Aircraft wind tunnel test device

Abstract

The utility model provides an aircraft wind tunnel test device. The device comprises a base; the single-degree-of-freedom sliding mechanism is arranged on the base; the three-degree-of-freedom moving part is arranged on the single-degree-of-freedom sliding mechanism; the first test module is arranged on the three-degree-of-freedom movable part, and the first test module is used for measuring six force elements of the aircraft; the tilting mechanism is arranged on the first test module; wherein the aircraft can be mounted on the tilting mechanism; the second test module is arranged on the tilting mechanism, and the second test module is used for measuring the pitching rolling angle and the acceleration of the aircraft; the multifunctional test bed for the aircraft provided by the utility model has the characteristic of diversified test functions, is provided with a plurality of quick release interfaces and locking devices, can quickly switch the use state, is simple to operate, is convenient and efficient to use, and can provide three test states to meet different test requirements.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft test devices, and in particular relates to an aircraft wind tunnel test device. Background Art

[0002] Currently, rotorcraft, exemplified by traditional single-rotor helicopters with tail rotors, have reached a development bottleneck. However, in recent years, new rotorcraft configurations, such as multi-rotors, tilt-rotors, and composite wings, have experienced rapid growth. In the exploration of these new rotorcraft configurations, scale prototype testing has played a crucial, even decisive, role.

[0003] Compared with conventional configuration rotorcraft, new configuration aircraft mostly involve three modes: fixed wing, tilt-turn transition and helicopter. The test equipment of their scaled prototypes is no longer limited to conventional test methods such as ground bench tests and rotor tower tests, and the test equipment also urgently needs to be updated. Utility Model Content

[0004] Purpose of application: Based on real-world application scenarios and integrating the characteristics of various test devices, develop a multifunctional test bench that can meet the needs of fixed wind tunnel tests and pitch / roll wind tunnel tests for full-aircraft aerodynamic characteristics analysis, as well as the needs of three-degree-of-freedom wind tunnel tests for flight control law verification and dynamic adjustment of PID parameters, and at the same time meet the needs of aircraft ground test missions.

[0005] The present application provides an aircraft wind tunnel test device, the device comprising:

[0006] base;

[0007] A single-degree-of-freedom sliding mechanism is provided on the base;

[0008] A three-degree-of-freedom movable component is provided on the single-degree-of-freedom sliding mechanism;

[0009] a first testing module, disposed on the three-degree-of-freedom movable component, the first testing module being used to measure six force elements of the aircraft;

[0010] A tilting mechanism is provided on the first test module; wherein the aircraft can be mounted on the tilting mechanism;

[0011] The second testing module is arranged on the tilting mechanism, and is used to measure the pitch and roll angles and acceleration of the aircraft.

[0012] Preferably, the base comprises:

[0013] Support plate;

[0014] A cylinder is arranged on the support plate, and the cylinder has a cavity and a first mounting hole that passes through the cavity wall.

[0015] Preferably, the single-degree-of-freedom sliding mechanism comprises:

[0016] The fixed support is a hollow cylinder, on which a second mounting hole and a third mounting hole are provided, and one end of the hollow cylinder is embedded in the cavity;

[0017] A single-degree-of-freedom sliding member having a slideway and a fourth mounting hole and a fifth mounting hole;

[0018] A first bolt and nut pass through the second mounting hole and the fourth mounting hole in sequence to fix the single-degree-of-freedom sliding member in the hollow cylinder;

[0019] The second bolt and nut pass through the third mounting hole and the slideway in sequence, and the second bolt is used to limit the circumferential movement of the single-degree-of-freedom sliding member; wherein, the single-degree-of-freedom sliding member can slide vertically in the hollow cylinder through the slideway.

[0020] Preferably, the single-degree-of-freedom sliding mechanism further comprises:

[0021] A third bolt and nut pass through the first mounting hole and the fifth mounting hole in sequence to fix the hollow cylinder in the cavity;

[0022] Preferably, the three-degree-of-freedom movable component includes:

[0023] a spherical universal joint fixing seat connected to the single-degree-of-freedom sliding member, wherein the outer ring of the spherical universal joint fixing seat is provided with threads;

[0024] A spherical universal joint is provided on the spherical universal joint fixing seat, and the top of the spherical universal joint is circumferentially threaded;

[0025] A locking mechanism having an internal thread, wherein the locking mechanism is threadedly connected to the spherical universal hinge fixing seat;

[0026] The locking mechanism is rotated and screwed upward until it is connected with the top circumferential thread of the spherical universal joint, thereby locking the spherical universal joint.

[0027] Preferably, the first test module includes:

[0028] a force balance, arranged on top of the spherical universal joint, for measuring the six force elements of the aircraft;

[0029] The second test module includes:

[0030] The IMU sensor is arranged on the tilt mechanism, and is used to measure the pitch and roll angles and acceleration of the aircraft.

[0031] Beneficial technical effects of this application:

[0032] The aircraft multi-functional test bench provided in this application has the characteristics of diverse test functions. It is equipped with multiple quick-release interfaces and locking devices, which can quickly switch the use status. It is simple to operate, convenient and efficient to use, and can provide three test states to meet different test needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 This is a three-degree-of-freedom test state diagram of an aircraft wind tunnel test device provided in an embodiment of the present application;

[0034] Figure 2 This is a pitch / roll characteristic test state diagram of an aircraft wind tunnel test device provided in an embodiment of the present application;

[0035] Figure 3 This is a four-degree-of-freedom test state diagram of an aircraft wind tunnel test device provided in an embodiment of the present application;

[0036] Figure 4 This is a schematic structural diagram of an aircraft wind tunnel test device provided in an embodiment of the present application;

[0037] Figure 5 This is an exploded view of an aircraft wind tunnel test device provided in an embodiment of the present application;

[0038] Among them: 1-IMU sensor; 2-aircraft mounting platform; 3-tilt bracket; 4-dual-axis servo; 5-first adapter plate; 6-force balance; 7-second adapter plate; 8-first mounting bolt; 9-spherical universal joint; 10-locking mechanism; 11-second mounting bolt; 12-spherical universal joint fixing seat; 13-third adapter plate; 14-fourth mounting hole; 15-single-degree-of-freedom sliding member; 16-slide; 17-second mounting hole; 18-third mounting hole; 19-first mounting hole; 20-hollow cylinder; 21-base; 22-first bolt and nut; 23-second bolt and nut; 24-third bolt and nut; 25-fifth mounting hole. DETAILED DESCRIPTION

[0039] See also Figure 4 and Figure 5The connection relationship between the various components of an aircraft wind tunnel test device provided in this application is as follows: a first mounting hole 19 is provided on the base 21, which is used to mount a hollow cylinder 20. The hollow cylinder is provided with a second mounting hole 17 and a third mounting hole 18. The hollow cylinder is used to engage with a single-degree-of-freedom sliding member 15 and a second bolt and nut 23 to form a single-degree-of-freedom sliding mechanism. The single-degree-of-freedom sliding member is connected to the third adapter plate 13, which is connected to the spherical universal joint fixing seat 12 via a second mounting bolt 11. The spherical universal joint fixing seat is used to mount a spherical universal joint 9, which is connected to the second adapter plate 7 via a first mounting bolt 8. A force balance 6 is provided on the second adapter plate, a first adapter plate 5 is provided on the force balance, a dual-axis servo 4 is provided on the first adapter plate, a tilt bracket 3 is connected to the dual-axis servo, a mounting groove is provided on the upper surface of the tilt bracket, and the mounting groove is used to mount an IMU sensor 1. The aircraft is mounted on the upper surface of the tilt bracket.

[0040] The present application uses a spherical universal joint with a thread on the top and a spherical universal joint fixing seat with a thread on the outer ring to form a three-degree-of-freedom movable component.

[0041] The present application uses a spherical universal joint with a thread on the top, a spherical universal joint fixing seat with a thread on the outer ring, and a locking mechanism with a built-in thread to form a three-degree-of-freedom movable component with a locking function.

[0042] This application uses a dual-axis servo with a tilt bracket and a built-in IMU sensor to form a tilt mechanism that can adjust any tilt angle according to an external signal.

[0043] This application uses a single-degree-of-freedom sliding part with a slideway and a locking mechanism mounting hole, which is combined with a fixed support and uses bolts and nuts to lock the axial rotation of the single-degree-of-freedom sliding part. The overall structure is a single-degree-of-freedom sliding mechanism with a locking function.

[0044] The present application provides an aircraft wind tunnel test device, the device comprising:

[0045] base;

[0046] A single-degree-of-freedom sliding mechanism is provided on the base;

[0047] A three-degree-of-freedom movable component is provided on the single-degree-of-freedom sliding mechanism;

[0048] a first testing module, disposed on the three-degree-of-freedom movable component, the first testing module being used to measure six force elements of the aircraft;

[0049] A tilting mechanism is provided on the first test module; wherein the aircraft can be mounted on the tilting mechanism;

[0050] The second testing module is arranged on the tilting mechanism, and is used to measure the pitch and roll angles and acceleration of the aircraft.

[0051] Wherein, the first test module includes:

[0052] a force balance, arranged on top of the spherical universal joint, for measuring the six force elements of the aircraft;

[0053] The second test module includes:

[0054] The IMU sensor is arranged on the tilt mechanism, and is used to measure the pitch and roll angles and acceleration of the aircraft.

[0055] This application uses a force balance and a built-in IMU sensor to form a six-force, angle and acceleration integrated test module.

[0056] In the present application, the vertical degree of freedom of the test bench can be released by removing the bolts and nuts of the single-degree-of-freedom sliding member locking mechanism.

[0057] The present application releases the three degrees of freedom of pitch, roll and yaw of the test bench or locks it into a fixed structure by rotating the locking mechanism with built-in threads.

[0058] This application can quickly meet the needs of fixed, single-degree-of-freedom (pitch / roll), three-degree-of-freedom and four-degree-of-freedom aircraft wind tunnel and ground testing by quickly switching between different combinations of test bench components.

[0059] See also Figure 1 、 Figure 2 and Figure 3 , the three test states provided in this application are as follows:

[0060] The first bolt and nut pass through the second mounting hole and the fourth mounting hole in sequence to fix the single-degree-of-freedom sliding member in the hollow cylinder. The built-in threaded locking mechanism is screwed downward, and the tilt bracket angle and the circumferential mounting angle of the tilt mechanism remain fixed, achieving a three-degree-of-freedom test state. Figure 1 .

[0061] The first bolt and nut pass through the second and fourth mounting holes in sequence to secure the single-degree-of-freedom slide within the hollow cylinder. The built-in threaded locking mechanism is screwed upward. By controlling the servo to change the tilt bracket angle of the tilt mechanism, the circumferential mounting angle of the tilt mechanism can be changed to achieve fixed / pitch / roll characteristic test states. Figure 2 .

[0062] Remove the first bolt and nut, screw the built-in threaded locking mechanism downward, and the tilt bracket angle and circumferential installation angle of the tilt mechanism remain fixed, so that the four-degree-of-freedom test state can be achieved. Figure 3 .

[0063] It should be noted that the three-degree-of-freedom test state can be applied to PID parameter adjustment of aircraft with fixed-wing configuration, multi-rotor configuration, tilt-rotor configuration, etc. during wind tunnel tests, and can also be applied to PID parameter adjustment tests of aircraft with multi-rotor configuration and tilt-rotor configuration (helicopter mode) during ground tests.

[0064] The fixed / pitch / roll characteristic test state can be applied to conventional wind tunnel tests and ground tests of aircraft.

[0065] The four-degree-of-freedom test state can be applied to PID parameter adjustment tests of conventional fixed-wing aircraft during wind tunnel tests, and can also be applied to verification of tilt-transition mode control laws and multi-mode PID parameter adjustment tests of tilt-configuration aircraft during wind tunnel tests.

Claims

1. An aircraft wind tunnel test device, characterized in that: The device comprises: base; A single-degree-of-freedom sliding mechanism is provided on the base; A three-degree-of-freedom movable component is provided on the single-degree-of-freedom sliding mechanism; a first testing module, disposed on the three-degree-of-freedom movable component, the first testing module being used to measure six force elements of the aircraft; A tilting mechanism is provided on the first test module; wherein the aircraft can be mounted on the tilting mechanism; The second testing module is arranged on the tilt mechanism, and is used to measure the pitch and roll angles and acceleration of the aircraft.

2. The device according to claim 1, characterized in that The base comprises: Support plate; A cylinder is arranged on the support plate, and the cylinder has a cavity and a first mounting hole (19) penetrating the cavity wall.

3. The device according to claim 2, characterized in that The single-degree-of-freedom sliding mechanism comprises: The fixed support is a hollow cylinder, the hollow cylinder is provided with a second mounting hole (17) and a third mounting hole (18), and one end of the hollow cylinder is embedded in the cavity; A single-degree-of-freedom sliding member having a slideway (16), a fourth mounting hole (14), and a fifth mounting hole (25); A first bolt and nut (22) passes through the second mounting hole and the fourth mounting hole in sequence to fix the single-degree-of-freedom sliding member in the hollow cylinder; A second bolt and nut (23) passes through the third mounting hole and the slideway in sequence, and the second bolt is used to limit the circumferential movement of the single-degree-of-freedom sliding member; wherein the single-degree-of-freedom sliding member can slide vertically in the hollow cylinder through the slideway.

4. The device according to claim 3, characterized in that The single-degree-of-freedom sliding mechanism further comprises: A third bolt and nut (24) passes through the first mounting hole and the fifth mounting hole in sequence to fix the hollow cylinder in the cavity.

5. The device according to claim 3, characterized in that The three-degree-of-freedom movable component includes: a spherical universal joint fixing seat connected to the single-degree-of-freedom sliding member, wherein the outer ring of the spherical universal joint fixing seat is provided with threads; A spherical universal joint is provided on the spherical universal joint fixing seat, and the top of the spherical universal joint is circumferentially threaded; A locking mechanism having an internal thread, wherein the locking mechanism is threadedly connected to the spherical universal hinge fixing seat; The locking mechanism is rotated and screwed upward until it is connected with the top circumferential thread of the spherical universal joint, thereby locking the spherical universal joint.

6. The device according to claim 5, characterized in that The first test module includes: a force balance, arranged on top of the spherical universal joint, for measuring the six force elements of the aircraft; The second test module includes: The IMU sensor is arranged on the tilt mechanism, and is used to measure the pitch and roll angles and acceleration of the aircraft.

Images