 fixed inside the winglet cap 431, both of the small spars 432 passing through the aft rib 415 and being fixedly connected to the aft rib 415, the winglet cap 431 being angled up aft.
Further, in this embodiment, the bottom of the main wing cover 411 is provided with a hinge hole, the hole cover 418 is installed at the hinge hole, the hinge component 8 includes a hinge block 81, a hinge seat 82 and a connecting rod 83, the hinge block 81 is installed inside the hole cover 418, the hinge seat 82 is fixed at the bottom of the auxiliary wing cover 421, one end of the connecting rod 83 is rotatably connected with the hinge seat 82, and the other end of the connecting rod passes through the hole cover 418 and is rotatably connected with the hinge block 81.
Meanwhile, in this embodiment, as shown in fig. 10, the undercarriage 3 includes a "U" shaped bracket 31 and two rollers 32, the undercarriage 3 mounting hole is opened at the bottom of the hood 11, the top of the "U" shaped bracket 31 passes through the undercarriage 3 mounting hole and is fixedly connected with the two support beams 19, and the two rollers 32 are respectively fixed at two ends of the "U" shaped bracket 31.
The main assembly methods and processes of the unmanned aerial vehicle provided by this embodiment are as follows: the front rib 414 of the main wing 41 is matched with the wing installation sleeve 14 of the hood 11, the wing prepositive installation carbon tube 412 and the wing postpositive installation carbon tube 413 are inserted into the wing installation hole 13 and are respectively inserted with the fuselage prepositive installation carbon tube 17 and the fuselage postpositive installation carbon tube 18 to complete the installation of the two wings 4 and the fuselage 1, and the tail support 6 is inserted into the tail support rod connecting piece 15 to complete the installation of the horizontal tail 2, the vertical tail 5 and the fuselage 1.
In the embodiment, a front-mounted carbon tube 17 of the fuselage, a rear-mounted carbon tube 18 of the fuselage, a support beam 19, an oil tank bulkhead 110, an equipment mounting plate 111, a front-side fuselage bulkhead 113, a photoelectric pod mounting plate 114, a nose landing gear rotating shaft 116, a tail bulkhead 117 and a secondary beam 118 form a fuselage framework; the wing framework is formed by the wing preposed installation carbon tube 412, the wing postpositive installation carbon tube 413, the front wing rib 414, the rear wing rib 415, the middle wing rib 416, the wing beam 417, the rotating shaft 422 and the support piece 423. The unmanned aerial vehicle provided by the embodiment adopts a wing body fusion body design, and the wings and the fuselage are naturally fused to form a wing body fusion body, so that the flight resistance is reduced; meanwhile, wings with fused wing bodies naturally extend in the body to form strake wings, so that the lift force and the large attack angle performance are improved; the flat and streamline fuselage is subjected to pneumatic optimization design to generate considerable lift force; the central line of the upper part and the lower part of the hood 11 plays a role in guiding airflow, optimizes the whole flow field of the machine body and avoids asymmetric separation of the airflow; the nose of the lower bay reduces the local attack angle of the nose accessory, simultaneously starts the washing effect to the incoming flow, and improves the large attack angle performance of the whole machine; the high tail support design improves the operation performance of the aircraft under the condition of a large angle of attack and improves the flight performance under the condition of the large angle of attack.
The above-mentioned embodiments are only preferred embodiments of the present invention, and the scope of the present invention is not limited thereto, and any simple modifications or equivalent substitutions of the technical solutions that can be obviously obtained by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Claims (5)
1. The unmanned aerial vehicle is characterized by comprising a fuselage (1), a horizontal tail (2), an undercarriage (3), two wings (4), vertical tails (5) and tail supports (6), wherein the undercarriage (3) is arranged at the bottom of the fuselage (1), the two wings (4) are symmetrically arranged at two sides of the fuselage (1), the two vertical tails (5) are arranged behind the fuselage (1) in parallel, the horizontal tail (2) is arranged at the tops of the two vertical tails (5) and is fixedly connected with the vertical tails (5), and the bottoms of the two vertical tails (5) are respectively connected with two ends of the rear side of the fuselage (1) through the two tail supports (6);
the aircraft body (1) comprises an aircraft body frame and an aircraft bonnet (11), a central line is arranged above and below the aircraft bonnet (11), power equipment (7) is arranged on the aircraft body frame, and the aircraft body frame is arranged in the aircraft bonnet (11) and supports the aircraft bonnet (11);
the top of the hood (11) is of an upwards arched curved surface structure, the nose part on the front side of the hood (11) is inwardly contracted and downwardly bent, the middle of the rear side of the hood (11) is bulged towards the periphery to form a columnar empennage (12), wing mounting holes (13) are respectively formed in two sides of the hood (11), wing mounting sleeves (14) are arranged on the outer sides of the wing mounting holes (13), tail brace connecting pieces (15) are arranged behind the two wing mounting sleeves (14), an observation window is formed in the top of the hood (11), and a cover plate (16) is arranged on the observation window;
the two wings (4) are respectively matched with the two wing mounting sleeves (14) and detachably connected with the fuselage airframe, and the two tail braces (6) are respectively detachably connected with the two tail brace rod connecting pieces (15).
2. An unmanned aerial vehicle according to claim 1, wherein the fuselage frame comprises a front-mounted carbon tube (17), a rear-mounted carbon tube (18), two support beams (19) arranged side by side and a group of oil tank frames (110) arranged perpendicular to the support beams (19), the support beams (19) pass through the bottoms of the oil tank frames (110), the support beams (19) on both sides of the oil tank frames (110) are provided with equipment mounting plates (111), and the power equipment (7) is mounted on the equipment mounting plates (111);
an oil tank (112) is arranged between the two oil tank partition frames (110), two sides of the two oil tank partition frames (110) are respectively opposite to the wing mounting hole (13), and the front-mounted carbon tube (17) of the fuselage and the rear-mounted carbon tube (18) of the fuselage are respectively arranged on the outer sides of the two oil tank partition frames (110);
a front side body bulkhead (113) is arranged at the front end of the support beam (19), a photoelectric pod mounting plate (114) is arranged on the outer wall of the front side body bulkhead (113), a photoelectric pod (115) is mounted on the photoelectric pod mounting plate (114), and a front landing gear rotating shaft (116) is arranged on the photoelectric pod mounting plate (114) and close to the front side body bulkhead (113); the rear end of the support beam (19) is provided with a tail bulkhead (117), and the tail bulkhead (117) is connected with the oil tank bulkhead (110) at the rear side through a secondary beam (118); the columnar empennage (12) is matched with the positions of the tail bulkhead (117) and the auxiliary beam (118), and the lower end of the photoelectric pod (115) penetrates through the front side bottom plate of the hood (11).
3. Unmanned aerial vehicle according to claim 2, wherein the wing (4) comprises a main wing (41), an aileron (42) and a winglet (43), the main wing (41) comprises a main wing cover (411) and a main wing frame which is arranged in the main wing cover (411) and supports the main wing cover (411), the main wing frame comprises a front-mounted carbon tube (412) of the wing, a rear-mounted carbon tube (413) of the wing, a front wing rib (414) and a rear wing rib (415) which are arranged side by side, a plurality of middle wing ribs (416) positioned between the front wing rib (414) and the rear wing rib (415), and two wing beams (417) which are arranged side by side, wherein the two wing beams (417) penetrate through the front wing rib (414), the middle wing ribs (416) and the rear wing rib (415), the wing preposed installation carbon tube (412) and the wing postposed installation carbon tube (413) both penetrate through the front wing rib (414); the front wing rib (414) is matched with the wing installation sleeve (14), the wing preposed installation carbon tube (412) is detachably connected with the fuselage preposed installation carbon tube (17), and the wing postpositional installation carbon tube (413) is detachably connected with the fuselage postpositional installation carbon tube (18);
the aileron (42) comprises an aileron cover (421) and an aileron frame which is arranged in the aileron cover (421) and drives the aileron cover (421) to rotate, the aileron frame comprises a rotating shaft (422) and a plurality of support pieces (423) which are uniformly arranged on the rotating shaft (422), two ends of the rotating shaft (422) are respectively connected with the rear rib (415) and one middle rib (416) in a rotating way, and the bottom of the aileron cover (421) is hinged with the bottom of the main wing cover (411) through a hinge component (8);
the wingtip winglet (43) comprises a small wing cover (431) and two small wing beams (432) fixed on the inner side of the small wing cover (431), the two small wing beams (432) penetrate through the rear wing rib (415) and are fixedly connected with the rear wing rib (415), and the tail part of the small wing cover (431) tilts upwards.
4. The unmanned aerial vehicle of claim 3, wherein a hinge hole is formed in the bottom of the main wing cover (411), a hole cover (418) is installed in the hinge hole, the hinge component (8) comprises a hinge block (81), a hinge seat (82) and a connecting rod (83), the hinge block (81) is installed inside the hole cover (418), the hinge seat (82) is fixed at the bottom of the auxiliary wing cover (421), one end of the connecting rod (83) is rotatably connected with the hinge seat (82), and the other end of the connecting rod penetrates through the hole cover (418) to be rotatably connected with the hinge block (81).
5. The unmanned aerial vehicle of claim 2, wherein the landing gear (3) comprises a U-shaped bracket (31) and two rollers (32), a mounting hole of the landing gear (3) is formed in the bottom of the hood (11), the top of the U-shaped bracket (31) penetrates through the mounting hole of the landing gear (3) and is fixedly connected with the two support beams (19), and the two rollers (32) are respectively fixed at two ends of the U-shaped bracket (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911200236.9A CN110775273A (en) | 2019-11-29 | 2019-11-29 | Unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112429200A (en) * | 2020-10-14 | 2021-03-02 | 陈东旭 | Aviation aircraft device capable of assisting steering |
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| CN108583849A (en) * | 2018-05-25 | 2018-09-28 | 中国航天空气动力技术研究院 | A kind of mute UAV aerodynamic layout of supersonic speed |
| CN110498041A (en) * | 2019-08-22 | 2019-11-26 | 西安探索鹰航空科技有限公司 | A kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard |
| CN211001843U (en) * | 2019-11-29 | 2020-07-14 | 西安航空学院 | Unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108583849A (en) * | 2018-05-25 | 2018-09-28 | 中国航天空气动力技术研究院 | A kind of mute UAV aerodynamic layout of supersonic speed |
| CN110498041A (en) * | 2019-08-22 | 2019-11-26 | 西安探索鹰航空科技有限公司 | A kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard |
| CN211001843U (en) * | 2019-11-29 | 2020-07-14 | 西安航空学院 | Unmanned aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112429200A (en) * | 2020-10-14 | 2021-03-02 | 陈东旭 | Aviation aircraft device capable of assisting steering |
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