An unmanned aerial vehicle and a lateral direct force control device thereof

Abstract

The application discloses an unmanned aerial vehicle and a lateral direct force control device thereof, and relates to the technical field of aircrafts. The lateral direct force control device comprises a lateral direct force control surface which is rotatably arranged in a wing cowling. The lateral direct force control surface is arranged in parallel to the symmetry plane of the aircraft. The lateral direct force control surface is symmetrically arranged about the symmetry plane of the aircraft and symmetrically spread about the horizontal plane of the aircraft. The spread angle alpha of the lateral direct force control surface and the horizontal plane satisfies 0°<=alpha<=90°. The size of the side force can be adjusted by adjusting the spread angle alpha of the lateral direct force control surface. When the upper and lower lateral direct force control surfaces of the same side wing cowling are symmetrically spread, the side force can be generated and the lateral force direct control of the aircraft can be realized.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically, to a lateral direct force control device. Furthermore, this invention also provides a drone including the aforementioned lateral direct force control device. Background Technology

[0002] Direct force control refers to the process of providing additional lift or lateral force by appropriately manipulating control surfaces or coordinating thrust vectoring, without altering the aircraft's flight attitude, thereby causing the aircraft to translate vertically or laterally to change its trajectory.

[0003] Commonly used aircraft aerodynamic layouts include conventional layout, canard layout, and triplane layout. Among them, the conventional layout cannot achieve direct force control through the deflection of control surfaces; the canard layout can achieve direct force control in the vertical direction by deflecting the canard and flaps in combination, canceling the moment and generating additional lift, but it cannot achieve direct force control in the lateral direction; the triplane layout can achieve direct force control in the vertical direction by deflecting the canard and tail control surfaces in the same direction, canceling the moment and generating additional lift, but it cannot achieve direct force control in the lateral direction.

[0004] In summary, how to achieve lateral direct force control of an aircraft is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] In view of this, the purpose of the present invention is to provide a lateral direct force control device, in which the upper and lower lateral direct force control surfaces on the same side can be symmetrically deployed to generate a lateral force pointing to that side, thereby realizing direct control of the lateral force of the aircraft.

[0006] In addition, the present invention also provides a drone including the above-described lateral direct force control device.

[0007] To achieve the above objectives, the present invention provides the following technical solution:

[0008] A lateral direct force control device includes lateral direct force control surfaces rotatably disposed within a wing fairing. The lateral direct force control surfaces are arranged parallel to the symmetry plane of the aircraft and are symmetrically arranged left and right about the symmetry plane of the aircraft. The lateral direct force control surfaces are also symmetrically deployed vertically about the horizontal plane of the aircraft. The deployment angle α between the lateral direct force control surfaces and the horizontal plane satisfies 0°≤α≤90°, so that the magnitude of the lateral force can be adjusted by adjusting the deployment angle α of the lateral direct force control surfaces.

[0009] Preferably, the lateral direct force control surface includes a lateral direct force control surface and an opening / closing adjustment assembly for adjusting the deployment angle α of the lateral direct force control surface. The lateral direct force control surface is rotatably disposed within the reinforcing frame of the wing fairing via a rotating shaft. The fixed end of the opening / closing adjustment assembly is connected to the reinforcing frame, and the movable end of the opening / closing adjustment assembly is hinged to the end of the lateral direct force control surface that is closer to the rotating shaft.

[0010] Preferably, the opening and closing adjustment assembly includes an adjustment motor, an adjustment lead screw, an adjustment slider, a guide rod, and a connecting rod. The adjustment lead screw and the guide rod are both arranged along the axial direction of the aircraft. The output shaft of the adjustment motor is connected to the adjustment lead screw. The adjustment slider is threaded onto the outside of the adjustment lead screw, and the adjustment slider is slidably connected to the guide rod.

[0011] One end of the connecting rod is hinged to the adjusting slider, and the other end of the connecting rod is hinged to the lateral direct force control surface.

[0012] Preferably, the guide rods are provided on both sides of the adjusting screw, and the guide rods on both sides have the same axial distance from the adjusting screw.

[0013] Preferably, the end of the adjusting screw that is relatively far from the adjusting motor is provided with a clamping block, and the rotating shaft passes through the shaft hole on one side of the clamping block, the shaft hole of the lateral direct force control surface, and the shaft hole on the other side of the clamping block in sequence.

[0014] Preferably, the two lateral direct force control surfaces located on the same side are rotatably mounted in the same clamping block, and a thrust bearing is provided between two adjacent lateral direct force control surfaces.

[0015] Preferably, the cross-sectional shape of the lateral direct force control surface is a high-lift airfoil, and one end of the lateral direct force control surface located inside the wing fairing is an arc-shaped connection end, which is provided with a shaft mounting hole for mounting the shaft.

[0016] An unmanned aerial vehicle (UAV) includes a fuselage and two wings. The wings are connected to the fuselage via wing fairings. The fuselage has canards on both the left and right sides in the forward direction. The canards are equipped with elevators. The fuselage has a propeller at the tail. The trailing edges of the wings are provided with flaps, flaperons, and ailerons from the inside out. The wingtips of the wings are equipped with vertical tails. The trailing edges of the vertical tails are equipped with rudders. The wing fairings contain a lateral direct force control device as described above.

[0017] Preferably, the dihedral angle of the canard is 15°-25°, so as to increase the yaw moment generated by the elevator when controlling yaw.

[0018] Preferably, the wing includes a λ-shaped wing, the flaps are located on the inner side of the wing with a large sweep, and the flaps and ailerons are both located on the outer side of the wing with a small sweep.

[0019] The lateral direct force control device provided by this invention can generate a lateral force pointing to that side when the upper and lower lateral direct force control surfaces of the same-side wing fairing are symmetrically deployed, thereby realizing direct control of the aircraft's lateral force.

[0020] In addition, the present invention also provides a drone including the above-described lateral direct force control device. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0022] Figure 1 A schematic diagram of a specific embodiment of the lateral direct force control device provided by the present invention;

[0023] Figure 2 This is a schematic diagram of the structure when the lateral direct force control surfaces are not deployed;

[0024] Figure 3 This is a schematic diagram of the structure when the rudder surface is deployed under lateral direct force control;

[0025] Figure 4 This is a schematic diagram of the cross-sectional shape of the lateral direct force control surface;

[0026] Figure 5 This is a schematic diagram of the structure of the UAV provided by the present invention;

[0027] Figure 6 for Figure 5 A structural diagram from another direction;

[0028] Figure 7 This is a schematic diagram of the lateral direct force control surface when it is not deployed.

[0029] Figure 8 A schematic diagram of the lateral direct force control surface when deployed at 45°.

[0030] Figure 9 This is a schematic diagram of the lateral direct force control surface when it is deployed at 90°.

[0031] Figures 1-9 middle:

[0032] 10-Fuselage; 20-Canard; 201-Elevator; 30-Wing fairing; 40-Lateral direct force control surface; 401-Lateral direct force control surface; 402-Adjusting motor; 403-Adjusting screw; 404-Guide rod; 405-Adjusting slider; 406-Connecting rod; 407-Clamping block; 408-Shaft; 409-Base; 50-Wing; 501-Leading edge slat; 502-Flap; 503-Flap aileron; 504-Aileron; 60-Vertical tail; 601-Rudder; 70-Air inlet; 80-Propeller; 90-Propeller fairing. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] The core of this invention is to provide a lateral direct force control device. When the upper and lower lateral direct force control surfaces on the same side are symmetrically deployed, they can generate a lateral force pointing to that side, thereby realizing direct control of the lateral force of the aircraft.

[0035] In addition, the present invention also provides a drone including the above-described lateral direct force control device.

[0036] The lateral direct force control device provided by the present invention includes a lateral direct force control surface 40 rotatably disposed within a wing fairing 30. The lateral direct force control surface 40 is arranged parallel to the symmetry plane of the aircraft and is symmetrically arranged left and right about the symmetry plane of the aircraft. The lateral direct force control surface 40 is also symmetrically deployed up and down about the horizontal plane of the aircraft. The deployment angle α between the lateral direct force control surface 40 and the horizontal plane satisfies 0°≤α≤90°, so that the magnitude of the lateral force can be adjusted by adjusting the deployment angle α of the lateral direct force control surface 40.

[0037] Please refer to Figure 5 The lateral direct force control surface 40 is set parallel to the plane of symmetry of the aircraft. The cross-sectional shape and profile shape of the lateral direct force control surface 40 are determined according to the actual operating conditions of the aircraft in production, such as the design flight speed and design flight altitude of the aircraft.

[0038] For example, in a specific embodiment, please refer to Figure 4 The lateral direct force control surface 401 of the lateral direct force control surface 40 has a high lift airfoil cross-section. One end of the lateral direct force control surface 401 located inside the wing fairing 30 is an arc-shaped connection end, and the arc-shaped connection end is provided with a shaft mounting hole for mounting the shaft 408.

[0039] When the lateral direct force control surface 40 of the left wing fairing 30 is deployed, the airflow path on the left side of the lateral direct force control surface 40 is longer than the airflow path on the right side. When the airflow passes through the lateral direct force control surface 40, the airflow velocity on the left side is higher, the dynamic pressure is greater and the static pressure is smaller, while the airflow velocity on the right side is slower, the dynamic pressure is smaller and the static pressure is larger. Therefore, the pressure difference generated by the airflow on both sides can form a lateral force to the left.

[0040] Similarly, when the lateral direct force control surface 40 of the right wing fairing 30 is deployed, the pressure difference generated by the airflow on the right side of the lateral direct force control surface 40 can form a lateral force to the right because the airflow path on the right side of the lateral direct force control surface 40 is longer than the airflow path on the left side of the lateral direct force control surface 40.

[0041] Therefore, when the upper and lower lateral direct force control surfaces 40 inside the left wing fairing 30 are symmetrically deployed, a lateral force to the left can be generated; when the upper and lower lateral direct force control surfaces 40 inside the right wing fairing 30 are symmetrically deployed, a lateral force to the right can be generated.

[0042] Assuming the incoming airflow velocity of the aircraft is V and the deployment angle of the lateral direct force control surface 40 is α, when the deployment angle of the lateral direct force control surface 40 is α=90°, the incoming airflow direction is completely perpendicular to the leading edge of the lateral direct force control surface 40, and the incoming airflow velocity V can be fully used to generate lateral force.

[0043] When the deployment angle α of the lateral direct force control surface 40 satisfies 0°≤α<90°, the normal velocity component Vn=Vsinα of the airflow perpendicular to the lateral force control surface 40 is used to generate lateral force. As the deployment angle α of the lateral direct force control surface 40 increases, the normal velocity component Vn of the incoming flow increases, and the generated lateral force increases accordingly.

[0044] In this embodiment, when the upper and lower direct force control surfaces 40 of the same-side wing fairing 30 are symmetrically deployed, a lateral force pointing to that side can be generated, realizing direct control of the aircraft's lateral force.

[0045] In the above embodiment, the structure of the lateral direct force control surface 40 is defined. The lateral direct force control surface 40 includes a lateral direct force control surface 401 and an opening and closing adjustment assembly for adjusting the deployment angle α of the lateral direct force control surface 401. The lateral direct force control surface 401 is rotatably disposed in the reinforcing frame of the wing fairing 30 via a rotating shaft 408. The fixed end of the opening and closing adjustment assembly is connected to the reinforcing frame, and the movable end of the opening and closing adjustment assembly is hinged to the end of the lateral direct force surface 401 that is relatively close to the rotating shaft 408.

[0046] Please refer to Figure 1 The lateral direct force control surface 401 is the actual control surface of the lateral direct force control rudder surface 40, and the opening and closing adjustment component is used to adjust the lateral force generated by the lateral direct force control surface 401 relative to the horizontal plane by adjusting the unfolding angle α.

[0047] The opening and closing adjustment component can be specifically set as a linear power mechanism such as a ball screw, cylinder, or electric push rod. One end of the linear power mechanism is hinged to the reinforcing frame, and the other end of the linear power mechanism is hinged to the lateral direct force control surface 401. Through the extension and retraction of the piston or push rod of the linear power mechanism, the lateral direct force control surface 401 is driven to rotate around the rotating shaft 408 relative to the horizontal plane.

[0048] In this embodiment, the lateral direct force control surface 401 is driven by the opening and closing adjustment component. Compared with the lateral direct force control surface 401 being driven to rotate by the rotary motor, the driving torque is greater, the response speed is faster, and it has a self-locking capability, which is beneficial to improving the lateral displacement control effect of the aircraft.

[0049] Of course, the lateral direct force control surface 401 can also be driven by a rotary power mechanism such as a rotary motor. For example, the lateral direct force control surface 401 can be keyed to the output shaft of the rotary motor, or the lateral direct force control surface 401 can be connected to the output shaft of the rotary motor through a coupling or the like, so that the rotary motor can directly drive the rotation of the lateral direct force control surface 401 relative to the horizontal plane.

[0050] Based on the above embodiments, the structure of the opening and closing adjustment assembly is further defined. The opening and closing adjustment assembly includes an adjustment motor 402, an adjustment screw 403, an adjustment slider 405, a guide rod 404, and a connecting rod 406. The adjustment screw 403 and the guide rod 404 are both arranged along the axial direction of the aircraft. The output shaft of the adjustment motor 402 is connected to the adjustment screw 403. The adjustment slider 405 is threaded onto the adjustment screw 403, and the adjustment slider 405 is slidably connected to the guide rod 404.

[0051] One end of the connecting rod 406 is hinged to the adjusting slider 405, and the other end of the connecting rod 406 is hinged to the lateral direct force control surface 401.

[0052] Please refer to Figure 1 The adjustment motor 402 is mounted on the base 409, which is installed inside the reinforcing frame of the wing fairing 30. The adjustment motor 402 can be connected to the base 409 by detachable connection methods such as bolts, so as to facilitate the installation, maintenance and replacement of the adjustment motor 402. The base 409 can be connected to the reinforcing frame by detachable connection methods such as bolts and rivets, or by non-detachable connection methods such as welding, or it can be set as an integral structure with the reinforcing frame.

[0053] The guide rod 404 is set parallel to the adjusting screw 403 and is slidably connected to the adjusting slider 405 so as to limit the rotation of the adjusting slider 405 relative to the adjusting screw 403 through the sliding pair, thereby converting the rotation of the adjusting screw 403 into the linear displacement of the adjusting slider 405.

[0054] The guide rod 404 is fixedly disposed between the base 409 and the mounting seat at the other end of the adjusting screw 403 to simplify the structure of the opening and closing adjustment assembly. Preferably, guide rods 404 can be provided on both sides of the adjusting screw 403, and the guide rods 404 on both sides are axially spaced the same as the adjusting screw 403, so as to actively limit the left and right sides of the adjusting slider 405 and avoid unilateral deviation of the adjusting slider 405 when it moves.

[0055] The adjustment motor 402 drives the adjustment screw 403 to rotate, which is restricted by the sliding pair of the guide rod 404 and the adjustment slider 405. The adjustment slider 405 is threaded onto the adjustment screw 403. When the adjustment screw 403 rotates, the adjustment slider 405 moves along the direction of the guide rod 404. The distance from the hinge point of the connecting rod 406 and the adjustment slider 405 to the rotating shaft 408 changes, thereby driving the lateral direct force control surface 401 to rotate relative to the rotating shaft 408.

[0056] The type and power of the adjusting motor 402 are determined based on the load of the lateral direct force control surface 401, etc.; the specific structure and dimensions of the threaded pair of the adjusting screw 403 and the adjusting slider 405 are determined based on the adjustment range and adjustment accuracy requirements of the unfolding angle α in actual production.

[0057] In this embodiment, the sliding pair drives the adjusting slider 405 to move precisely along the adjusting screw 403, thereby accurately adjusting the unfolding angle α of the lateral direct force control surface 401. The adjustment accuracy is high, and the structure is simple and compact, which helps to reduce the installation space required for the lateral direct force control surface 40.

[0058] Based on the above embodiments, a clamping block 407 can be provided at one end of the adjusting screw 403 that is relatively far away from the adjusting motor 402, and the rotating shaft 408 passes through the shaft hole on one side of the clamping block 407, the shaft hole of the lateral direct force control surface 401, and the shaft hole on the other side of the clamping block 407 in sequence.

[0059] Please refer to Figure 1 The clamping block 407 has a U-shaped structure, and the lateral direct force control surface 401 is inserted into the opening of the clamping block 407, which helps to improve the connection stability and reliability between the lateral direct force control surface 401 and the clamping block 407.

[0060] Preferably, in order to further simplify the structure of the lateral direct force control surface 40, two lateral direct force control surfaces 401 located on the same side can be rotatably mounted in the same clamping block 407, and a thrust bearing is provided between two adjacent lateral direct force control surfaces 401 to avoid mutual friction between the two adjacent lateral direct force control surfaces 401 affecting their rotation, thereby ensuring the rotation adjustment accuracy of the lateral direct force control surface 401.

[0061] In addition to the aforementioned lateral direct force control device, the present invention also provides a drone including the lateral direct force control device disclosed in the above embodiments. The drone includes a fuselage 10 and wings 50 on both sides. The wings 50 are connected to the fuselage 10 through wing fairings 30. The fuselage 10 is provided with canards 20 on the left and right sides in the forward direction. The canards 20 are provided with elevators 201. The tail of the fuselage 10 is provided with a propeller 80. The trailing edge of the wings 50 is provided with flaps 502, flaperons 503 and ailerons 504 from the inside to the outside. The wing 50 is provided with a vertical tail 60 at its end. The trailing edge of the vertical tail 60 is provided with a rudder 601. The aforementioned lateral direct force control device 40 is provided inside the wing fairings 30.

[0062] Among them, the trailing edge of the canard 20 is equipped with an elevator 201. The elevator 201 is mainly used to control the pitch motion of the UAV. When the demand for lateral control is high and the lateral force generated by the lateral direct force control device 40 is insufficient, the rudder 601 of the canard 20 and the vertical tail 60 can be controlled to generate opposite torques and lateral forces in the same direction, generating additional lateral force to meet the requirements of lateral translational movement.

[0063] Preferably, the dihedral angle of the canard 20 can be set to 15°-25° in order to increase the yaw moment generated by the elevator 201 when controlling yaw, thereby increasing the magnitude of the lateral force that it can generate in conjunction with the rudder 601.

[0064] The wing 50 has a leading edge slat 501 at its leading edge, and flaps 502, flaperons 503, and ailerons 504 arranged sequentially from the inside to the outside at its trailing edge. When the flaps 502 on both sides deflect downwards simultaneously, the lift of the UAV can be increased; when the flaperons 503 on both sides deflect downwards simultaneously, the lift of the UAV can be increased; when the flaperons 503 on both sides deflect differentially, the roll motion of the UAV can be controlled; when the ailerons 504 on both sides deflect differentially, the roll motion of the UAV can be controlled.

[0065] The wingtip of the wing 50 is equipped with a vertical tail 60, and the trailing edge of the vertical tail 60 is equipped with a rudder 601, which is used to control the yaw motion of the UAV.

[0066] Preferably, the wing 50 may include a λ-shaped wing, with flaps 502 located on the inner side of the wing 50 with a large sweep, and flaps 503 and ailerons 504 located on the outer side of the wing 50 with a small sweep.

[0067] The fuselage 10 has a propeller 80 at its end for providing propulsion power. The propeller 80 is located inside a propeller cover 90. Please refer to [reference needed]. Figure 5 and Figure 6 Airflow enters propeller 80 through air intake 70 on the back of the aircraft, and propeller 80 generates thrust.

[0068] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0069] The above provides a detailed description of the UAV and its lateral direct force control device provided by the present invention. Specific examples have been used to illustrate the principles and implementation methods of the invention. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and core ideas of the present invention. It should be noted that those skilled in the art can make various improvements and modifications to the present invention without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of the present invention.

Claims

1. A lateral direct force control device, characterized in that, The system includes a lateral direct force control surface (40) rotatably disposed within the wing fairing (30). The lateral direct force control surface (40) is arranged parallel to the plane of symmetry of the aircraft. The lateral direct force control surface (40) is symmetrically arranged about the plane of symmetry of the aircraft and is symmetrically deployed about the horizontal plane of the aircraft. The deployment angle α between the lateral direct force control surface (40) and the horizontal plane satisfies 0°≤α≤90°, so that the magnitude of the lateral force can be adjusted by adjusting the deployment angle α of the lateral direct force control surface (40). The lateral direct force control surface (40) includes a lateral direct force control surface (401) and an opening and closing adjustment assembly for adjusting the deployment angle α of the lateral direct force control surface (401). The lateral direct force control surface (401) is rotatably mounted in the reinforcing frame of the wing fairing (30) via a rotating shaft (408). The fixed end of the opening and closing adjustment assembly is connected to the reinforcing frame, and the movable end of the opening and closing adjustment assembly is hinged to one end of the lateral direct force control surface (401) that is closer to the rotating shaft (408). The opening and closing adjustment assembly includes an adjustment motor (402), an adjustment screw (403), an adjustment slider (405), a guide rod (404), and a connecting rod (406). The adjustment screw (403) and the guide rod (404) are both arranged along the axial direction of the aircraft. The output shaft of the adjustment motor (402) is connected to the adjustment screw (403). The adjustment slider (405) is threaded onto the adjustment screw (403), and the adjustment slider (405) is slidably connected to the guide rod (404). One end of the connecting rod (406) is hinged to the adjusting slider (405), and the other end of the connecting rod (406) is hinged to the lateral direct force control surface (401).

2. The lateral direct force control device according to claim 1, characterized in that, The adjusting screw (403) is provided with guide rods (404) on both sides, and the guide rods (404) on both sides have the same axial distance as the adjusting screw (403).

3. The lateral direct force control device according to claim 1, characterized in that, The adjusting screw (403) has a clamp (407) at one end that is relatively far from the adjusting motor (402). The rotating shaft (408) passes through the shaft hole on one side of the clamp (407), the shaft hole of the lateral direct force control surface (401), and the shaft hole on the other side of the clamp (407) in sequence.

4. The lateral direct force control device according to claim 3, characterized in that, The two lateral direct force control surfaces (401) located on the same side are rotatably mounted in the same clamping block (407), and a thrust bearing is provided between two adjacent lateral direct force control surfaces (401).

5. The lateral direct force control device according to any one of claims 1-4, characterized in that, The cross-sectional shape of the lateral direct force control surface (401) is a high-lift airfoil. One end of the lateral direct force control surface (401) located inside the wing fairing (30) is an arc-shaped connection end. The arc-shaped connection end is provided with a shaft mounting hole for mounting the shaft (408).

6. A drone, characterized in that, The fuselage includes a fuselage (10) and wings (50) on both sides. The wings (50) are connected to the fuselage (10) through wing fairings (30). The fuselage (10) is provided with canards (20) on the left and right sides in the forward direction. The canards (20) are provided with elevators (201). The tail of the fuselage (10) is provided with a propeller (80). The trailing edge of the wings (50) is provided with flaps (502), flaperons (503) and ailerons (504) from the inside to the outside. The wingtips of the wings (50) are provided with vertical tails (60). The trailing edge of the vertical tails (60) is provided with rudders (601). The wing fairings (30) are provided with a lateral direct force control device as described in any one of claims 1-5.

7. The UAV according to claim 6, characterized in that, The dihedral angle of the canard (20) is 15°-25° in order to increase the yaw moment generated by the elevator (201) when controlling yaw.

8. The UAV according to claim 7, characterized in that, The wing (50) includes a λ-shaped wing, the flap (502) is located on the inner side of the wing (50) with a large sweep, and the flap aileron (503) and the aileron (504) are both located on the outer side of the wing (50) with a small sweep.

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