Vehicle-mounted testing device of tilt-wing vertical take-off and landing aircraft

Abstract

The utility model discloses a vehicle-mounted testing device of a tilt-wing vertical take-off and landing aircraft, and belongs to the technical field of aircraft testing devices. A vehicle-mounted testing device of a tilt wing vertical take-off and landing aircraft comprises an upper supporting frame, an adjusting rotary disc, a lower supporting frame and a supporting rod adjusting assembly. The adjusting turntable comprises a plurality of connecting pieces; the upper supporting frame is installed at the top of the adjusting rotary disc through a connecting piece, the adjusting rotary disc is installed at the top of the lower supporting frame, and the upper supporting frame is rotationally adjusted through the adjusting rotary disc. A plurality of adjusting assemblies are installed at the bottom of the lower supporting frame, and the height of the lower supporting frame in the vertical direction is adjusted through the adjusting assemblies. By means of the arrangement, three-axis force and torque measurement of the aircraft under the simulated incoming flow condition and different tilt angle, attitude and power combined working conditions can be achieved.

Description

TECHNICAL FIELD

[0001] The utility model belongs to aircraft testing device technical field, more specifically, relate to a vehicle test device of tilt wing vertical take-off and landing aircraft. BACKGROUND

[0002] In recent years, tilt wing vertical take-off and landing aircraft because it has the vertical take-off and landing ability of helicopter and the high speed cruise ability of fixed wing aircraft, become the research hotspot in aviation field. This kind of aircraft realizes the conversion of vertical take-off and landing and horizontal flight by tilting its rotor, has broad application prospect in city air traffic (UAM), military reconnaissance, material transportation and other fields. However, because the flight state of tilt wing vertical take-off and landing aircraft is complex, covers multiple tilt angles, attitudes and power combinations, its dynamic characteristics, aerodynamic performance and three-axis moment measurement and analysis have been the difficulties in technical development;

[0003] At present, aircraft force testing method mainly has two kinds:

[0004] Static test bench: this method can accurately measure the three-axis force and moment of multi-rotor aircraft or propeller under different power conditions in no flow condition, is usually used in laboratory or indoor environment. Its shortcomings are that the actual flight state with flow cannot be simulated, and the aircraft attitude cannot be adjusted, and it is not suitable for fixed wing aircraft test relying on flow to generate aerodynamic force;

[0005] Wind tunnel test: this method can accurately measure the force of aircraft in simulated flow environment, and is widely used in the test of fixed wing aircraft. Wind tunnel test can simulate different flow velocities, but the cost is higher, and the aircraft with propeller cannot be tested, so it is not suitable for tilt wing vertical take-off and landing aircraft;

[0006] From this, it can be seen that the above-mentioned prior art cannot meet the real force measurement demand of tilt wing vertical take-off and landing aircraft under the condition of flow. Especially for multi-rotor configuration, the existing static test bench and wind tunnel test method all have limitations. UTILITY MODEL CONTENT

[0007] The utility model solves the technical problem in providing a vehicle test device of tilt wing vertical take-off and landing aircraft, which can realize the three-axis force and moment measurement of aircraft under different tilt angles, attitudes and power combination conditions under the condition of simulated flow.

[0008] The utility model discloses a vehicle test device of tilting wing vertical take-off and landing aircraft is set up on the vehicle, including upper support frame, adjusting carousel, lower support frame and support rod adjusting assembly, adjusting carousel includes a plurality of connecting pieces, and the upper support frame is installed and set up on the top of adjusting carousel through connecting piece, and adjusting carousel is installed and set up on the top of lower support frame, and the upper support frame is adjusted through adjusting carousel rotation, a plurality of adjusting assemblies are installed and set up on the bottom of lower support frame, and the height in vertical direction is adjusted through adjusting assembly.

[0009] As a further improvement of the utility model, the adjusting carousel further comprises a ring; the connecting pieces are arranged at intervals on the top of the ring; and the ring is installed on the top of the lower support frame.

[0010] As a further improvement of the utility model, the connecting pieces are arranged at equal intervals around the ring.

[0011] As a further improvement of the utility model, the connecting piece comprises a spring, a bracket and a connecting rod; the bracket is fixedly arranged on the top of the ring, the spring is arranged on the top of the corresponding bracket; a cover sheet is arranged on the end of the spring away from the bracket; the connecting rod is sequentially arranged through the top of the cover sheet, the spring and the bracket; the spring is sleeved on the outer periphery of the connecting rod; and the connecting piece is connected with the upper support frame through the connecting rod.

[0012] As a further improvement of the utility model, an inner tooth is fixedly arranged on the inner side wall of the ring, and the inner tooth is arranged around the inner side wall of the ring.

[0013] As a further improvement of the utility model, the bracket is arranged in a U shape, connecting plates are fixedly arranged on both sides of the opening of the bracket, the connecting plates are installed on the top of the ring, and the bracket is fixedly connected with the bracket through the connecting plates.

[0014] As a further improvement of the utility model, the adjusting assembly is arranged in four groups and arranged at intervals on the bottom of the lower support frame.

[0015] As a further improvement of the utility model, the adjusting assembly is a screw jack.

[0016] As a further improvement of the utility model, part of the bottom of the connecting plate is suspended above the inner tooth, and the other part is abutted with the top of the ring.

[0017] As a further improvement of the utility model, the upper support frame comprises a support table, a first base plate and a plurality of support rods; the support rods are fixedly arranged on the top of the first base plate to form a platform frame; the support table is fixedly arranged on the top of the platform frame; and the support table is arranged above the first base plate through the support rods.

[0018] Compared with the prior art, the utility model has the beneficial effects that:

[0019] The test device realizes accurate adjustment of various tilt angles and postures of the tilt wing aircraft through a mechanical adjustment system of the adjusting turntable and the adjusting assembly; and the design of the connecting piece of the adjusting turntable enhances the flexibility of the structure.

[0020] The mechanical adjustment of the adjusting assembly and the adjusting turntable is used to realize the posture adjustment of the aircraft; the three-axis force and torque measurement of the tilt wing VTOL aircraft under different tilt angles, postures and power combination working conditions in the simulated airflow condition is realized through the three-axis force sensor, the adjusting turntable and the adjusting assembly.

[0021] The test device has low cost and is easy to operate; the test device is convenient to assemble and maintain, and is suitable for rapid experiment in the early research and development and design verification stages, thereby saving development time and resources. BRIEF DESCRIPTION OF DRAWINGS

[0022] Fig. 1 Fig. 1 is a structural schematic view of the test device of the utility model;

[0023] Fig. 2 Fig. 2 is a structural schematic view of the adjusting turntable of the utility model;

[0024] Fig. 3 Fig. 3 is a structural schematic view of the adjusting turntable and the upper support frame of the utility model.

[0025] Mark explanation in the drawing:

[0026] 1, upper support frame; 2, adjusting turntable; 21, spring; 22, cover sheet; 23, bracket; 24, connecting rod; 25, ring; 26, inner tooth; 3, lower support frame; 4, adjusting assembly; 5, roller. DETAILED DESCRIPTION

[0027] The utility model will be further explained in detail in combination with the embodiments, and the following embodiments are the explanation of the utility model, and the utility model is not limited to the following embodiments.

[0028] Specific embodiment one: please refer to Figs. 1-3 A vehicle-mounted test device of a tilt wing VTOL aircraft, which is arranged on a vehicle, comprises an upper support frame 1, an adjusting turntable 2, a lower support frame 3 and a support rod adjusting assembly 4; the adjusting turntable 2 comprises a plurality of connecting pieces; the upper support frame 1 is arranged on the top of the adjusting turntable 2 through the connecting pieces, the adjusting turntable 2 is arranged on the top of the lower support frame 3, and the upper support frame 1 is adjusted through the rotation of the adjusting turntable 2.

[0029] The bottom of the lower support frame 3 is provided with a plurality of adjusting assemblies 4, and the height in the vertical direction of the lower support frame 3 is adjusted through the adjusting assemblies 4.

[0030] The adjusting turntable 2 further comprises a ring 25, and the connecting members are arranged on the top of the ring 25 in a spaced manner; the ring 25 is arranged on the top of the lower support frame 3;

[0031] Preferably, the connecting members are arranged on the ring 25 in an equidistant manner.

[0032] The connecting member comprises a spring 21, a bracket 23 and a connecting rod 24; the bracket 23 is fixedly arranged on the top of the ring 25, and the spring 21 is arranged on the top of the corresponding bracket 23; the end of the spring 21 away from the bracket 23 is provided with a cover plate 22; one end of the connecting rod 24 penetrates the cover plate 22, the spring 21 and the top of the bracket 23 in sequence; the spring 21 is sleeved on the outer periphery of the connecting rod 24; and the connecting member is connected with the upper support frame 1 through the connecting rod 24.

[0033] Preferably, an inner tooth 26 is fixedly arranged on the inner side wall of the ring 25, and the inner tooth 26 is arranged on the inner side wall of the ring 25.

[0034] Optionally, the inner tooth 26 can be used for auxiliary adjustment to rotate the ring 25.

[0035] Preferably, the bracket 23 is arranged in a U shape, and connecting plates are fixedly arranged on both sides of the opening of the bracket 23; the connecting plates are arranged on the top of the ring 25, and the bracket 23 is fixedly connected with the bracket 23 through the connecting plates.

[0036] Preferably, part of the bottom of the connecting plate is suspended above the inner tooth 26, and the other part is abutted with the top of the ring 25.

[0037] The upper support frame 1 comprises a support table 11, a first bottom plate and a plurality of supporting rods; the supporting rods are fixedly arranged on the top of the first bottom plate to form a platform frame; the support table 11 is fixedly arranged on the top of the platform frame; the support table 11 is arranged above the first bottom plate through the supporting rods; and the support table 11 is used for carrying the three-axis force sensor.

[0038] Preferably, the adjusting assembly 4 is arranged in four groups and arranged on the bottom of the lower support frame 3 in a spaced manner; the height is adjusted to realize the adjustment of the pitch and roll attitude of the measured aircraft.

[0039] Optionally, the adjusting assembly 4 is arranged on the four corners of the bottom of the lower support frame 3 in a spaced manner.

[0040] Optionally, the adjusting assembly 4 comprises an adjusting base, an adjusting rod and a knob disc; the top of the base of the adjusting assembly 4 is fixedly connected with the bottom of the lower support frame 3; the adjusting rod is slidably connected with the base, and the top of the adjusting rod penetrates the entire base from bottom to top; the knob disc is arranged on the outer side wall of the base in a rotating manner and is connected with the adjusting rod through the base; the base reciprocates along the vertical direction of the adjusting rod through the knob disc.

[0041] Preferably, the adjusting assembly 4 is a screw jack.

[0042] The bottom of the lower support frame 3 is also provided with a plurality of rollers 5 for carrying the test device as a whole.

[0043] Test method of the aircraft:

[0044] The test device is installed on the rear platform of the vehicle, and the corresponding vehicle-mounted sensors and control system are carried on the vehicle. The vehicle speed, vehicle-mounted sensors and control system are used to realize the adjustment of the inflow velocity condition and accurate attitude measurement. The forward inflow generated during the driving of the vehicle can simulate the air flow in the real flight environment. Different inflow velocities can be simulated by adjusting the vehicle speed.

[0045] The top of the test device is provided with a three-axis force sensor, and the aircraft to be tested is installed on the three-axis force sensor.

[0046] The circular ring 25 provided with the inner teeth 26 is used to realize the function of the turntable, and the rotation freedom of the circular ring 25 provided with the inner teeth 26 is adjusted by a mechanical method, so as to realize the adjustment of the yaw attitude of the aircraft.

[0047] The adjusting assembly 4 is used to realize the height adjustment function of the vehicle-mounted test device in the vertical direction. Four adjusting assemblies 4 are respectively installed at the bottom of the vehicle-mounted test device, and the height is adjusted by a mechanical method, so as to realize the adjustment of the pitch and roll attitudes of the measured aircraft, and the actual angle of the measured aircraft is measured by using the level.

[0048] The three-axis force sensor is installed on the top support table and is used to accurately measure the force and torque of the aircraft in three axial directions. The data of the three-axis force sensor is transmitted wirelessly or connected by wire to the computer system arranged in the vehicle, and the force condition of the aircraft under different test conditions is recorded in real time.

[0049] The computer system includes a computer control system and a data acquisition module, which can process the data transmitted from the sensor in real time, and display the force information through a software interface. The collected data includes:

[0050] ;

[0051] At the same time, the tilt angle of the aircraft and the power test working condition can be changed in real time, and the force condition of the aircraft under different test conditions is recorded. In addition, a flight control system can also be carried to realize the preliminary verification of the flight control system design and improve the reliability of the control law design.

[0052] The above descriptions are merely specific embodiments of the present application, and the protection scope of the present application is not limited to this. Any person skilled in the art, according to the technical solutions disclosed in the present application and the improved concepts thereof, can make equivalent replacements or changes, and these should be covered in the protection scope of the present application.

Claims

1. A ground-based test apparatus for a tiltwing vertical takeoff and landing aircraft, the apparatus comprising: The application is arranged on a vehicle and comprises an upper support frame (1), an adjusting turntable (2), a lower support frame (3) and a support rod adjusting assembly (4). The adjusting turntable (2) comprises a plurality of connecting pieces. The upper support frame (1) is arranged on the top of the adjusting turntable (2) through the connecting pieces. The adjusting turntable (2) is arranged on the top of the lower support frame (3). The upper support frame (1) is adjusted in rotation through the adjusting turntable (2). The bottom of the lower support frame (3) is provided with a plurality of adjusting assemblies (4). The height of the lower support frame (3) in the vertical direction is adjusted through the adjusting assemblies (4).

2. The test device for a tilt-wing VTOL aircraft according to claim 1, characterized in that: The adjusting turntable (2) further comprises a ring (25). The connecting pieces are arranged on the top of the ring (25) at intervals. The ring (25) is arranged on the top of the lower support frame (3).

3. A ground-based test apparatus for a tiltwing vertical takeoff and landing aircraft as recited in claim 2, wherein: The connecting pieces are arranged at intervals around the ring (25).

4. The on-board test device of a tilt-wing vertical take-off and landing aircraft according to claim 2, characterized in that: The connecting piece comprises a spring (21), a bracket (23) and a connecting rod (24). The bracket (23) is fixedly arranged on the top of the ring (25). The spring (21) is arranged on the top of the corresponding bracket (23). The end of the spring (21) away from the bracket (23) is provided with a cover sheet (22). One end of the connecting rod (24) is sequentially arranged through the cover sheet (22), the spring (21) and the top of the bracket (23). The spring (21) is sleeved on the outer periphery of the connecting rod (24). The connecting piece is connected with the upper support frame (1) through the connecting rod (24).

5. The on-board test device of a tilt-wing vertical take-off and landing aircraft according to claim 2, characterized in that: An inner tooth (26) is fixedly arranged on the inner side wall of the ring (25) and arranged around the inner side wall of the ring (25).

6. A test device for a tilt-wing vertical take-off and landing aircraft according to claim 4, characterised in that: The bracket (23) is arranged in a U shape. Two sides of the opening of the bracket (23) are fixedly provided with connecting plates. The connecting plates are arranged on the top of the ring. The bracket (23) is fixedly connected with the bracket (23) through the connecting plates.

7. The on-board test device of a tilt-wing vertical take-off and landing aircraft according to claim 1, characterized in that: The adjusting assembly (4) is arranged in four groups and arranged at intervals on the bottom of the lower support frame (3).

8. The on-board test device of a tilt-wing vertical take-off and landing aircraft according to claim 1, characterized in that: The adjusting assembly (4) is a screw jack.

9. The on-board test device of a tilt-wing vertical take-off and landing aircraft according to claim 5, characterized in that: Part of the bottom of the connecting plate is suspended above the inner tooth (26). The other part is abutted with the top of the ring (25).

10. The on-board test device of a tilt-wing vertical take-off and landing aircraft according to claim 1, characterized in that: The upper support frame (1) comprises a support table (11), a first bottom plate and a plurality of support rods. The support rods are fixedly arranged on the top of the first bottom plate to form a platform frame. The support table (11) is fixedly arranged on the top of the platform frame. The support table (11) is arranged above the first bottom plate through the support rods.

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