CN111619797A - Compound many rotors unmanned vehicles and wing connecting device - Google Patents
Compound many rotors unmanned vehicles and wing connecting device Download PDFInfo
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- CN111619797A CN111619797A CN202010505462.4A CN202010505462A CN111619797A CN 111619797 A CN111619797 A CN 111619797A CN 202010505462 A CN202010505462 A CN 202010505462A CN 111619797 A CN111619797 A CN 111619797A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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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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Abstract
The invention discloses a wing connecting device of a composite multi-rotor unmanned aerial vehicle, which comprises a pair of rotor power systems symmetrically arranged on two wings, wherein the rotor power systems are provided with a plurality of rotors, and two sides of each rotor power system are respectively detachably and fixedly connected with an outer wing section and an inner wing section of each wing. The invention also discloses a composite multi-rotor unmanned aerial vehicle. Above-mentioned compound many rotors unmanned vehicles wing connecting device, simple structure installs and removes the convenience, can select to install or dismantle rotor driving system in order to realize fixed wing aircraft or compound many rotors aircraft mode flight according to the task needs.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a wing connecting device of a composite multi-rotor unmanned aerial vehicle. Still relate to a compound many rotors unmanned vehicles.
Background
In recent years, unmanned aircraft play a remarkable role in military and civil fields, but the conventional unmanned aircraft often shows a certain limitation when meeting the requirements of various tasks.
Many rotors and compound unmanned vehicles of fixed wing obtain unique VTOL performance advantage through synthesizing fixed wing aircraft and many rotors aircraft, and furthest keeps the flight performance of fixed wing aircraft platform for many rotors and compound unmanned vehicles of fixed wing have speed envelope big, need not the runway, need not the transmission recovery system, advantages such as the engine oil consumption rate of cruising is little for other unmanned aerial vehicle systems. Generally, a multi-rotor vertical take-off and landing system is added on a fixed-wing unmanned aerial vehicle platform of the composite multi-rotor unmanned aerial vehicle, and the multi-rotor system arranged on wings or tail booms provides lift force in the take-off and landing stage; however, when loads are transferred to the wings through the mounting structures, the load-bearing and force-transferring routes of the wings are greatly changed, and the wings are easily damaged at the joints.
Therefore, how to provide a composite multi-rotor unmanned aerial vehicle which has reasonable structure loading and force transmission routes, safe and reliable connection, simple structure, convenient assembly and disassembly and can be selectively assembled or disassembled according to task requirements to realize the mode flight of a fixed-wing aircraft or a composite multi-rotor aircraft is a technical problem which needs to be solved urgently by technical personnel in the field.
Disclosure of Invention
The invention aims to provide a wing connecting device of a composite multi-rotor unmanned aerial vehicle, which has the advantages of simple structure and convenient assembly and disassembly, and can selectively assemble or disassemble a rotor power system according to task requirements to realize the mode flight of a fixed-wing aircraft or a composite multi-rotor aircraft. Another object of the present invention is to provide a composite multi-rotor unmanned aerial vehicle.
In order to achieve the above object, the present invention provides a wing connection device for a composite multi-rotor unmanned aerial vehicle, including a pair of rotor power systems symmetrically disposed on two wings, wherein the rotor power systems are provided with a plurality of rotors, and two sides of the rotor power systems are respectively used for being detachably and fixedly connected with an outer rotor section and an inner rotor section of the wings.
Preferably, the rotor power system is configured to be coupled to the outer wing section and the inner wing section via a plurality of sets of ears and fasteners.
Preferably, one side of rotor driving system is equipped with and is used for corresponding two sets of that link to each other with the first wing spar joint of outer wing panel and first wing wall joint the fork ear, rotor driving system's opposite side is equipped with and is used for corresponding two sets of that link to each other with the second wing spar joint of inner wing panel and second wing wall joint the fork ear.
Preferably, an eccentric bushing is arranged in the fork ear, and wear-resistant parts are arranged between the fork ear and the fastener and between the fork ear and the eccentric bushing.
Preferably, the rotor power system includes a cantilever strut extending through the cantilever spar adapter plate and the cantilever wing wall adapter plate.
Preferably, the cantilever spar adapter plate is configured to have a pallet nut at the second spar joint.
Preferably, the cantilever wing wall adapter plate is used for arranging a self-locking nut at the joint of the second wing wall.
Preferably, the quantity of rotor is two sets of, the rotor is including locating the motor mount pad at rotor driving system both ends and in motor and rotor oar that motor mount pad department installation is fixed.
Preferably, the outermost layer of the rotor power system is provided with a fairing.
The invention also provides a composite multi-rotor unmanned aerial vehicle which comprises a vehicle body, wings arranged on two sides of the vehicle body and the composite multi-rotor unmanned aerial vehicle wing connecting device, wherein the wings comprise outer wing sections and inner wing sections, and a rotor power system of the composite multi-rotor unmanned aerial vehicle wing connecting device is detachably fixed between the outer wing sections and the inner wing sections.
Compared with the background technology, the composite multi-rotor unmanned aerial vehicle wing connecting device provided by the invention comprises a pair of rotor power systems, the rotor power systems are symmetrically arranged on two wings, the rotor power systems are provided with a plurality of rotors, and the two sides of the rotor power systems are respectively and fixedly connected with the detachable wings, wherein one side of each rotor power system is connected with an outer wing section of each wing, and the other side of each rotor power system is connected with an inner wing section of each wing, the composite multi-rotor unmanned aerial vehicle wing connecting device realizes composite multi-rotor unmanned aerial vehicle mode flight by installing the rotor power systems at the wings, realizes fixed wing aircraft mode flight by detaching the rotor power systems at the wings, forms a stable and reliable connecting structure capable of transferring force when being installed, and can integrate the vertical take-off and landing performance of a multi-rotor unmanned aerial vehicle, the aircraft can maintain the flight performance of the fixed-wing aircraft, can be selectively installed or disassembled according to different task sites, and has the advantages of wide application range, convenience in assembly and disassembly, simple structure, reasonable structure loading and force transmission routes, and safety and reliability in connection.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a rotor state of a composite multi-rotor unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a fixed wing state of the composite multi-rotor unmanned aerial vehicle provided by the embodiment of the invention;
FIG. 3 is a schematic view of the installation of a composite multi-rotor UAV wing attachment provided in accordance with an embodiment of the present invention;
FIG. 4 is a schematic view of the wing attachment arrangement of the composite multi-rotor UAV of FIG. 3;
fig. 5 is a schematic structural diagram of an outer wing panel according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of an inner wing panel according to an embodiment of the present invention.
Wherein:
1-outer wing section, 2-rotor wing power system, 3-inner wing section, 4-fork ear, 5-first bolt, 6-first copper sleeve, 7-pallet nut, 8-second bolt, 9-eccentric bushing, 10-second copper sleeve, 11-self-locking nut, 12-cantilever wing beam adapter plate, 13-cantilever wing wall adapter plate, 14-fairing, 15-motor mounting seat, 16-cantilever brace rod, 17-motor, 18-rotor wing paddle, 19-skin, 20-wing rib, 21-first wing beam, 22-first wing wall, 23-first wing beam joint, 24-first wing wall joint, 25-second wing beam, 26-second wing wall, 27-reinforcing plate, 28-tail brace rod, 29-tail brace rod joint, 30-second wing joint, 31-second spar joint.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Referring to fig. 1 to 6, fig. 1 is a schematic structural diagram of a rotor state of a composite multi-rotor unmanned aerial vehicle according to an embodiment of the present invention, fig. 2 is a schematic structural diagram of a fixed wing state of the composite multi-rotor unmanned aerial vehicle according to the embodiment of the present invention, fig. 3 is a schematic mounting diagram of a wing connection device of the composite multi-rotor unmanned aerial vehicle according to the embodiment of the present invention, fig. 4 is a schematic structural diagram of the wing connection device of the composite multi-rotor unmanned aerial vehicle shown in fig. 3, fig. 5 is a schematic structural diagram of an outer wing segment according to the embodiment of the present invention, and fig. 6 is a schematic structural diagram of an inner wing segment according to the embodiment of the present invention.
In a first specific embodiment, the wing connection device of the composite multi-rotor unmanned aerial vehicle provided by the invention is detachably arranged on the wings, and comprises a pair of rotor power systems 2, wherein the pair of rotor power systems 2 are symmetrically arranged on the two wings. Wherein, rotor driving system 2 is equipped with a plurality of rotors, and the wing divide into outer wing section 1 and 3 two parts in the interior wing section, and rotor driving system 2's both sides respectively with outer wing section 1 and the detachable fixed connection of interior wing section 3 to realize the effect of rotor driving system 2's independent dismantlement.
In the embodiment, the rotor power system 2 can be independently disassembled, and the wing connecting device of the composite multi-rotor unmanned aerial vehicle can be detachably arranged on the wing; when the wing connecting device of the composite multi-rotor unmanned aerial vehicle is installed on the wings of the aircraft, the aircraft has flight characteristics of multiple rotors and fixed wings, so that the mode flight of the composite multi-rotor unmanned aerial vehicle is realized.
Exemplarily, aiming at the problem that the load is transferred to the wing by the mounting structure, and the damage of the wing at the joint is easily caused by the large change of the load and force transfer route of the wing, the fork ears 4 are adopted for connection and force transfer in the embodiment, wherein, a plurality of groups of fork ears 4 are respectively arranged on both sides of the rotor power system 2, the outer wing section 1 and the inner wing section 3 are also provided with the corresponding fork ears 4, and the rotor power system 2 is connected with the outer wing section 1 and the inner wing section 3 by the way of the fork ears 4 and the fastening piece.
Furthermore, two groups of fork ears 4 are arranged on one side of the rotor wing power system 2, and the two groups of fork ears 4 are correspondingly connected with a first wing beam joint 23 and a first wing wall joint 24 of the outer wing section 1 respectively; and two sets of fork ears 4 are arranged on the other side of the rotor wing power system 2, and the two sets of fork ears 4 are correspondingly connected with the second wing beam joint 31 and the second wing wall joint 30 of the inner wing section 3 respectively.
Specifically, two first groups of fork ears 4 on two sides of the rotor wing power system 2 are a first pair, two second groups of fork ears 4 are a second pair, and the first pair of fork ears 4 are connected with the fork ears 4 of the first wing beam joint 23 and the second wing beam joint 31 through the first bolt 5, so that the outer wing section 1 and the inner wing section 3 are fixed along the first wing beam 21 of the outer wing section 1 and the second wing beam 25 of the inner wing section 3; the second pair of fork lugs 4 is connected to the first wing wall joint 24 and the second wing wall joint 30 by the second bolt 8, so that the outer wing panel 1 and the inner wing panel 3 are fixed along the first wing wall 22 of the outer wing panel 1 and the second wing wall 26 of the inner wing panel 3.
In the present embodiment, the rotor power system 2 includes a cantilever strut 16 that extends through the cantilever spar adapter plate 12 and the cantilever wing wall adapter plate 13.
Besides, the outermost layer of the rotor power system 2 is provided with a fairing 14; for convenience of assembly and disassembly, a supporting plate nut 7 is arranged at the cantilever spar adapter plate 12 and the second spar joint 31 of the inner wing section 3, and a self-locking nut 11 is arranged at the cantilever wing wall adapter plate 13 and the second wing wall joint 30 of the inner wing section 3; in consideration of assembly adjustability and movement coordination, the fork lugs 4 are internally provided with eccentric bushings 9, namely the eccentric bushings 9 are arranged in the first wing wall joint 24 of the outer wing section 1 and the fork lugs 4 of the cantilever spar adapter plate 12; in consideration of friction and abrasion, abrasion-resistant parts are arranged between the fork lug 4 and the fastening piece and between the fork lug 4 and the eccentric bushing 9, namely a first copper sleeve 6 is arranged between the first bolt 5 and the fork lug 4 and between the second bolt 8 and the fork lug 4, and a second copper sleeve 10 is arranged between the eccentric bushing 9 and the fork lug 4.
Exemplarily, cantilever vaulting pole 16 runs through cantilever spar keysets 12, cantilever wing wall keysets 13 and motor mount pad 15, and the quantity of rotor is two sets of, and the rotor is including being located rotor driving system 2 both ends and in the fixed motor mount pad 15 of cantilever vaulting pole 16, and motor 17 passes through the bolt and installs in motor mount pad 15, and rotor oar 18 links to each other with motor 17 is coaxial or wrong axle.
It should be emphasized once more that the rotor power systems 2 in this embodiment are independently detachable, that is, the wing connection device of the composite multi-rotor unmanned aerial vehicle is detachable, and in use, the rotor power systems 2 can be selectively installed to form the composite multi-rotor unmanned aerial vehicle or the rotor power systems 2 can not be installed to form the fixed-wing unmanned aerial vehicle according to task requirements.
The force transfer process of the whole machine after the rotor power system 2 is installed is provided, and the force transfer process comprises a vertical take-off and landing state, a transition flight state and a fixed wing flight state respectively.
In the vertical take-off and landing state, the outer wing section 1 and the inner wing section 3 do not provide lift force. The lift force generated by the rotor wing power system 2 is transmitted to the cantilever wing spar adapter plate 12 and the cantilever wing wall adapter plate 13 in the form of bending moment through the cantilever brace rod 16; the cantilever spar adapter plate 12 and the cantilever wing wall adapter plate 13 are sheared through the first bolt 5 and the second bolt 8 and transmitted to the second spar joint 31 and the second wing wall joint 30 of the inner wing section 3 in the form of tension or pressure; and then transmitted to the skin 19 of the inner wing section 3 and the webs of the second spar 25 and second wall 26, respectively, in the form of tensile or compressive and shear forces, so that the forces generated by the rotor are transmitted to the entire airframe structure.
In a transitional flight state, the outer wing section 1, the inner wing section 3 and the rotor power system 2 provide lift simultaneously. Bending moment and torque generated by the aerodynamic action of the outer wing section 1 are sheared through a first wing beam joint 23 and a first wing wall joint 24 of the outer wing section 1 through a first bolt 5 and a second bolt 8 and transmitted to the cantilever wing beam adapter plate 12 and the cantilever wing wall adapter plate 13 in the form of tension or pressure; the lift force generated by the rotor wing power system 2 is transmitted to the cantilever wing spar adapter plate 12 and the cantilever wing wall adapter plate 13 in the form of bending moment through the cantilever brace rod 16; then the first bolt 5 and the second bolt 8 are sheared, and the shearing force or the pressure is transmitted to the second wing beam joint 31 and the second wing wall joint 30 of the inner wing section 3, meanwhile, the inner wing section 3 generates bending moment and torque under the action of aerodynamic force, and finally the bending moment and the torque are transmitted to the whole machine body structure in the form that the skin 19 of the inner wing section 3 is subjected to the shearing force or the pressure and the web plates of the second wing beam 25 and the second wing wall 26.
In the fixed-wing flight state, the outer wing section 1 and the inner wing section 3 provide lift. Bending moment and torque generated by the aerodynamic action of the outer wing section 1 are sheared through a first wing beam joint 23 and a first wing wall joint 24 of the outer wing section 1 through a first bolt 5 and a second bolt 8 and transmitted to the cantilever wing beam adapter plate 12 and the cantilever wing wall adapter plate 13 in the form of tension or pressure; then the first bolt 5 and the second bolt 8 are sheared, and the shearing force or the pressure is transmitted to the second wing beam joint 31 and the second wing wall joint 30 of the inner wing section 3, meanwhile, the inner wing section 3 generates bending moment and torque under the action of aerodynamic force, and finally the bending moment and the torque are transmitted to the whole machine body structure in the form that the skin 19 of the inner wing section 3 is subjected to the shearing force or the pressure and the web plates of the second wing beam 25 and the second wing wall 26.
The invention also provides a composite multi-rotor unmanned aerial vehicle comprising the composite multi-rotor unmanned aerial vehicle wing connecting device, which comprises a vehicle body, wings arranged on two sides of the vehicle body and the composite multi-rotor unmanned aerial vehicle wing connecting device, wherein the wings comprise an outer wing section 1 and an inner wing section 3, and a rotor power system 2 of the composite multi-rotor unmanned aerial vehicle wing connecting device is detachably fixed between the outer wing section 1 and the inner wing section 3.
Illustratively, the outer wing section 1 is a high aspect ratio wing having an airfoil profile, and the inner wing section 3 is a straight wing having an airfoil profile.
In this embodiment, through with the part modularization, outer wing section 1, rotor driving system 2 and interior wing section 3 homoenergetic are independently dismantled, dismouting and transportation convenience. The aircraft can selectively install or dismantle the wing connecting device of the composite multi-rotor unmanned aircraft according to different task sites, achieves take-off and landing in a fixed wing mode or a composite multi-rotor mode, is wide in application range, reasonable in structure loading and force transmission route, safe and reliable in connection, few in main load-bearing structural parts, few in check items before flight and good in maintainability.
The outer wing section 1 is composed of a wing rib 20, a first wing beam 21, a first wing wall 22, a first wing beam joint 23 and a first wing wall joint 24, the inner wing section 3 is composed of a second wing beam 25, a second wing wall 26, a reinforcing plate 27, a tail stay 28, a tail stay joint 29, a second wing wall joint 30 and a second wing beam joint 31, and skins 19 of the outer wing section 1 and the inner wing section 3 are of composite honeycomb sandwich structures.
When the rotor power system 2 of the composite multi-rotor unmanned aerial vehicle wing connecting device is not installed, the fixed-wing unmanned aerial vehicle is formed. The aircraft can only fly in a fixed wing state, and the lift required by the flight is provided by the outer wing section 1 and the inner wing section 3. Bending moment and torque generated by the aerodynamic action of the outer wing section 1 are sheared through a first wing beam joint 23 and a first wing wall joint 24 of the outer wing section 1 through a first bolt 5 and a second bolt 8 and transmitted to the cantilever wing beam adapter plate 12 and the cantilever wing wall adapter plate 13 in the form of tension or pressure; then the first bolt 5 and the second bolt 8 are sheared, and the shearing force or the pressure is transmitted to the second wing beam joint 31 and the second wing wall joint 30 of the inner wing section 3, meanwhile, the inner wing section 3 generates bending moment and torque under the action of aerodynamic force, and finally the bending moment and the torque are transmitted to the whole machine body structure in the form that the skin 19 of the inner wing section 3 is subjected to the shearing force or the pressure and the web plates of the second wing beam 25 and the second wing wall 26.
It is noted that, in this specification, relational terms such as first and second, and the like are used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities.
The composite multi-rotor unmanned aerial vehicle and the wing connecting device provided by the invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (10)
1. The utility model provides a compound many rotors unmanned vehicles wing connecting device which characterized in that, includes a pair of rotor driving system (2) that are used for the symmetry to locate two wings, rotor driving system (2) are equipped with a plurality of rotors, the both sides of rotor driving system (2) are used for respectively with the outer wing section (1) of wing and the detachable fixed connection of inner wing section (3).
2. The wing attachment system of claim 1, wherein the rotor power system (2) is configured to connect to the outer wing section (1) and the inner wing section (3) via sets of ears (4) and fasteners.
3. The wing connection device of a compound multi-rotor unmanned aerial vehicle according to claim 2, wherein one side of the rotor power system (2) is provided with two sets of the fork ears (4) for corresponding connection with the first spar joint (23) and the first wing wall joint (24) of the outer wing section (1), and the other side of the rotor power system (2) is provided with two sets of the fork ears (4) for corresponding connection with the second spar joint (31) and the second wing wall joint (30) of the inner wing section (3).
4. The wing connection device of a composite multi-rotor unmanned aerial vehicle according to claim 3, wherein an eccentric bushing (9) is arranged in the fork ear (4), and wear-resistant parts are arranged between the fork ear (4) and the fastener and between the fork ear (4) and the eccentric bushing (9).
5. The composite multi-rotor UAV wing attachment of claim 3, wherein the rotor power system (2) includes a cantilever strut (16) extending through a cantilever spar adapter plate (12) and a cantilever wing wall adapter plate (13).
6. The composite multi-rotor UAV wing attachment device of claim 5, wherein the cantilevered spar adapter plate (12) is configured to provide a pallet nut (7) at the second spar joint (31).
7. The wing connection device of a composite multi-rotor unmanned aerial vehicle according to claim 6, wherein the cantilever wing adapter plate (13) is configured to provide a self-locking nut (11) at the second wing joint (30).
8. The wing attachment device for a compound multi-rotor unmanned aerial vehicle of any one of claims 1 to 7, wherein the number of rotors is two, and the rotors comprise motor mounts (15) provided at both ends of the rotor power system (2), and a motor (17) and a rotor paddle (18) fixedly mounted at the motor mounts (15).
9. The wing attachment arrangement for a compound multi-rotor unmanned aerial vehicle according to any one of claims 1 to 7, wherein the outermost layers of the rotor power systems (2) are provided with fairings (14).
10. A composite multi-rotor unmanned aerial vehicle, comprising a body, wings arranged on two sides of the body, and the composite multi-rotor unmanned aerial vehicle wing connection device according to any one of claims 1 to 9, wherein the wings comprise an outer wing section (1) and an inner wing section (3), and a rotor power system (2) of the composite multi-rotor unmanned aerial vehicle wing connection device is detachably fixed between the outer wing section (1) and the inner wing section (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010505462.4A CN111619797A (en) | 2020-06-05 | 2020-06-05 | Compound many rotors unmanned vehicles and wing connecting device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010505462.4A CN111619797A (en) | 2020-06-05 | 2020-06-05 | Compound many rotors unmanned vehicles and wing connecting device |
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| CN111619797A true CN111619797A (en) | 2020-09-04 |
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| CN202010505462.4A Pending CN111619797A (en) | 2020-06-05 | 2020-06-05 | Compound many rotors unmanned vehicles and wing connecting device |
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Application publication date: 20200904 |
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| RJ01 | Rejection of invention patent application after publication |