CN212423462U

CN212423462U - A highly versatile large-loaded small unmanned aerial vehicle

Info

Publication number: CN212423462U
Application number: CN201920632373.9U
Authority: CN
Inventors: 甘文彪; 向锦武; 王红波; 李道春; 彭博
Original assignee: Beihang University
Current assignee: Beihang University
Priority date: 2019-05-06
Filing date: 2019-05-06
Publication date: 2021-01-29
Anticipated expiration: 2029-05-06

Abstract

The utility model provides a high versatility loads small-size unmanned vehicles greatly. The aircraft comprises: the wing body fuses the fuselage, sets up two fixed main wings of fuselage both sides set up two vaulting poles and the modularization fin subassembly of setting in two vaulting pole rear ends of two main wings below. The two main wings adopt optimized high-lift wing shapes, so that the whole aircraft has a smaller stall speed; the fuselage has carried out wing body and has fused the design, has great loading volume in the fuselage, can carry on multiple task load, and fuel weight coefficient can reach 0.5 to the utmost, and simultaneously, the whole machine has nimble ability of taking off and land, can launch according to the task needs and take off, take off or take off and land perpendicularly to unmanned vehicles's adaptability and the execution efficiency to different grade type flight task have been improved.

Description

Small-size unmanned vehicles of high commonality big load

Technical Field

The embodiment of the invention relates to the aircraft technology, in particular to a high-pass large-loading small unmanned aircraft.

Background

The small-sized fixed wing unmanned aerial vehicle is widely applied in military and civil fields in China. For example, in the military field, it can be used for battlefield reconnaissance, information collection, information support, etc.; in the civil field, the method can be used for traffic inspection, resource exploration, agriculture and forestry plant protection and the like. Although the unmanned aerial vehicle technology is mature day by day, most of the existing small-sized fixed wing unmanned aerial vehicles are used for specific purposes and carry specific mission loads to carry out actual operation under specific flight environments. When the uncertainty of external factors such as geographic environment, task demand and task load changes, the limitation of the geometric dimension of the task load, the restriction of the takeoff field environment, the improvement of the requirement of the air leaving operation time and other factors can obviously reduce the adaptability and the execution capacity of the existing small fixed wing unmanned aerial vehicle to flight tasks, and further limit the wider application of the unmanned aerial vehicle to a certain extent.

Disclosure of Invention

Aiming at the defects in the prior art, the invention provides a high-throughput large-loading small unmanned aerial vehicle which can correspondingly carry out catapult takeoff, sliding takeoff or vertical take-off and landing according to the change of geographic environment and task requirements; meanwhile, the wing body is integrated with the large-volume fuselage, so that various task loads with larger geometric sizes can be carried, and the adaptability and the execution capacity of the flight task are obviously enhanced.

The invention provides a high-universality large-loading small-sized unmanned aerial vehicle, which comprises:

the wing body fuses big volume fuselage, sets up the big volume oil tank in fuselage middle part, and fuel weight coefficient can reach 0.5 at most, sets up two fixed main wings of fuselage both sides set up the tail pushing-type screw propeller of fuselage afterbody, two vaulting poles that length equals that set up in the main wing below and set up the fin subassembly at the vaulting pole rear end to the whole machine has three kinds of modes of taking off of catapult take off, take off and the VTOL.

The main wing is symmetrically distributed on two sides of the fuselage along the longitudinal axis of the fuselage, and the rear edge of the wing is symmetrically provided with integrated flaperons.

Two vaulting poles that length equals are followed fuselage longitudinal axis symmetry sets up the main wing below just is close to main wing root position department.

The rear end of the stay bar is symmetrically provided with two vertical tail wings along the longitudinal axis of the machine body, and the rear edges of the two vertical tail wings are symmetrically provided with rudders.

The wingtips of the two vertical tail wings are connected through a horizontal tail wing, and the rear edge of the horizontal tail wing is provided with an elevator.

The modular tail assembly is composed of the two vertical tail wings and the horizontal tail wing and is detachably connected with the stay bar.

Optionally, the main wing is a flat wing, a trapezoidal wing, or a swept back wing.

Optionally, the main wing is mounted on the fuselage in a position of an upper single wing, a middle single wing or a lower single wing.

Alternatively, the engine may be built into the aft or exposed, and when built into the fuselage, the back of the fuselage will be provided with air intake ducts.

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 to be understood that the drawings in the following description are of some embodiments of the invention, and are intended to provide further understanding of the invention and are not to be construed as limiting the invention.

Fig. 1 is a schematic structural diagram of a high-universality large-loading small-sized unmanned aerial vehicle in an catapult takeoff mode according to an embodiment of the invention;

FIG. 2 is a schematic diagram of the assembly of structural components of the high-universality large-loading small-sized unmanned aerial vehicle in catapult takeoff mode provided by the embodiment of the invention

FIG. 3 is a schematic structural diagram of a high versatility and large loading small unmanned aerial vehicle in a vertical take-off and landing mode according to an embodiment of the present invention;

FIG. 4 is a schematic diagram of the assembly of the structural components of the small-sized unmanned aerial vehicle with high universality and large loading capacity in the vertical take-off and landing mode provided by the embodiment of the invention

Description of reference numerals:

1: a body; 2: a main wing; 3: a vertical tail; 4: a horizontal rear wing; 5: a tail-pushing propeller; 6: a flap; 7: a rudder; 8: an elevator; 9: a stay bar; 10: an air inlet channel; 11: an exhaust pipe; 12: a front lift propeller; 13: rear-mounted lift propeller

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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. It should be understood that the detailed description and specific examples, while indicating the present invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.

The high-pass large-loading small unmanned aerial vehicle provided by the embodiment has three take-off and landing modes, namely catapult take-off, running take-off and vertical take-off and landing. Fig. 1 is a schematic structural diagram of a high-throughput large-loading small unmanned aerial vehicle in an catapult takeoff mode, which is provided by the implementation of the invention. Fig. 1 provides a high-versatility large-loading unmanned aerial vehicle, which comprises: the airplane comprises a fuselage 1, a main wing 2, a vertical tail wing 3, a horizontal tail wing 4, a tail pushing type propeller 5, a flaperon 6, a rudder 7, an elevator 8 and a support rod 9. The fuselage 1 and the main wing 2, the main wing 2 and the stay bar 9, and the stay bar 9 and the vertical tail fin 3 can be detachably connected for transportation, and the assembly schematic diagram of the structural components is shown in fig. 2.

The main wings 2 are symmetrically arranged on two sides of the fuselage 1, and the stay bars 9 are arranged below the two main wings and close to the wing roots. Two vertical tail fins 3 are symmetrically arranged at the rear end of the stay 9 along the longitudinal axis of the fuselage 1. The horizontal tail 4 and the wing tip of the vertical tail 3 can be detachably connected. In the vertical lifting mode, the front end of the stay bar 9 can be extended forwards, a front lifting propeller 12 is arranged at the front end of the stay bar, and a rear lifting propeller 13 is arranged at the rear end of the stay bar 9 to ensure the moment balance of the whole machine.

The fuselage 1 adopts the wing body to fuse the design, and smooth transition has increased fuselage loading space again when reducing the wing body interference resistance in the whole quick-witted cruise phase between fuselage 1 and the main wing 2. The machine head adopts the olecranon-like shape design, thereby being beneficial to improving the pitching moment characteristic of the machine body. The front section of the body 1 from the head to the position of about 1/3 the length of the body is provided as a task load cabin which can accommodate task equipment with various geometric sizes such as photoelectric balls, radars, cameras and the like. The middle section of the machine body 1 is provided with a large-volume oil tank, and the weight coefficient of fuel oil can reach 0.5 under the full oil state. The two sides of the middle section of the machine body 1 are connected with the front main beam and the rear main beam of the main wing 2, the rear main beam of the main wing is connected on a partition frame at the rear end of the middle section of the machine body 1, and the partition frame is a solid wall plate and is used as a rear wall plate of an oil tank to seal the oil tank. The rear section of the fuselage 1 is mainly provided with a tail pushing type propeller 5 and an engine, and the tail pushing type propeller 5 is used for providing thrust when the aircraft flies flat.

Alternatively, the engine may be built into the aft or exposed; when the engine is arranged in the tail part of the fuselage, air inlet channels are correspondingly arranged on the back and the belly of the fuselage.

Alternatively, the cross-sectional shape of the fuselage 1 may be circular, oval or other shapes, and the cross-sectional shape of the rear section of the fuselage 1 may be the same as the cross-sectional shape of the middle section of the fuselage. The cross-sectional shape of the body 1 is not limited in this embodiment.

Alternatively, the structure of the fuselage 1 and the main wing 2 is mainly composed of an aluminum frame, an aluminum reinforcing frame, and an aluminum stringer. The frame is covered with a skin, the skin material can be made of composite materials, and the weight of the whole aircraft structure can be effectively reduced while the bearing capacity of the aircraft body and the main wing is enhanced.

The main wings 2 are symmetrically arranged on two sides of the middle section of the fuselage 1 along the longitudinal axis of the fuselage 1 and are used for providing main lifting force for the unmanned aerial vehicle in the cruising stage. The main wing 2 may have a geometric shape such as a straight wing, a swept-back wing, a trapezoidal wing, etc., and the geometric shape of the main wing 2 is not limited in this embodiment.

Alternatively, the main wing 2 is bolted or welded to the middle of the fuselage 1, and the rib may be formed by bonding high-strength aviation foam and carbon fiber plates, and the rib is covered by a skin, which may be made of carbon fiber.

The rear edge of the main wing 2 is provided with a flaperon 6 which can simultaneously have the dual functions of a flap and an aileron, and the flaperon is operated by a built-in steering engine at the joint of a flaperon rotating shaft and the rear edge of the main wing. When the flaperons at two sides of the fuselage are deflected downwards at the same time, the flap lift-increasing effect is achieved, so that the take-off and landing performance of the unmanned aerial vehicle is improved; when the flaperons on two sides of the fuselage deflect differentially, the unmanned aerial vehicle generates rolling torque so as to change the flight attitude.

Two stay bars 9 with equal length are symmetrically arranged below the main wing 2 and close to the wing root along the longitudinal axis of the fuselage. The connection mode of the stay bar and the main wing can adopt bolt connection, welding or connector connection, and can adopt high-strength and light aviation materials, such as aluminum alloy or titanium alloy for manufacturing, thereby enhancing the bearing capacity of the stay bar and reducing the weight of the stay bar.

The rear end of the stay bar 9 is provided with a vertical tail wing 3, wherein the vertical stabilizing surface has a course stabilizing effect on the unmanned aerial vehicle; the rear edge of the vertical stabilizer is provided with a rudder so as to facilitate the course control of the unmanned aerial vehicle, and the deflection of the rudder is realized through a built-in steering engine at the joint of a rudder rotating shaft and the vertical stabilizer. Vertical tail 3 and vaulting pole 9 can quick assembly disassembly, can accomodate it alone in the transportation, are favorable to reducing the damage to vertical tail subassembly.

The wingtips of the two vertical tail wings 3 are connected with a horizontal tail wing 4, and the connection between the wingtips of the vertical tail wings and the wingtips of the horizontal tail wings adopts a smooth transition mode. The rear edge of the horizontal tail wing 4 is provided with an elevator 8, so that the longitudinal pitching motion of the unmanned aerial vehicle is controlled, and the deflection of the elevator is realized through a built-in steering engine which is arranged at the symmetrical plane of the horizontal tail wing and is close to the rear edge of the horizontal stabilizer.

Optionally, the takeoff phase of the high-throughput large-loading small unmanned aerial vehicle provided by the embodiment of the invention can adopt an ejection takeoff mode, and the landing mode can be recovered in a parachuting mode. The recovery system is composed of an umbrella opening mechanism, a main umbrella, a falling joint and the like, wherein the parachute is a circular parachute and is arranged behind the position of an oil tank in the machine body 1. If catapult takeoff and parachuting recovery are not allowed due to certain special factors, a sliding takeoff and landing mode can be selected.

Fig. 3 is a schematic structural diagram of the vertical take-off and landing mode provided in this embodiment. In the vertical take-off and landing mode, the unmanned aerial vehicle includes, in addition to: the aircraft comprises an aircraft body 1, a main wing 2, a vertical tail wing 3, a horizontal tail wing 4, a tail pushing type propeller 5, a flaperon 6, a rudder 7, an elevator 8 and a support rod 9, and further comprises a front lift propeller 12 and a rear lift propeller 13. Similar to the dismounting manner in the catapult takeoff mode, the fuselage 1 and the main wing 2, the main wing 2 and the stay bar 9, and the stay bar 9 and the vertical tail fin 3 are all dismounted and connected for transportation in the vertical takeoff and landing mode, and the assembly schematic diagram of the structural components is shown in fig. 4.

When the high-universality large-loading unmanned aerial vehicle provided by the embodiment is used for vertical take-off and landing, the thrust axes of the front lift propeller 12 and the rear lift propeller 13 are both vertical to the ground, and the front lift propeller 12 and the rear lift propeller 13 form a four-rotor mode to provide vertical upward lift force simultaneously, so that the whole aircraft is driven to rapidly realize vertical take-off and landing. After the takeoff is finished, the rotating speeds of the front lift propeller 12 and the rear lift propeller 13 are adjusted, so that the lift generated by the front lift propeller and the rear lift propeller are balanced with the gravity of the aircraft, and the hovering of the whole aircraft is realized. When the whole aircraft needs head raising, head lowering and lateral movement, the rotating speeds of the front propeller and the rear propeller can be controlled to enable the lift force generated by the front propeller and the rear propeller to be different in the front, the rear, the left and the right, so that head raising/lowering or lateral rolling torque is generated, and pitching movement or lateral rolling movement of the aircraft is further achieved.

After the high-pass large-loading small-sized unmanned aerial vehicle provided by the embodiment finishes vertical takeoff, the tail pushing type propeller 5 starts to rotate at high speed to provide forward thrust for the whole vehicle to accelerate and fly horizontally, so that the transition stage is entered, at the moment, the front lifting propeller 12 and the rear lifting propeller 13 still provide lifting force for the whole vehicle, but the rotating speed is gradually reduced along with the increase of the front flying speed of the whole vehicle, and the operation is stopped after the rotating speed is higher than the stall speed; or the rotating speeds of the front lift propeller 12 and the rear lift propeller 13 in the transition stage are kept unchanged, and the operation is stopped quickly after the full-aircraft flat flight speed is higher than the stall speed.

When the small unmanned aerial vehicle provided by the embodiment enters a level flight mode, the front lift propeller 12 and the rear lift propeller 13 stop working, and the propeller blades are locked by the locking mechanism. The lift force required by the whole plane in the flat flight stage is mainly provided by the main wing 2, and the pitching motion, the rolling motion and the yawing motion of the whole plane are controlled and controlled by corresponding pneumatic control surfaces, namely an elevator 8, a flaperon 6 and a rudder 7.

Similarly, when the unmanned aerial vehicle provided by the embodiment of the present invention shifts from the level flight state to the transition phase and then enters the vertical take-off and landing process, the working processes of the front lift propeller 12, the rear lift propeller 13, and the tail push propeller 5 are the reverse process of the vertical take-off, flight-to-level flight process, thereby completing the vertical landing action of the whole unmanned aerial vehicle, and details are not described herein.

Finally, it should be noted that: the above embodiments are merely illustrative of the technical solutions of the present invention, and not restrictive; although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that the present invention may be modified in various ways, or equivalents may be substituted for some or all of the features thereof; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. a kind of high versatility large loading small unmanned aerial vehicle, it is characterized in that, comprise: wing body is integrated with large volume fuselage, be arranged in the large volume fuel tank of described fuselage middle, the fuel weight coefficient can reach 0.5 at most, be arranged in Two fixed main wings on both sides of the fuselage, a tail push propeller arranged at the tail of the fuselage, and two struts with equal lengths arranged below the main wings, and the whole machine has catapult take-off and roll-off take-off. and vertical take-off and landing three take-off modes;

The two struts with the same length are symmetrically arranged below the main wing along the longitudinal axis of the fuselage;

Two vertical tails are symmetrically arranged at the rear end of the strut along the longitudinal axis of the fuselage;

The wing tips of the two vertical tails are connected through the horizontal tail;

The two vertical tail fins and the horizontal tail fin form a modular tail fin assembly, which is detachably connected to the strut.

2 . The small unmanned aerial vehicle with high versatility and large load according to claim 1 , wherein two pairs of lift propellers are arranged at the front and rear ends of the strut to complete the vertical take-off and landing mode. 3 .

3. The highly versatile large-loaded small unmanned aerial vehicle according to claim 1, characterized in that: the engine is installed at the rear of the fuselage, which can be either built-in or external; when the engine is built in the rear of the fuselage, the back of the fuselage is Intake ducts are provided accordingly.

4 . The high-compatibility, large-loaded and small-sized unmanned aerial vehicle according to claim 1 , wherein the fuselage bulkhead connecting the rear spar of the two main wings forms the rear wall of the fuel tank. 5 .

5 . The small unmanned aerial vehicle with high versatility and large load according to claim 2 , wherein the strut and the main wing can be detachably connected, and the strut and the two pairs of lift propellers are detachable. 6 .