Online status-aware ground effect vehicle dynamic characteristic ground simulation experiment system

Abstract

The present application relates to the technical field of flight test equipment, and discloses a ground simulation experiment system for dynamic characteristics of a ground effect aircraft with online state sensing, which is used to solve the problem of difficulty in ground simulation of dynamic characteristics of an existing aircraft under the effect of environmental boundaries; the system comprises a base, a rotating column is rotatably arranged at the middle position of the upper end of the base, a rotating driving member is connected to the lower end of the rotating column for driving high-speed rotation of the rotating column, a lifting disc is slidably arranged outside the rotating column, and a lifting member is connected to the lifting disc for driving height adjustment of the lifting disc. The present application is designed in view of the existing needs, detects environmental interference and acting force on the head and tail of the aircraft by simulating the flight state of the aircraft, simulates the dynamic characteristics of the aircraft, adjusts the distance between the aircraft and the water surface under the high-speed flight state of the aircraft, switches the water surface information into obstacle information, tests the influence of the two on the dynamic characteristics of the aircraft in actual work, provides a reference for automatic adjustment of the state of the aircraft, and greatly improves the safety of real flight of the aircraft.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of flight test equipment, in particular to an online state-aware ground effect vehicle dynamic characteristic ground simulation experiment system. BACKGROUND

[0002] Ground effect, also known as wing-ground effect, ground effect or wing effect, is a fluid mechanics effect that reduces induced drag of an aircraft and allows for higher lift-to-drag ratios than in flight: when a moving aircraft drops to very close to the ground (or water surface), the pressure difference between the top and bottom of the entire aircraft body 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 the flow field and aerodynamic characteristics around the aircraft change significantly when flying close to the ground or water surface.

[0004] a. Real-time monitoring and adjustment: using advanced sensor technology and data analysis, the flight state of the aircraft is monitored in real time. By analyzing the aerodynamic and dynamic response during flight, unstable factors caused by boundary interference can be found and corrected in time.

[0005] b. Feedback control mechanism: design an effective flight control system, combined with real-time sensor data, to dynamically adjust the attitude and motion state of the aircraft. This feedback control can help the aircraft correct in time when it is disturbed by the boundary, and ensure the stability of the flight.

[0006] c. Flight height and strategy planning: in flight mission planning, choose the flight height and route reasonably to ensure that the aircraft operates in the optimal aerodynamic environment and avoids long-term flight in the unfavorable boundary effect area.

[0007] Through the above measures, the boundary effect or boundary interference of the ground effect vehicle can be controlled and reduced to some 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] Now provide an online state-aware ground effect vehicle dynamic characteristic ground simulation experiment system, which can eliminate the drawbacks of existing devices. SUMMARY

[0009] The purpose of the present application is to provide an online state-aware ground effect vehicle dynamic characteristic ground simulation experiment system, which solves the problems in the prior art.

[0010] To achieve the above purpose, the present application provides the following technical scheme:

[0011] The online state sensing ground effect aircraft dynamic characteristic ground simulation experiment system comprises a base, a rotating column is rotatably arranged at the middle position of the upper end of the base, the lower end of the rotating column is connected with a rotating driving member for driving the high-speed rotation of the rotating column, a lifting disc is slidably arranged outside the rotating column, the lifting disc is connected with a lifting member for driving the height adjustment of the lifting disc, at least two steering arms are arrayed outside the lifting disc, an aircraft component is arranged at the outer end of each steering arm, the symmetrically arranged aircraft components are arranged to balance the force acting on the rotating column, and the upper end of the base is provided with an obstacle assembly for building ground obstacles.

[0012] Based on the above technical scheme, the application further provides the following optional technical schemes.

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

[0014] In an optional scheme, the steering arm is provided with a reinforcing rib.

[0015] In an optional scheme, the lower end of the base is provided with a plurality of supporting legs.

[0016] In an optional scheme, the obstacle assembly comprises a water storage tank arranged at the upper end of the base, the water storage tank is filled with water, a plurality of overturning motors are arrayed outside the water storage tank, and a building baffle is arranged at the output end of the overturning motor.

[0017] In an optional scheme, the aircraft component comprises a fuselage, the tail axis position of the fuselage is rotatably connected with a hanger rod at the end of the steering arm through a universal ball, wings are rotatably arranged at the two sides of the fuselage, the inner end of the wing is connected with a steering driving member for driving the rotation of the wing, so that the rotation angle of the wing can be adjusted through the steering driving member to adjust the lifting force of the fuselage in flight, a tail rudder is rotatably arranged at the upper end of the tail of the fuselage, the tail rudder is connected with a tail motor for driving the rotation of the tail rudder, and the tail of the fuselage is further provided with a detection unit for detecting the flight state of the fuselage.

[0018] In an optional scheme, the detection unit comprises a detection rod arranged at the tail of the universal ball, the universal ball is coaxially arranged with the fuselage, a plurality of abutting arc blocks are arrayed outside the detection rod, the abutting surface of the abutting arc block matches the outside of the detection rod, and the abutting arc block is fixedly connected with the input end of the pressure sensor.

[0019] In an optional scheme, the fuselage is further provided with a level.

[0020] In an alternative: the lifting piece includes a lifting chute arranged on the rotating column, the lifting chute is opened at the position of the rotating column axis, a transmission sliding plate connected with the lifting disc is slidingly arranged at the position of the lifting chute, a lifting screw is rotatably arranged at the middle position of the lifting chute, the lifting screw is in threaded connection with the transmission sliding plate, and the upper end of the lifting screw is connected with a lifting motor used for driving the rotation of the lifting screw.

[0021] In an alternative: the rotating driving piece includes a driven gear arranged at the lower end of the rotating column, an active gear is engaged with the outer side of the driven gear, and the lower end of the active gear is connected with a first motor used for driving the rotation of the active gear.

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

[0023] 1、The present application is designed for the existing needs, by simulating the flight state of the aircraft, detecting the environmental interference and force received by the head and tail of the aircraft, simulating the dynamic characteristics of the aircraft, adjusting the distance between the aircraft and the water surface in the high-speed flight state, and switching the water surface information into 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 greatly improve the safety of the real flight of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

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

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

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

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

[0028] Figure 5 It is a structural schematic diagram of the position of the auxiliary pressure sensor of the present application

[0029] Legend of the drawing: base 100, water storage tank 101, supporting leg 102, driven gear 103, first motor 104, active gear 105;

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

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

[0032] Steering arm 400, lifting plate 401;

[0033] Building baffle 501, tilting motor 502. Detailed Implementation

[0034] 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.

[0035] Example 1

[0036] like Figures 1-5 As shown, this embodiment of the invention provides a ground simulation experimental system for the dynamic characteristics of a ground effect vehicle with online state awareness, including a base 100. The base 100 has multiple legs 102 at its lower end, which fix the base 100 in place. A rotating column 302 is rotatably mounted at the middle of the upper end of the base 100. The lower end of the rotating column 302 is connected to a rotation drive component for high-speed rotation. A lifting plate 401 is slidably mounted on the outer side of the rotating column 302. The lifting plate 401 is connected to a lifting component for height adjustment, which adjusts the flight height of the vehicle component 200. At least two steering arms 400 are arrayed on the outer side of the lifting plate 401, each steering arm 400 having a vehicle component 200 at its outer end. The symmetrical arrangement of the vehicle components 200 balances the forces on the rotating column 302. An obstacle assembly for constructing ground obstacles is provided at the upper end of the base 100, providing corresponding obstacles for the flight of the vehicle component 200 to simulate the realistic ground-hugging flight state of the vehicle component 200.

[0037] The obstacle assembly includes a water storage tank 101 located on the upper end of the base 100. The water storage tank 101 is filled with water to construct water surface information. Multiple rotating motors 502 are arrayed on the outer side of the water storage tank 101. A building baffle 501 is provided at the output end of the rotating motor 502. The rotating motor 502 drives the building baffle 501 to rotate. 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 it is necessary to construct a ground obstacle, the building baffle 501 is rotated to a vertical state, so that the building baffle 501 will affect the airflow close to the ground.

[0038] The aircraft component 200 includes a fuselage 201, the tail axis position of the fuselage 201 is connected with the boom of the end of the steering arm 400 through the universal ball 202, the both sides of the fuselage 201 are rotatably provided with wings 204, the inner end of the wings 204 is connected with the steering driving part 203 for driving the rotation of the wings 204, so that the rotation angle of the wings 204 can be adjusted through the steering driving part 203, so as to adjust the lifting force of the flight of the fuselage 201, the upper end of the tail of the fuselage 201 is rotatably provided with a tail rudder 205, the tail rudder 205 is connected with the tail motor for driving the rotation of the tail rudder 205, the tail rudder 205 is driven to rotate through the tail motor, so that the fuselage 201 can swing in the horizontal direction, the tail of the fuselage 201 is also provided with a detection unit for detecting the flight state of the fuselage 201, the acting force generated by the flight of the fuselage 201 can be detected through 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, a plurality of abutting arc blocks 207 are arrayed on the outer side of the detection rod 208, the abutting surface of the abutting arc block 207 matches the outer side of the detection rod 208, the abutting arc block 207 is fixedly connected with 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 moves towards the opposite direction of the fuselage 201, so that the detection rod 208 generates pressure on the corresponding abutting arc block 207, the pressure is transmitted to the pressure sensor 206, so as to detect the pressure of the detection rod 208, the detected force is equivalent to the external force suffered by the fuselage 201 during flight, it should be noted that the pressure sensor 206 will be zeroed before detection, so as 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 connecting end matching the tip, so that the pressure suffered by the head of the fuselage during rapid flight can be detected;

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

[0042] The auxiliary pressure sensor 209, the radio frequency sensor and the pressure sensor 206 herein wirelessly interact with the control terminal, so that the flight state 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 wings 204, so as to provide data for the experiment;

[0043] The level is also arranged on the fuselage 201, so as to detect the state of the fuselage 201 itself;

[0044] The lifting member includes a lifting chute 303 arranged on the rotating column 302, the lifting chute 303 is arranged at the axis position of the rotating column 302, a transmission sliding plate connected with the lifting disc 401 is arranged at the position of the lifting chute 303, a lifting screw 304 is rotatably arranged at the middle position of the lifting chute 303, the lifting screw 304 is threadedly connected with the transmission sliding plate, the upper end of the lifting screw 304 is connected with a lifting motor 301 for driving the rotation of the lifting screw 304, under the action of the lifting motor 301, the lifting screw 304 rotates relative to the transmission sliding plate, under the action of the thread, the transmission sliding plate drives the lifting disc 401 to slide along the axis of the rotating column 302, so as to adjust the flight height of the aircraft component 200;

[0045] The rotating driving member includes a driven gear 103 arranged at the lower end of the rotating column 302, an driving gear 105 is engaged with the outer side of the driven gear 103, the lower end of the driving gear 105 is connected with a first motor 104 for driving the rotation of the driving gear 105, the driving gear 105 drives the rotating column 302 to rotate through the driven gear 103, so as to provide 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 by the rotating driving member to rotate at high speed, so that the rotating column 302 drives the steering arm 400 to rotate quickly, the steering arm 400 drives the aircraft component 200 to fly, so as to provide 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 by the detection unit, at this time, the pressure sensor 206 is cleared, then the lifting disc 401 and the aircraft component 200 are lowered by the lifting member, so that the flight height of the aircraft component 200 is lowered, when the lowering distance approaches the water surface distance, the instantaneous upward force suffered by the aircraft component 200 is observed, and the ratio of the upward force to the wing is observed;

[0047] If the aircraft component 200 is detected to fly in the obstacle area, the building baffle 501 is only driven to rotate by the overturning motor 502, so that the building baffle 501 is rotated to the vertical state, so that the building baffle 501 forms a ground obstacle below the aircraft component 200, so as to block the airflow, and then the flight state of the aircraft component 200 is observed;

[0048] The ranging unit and the camera are arranged at the lower end of the aircraft component 200, if it is judged that the lower side is an obstacle or water, the flight state of the aircraft component 200 is adjusted by rotating the steering driving member 203 and the tail rudder 205, so that the aircraft can be automatically adjusted without manual adjustment.

[0049] The above merely provides the preferred embodiment of the present application, and is not used to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims

1. A ground simulation experimental system for the dynamic characteristics of an online state-aware ground effect vehicle, comprising a base (100), wherein a rotating column (302) is rotatably disposed at the middle position of the upper end of the base (100), and the lower end of the rotating column (302) is connected to a rotating drive component for driving its high-speed rotation, characterized in that: The rotating column (302) is externally slidably provided with a lifting disc (401), the lifting disc (401) is connected to a lifting member for driving the height adjustment of the lifting disc (401), the lifting disc (401) is externally arrayed with at least two steering arms (400), the outer end of each steering arm (400) is provided with an aircraft component (200), the symmetrically arranged aircraft components (200) are arranged to balance the force of the rotating column (302), and the base (100) is provided at the upper end with an obstacle assembly for building ground obstacles; The obstacle assembly comprises a water storage tank (101) arranged at the upper end of the base (100), the water storage tank (101) is filled with water, and the water storage tank (101) is externally arrayed with a plurality of overturning motors (502), and the output end of the overturning motor (502) is provided with a building baffle (501); The aircraft component (200) comprises a fuselage (201), the tail axis position of the fuselage (201) is pivotally connected to the hanger rod at the end of the steering arm (400) through a universal ball (202), the two sides of the fuselage (201) are pivotally provided with wings (204), the inner end of the wing (204) is connected to a steering drive (203) for driving the rotation of the wing (204), so that the rotation angle of the wing (204) can be adjusted through the steering drive (203), so as to adjust the lifting force of the fuselage (201) in flight, and a tail rudder (205) is pivotally arranged at the upper end of the tail of the fuselage (201), the tail rudder (205) is connected to a tail motor for driving the rotation of the tail rudder (205), and the tail of the fuselage (201) is further provided with a detection unit for detecting the flight state of the fuselage (201).

2. The online state-aware ground effect vehicle dynamic characteristics ground simulation experiment system according to claim 1, wherein, The number of steering arms (400) is even.

3. The online state-aware ground effect vehicle dynamic characteristics ground simulation experiment system according to claim 1, wherein, The steering arm (400) is provided with a reinforcing rib.

4. The online state-aware ground effect vehicle dynamic characteristics ground simulation experiment system according to claim 1, wherein, The lower end of the base (100) is provided with a plurality of supporting legs (102).

5. The online state-aware ground effect vehicle dynamic characteristics ground simulation experiment system according to claim 1, wherein, The detection unit comprises a detection rod (208) arranged at the tail of the universal ball (202), the universal ball (202) is coaxially arranged with the fuselage (201), the detection rod (208) is externally arrayed with a plurality of abutting arc blocks (207), the abutting surface of the abutting arc block (207) matches the outer side of the detection rod (208), and the abutting arc block (207) is fixedly connected with the input end of the pressure sensor (206).

6. The online state-aware ground effect vehicle dynamic characteristics ground simulation experiment system according to claim 1, wherein, The fuselage (201) is further provided with a level.

7. The online state-aware ground effect vehicle dynamic characteristics ground simulation experiment system according to claim 1, wherein, The lifting member comprises a lifting chute (303) arranged on the rotating column (302), the lifting chute (303) is arranged at the axis position of the rotating column (302), the lifting chute (303) is slidably provided with a transmission sliding plate connected with the lifting disc (401), a lifting screw (304) is pivotally arranged at the middle position of the lifting chute (303), the lifting screw (304) is threadedly connected with the transmission sliding plate, and the upper end of the lifting screw (304) is connected to a lifting motor (301) for driving the rotation of the lifting screw (304).

8. The online state-aware ground effect vehicle dynamic characteristics ground simulation experiment system according to claim 1, wherein, The rotating driving part comprises a driven gear (103) arranged at the lower end of the rotating column (302), and a driving gear (105) is engaged with the outside of the driven gear (103), and the lower end of the driving gear (105) is connected with a first motor (104) for driving the rotation of the driving gear (105).

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