Ground-effect aircraft dynamic characteristic ground simulation experiment system capable of sensing on-line state

Abstract

The invention relates to the technical field of flight test equipment, and particularly discloses an on-line state sensing ground effect aircraft dynamic characteristic ground simulation experiment system which is used for solving the problem that ground simulation of dynamic characteristics of an existing aircraft under the environment boundary effect is difficult. Comprising a base, a rotating column is rotationally arranged in the middle of the upper end of the base, the lower end of the rotating column is connected with a rotating driving part used for driving the rotating column to rotate at a high speed, and a lifting disc is slidably arranged on the outer side of the rotating column and connected with a lifting part used for driving the lifting disc to adjust the height of the lifting disc. The device is designed according to existing requirements, the flight state of the aircraft is simulated, environment interference and acting force borne by the head and the tail of the aircraft are detected, the dynamic characteristics of the aircraft are simulated, the distance between the aircraft and the water surface can be adjusted in the high-speed flight state of the aircraft, and water surface information can be switched into obstacle information; therefore, the influence on the dynamic characteristics of the aircraft during actual work is tested, reference is provided for automatically adjusting the state of the aircraft, and the safety of the real flight of the aircraft is greatly improved.

Description

Technical Field

[0001] The invention relates to the technical field of flight test equipment, in particular to a ground simulation experiment system for dynamic characteristics of a ground effect vehicle with online state perception. Background Art

[0002] Ground effect, also known as wing-to-ground effect, ground effect or wing effect, is a fluid mechanics effect that reduces the induced drag of an aircraft and achieves a higher lift-to-drag ratio than flying in the air: when a moving aircraft falls very close to the ground (or water), the pressure difference between the upper and lower parts of the entire aircraft increases, and the lift increases sharply;

[0003] If the main engine of the ground effect vehicle is a turboprop engine and the auxiliary engine is a turbofan engine. The boundary effect or boundary interference of the ground effect vehicle mainly refers to the phenomenon that when the vehicle is flying close to the ground or water, the flow field and aerodynamic characteristics around the vehicle change significantly due to its flying altitude being very close to the ground or water. The connotation of boundary effect control:

[0004] a. Real-time monitoring and adjustment: Using advanced sensor technology and data analysis, the flight status of the aircraft is monitored in real time. By analyzing the aerodynamic and power responses during flight, unstable factors caused by boundary interference can be discovered and corrected in a timely manner.

[0005] b. Feedback control mechanism: Design an effective flight control system that combines real-time sensor data to dynamically adjust the aircraft's attitude and motion state. This feedback control can help the aircraft make timely corrections when it is disturbed by boundaries to ensure flight stability.

[0006] c. Flight altitude and strategy planning: In flight mission planning, the flight altitude and route should be reasonably selected to ensure that the aircraft operates in the optimal aerodynamic environment and avoid long-term flight in adverse boundary effect areas.

[0007] Through the above measures, the boundary effect or boundary interference of the ground effect vehicle can be controlled and alleviated to a certain extent, thereby improving its flight safety and stability in complex environments. In order to detect the performance of the above control method in the experiment.

[0008] The ground simulation experiment system of the dynamic characteristics of ground effect vehicles with online state perception is now provided, which can eliminate the drawbacks of the existing devices. Summary of the invention

[0009] The purpose of the present invention is to provide a ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception, which solves the problems in the prior art.

[0010] To achieve the above object, the present invention provides the following technical solutions:

[0011] The invention discloses a ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception, comprising a base, a rotating column is rotatably provided at the middle position of the upper end of the base, the lower end of the rotating column is connected to a rotating driving member for driving the rotating column to rotate at high speed, a lifting plate is slidably provided on the outer side of the rotating column, the lifting plate is connected to a lifting member for driving the height adjustment thereof, at least two steering arms are distributed in an array on the outer side of the lifting plate, an aircraft component is provided at the outer end of each steering arm, the force of the rotating column is balanced by arranging symmetrically arranged aircraft components, and an obstacle component for constructing a ground obstacle is provided on the upper end of the base.

[0012] On the basis of the above technical solution, the present invention also provides the following optional technical solution:

[0013] In an optional solution, the number of the steering arms is an even number.

[0014] In an optional solution: a reinforcing rib is provided on the steering arm.

[0015] In an optional solution: a plurality of legs are provided at the lower end of the base.

[0016] In an optional solution: the obstacle component includes a water tank arranged at the upper end of the base, the water tank is filled with water, a plurality of flip motors are distributed in an array outside the water tank, and a building baffle is provided at the output end of the flip motor.

[0017] In an optional scheme: the aircraft component includes a fuselage, the tail axis position of the fuselage is rotatably connected to the suspension rod at the end of the steering arm through a universal ball, wings are rotatably provided on both sides of the fuselage, the inner ends of the wings are connected to a steering drive member used to drive the rotation thereof, so that the rotation angle of the wings can be adjusted by the steering drive member to adjust the lift force of the fuselage during flight, a tail rudder is rotatably provided at the upper end of the tail of the fuselage, the tail rudder is connected to a tail motor used to drive the rotation thereof, and the tail of the fuselage is also provided with a detection unit for detecting the flight status of the fuselage.

[0018] In an optional solution: the detection unit includes a detection rod arranged at the tail of the universal ball, the universal ball is coaxially arranged with the fuselage, a plurality of pressure arc blocks are distributed in an array on the outer side of the detection rod, the pressure surface of the pressure arc block matches the outer side of the detection rod, and the pressure arc block is connected and fixed to the input end of the pressure sensor.

[0019] In an optional solution: a spirit level is also provided on the fuselage.

[0020] In an optional solution: the lifting member includes a lifting slide groove arranged on the rotating column, the lifting slide groove is opened at the axis position of the rotating column, a transmission slide plate connected to the lifting plate is slidably provided at the position of the lifting slide groove, a lifting screw is rotatably provided at the middle position of the lifting slide groove, the lifting screw is threadedly connected to the transmission slide plate, and the upper end of the lifting screw is connected to a lifting motor for driving it to rotate.

[0021] In an optional solution: the rotary driving member includes a driven gear arranged at the lower end of the rotating column, a driving gear is meshed on the outer side of the driven gear, and the lower end of the driving gear is connected to a first motor for driving the driving gear to rotate.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. The present invention is designed according to existing needs. By simulating the flight state of an aircraft, detecting the environmental interference and forces on the head and tail of the aircraft, and simulating the dynamic characteristics of the aircraft, the aircraft can adjust its distance from the water surface in a high-speed flight state. The water surface information can also be switched to an obstacle, so as to test the influence of the two on the dynamic characteristics of the aircraft in actual work, provide a reference for automatically adjusting the state of the aircraft, and thus greatly improve the safety of the actual flight of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a structural schematic diagram of the present invention.

[0025] Figure 2 It is a structural schematic diagram of the lower side of the present invention.

[0026] Figure 3 It is a schematic diagram of the structure of the aircraft component of the present invention.

[0027] Figure 4 It is a schematic diagram of the structure of the detection unit of the present invention.

[0028] Figure 5 The schematic diagram of the auxiliary pressure sensor position structure of the present invention is

[0029] Reference numerals: base 100, water storage tank 101, legs 102, driven gear 103, first motor 104, driving gear 105;

[0030] Aircraft component 200, fuselage 201, universal ball 202, steering drive 203, wing 204, tail rudder 205, pressure sensor 206, pressure arc block 207, detection rod 208, auxiliary pressure sensor 209;

[0031] Lifting motor 301, rotating column 302, lifting slide 303, lifting screw 304;

[0032] Steering arm 400, lifting plate 401;

[0033] Building baffle 501, turning motor 502. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] Example 1

[0036] like Figure 1-5 As shown, an embodiment of the present invention provides a ground simulation experiment system for dynamic characteristics of a ground effect vehicle with online state perception, comprising a base 100, a plurality of legs 102 are provided at the lower end of the base 100, the base 100 is fixed by the legs 102, a rotating column 302 is rotatably provided at the middle position of the upper end of the base 100, the lower end of the rotating column 302 is connected to a rotating driving member for driving the high-speed rotation thereof, a lifting plate 401 is slidably provided on the outer side of the rotating column 302, the lifting plate 401 is connected to a lifting member for driving the height adjustment thereof, the flight height of the aircraft component 200 is adjusted by the lifting member, at least two steering arms 400 are distributed in an array on the outer side of the lifting plate 401, an aircraft component 200 is provided at the outer end of each steering arm 400, the force of the rotating column 302 is balanced by arranging the symmetrically arranged aircraft components 200, an obstacle assembly for constructing a ground obstacle is provided at the upper end of the base 100, and corresponding obstacles are provided for the flight of the aircraft component 200 through the obstacles, so as to simulate the real ground-flying state of the aircraft component 200;

[0037] The obstacle assembly includes a water tank 101 disposed at the upper end of the base 100. The water tank 101 is filled with water for constructing water surface information. A plurality of flip motors 502 are arranged in an array outside the water tank 101. A building baffle 501 is provided at the output end of the flip motor 502. The building baffle 501 is rotated by the flip motor 502. When not in use, the building baffle 501 is rotated to a horizontal state, at which time the building baffle 501 is submerged in water. When a ground obstacle needs to be constructed, the building baffle 501 is rotated to a vertical state, so that the building baffle 501 affects the airflow close to the ground.

[0038] The aircraft component 200 includes a fuselage 201, the tail axis position of the fuselage 201 is rotatably connected to the suspension rod at the end of the steering arm 400 through a universal ball 202, wings 204 are rotatably provided on both sides of the fuselage 201, the inner ends of the wings 204 are connected to a steering drive 203 for driving the wings 204 to rotate, so that the rotation angle of the wings 204 can be adjusted by the steering drive 203, so as to adjust the lift force of the fuselage 201 during flight, a tail rudder 205 is rotatably provided at the upper end of the tail of the fuselage 201, the tail rudder 205 is connected to a tail motor for driving the tail rudder 205 to rotate, and the tail motor drives the tail rudder 205 to rotate, so that the fuselage 201 can swing in the horizontal direction, and a detection unit for detecting the flight state of the fuselage 201 is also provided at the tail of the fuselage 201, and the force generated by the flight of the fuselage 201 can be detected by the detection unit;

[0039] The detection unit includes a detection rod 208 arranged at the tail of the universal ball 202, the universal ball 202 is coaxially arranged with the fuselage 201, and a plurality of pressure arc blocks 207 are distributed in an array on the outer side of the detection rod 208, and the pressure surface of the pressure arc block 207 matches the outer side of the detection rod 208, and the pressure arc block 207 is connected and fixed to the input end of the pressure sensor 206, so that when the fuselage 201 rotates around the universal ball 202, the outer side of the detection rod 208 will move in the opposite direction of the fuselage 201, so that the detection rod 208 will generate pressure on the corresponding pressure arc block 207, and the pressure is transmitted to the pressure sensor 206, so as to detect the pressure of the detection rod 208, and the detected force is equivalent to the external force on the fuselage 201 during the flight. It should be noted that the pressure sensor 206 will be cleared before the detection to avoid the influence of the weight of the fuselage 201 on the detection;

[0040] The detection unit also includes an auxiliary pressure sensor 209 arranged at the head of the fuselage 201. The detection end of the auxiliary pressure sensor 209 is provided with a connection end matching the tip, so that when flying quickly, the pressure on the head of the fuselage during flight can be detected;

[0041] The bottom of the fuselage 201 is also provided with a radio frequency sensor for detecting the distance between it and the ground, and for detecting the distance between it and the liquid surface or obstacles;

[0042] Here, the auxiliary pressure sensor 209, the radio frequency sensor, and the pressure sensor 206 interact wirelessly with the control terminal, so that the flight status of the aircraft component 200 can be observed in real time, and then the flight of the fuselage 201 can be corrected by adjusting the tail rudder 205 and the wing 204, thereby providing data for the experiment;

[0043] The fuselage 201 is also provided with a level gauge to detect the state of the fuselage 201 itself;

[0044] The lifting member includes a lifting slot 303 arranged on the rotating column 302, the lifting slot 303 is opened at the axis position of the rotating column 302, a transmission slide connected to the lifting plate 401 is slidably provided at the lifting slot 303, a lifting screw 304 is rotatably provided at the middle position of the lifting slot 303, the lifting screw 304 is threadedly connected to the transmission slide, and the upper end of the lifting screw 304 is connected to a lifting motor 301 for driving the lifting screw 304 to rotate. Under the action of the lifting motor 301, the lifting screw 304 and the transmission slide rotate relatively, and under the action of the thread, the transmission slide drives the lifting plate 401 to slide along the axis of the rotating column 302, thereby adjusting the flight height of the aircraft component 200;

[0045] The rotary drive member includes a driven gear 103 disposed at the lower end of the rotating column 302, and a driving gear 105 is meshed on the outer side of the driven gear 103. The lower end of the driving gear 105 is connected to a first motor 104 for driving the driving gear 105 to rotate. The first motor 104 drives the driving gear 105 to rotate, and the driving gear 105 drives the rotating column 302 to rotate through the driven gear 103, thereby providing power for the high-speed flight of the aircraft component 200:

[0046] Working principle / working process: in actual use, the rotating column 302 is driven to rotate at high speed by the rotating driving member, so that the rotating column 302 drives the steering arm 400 to rotate quickly, and the steering arm 400 drives the aircraft component 200 to fly, thereby providing flight power. The flight state of the fuselage 201 is adjusted by adjusting the tail rudder 205 and the wing 204, and then the state of the fuselage 201 is adjusted to the target state through the detection unit. At this time, the pressure sensor 206 is reset, and then the lifting plate 401 and the aircraft component 200 are driven to descend by the lifting member, so that the flight height of the aircraft component 200 is reduced. When the descending distance is close to the water surface, observe how much instantaneous lifting force the aircraft component 200 suffers, and the ratio of the lifting force to the wing;

[0047] If it is to be detected that the aircraft component 200 is flying in an obstacle area, it is only necessary to rotate the building baffle 501 by turning the motor 502 so that the building baffle 501 rotates to a vertical state, so that the building baffle 501 forms a ground obstacle under the aircraft component 200, thereby blocking the airflow, and then observe the flight state of the aircraft component 200;

[0048] A distance measuring unit and a camera are arranged at the lower end of the aircraft component 200. If it is determined that there is an obstacle or water below, the flight state of the aircraft component 200 will be adjusted by rotating the steering drive 203 and the tail rudder 205, so that the aircraft can be adjusted automatically without manual adjustment.

[0049] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A ground simulation experimental system for dynamic characteristics of a ground-effect vehicle with online state perception, comprising a base (100), a rotating column (302) being rotatably arranged at the middle position of the upper end of the base (100), and a rotating driving member for driving the rotating column (302) to rotate at a high speed connected to the lower end thereof, characterized in that: A lifting plate (401) is slidably disposed on the outer side of the rotating column (302), and the lifting plate (401) is connected to a lifting member for driving its height adjustment. At least two steering arms (400) are arranged in an array on the outer side of the lifting plate (401), and an aircraft component (200) is disposed at the outer end of each steering arm (400). The rotating column (302) is subjected to balanced force by symmetrically arranging the aircraft components (200). An obstacle component for constructing a ground obstacle is disposed at the upper end of the base (100).

2. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 1 is characterized in that: The number of the steering arms (400) is an even number.

3. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 1 is characterized in that: The steering arm (400) is provided with reinforcing ribs.

4. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 1 is characterized in that: A plurality of supporting legs (102) are provided at the lower end of the base (100).

5. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 1 is characterized in that: The barrier assembly comprises a water storage tank (101) arranged at the upper end of a base (100), the water storage tank (101) being filled with water, a plurality of flip motors (502) being distributed in an array outside the water storage tank (101), and a building baffle (501) being provided at the output end of the flip motor (502).

6. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 1 is characterized in that: The aircraft component (200) comprises a fuselage (201), wherein the tail axis position of the fuselage (201) is rotatably connected to a suspension rod at the end of a steering arm (400) via a universal ball (202), wings (204) are rotatably provided on both sides of the fuselage (201), the inner ends of the wings (204) are connected to a steering drive member (203) for driving the wings (204) to rotate, so that the rotation angle of the wings (204) can be adjusted by the steering drive member (203) to adjust the lift force of the fuselage (201) during flight, a tail rudder (205) is rotatably provided at the upper end of the tail of the fuselage (201), and the tail rudder (205) is connected to a tail motor for driving the wings (204) to rotate, and a detection unit for detecting the flight state of the fuselage (201) is also provided at the tail of the fuselage (201).

7. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 6 is characterized in that: The detection unit comprises a detection rod (208) arranged at the tail of a universal ball (202), the universal ball (202) being coaxially arranged with the fuselage (201), a plurality of pressure arc blocks (207) being distributed in an array outside the detection rod (208), the pressure arc blocks (207) having pressure surfaces matching the outside of the detection rod (208), and the pressure arc blocks (207) being connected and fixed to the input end of the pressure sensor (206).

8. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 1 is characterized in that: The fuselage (201) is also provided with a level.

9. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 1 is characterized in that: The lifting member comprises a lifting slot (303) arranged on a rotating column (302), wherein the lifting slot (303) is opened at the axis position of the rotating column (302), a transmission slide plate connected to a lifting plate (401) is slidably arranged at the position of the lifting slot (303), a lifting screw (304) is rotatably arranged at the middle position of the lifting slot (303), the lifting screw (304) is threadedly connected to the transmission slide plate, and the upper end of the lifting screw (304) is connected to a lifting motor (301) for driving the lifting screw (304) to rotate.

10. The ground simulation experiment system for dynamic characteristics of ground effect vehicles with online state perception according to claim 1 is characterized in that: The rotary drive member comprises a driven gear (103) arranged at the lower end of the rotary column (302), a driving gear (105) is meshed on the outer side of the driven gear (103), and the lower end of the driving gear (105) is connected to a first motor (104) for driving the driving gear (105) to rotate.

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