CN110498041B - Small-sized carrier-borne unmanned aerial vehicle suitable for catapult-assisted take-off and hanging rope recovery - Google Patents
Small-sized carrier-borne unmanned aerial vehicle suitable for catapult-assisted take-off and hanging rope recovery Download PDFInfo
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- CN110498041B CN110498041B CN201910779364.7A CN201910779364A CN110498041B CN 110498041 B CN110498041 B CN 110498041B CN 201910779364 A CN201910779364 A CN 201910779364A CN 110498041 B CN110498041 B CN 110498041B
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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
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/68—Arrester hooks
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/30—Launching, take-off or landing arrangements for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U80/00—Transport or storage specially adapted for UAVs
- B64U80/70—Transport or storage specially adapted for UAVs in containers
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Abstract
The invention belongs to the technical field of aviation aircraft design, and particularly relates to a small carrier-borne unmanned aerial vehicle suitable for catapult-assisted take-off and hanging rope recovery, which comprises a machine head, a machine body, wings, an engine, a propeller and a flat tail wing, wherein the machine head is detachably connected to the front end surface of the machine body; the aircraft body is of a hard shell structure with side strip wings, ejection hooks are arranged on the lower surface of the aircraft body, and wings are arranged on the side strip wings on the two sides of the aircraft body; the slightly part of the wing is provided with a recovery hook; the engine is arranged on the rear end face of the engine body and used for driving the propeller to rotate to provide thrust; the flat tail fin is connected with the machine body through a tail fin supporting pipe. The unmanned aerial vehicle has the following advantages: the structure strength and the force transmission path are excellent, and the requirements of short-distance catapult-assisted take-off and lossless rope hanging recovery on a small unmanned plane are met; the device has excellent aerodynamic performance and flight stability, can realize long-endurance flight, has strong wind resistance, and is suitable for operation in complex scenes such as marine carrier-borne and the like; the modularized design is adopted, so that the assembly and the disassembly are convenient, and the boxing storage and the transportation are facilitated.
Description
Technical Field
The invention belongs to the technical field of aviation aircraft design, and particularly relates to a small carrier-borne unmanned aerial vehicle suitable for catapult-assisted take-off and hanging rope recovery.
Background
The fixed wing unmanned aerial vehicle system has the characteristics of high cruising speed, high carrying capacity, long endurance time, high wind resistance and the like, and has wide application space in the fields of information investigation, frontier defense patrol, emergency rescue and the like. The traditional fixed wing unmanned aerial vehicle generally adopts the mode of wheeled running to take off and land the operation, and the in-process of taking off and land needs a section relatively more smooth runway, and this mode of taking off and land has restricted the fixed wing unmanned aerial vehicle's in many scenes application, like: land complex terrain, island reefs, especially in marine shipboard environments.
At present, the take-off mode of the carrier-based fixed wing unmanned aerial vehicle mainly comprises catapult take-off, recovery modes mainly comprise landing padlock, parachute salvage, overhead bump net and rope hanging recovery and the like, and most of the carrier-based fixed wing unmanned aerial vehicles are required to be provided with corresponding safe carrier landing systems. Whether the unmanned aerial vehicle can be safely and conveniently transmitted and recovered is an important index for evaluating the performance of the unmanned aerial vehicle, and becomes one of key points affecting the application of the unmanned aerial vehicle.
Compared with the recovery modes such as sliding padlock, overhead bump net or parachute salvage, the overhead hanging rope recovery mode can suspend the recovery rope of the recovery device outside the ship, and the obvious advantages mainly comprise: (1) The deck space occupied by the recovery device can be reduced, and the task equipment arrangement of the small and medium-sized ships is not affected; (2) the unmanned aerial vehicle can be recovered rapidly and nondestructively; (3) The recovery position can be adjusted in multiple degrees of freedom according to the recovery route and specific working conditions; (4) The safety is higher, and the damage to equipment on the ship can be avoided when the accident happens.
In recent years, a carrier-based unmanned aerial vehicle recovery mode represented by an 'air-hit net' is rapidly developed in China, such as unmanned aerial vehicles with patent numbers CN201610025095.1 and CN201310439035.0 belonging to the recovery mode, and the problem that the structural strength of the existing small unmanned aerial vehicle cannot meet the requirement of high-strength overload recovery of the hit net is solved, but compared with the recovery mode of 'hanging rope recovery', on one hand, recovery devices required by the 'hit net recovery' are required to be arranged on a ship deck, namely in a ship space, and potential safety risks are provided; on the other hand, "hit the net and retrieve" is that unmanned aerial vehicle wholly flies to retrieving the net, and wing fuselage leading edge is together atress, and "hang the rope and retrieve" is that single recovery rope slides to the slightly department of retrieving the hook along wing one side leading edge, realizes unmanned aerial vehicle's locking through retrieving the mechanical auto-lock of hook. The two recovery modes are completely different, and the stress form and the force transmission path are also completely different, so that the unmanned aerial vehicle layout and the structural scheme corresponding to the 'collision net recovery' mode are not suitable for the unmanned aerial vehicle with 'hanging rope recovery'.
In view of the above, the invention designs a small carrier-borne unmanned aerial vehicle suitable for catapult-assisted take-off and hanging rope recovery in consideration of the specificity of all-terrain application, so as to solve the problems.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a small carrier-borne unmanned aerial vehicle suitable for recovering an catapult-assisted take-off hanging rope, the unmanned aerial vehicle adopts a modularized design, so that the unmanned aerial vehicle is convenient to assemble and disassemble and convenient to store and transport, an catapult hook is arranged on the lower surface of an unmanned aerial vehicle body, recovery purchase is arranged in a front edge area of the end face of a slightly part of a wing, creatively improves the unmanned aerial vehicle body and the wing, and meets the requirements of short-distance catapult-assisted take-off and lossless hanging rope recovery.
The technical problems to be solved by the invention are realized by the following technical scheme: comprises a nose, a fuselage, wings, an engine, a propeller and a flat tail;
The unmanned aerial vehicle is of a modularized design, the aircraft nose is detachably connected to the front end face of the fuselage, the wings are inserted into the end faces of the left side and the right side of the fuselage, the engine is arranged on the rear end face of the fuselage and used for driving the propeller to rotate so as to provide power for the unmanned aerial vehicle, and the vertical fin is connected with the fuselage through a vertical fin support pipe;
the middle part of the upper curved surface of the machine head is provided with a machine head cabin cover, and the lower curved surface of the machine head is provided with a nacelle with a concave structure and equipment for mounting and executing tasks;
The fuselage is a hard shell structure with side strip wings, and comprises a fuselage main body, side strip wings, a fuselage main beam, fuselage tail support pipes and a fuselage skin, wherein the side strip wings are symmetrically arranged on two sides of the fuselage main body, the fuselage main beam is arranged in the side strip wings on two sides and penetrates through the middle part of the fuselage main body, the fuselage tail support pipes are symmetrically arranged on the lower surfaces of the side strip wings on two sides and integrally manufactured and formed with the fuselage skin in an adhesive mode, the fuselage skin is coated with the fuselage tail support pipes by arranging skirt edges, the fuselage tail support pipes are connected with the vertical tail support pipes, ejection hooks are symmetrically arranged on two sides of the lower surface of the fuselage close to the fuselage tail support pipes, and are connected with embedded parts in the fuselage skin by fasteners, and the embedded parts are connected with the fuselage main beam into a whole;
symmetrical wings are arranged on the two side strip wings, each wing comprises a wing girder, a wing auxiliary girder, a wing skin, a wing front edge, a wing rear edge, a wing tip end face and a wing tip winglet, the wing girders and the wing auxiliary girders are arranged in the wing skin, the wing front edge and the wing rear edge are filled with fillers, the wing tip winglet is inserted into the wing and fixed with the wing tip end face, the wing tip end face is a carbon fiber board, and when the wing is connected with a fuselage, the wing girder is inserted into the fuselage girder until the wing is completely attached to the end face of the side strip wing, and then the wing is locked through a quick latch;
The unmanned aerial vehicle further comprises a recovery hook which is used for recovering and purchasing a front edge area arranged on the end face of the tip of the wing and is connected with the end face of the tip of the wing and the wing main beam through a fastener;
The vertical fin comprises a left vertical fin, a right vertical fin, a high-altitude Ping Weiyi, a detachable connection between the left vertical fin and the right vertical fin, a vertical fin supporting pipe arranged at the lower part and a rudder arranged at the rear edge of the vertical fin, wherein the rear edge of the vertical fin is provided with an elevator.
Further, each wing also includes an aileron and a flap, both of which are disposed in the trailing edge region of the wing, and the aileron is located on a side of the wing that is adjacent to a tip face.
Furthermore, the nose, the main body, the tail support pipe, the body skin, the wing skin and the wing main body are all made of high-strength carbon fiber composite materials.
Further, the filler at the leading edge and trailing edge of the wing is a rigid foam.
Further, the ejection hook is arranged at the inner side of the tail support pipe of the machine body and is 5 cm-20 cm away from the tail support pipe of the machine body.
Further, the wing span of the wing is 3.6m.
Further, the leading edge sweep of the wing is 7 °.
Further, the flat tail has a spread of 0.78m.
Further, the sweep angle of the front edge of the flat tail is 0 DEG
Further, the leading edge sweep of the tailplane is 25 °.
Compared with the prior art, the invention has the beneficial effects that:
1. The unmanned aerial vehicle is characterized in that ejection hooks are arranged on the left side and the right side of the lower surface of a fuselage, the ejection hooks are connected with embedded parts in a fuselage skin through fasteners, carbon fiber materials are paved on the periphery of the embedded parts for structural reinforcement, and meanwhile, the embedded parts are connected with a fuselage main beam into a whole; during catapulting and taking off, the forward thrust on the catapulting hook is completely transmitted to the integral part of the embedded part and the main beam of the machine body, and is further borne and transmitted to the skin of the machine body and the main body of the machine body, so that all the forward thrust is dispersed, and the machine body structure is protected. The excellent local structural strength and force transmission path can ensure that the unmanned aerial vehicle of the invention can completely meet the structural strength requirement of the unmanned aerial vehicle on the maximum overload generated by catapult-assisted take-off while realizing light weight.
2. The unmanned aerial vehicle is provided with a recovery hook in the front edge area of the end face of the tip of the wing, and is connected with a carbon fiber plate of the end face of the tip of the wing and a wing main beam through a fastener; when the hanging ropes are recovered, after the recovery ropes slide to the recovery hooks along the front edges of the wings and are locked, the recovery hooks can generate extremely large outward tension in the wingspan direction, extremely large bending moment and torque are generated in the process that the unmanned aerial vehicle is recovered to be static, corresponding loads are transmitted to the wing main beams through the recovery hooks, the wing main beams serve as direct bearing structural members, on one hand, partial loads are transmitted to the wing skins and are borne by the wing main beams and the wing auxiliary beams, on the other hand, the bending moment and the tension are transmitted to the main beams of the fuselage, and the bending moment and the tension are borne by the main beams and are further transmitted to the components such as the fuselage skins and the main body of the fuselage. The excellent local structural strength and force transmission path can ensure that the unmanned aerial vehicle of the invention can realize light weight and completely meet the structural strength requirement of the unmanned aerial vehicle on the maximum overload generated by the recovery of the hanging rope.
3. The unmanned aerial vehicle adopts a modularized design, and when the unmanned aerial vehicle is stored after the flying operation is finished, the unmanned aerial vehicle only needs to be quickly disassembled into four modules, namely a machine head, a machine body, wings and a flat tail wing, and the connecting mechanisms of the machine head-machine body, the connection of the wings and the machine body, the connection of the machine body and the flat tail wing and the like are all of quick mounting/dismounting type designs, so that the unmanned aerial vehicle is convenient for outdoor operation, can be conveniently mounted into a pre-designed aircraft case after being disassembled, is convenient for storage and transportation in space such as ships and car bodies, and realizes the optimal utilization of space resources.
4. The fixed wing unmanned aerial vehicle adopts the overall layout of H-shaped double vertical tails and tail pushing force, adopts the autonomous design of the laminar flow wing profile with high lift-drag ratio, and has excellent aerodynamic performance. Through iterative optimization design of multiple rounds of overall layout, pneumatic design, structural design and system integration, the optimal parameters such as the length, the length expansion, the wing front edge sweepback angle, the horizontal vertical tail area, the sweepback angle and the like are determined. Through a large number of flight tests, the aerodynamic performance and the stability of operation are verified. On one hand, the aircraft has high lift-drag ratio under the condition of high design lift coefficient, has excellent lift characteristic and stall characteristic, and has higher maximum takeoff weight and endurance time index; on the other hand, the configuration of the upper single wing layout ensures that the aircraft has excellent transverse heading stability, and can not be disturbed by strong wind air current when flying in a complex climatic environment; finally, the proper matching of the pneumatic center and the gravity center of the whole machine ensures that the machine has excellent longitudinal stability and maneuverability, can resist external disturbance such as gusts and the like, and can timely adjust the self flight attitude and the route control in the catapult-assisted take-off and rope-hanging recovery stage.
5. The lower curved nacelle of the unmanned aerial vehicle head is of a concave structure, so that when task equipment such as a photoelectric nacelle is mounted, the recovery rope can not contact the mounting equipment during recovery, the safety of the equipment can be effectively protected, and in addition, the execution equipment is arranged in the concave structure, and the pneumatic drag reduction characteristic and the nacelle field angle range are considered.
Drawings
FIG. 1 is a schematic view of the overall structure of a unmanned aerial vehicle of the present invention;
FIG. 2 is an exploded view of the structure of the unmanned aerial vehicle of the present invention;
FIG. 3 is a schematic view of the structure of the unmanned aerial vehicle according to the present invention;
FIG. 4 is a schematic view of the wing structure of the unmanned aerial vehicle of the present invention;
FIG. 5 is a cross-sectional view of the wing structure of the unmanned aerial vehicle of the present invention;
FIG. 6 is a schematic view of the horizontal vertical tail structure of the unmanned aerial vehicle of the present invention;
FIG. 7 is a schematic view of the connection structure of the ejection hook and the fuselage of the unmanned aerial vehicle of the present invention;
FIG. 8 is a schematic view of the connection structure of the recovery hook and the wing of the unmanned aerial vehicle of the present invention;
FIG. 9 is a schematic view of the wing-to-fuselage plug connection of the unmanned aerial vehicle of the present invention;
FIG. 10 is a cross-sectional view of a unmanned wing-to-fuselage plug connection of the present invention;
FIG. 11 is a schematic illustration of the unmanned aerial vehicle storage and boxing step of the present invention;
FIG. 12 is a diagram showing the effects of the present invention after the unmanned aerial vehicle is stowed;
FIG. 13 is a graph of unmanned aerial vehicle flight effect versus time of flight for the present invention;
FIG. 14 is a graph of the effect of flight of the unmanned aerial vehicle of the present invention versus time of flight;
FIG. 15 is a graph of unmanned aerial vehicle flight effects-unmanned aerial vehicle pitch angle versus time of flight according to the present invention;
FIG. 16 is a schematic view of an catapult-assisted take-off and roping recovery structure in the land environment of the unmanned aerial vehicle of the present invention;
fig. 17 is a schematic view of catapult-assisted take-off and rope-hanging recovery in an unmanned aerial vehicle marine vessel environment.
In the figure: 1. a machine head; 2. a body; 3. a wing; 4. an engine; 5. a propeller; 6. a vertical tail; 7. a storage box; 11. a nose hatch cover; 12. a nacelle; 21. a main body of the main body; 22. a strake wing; 23. a main body girder; 24. a tail support tube of the machine body; 25. a fuselage skin; 26. an ejection hook; 27. an embedded part; 28. a front end face; 29. a rear end face; 31. a left wing; 32. a right wing; 33. a filler; 34. a quick plug pin; 35. a recovery hook; 41. an engine cover; 62. a vertical fin; 63. a flat tail; 211. umbrella cabin cover; 212. a middle hatch cover; 213. a rear hatch; 301. a wing main beam; 302. an auxiliary wing beam; 303. a wing skin; 304. a wing leading edge; 305. a trailing edge of the wing; 306. a wing tip end face; 307. wing tip winglets; 308. aileron; 309. a flap; 601. a vertical tail support pipe; 602. a rudder; 603. a vertical tail steering engine; 604. a vertical tail skin; 631. an elevator; 632. a horizontal tail steering engine; 633. horizontal tail ribs; 634. and (5) a horizontal tail skin.
Detailed Description
The following detailed description, structural features and functions of the present invention are provided with reference to the accompanying drawings and examples in order to further illustrate the technical means and effects of the present invention to achieve the predetermined objects.
The invention relates to an unmanned aerial vehicle, which is shown in figures 1-10, and is suitable for catapult-assisted take-off and hanging rope recovery, and comprises a nose 1, a fuselage 2, wings 3, an engine 4, a propeller 5 and a flat tail 6.
According to the unmanned aerial vehicle, a modularized design is adopted, a nose 1 is detachably connected to the front end face of a machine body 2, wings 3 are inserted into the end faces of the left side and the right side of the machine body 2, an engine 4 is arranged on the rear end face of the machine body 2 and used for driving a propeller 5 to rotate so as to provide power for the unmanned aerial vehicle, and a vertical fin 6 is connected with the machine body 2 through a vertical fin support pipe 601.
Specifically, the middle part of the upper curved surface of the machine head 1 is provided with a machine head hatch cover 11, the machine head hatch cover 11 is used for operating a working area, and preferably, in the width range of 1 cm-5 cm around the opening cover, the opening structure reinforcement is performed by adopting carbon fibers and rigid foam materials, the lower curved surface nacelle 12 of the machine head 1 is arranged into a concave structure and is used for mounting task equipment such as a photoelectric nacelle, and the machine head hatch cover is designed into a concave structure and has two advantages: firstly, the aerodynamic drag reduction characteristic and the nacelle field angle range are considered; secondly, when the hanging rope is recovered, the recovery rope can not contact the mounting equipment under any condition and posture, and the safety of the equipment can be effectively protected.
The fuselage 2 is a hard shell structure with side wings, and comprises a fuselage main body 21, side wings 22, a fuselage main beam 23, a fuselage tail support tube 24 and a fuselage skin 25, wherein the side wings 22 are symmetrically arranged at two sides of the fuselage main body 21, the fuselage main beam 23 is arranged in the side wings 22 at two sides and penetrates through the middle part of the fuselage main body 21, the fuselage tail support tube 24 is symmetrically arranged at the lower surfaces of the side wings 22 at two sides and integrally manufactured and formed with the fuselage skin 25 in an adhesive mode, the fuselage skin 25 is coated with the fuselage tail support tube 24 by arranging a skirt, the fuselage tail support tube 24 is coated with the fuselage tail support tube 24, the pneumatic resistance can be reduced, the connection strength of the fuselage tail support tube 24 can be improved, in addition, the precise positioning of the fuselage tail support tube 24 can be realized while the fuselage tail support tube is connected with the vertical tail support tube 601, ejection hooks 26 are symmetrically arranged at two sides of the lower surface of the fuselage 2 near the fuselage tail support tube 24, the ejection hooks 26 are connected with embedded parts 27 in the fuselage skin 25 through fasteners, and the embedded parts 27 are connected with the fuselage main beam 23 into a whole; in order to enhance the strength of the joint, carbon fiber materials can be paved on the periphery of the embedded part 27 for structural reinforcement, the preferable embedded part 27 is made of aluminum materials to reduce the overall weight without losing strength, and the preferable ejection hooks 26 are arranged on the inner side of the tail support tube 24 and are 5 cm-20 cm away from the tail support tube 24, so that the ejection device can avoid the tail support tube 24 during ejection take-off.
The symmetrical wings 3 are arranged on the two side slat wings 22, and the wings adopt an upper single wing layout to enhance the flight stability of the whole unmanned aerial vehicle in consideration of the diversification of land application environments and the complex diversity of marine climate environments, the wings 3 comprise a left wing 31 and a right wing 32, the wings 3 adopt autonomous designed high lift-drag ratio laminar wing profiles, the maximum thickness of the wing profiles is 10 percent C, the chord direction position corresponding to the maximum thickness is 34 percent C, the maximum camber is 3.76 percent C, the chord direction position corresponding to the maximum camber is 41 percent C, and the thickness of the trailing edge is 0.3 percent C, wherein C is the chord length of the wing profiles;
wherein, the geometrical coordinate expressions of the upper surface and the lower surface of the airfoil are respectively:
Wherein x represents the surface abscissa of the airfoil and y up represents the upper surface ordinate of the airfoil; y low represents the lower surface ordinate of the airfoil; a up represents the expression coefficient of the geometrical coordinates of the upper surface of the airfoil; a low represents the expression coefficient of the geometrical coordinates of the lower surface of the airfoil;
the values of a up and a low are shown in table 1:
TABLE 1 expression coefficients for airfoil geometry
The wing 3 adopts a 'main and auxiliary girder structure' design, which comprises a wing main girder 301, a wing auxiliary girder 302, a wing skin 303, a wing front edge 304, a wing rear edge 305, a wing tip end face 306 and a wing tip winglet 307, wherein the arrangement of the wing tip winglet 307 reduces the induced resistance of the wing 3, improves the lift resistance characteristic of the unmanned aerial vehicle, increases the endurance time, the wing main girder 301 and the wing auxiliary girder 302 are arranged in the wing skin 303, the wing main girder 301 and the wing auxiliary girder 302 are tightly connected with the wing skin 303 into a whole in an adhesive mode, so as to enhance the bearing strength of the wing 3, the wing front edge 304 and the wing rear edge 305 are filled with filler 33, the filler 33 is preferably rigid foam with light mass and excellent physical impact property, the wing tip winglet 307 is inserted into the wing 3 and fixed with the wing tip end face 306, the wing tip end face 306 is preferably a carbon fiber board, when the wing 3 is connected with the fuselage 2, the wing main girder 301 is inserted into the fuselage main girder 23 until the end face of the wing 3 is completely attached with the side strip wing 22, and then the wing main girder 301 is locked in a fast-in a mode 34, the main girder is connected with the fuselage main girder 23, and the fuselage main girder is effectively connected with the fuselage frame 23, and the fuselage body is simultaneously, the main girder is connected with the fuselage frame 23, and the main body is connected with the main girder 25, and the main body 25 is well, and the main body is connected with the main body frame 25, and the main body frame 25 is well, and the main body frame is well, and the main body and the frame is well connected.
The unmanned aerial vehicle still includes recovery hook 35, retrieves and purchase 35 setting in the leading edge district of wing tip terminal surface 306, and be connected with wing tip terminal surface 306 and wing girder 301 through the fastener, and the upper and lower curved surface of preferred recovery hook 35 is unanimous with the appearance of wing 3 wing tip curved surfaces to guarantee that retrieve the rope can not block in local position department.
Through the arrangement, when the unmanned aerial vehicle is launched at the catapult-assisted take-off: the forward thrust on the ejection hook 26 is transmitted to the integral part of the embedded part 27 and the main body girder 23, and is further borne and transmitted to the main body skin 25, so that the unmanned aerial vehicle of the invention can completely meet the structural strength requirement of the maximum overload generated by ejection and take-off on the unmanned aerial vehicle while realizing light weight due to excellent local structural strength and force transmission path; when unmanned aerial vehicle hangs rope and retrieves: after the recovery rope slides to the recovery hook 35 along the wing front edge 304 and is locked, the recovery hook 35 generates extremely large outward tension along the span direction, and extremely large bending moment and torque are generated in the process of recovering the unmanned aerial vehicle to be stationary, corresponding loads are transmitted to the wing girder 301 through the recovery hook 35, the wing girder 301 serves as a direct bearing structure, on one hand, partial loads are transmitted to the wing skin 303 and are borne by the wing skin 303 and the wing auxiliary girder 302 and the like together, on the other hand, the bending moment and the tension are transmitted to the main body girder 23 and are borne by the wing skin 23 and are further transmitted to the main body skin 25, the main body frame and other parts to disperse stress, and therefore the structural strength requirement of the unmanned aerial vehicle due to the maximum overload generated by the recovery of the hanging rope is met.
Preferably, each wing 3 further comprises an aileron 308 and a flap 309, the aileron 308 and the flap 309 are arranged in the trailing edge area of the wing 3, the aileron 308 is close to one side of the end face 306 of the tip of the wing, the wing 3 is provided with the conventional aileron 308, and meanwhile, the flap 309 is additionally arranged to improve the lift force of the catapult-assisted take-off and the recovery stage of the hanging rope, when the unmanned aerial vehicle is in heavy full-load flight operation, the speed requirement can be reduced, namely the maximum overload during the catapult-assisted take-off and the recovery of the hanging rope is reduced, and the service life of the unmanned aerial vehicle is prolonged.
Preferably, the nose 1, the main body 23, the tail pipe 24, the body skin 25, the wing skin 303 and the wing main body 301 are all made of high-strength carbon fiber composite materials.
In order to ensure that the unmanned aerial vehicle flies stably and avoid winding of the propeller 5 and a hanging rope during recovery, the unmanned aerial vehicle adopts an H-shaped double-vertical-tail design, a vertical tail 6 of the unmanned aerial vehicle comprises a left vertical tail 62 and a right vertical tail 62 and a high-position vertical tail wing 63, the left vertical tail 62 and the right vertical tail 63 are both designed by adopting a main and auxiliary girder structure similar to that of a wing 3, the vertical tail wing 63 and the left vertical tail 62 are detachably connected, the vertical tail 62 comprises a vertical tail support pipe 601 arranged at the lower part and a rudder 602 arranged at the rear edge of the vertical tail 62, the rear edge of the vertical tail wing 63 is provided with an elevator 631, the two sides of the upper surface of the vertical tail 63 are also provided with a vertical tail rib 633, the vertical tail skin 604 on the left vertical tail 62 and the vertical tail skin 604 on the vertical tail 63 are also made of a high-strength carbon fiber composite material, the vertical tail steering engine 603 and the vertical tail rudder 632 are also arranged on the vertical tail 62 and the vertical tail wing 63, the steering engine is fully utilized, and the vertical tail steering engine is fully installed, and the resistance of the tail wing is reduced while the full use of the limited space of the steering engine can be fully utilized, and the resistance of the tail wing is fully installed.
The unmanned aerial vehicle body 2 adopts a hard shell structure with strake wings, and has the following advantages: 1. the aerodynamic characteristics of the unmanned aerial vehicle are improved, and the excellent wing body fusion appearance can effectively realize lift-increasing and drag-reducing, so that the endurance time is prolonged; 2. in the hanging rope recovery stage, as long as the unmanned aerial vehicle touches the recovery rope in the span range, the recovery rope at the next moment slides to the recovery hook 35 of the wing tip along the smooth front edge, so that the recovery is completed by locking, and the recovery rope can slide to the recovery hook 35 more easily and more quickly by adopting the shape of the machine body with the strake wing; 3. the length and thickness of the edge strip wing-shaped appearance at the wing root are larger, so that the structural strength of the wing root can be improved, and the unmanned aerial vehicle can be ensured to bear larger overload impact without structural damage during catapult-assisted take-off and hanging rope recovery; 4. the hard shell structure is easy to process and produce, high in strength, and convenient to arrange, use and maintain of internal equipment.
The unmanned aerial vehicle is provided with the umbrella cabin cover 211, the middle cabin cover 212 and the rear cabin cover 213 on the upper surface of the body 2, can be used for arranging avionics equipment such as an umbrella cabin, a flight control device, an oil tank, a picture transmission device and the like, and is provided with a high-strength carbon fiber composite material manufacturing reinforced bulkhead on the front end surface 28 and the rear end surface 29 of the body 2 so as to ensure sufficient strength when being connected with the machine head 1 and the engine 4, the engine 4 is connected on the rear end surface 29 through the engine cover 41 to play a role in rectifying and reducing resistance, the engine 4 mainly adopts a double-cylinder opposite gasoline engine to drive the propeller 5 to rotate so as to provide thrust, and the tail pushing type power layout form is beneficial to the recovery of the hanging rope of the unmanned aerial vehicle and can avoid the damage of the recovery rope to the propeller 5; the thrust axis is basically positioned at the central axis of the machine body and approximately passes through the center of gravity of the whole machine; the engine 4 may also carry a "stator-rotor" generator in which the stator is mounted on the engine crankcase via a stator mounting bracket and the rotor is directly driven by the engine crankshaft to provide a long-endurance power supply (multiple different voltages) for all avionics on board the vehicle.
The unmanned aerial vehicle adopts a modularized design, when the unmanned aerial vehicle is stored after the flying operation is finished, the aircraft nose, the wing and the vertical fin are respectively disassembled, and the unmanned aerial vehicle can be placed into the preset storage box 7 according to the steps shown in fig. 10, the effect after placement is shown in fig. 11, and the unmanned aerial vehicle can be taken out and installed according to the reverse sequence when in use, so that the unmanned aerial vehicle is convenient to store and transport in narrow spaces such as ships, vehicle bodies and the like, and the optimal utilization of space resources is realized.
Through a large number of design simulation and flight tests, the optimal unmanned aerial vehicle is designed, and has the parameters that the maximum take-off weight is 30kg, the cruising speed is 100km/h, the length of the aircraft is 2.1m, the wing span is 3.6m, the front-edge sweepback angle of the wing is 7 degrees, the span length of the horizontal tail is 0.78m, the front-edge sweepback angle of the horizontal tail is 0 degree, and the front-edge sweepback angle of the vertical tail is 25 degrees.
Examples of the invention
The following describes the invention in real time by way of three examples:
Example one: true aircraft flight test
The inventor carries out a large amount of flight tests to this unmanned aerial vehicle, take off and land the mode respectively for pneumatic catapult-assisted take off and hang down the rope and block the recovery. Fig. 13 to 15 show actual flight effects of the unmanned aerial vehicle, namely the change relation of the flight airspeed, the flight altitude and the pitch angle of the unmanned aerial vehicle along with the flight time, and the flight test time is 3 hours. According to the graph, the unmanned aerial vehicle is stable in performance in the catapult-assisted take-off and rope-hanging recovery stages, the unmanned aerial vehicle can maintain stable flight at the cruising altitude (altitude 750 m) and cruising speed (28 m/s) during the whole flight test period, and the pitch angle also fluctuates slightly around 0 degrees all the time, so that the unmanned aerial vehicle has excellent flight stability. The example shows that the unmanned aerial vehicle has excellent pneumatic lift-drag characteristic and pneumatic balancing characteristic, and has good engineering feasibility, thus being a small unmanned aerial vehicle very suitable for catapult-assisted take-off and rope hanging recovery.
Example two: emission and recovery in land vehicle-mounted environment
Because land operation has characteristics such as environment complicacy is various and task mobility is strong, especially to the long endurance flight of application scene such as border patrol often needs more than 10 hours, and traditional race take-off and landing fixed wing unmanned aerial vehicle is higher to the place requirement, and the restriction factor is more, and small-and-medium-sized many rotors and the unmanned aerial vehicle duration of taking off and landing vertically on the market is only 1~5 hours, also can't satisfy the task demand. Therefore, the small and medium-sized unmanned aerial vehicle adopting catapult-assisted take-off and hanging rope recovery as take-off and landing modes is required to be provided with a corresponding catapult-assisted/recovery device to complete the operation task. Fig. 16 shows a certain land launching and recovering integrated operation vehicle in which the unmanned aerial vehicle of the invention is practically applied, and the unmanned aerial vehicle can complete the subjects of deployment, assembly, catapult-assisted take-off, hanging rope recovery, storage and boxing and the like in the carriage range, so that the unmanned aerial vehicle of the invention is proved to fully meet the use requirements in a land-based environment.
Example three: launching and recovery in marine shipboard environments
The unmanned aerial vehicle has huge application requirements in the marine environment, and the ship and the island can provide small landing sites and greatly limited space; in addition, the marine fishery exploration, coastal border line patrol and other work tasks need to be equipped with a portable long-endurance unmanned plane. At this time, the unmanned aerial vehicle integrating the functions of catapult-assisted take-off and rope hanging recovery is required to be adopted to realize the unmanned aerial vehicle flight operation on a ship moving platform or an island platform. FIG. 17 shows the process of catapult-assisted take-off and rope-hanging recovery of a marine vessel using the unmanned aerial vehicle of the present invention, which is a modular design, so that the unmanned aerial vehicle of the present invention can efficiently utilize the limited space on the vessel to store the tank, and can also be conveniently deployed and assembled; meanwhile, the wing and the fuselage adopt an innovative structural scheme and a force transmission path, so that the wing and the fuselage can bear the maximum ejection overload to ensure that the fuselage and internal equipment are not damaged, and can efficiently absorb and transmit the impact overload during the recovery of the hanging rope to realize the lossless recovery. Therefore, the small unmanned aerial vehicle for catapult-assisted take-off and rope hanging recovery is suitable for launching and recovery in a marine ship-borne environment.
The foregoing is a further detailed description of the invention in connection with the preferred embodiments, and it is not intended that the invention be limited to the specific embodiments described. It will be apparent to those skilled in the art that several simple deductions or substitutions may be made without departing from the spirit of the invention, and these should be considered to be within the scope of the invention.
Claims (8)
1. The utility model provides a small-size carrier-borne unmanned aerial vehicle suitable for catapult-assisted take-off and hang rope recovery which characterized in that: comprises a nose (1), a fuselage (2), wings (3), an engine (4), a propeller (5) and a flat tail (6);
The unmanned aerial vehicle is of a modularized design, the machine head (1) is detachably connected to the front end face of the machine body (2), the wings (3) are inserted into the left side end face and the right side end face of the machine body (2), the engine (4) is arranged on the rear end face of the machine body (2) and used for driving the propeller (5) to rotate so as to provide power for the unmanned aerial vehicle, and the vertical fin (6) is connected with the machine body (2) through the vertical fin stay tube (601);
the middle part of the upper curved surface of the machine head (1) is provided with a machine head cabin cover (11), and the lower curved surface of the machine head (1) is provided with a nacelle (12) with a concave structure and equipment for mounting and executing tasks;
The utility model provides a fuselage (2) is hard shell body structure of taking strake wing, including fuselage main part (21), strake wing (22), fuselage girder (23), fuselage tail pipe (24) and fuselage covering (25), strake wing (22) symmetry sets up in fuselage main part (21) both sides, fuselage girder (23) set up in strake wing (22) both sides and run through fuselage main part (21) middle part, fuselage tail pipe (24) symmetry sets up in strake wing (22) both sides's lower surface, and through the integrated manufacturing shaping of form and fuselage covering (25) of bonding, fuselage covering (25) are through setting up shirt rim cladding fuselage tail pipe (24), fuselage tail pipe (24) are connected with perpendicular tail pipe (601), fuselage (2) lower surface both sides are close to fuselage tail pipe (24) department symmetry and are provided with ejection hook (26), ejection hook (26) are connected with embedded part (27) in fuselage covering (25) through the fastener, embedded part (27) are connected as an organic whole with fuselage girder (23);
Symmetrical wings (3) are arranged on the edge strip wings (22) on two sides, the wings (3) comprise wing main beams (301), wing auxiliary beams (302), wing skins (303), wing front edges (304), wing rear edges (305), wing tip end faces (306) and wing tip winglets (307), the wing main beams (301) and the wing auxiliary beams (302) are arranged in the wing skins (303), fillers (33) are filled at the wing front edges (304) and the wing rear edges (305), the wing tip winglets (307) are inserted into the wings (3) and fixed with the wing tip end faces (306), the wing tip end faces (306) are carbon fiber plates, and when the wings (3) are connected with the fuselage (2), the wing main beams (301) are inserted into the fuselage main beams (23) until the end faces of the wings (3) and the edge strip wings (22) are completely attached, and then are locked through fast bolts (34);
The unmanned aerial vehicle further comprises a recovery hook (35), wherein the recovery hook (35) is arranged in the front edge area of the wing tip end face (306) and is connected with the wing tip end face (306) and the wing main beam (301) through a fastener;
The vertical fin (6) comprises a left vertical fin (62) and a right vertical fin (63) and a high-mounted vertical fin (63), the horizontal fin (63) is detachably connected with the left vertical fin (62) and the right vertical fin (62), the vertical fin (62) comprises a vertical fin supporting tube (601) arranged at the lower part and a rudder (602) arranged at the rear edge of the vertical fin (62), and an elevator (631) is arranged at the rear edge of the horizontal fin (63);
Each of the wings (3) further comprises an aileron (308) and a flap (309), wherein the aileron (308) and the flap (309) are arranged in the trailing edge area of the wing (3) and the aileron (308) is close to one side of the tip end surface (306) of the wing;
The aircraft nose (1), the main body (23), the tail support pipe (24), the body skin (25), the wing skin (303) and the wing main body (301) are all made of high-strength carbon fiber composite materials;
The machine head hatch cover (11) is used for operating a working area, and an opening structure is reinforced by adopting carbon fiber and rigid foam materials within the width range of 1 cm-5 cm around the hatch cover.
2. The small-sized carrier-borne unmanned aerial vehicle suitable for recovering an catapult-assisted take-off hanging rope according to claim 1, wherein: the filler (33) at the leading edge (304) and trailing edge (305) of the wing is a rigid foam.
3. The small-sized carrier-borne unmanned aerial vehicle suitable for recovering an catapult-assisted take-off hanging rope according to claim 1, wherein: the ejection hook (26) is arranged on the inner side of the tail support pipe (24) of the machine body, and the distance between the ejection hook and the tail support pipe (24) of the machine body is 5 cm-20 cm.
4. The small-sized carrier-borne unmanned aerial vehicle suitable for recovering an catapult-assisted take-off hanging rope according to claim 1, wherein: the wing (3) has a wing span of 3.6m.
5. The small-sized carrier-borne unmanned aerial vehicle suitable for recovering an catapult-assisted take-off hanging rope according to claim 1, wherein: the forward sweep of the wing (3) is 7 °.
6. The small-sized carrier-borne unmanned aerial vehicle suitable for recovering an catapult-assisted take-off hanging rope according to claim 1, wherein: the spreading length of the horizontal tail wing (63) is 0.78m.
7. The small-sized carrier-borne unmanned aerial vehicle suitable for recovering an catapult-assisted take-off hanging rope according to claim 1, wherein: the forward sweep angle of the horizontal tail wing (63) is 0 degrees.
8. The small-sized carrier-borne unmanned aerial vehicle suitable for recovering an catapult-assisted take-off hanging rope according to claim 1, wherein: the leading edge sweep of the tailplane (62) is 25 °.
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| CN110775273A (en) * | 2019-11-29 | 2020-02-11 | 西安航空学院 | Unmanned aerial vehicle |
| CN110884642A (en) * | 2019-12-07 | 2020-03-17 | 湖南浩天翼航空技术有限公司 | Wing quick assembly disassembly structure based on square roof beam |
| UA145959U (en) * | 2020-05-22 | 2021-01-13 | Uav structural elements quick release fastening system | |
| CN112158323B (en) * | 2020-10-24 | 2024-06-21 | 西安航空学院 | Unmanned aerial vehicle fuselage-heat dissipation intake duct 3D additive integrated skin structure |
| CN113460282B (en) * | 2021-06-28 | 2023-06-06 | 航天时代飞鸿技术有限公司 | Pneumatic layout of unmanned aerial vehicle |
| US20230039018A1 (en) * | 2021-08-09 | 2023-02-09 | InSitu, Inc., a subsidiary of the Boeing Company | Unmanned aerial vehicles including wing capture devices and related methods |
| CN114408160B (en) * | 2021-12-17 | 2023-08-29 | 海丰通航科技有限公司 | Tail support pipe and unmanned aerial vehicle |
| CN116639274A (en) * | 2023-05-25 | 2023-08-25 | 西安航空学院 | Overall layout method and structure of whole-body unmanned aerial vehicle |
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