Device for adjusting angle of attack of aircraft in shaking test and implementation method thereof

Abstract

The application provides a device and a method for adjusting the attack angle of an aircraft in a shaking test, comprising a bottom plate, a rotating shaft support, a rotating platform, a threaded rotating block, a screw rod, a motor and a motor control system, the bottom plate is fixed on the table top of a vibration table at the bottom, and the top of the bottom plate is connected with the rotating shaft support; the rotating platform is used for installing a test aircraft, and the rotating platform is connected with the rotating shaft support and the threaded rotating block through rotating shafts at both ends; one end of the screw rod is screwed into the threaded rotating block, and the other end is connected with the motor through a coupling; the motor is connected with the motor support through a rotating shaft, and the motor support is fixed on the bottom plate; the motor control system drives the motor to operate. The application can adjust the attack angle of the test aircraft in the shaking test, and provides an effective ground test device for the environmental test verification of the aircraft.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of vibration test technology, in particular to a device for adjusting the attack angle of an aircraft in a sloshing test and an implementation method. BACKGROUND

[0002] With the continuous development of aircraft technology, the reliability requirements of aircraft and its components are also continuously improved. In order to eliminate as many faults as possible on the ground, the test and test requirements of the aircraft are further increased, especially the test and test of the aircraft under different flight states and different load environments, which includes the test and test of the aircraft under different attack angles. The attack angle is defined as the angle between the projection of the aircraft speed vector on the longitudinal symmetry plane and the longitudinal axis of the aircraft. The state of the fuel and some components in the aircraft will change under different attack angles, and their response will also change. The fuel sloshing analysis and component sloshing response analysis under different attack angles are of great significance to the test and test of the aircraft. The current test method is generally to design a test tool with an angle, or to set different angle pads on the ordinary test tool, simulate the attack angle of the aircraft, and then perform the sloshing test. This method makes it cumbersome to disassemble and assemble every time the attack angle is changed during the test, which is not conducive to test efficiency. At the same time, this method cannot change the attack angle of the tested aircraft during the sloshing test, and cannot meet many test requirements. Therefore, a device and an implementation method are needed to adjust the attack angle of the aircraft without repeated disassembly and assembly during the sloshing test. SUMMARY

[0003] In view of the defects in the prior art, the purpose of the present application is to provide a device for adjusting the attack angle of an aircraft in a sloshing test.

[0004] According to the device for adjusting the attack angle of an aircraft in a sloshing test provided by the present application, the device comprises a bottom plate 1, a rotating shaft support 2, a rotating platform 4, a threaded rotating block 6, a screw rod 7, a motor 8 and a motor control system, wherein:

[0005] The bottom plate 1 is fixed at the bottom of the vibration table 10, and the top of the bottom plate 1 is connected with the rotating shaft support 2;

[0006] The rotating platform 4 is used for installing the tested aircraft 5, and the rotating platform 4 is connected with the rotating shaft support 2 and the threaded rotating block 6 through rotating shafts at both ends;

[0007] One end of the screw rod 7 is screwed into the threaded rotating block 6, and the other end is connected with the motor 8 through a shaft coupling;

[0008] The motor 8 is connected with the motor support 9 through a rotating shaft, and the motor support 9 is fixed on the bottom plate 1;

[0009] The motor control system drives the motor 8 to operate.

[0010] Preferably, a vibration table 10 is further included, and the bottom plate 1 is fixed on the table top of the vibration table 10.

[0011] Preferably, the vibration table 10 is controlled by a vibration control system, which controls the vibration table 10 to output a desired shaking environment.

[0012] Preferably, the motor 8 drives the screw rod 7 to rotate forward or reverse, thereby driving the screw block 6 to move up or down along the axial direction of the screw rod 7.

[0013] Preferably, when the screw block 6 moves up or down along the axial direction of the screw rod 7, the motor 8 rotates on the motor support 9 through the rotating shaft.

[0014] Preferably, the bottom plate 1 includes a bottom panel and a support mounting plate arranged on the bottom panel, and the rotating shaft support 2 is fastened to the upper surface of the support mounting plate.

[0015] Preferably, the horizontal position and the height position of the rotating shaft support 2 on the support mounting plate are adjustable.

[0016] Preferably, a plurality of through holes for fastening to the vibration table 10 are arranged on the bottom panel.

[0017] Preferably, the height between the rotating shaft support 2 and the support mounting plate is adjusted by a spacer.

[0018] According to the implementation method of the device for adjusting the attack angle of the aircraft in the shaking test, the following steps are included:

[0019] Step S1: install the motor support 9 on the bottom plate 1, and install the motor 8 on the motor support 9 through the rotating shaft, so that the motor 8 can rotate around the rotating shaft and only rotate around the rotating shaft by adjusting the rotating shaft;

[0020] Step S2: screw the screw rod 7 into the screw block 6, install the screw block 6 on one end of the rotating platform 4 through the rotating shaft, and install the other end of the rotating platform 4 on the rotating shaft support 2 through the rotating shaft, so that the screw block 6 and the rotating platform 4 can rotate around the rotating shaft and only rotate around the rotating shaft by adjusting the rotating shaft;

[0021] Step S3: adjust the installation position of the rotating shaft support 2 on the bottom plate 1; and connect the screw rod 7 and the motor 8 through the coupling;

[0022] Step S4: install the base plate 1 on the vibration table 10 table top, and drive the motor 8 to output forward and reverse torque through the motor control system, check whether the rotating platform 4 can rotate normally, and measure the rotation angle range of the rotating platform 4 through the non-contact angle displacement sensor, if the rotation angle range does not meet the test requirements, repeat step S3 until the rotation angle range of the rotating platform 4 is greater than the required angle of attack range of the test aircraft 5;

[0023] Step S5: fix the test aircraft 5 on the rotating platform 4, drive the rotating platform 4 and the test aircraft 5 to rotate through the motor 8, check whether it can meet the required angle of attack of the test aircraft 5, and ensure that there is no interference between each component and the test aircraft 5 in the angle of attack range;

[0024] Step S6: start the vibration control system, drive the vibration table 10 to output the shaking excitation transmitted to the test aircraft 5, and collect the vibration excitation through the acceleration sensor arranged on the vibration table 10 and the test aircraft 5, and through closed-loop control, the vibration table 10 outputs the expected shaking environment; at the same time, the motor control system controls the motor 8 to output forward or reverse torque, the motor 8 drives the threaded rotating block 6 to move, and then drives the rotating platform 4 to rotate, and the inclination angle of the rotating platform 4 is measured through the non-contact angle displacement sensor, so as to adjust the output of the motor.

[0025] Compared with the prior art, the present application has the following beneficial effects:

[0026] The present application can adjust the angle of attack of the test aircraft in real time during the shaking test, avoids the cumbersome disassembly and assembly when adjusting the angle of attack in the traditional method, and can widen the angle of attack adjustment range by adjusting the installation position and installation size of each component, and meets the test and detection requirements of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0027] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0028] Figure 1 The device for adjusting the angle of attack of the aircraft in the shaking test in the embodiment of the present application;

[0029] Figure 2 The device for adjusting the angle of attack range of the aircraft in the embodiment of the present application;

[0030] Figure 3 The test aircraft angle of attack adjustment range diagram in the embodiment of the present application;

[0031] Figure 4 The test system block diagram for adjusting the angle of attack of the aircraft in the shaking test in the embodiment of the present application.

[0032] In the figure: 1. Base plate, 2. Shaft support, 3. Pad block, 4. Rotating platform, 5. Test aircraft, 6. Threaded rotating block, 7. Screw, 8. Motor, 9. Motor support, 10. Vibration table, 31. First pad block, 32. Second pad block. Detailed Implementation

[0033] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0034] like Figure 1 As shown, this embodiment of the invention provides a device and method for adjusting the angle of attack of an aircraft during a shaking test. The device for adjusting the angle of attack of the aircraft during the shaking test includes a base plate 1, a rotating shaft support 2, a pad block 3, a rotating platform 4, a test aircraft 5, a threaded rotating block 6, a screw 7, a motor 8, a motor support 9, a vibration table 10, a vibration control system, and a motor control system. The bottom of the base plate 1 is fixed to the surface of the vibration table 10, and the top is connected to the rotating shaft support 2. The two ends of the rotating platform 4 are respectively connected to the rotating shaft support 2 and the threaded rotating block 6 through rotating shafts. The test aircraft 5 is fixed on the rotating platform 4 by special tooling. One end of the screw 7 is screwed into the threaded rotating block 6, and the other end is connected to the motor 8 through a coupling. The motor 8 is connected to the motor support 9 through a rotating shaft, and the motor support 9 is fixed to the base plate 1.

[0035] like Figure 2 As shown, the rotating shaft support 2 and the rotating platform 4, the rotating platform 4 and the threaded rotating block 6, and the motor 8 and the motor support 9 are connected by a rotating shaft. By adjusting the fitting dimensions, the two connected components can rotate only around the rotating shaft. The base plate 1 is provided with several through holes or threaded holes and is connected to the rotating shaft support 2, the motor support 9, and the vibration table 10 by fasteners. The connection position between the base plate 1 and the rotating shaft support 2 is adjustable, thereby adjusting the rotation angle range of the rotating platform 4. A first pad 31 and a second pad 32 of different thicknesses can be provided between the base plate 1 and the rotating shaft support 2 to adjust the height of the rotating shaft support 2, thereby adjusting the rotation angle range of the rotating platform 4.

[0036] Furthermore, the base plate 1 includes a bottom panel and a support mounting plate disposed on the bottom panel. The bottom panel has two rows of connecting through holes along its length, respectively near the two long sides. When installing the base plate 1, its position can be adjusted according to actual needs. The support mounting plate is a T-shaped support mounting plate with two rows of connecting through holes along its length, respectively near the two long sides. The rotating shaft support 2 can be threadedly fixed to the corresponding connecting through holes as needed, realizing the horizontal position adjustment of the rotating shaft support 2. Simultaneously, the height of the rotating shaft support 2 and the support mounting plate can also be adjusted using shims, for example... Figure 2 The first pad 31 and the second pad 32 are shown.

[0037] like Figure 3 As shown, the tested aircraft has a certain range of angle of attack adjustment.

[0038] like Figure 4 As shown, the vibration control system can drive the vibration table 10 to output swaying excitation and transmit it to the test aircraft 5. The vibration excitation is collected by the acceleration sensors installed on the vibration table 10 and the test aircraft 5. The vibration table 10 outputs the desired vibration spectrum through closed-loop control. At the same time, the motor control system controls the motor 8 to output positive or negative torque. The motor 8 drives the screw block 6 to move through the screw 7, which in turn drives the rotating platform 4 to rotate. The tilt angle of the rotating platform 4 is measured by the non-contact angular displacement sensor, thereby adjusting the output of the motor. Finally, the angle of attack of the test aircraft 5 can be adjusted during the swaying test.

[0039] The specific implementation process of this specific implementation is as follows:

[0040] Step 1: Install the motor support 9 onto the base plate 1 using fasteners, and install the motor 8 onto the motor support 9 via a rotating shaft. Adjust the rotating shaft so that the motor 8 can rotate only around the rotating shaft.

[0041] Step 2: Screw the screw 7 into the threaded rotating block 6, and install the threaded rotating block 6 on one end of the rotating platform 4 through the rotating shaft. Install the other end of the rotating platform 4 on the rotating shaft support 2 through the rotating shaft. Adjust the rotating shaft so that the threaded rotating block 6 and the rotating platform 4 can rotate only around the rotating shaft.

[0042] Step 3: Set a first pad 31 and a second pad 32 of different thicknesses between the rotating shaft support 2 and the base plate 1, and adjust the specific installation position of the rotating shaft support 2 on the base plate 1. At the same time, connect the screw 7 and the motor 8 through the coupling.

[0043] Step four: Install the base plate 1 on the vibration table 10 using fasteners, and drive the motor 8 through the motor control system to output forward and reverse torques to check whether the rotating platform 4 can rotate normally. At the same time, measure the rotation angle range of the rotating platform 4 using a non-contact angular displacement sensor. If the rotation angle range does not meet the test requirements, repeat step three to adjust the thickness and specific installation position of the pad 3 between the rotating shaft support 2 and the base plate 1 until the rotation angle range of the rotating platform 4 is greater than the angle of attack range required for the test of the aircraft 5.

[0044] Step 5: Fix the test aircraft 5 onto the rotating platform 4 using a special tooling. Repeat step 4, drive the rotating platform 4 and the test aircraft 5 to rotate using the motor 8, check whether the angle of attack required for the test aircraft 5 can be met, and ensure that there is no interference between the components and the test aircraft 5 within the angle of attack range.

[0045] Step Six: Start the vibration control system, drive the vibration table 10 to output swaying excitation and transmit it to the test aircraft 5. The vibration excitation is collected by the acceleration sensors installed on the vibration table 10 and the test aircraft 5. The vibration table 10 outputs the desired swaying environment through closed-loop control. At the same time, the motor control system controls the motor 8 to output positive or negative torque. The motor 8 drives the screw block 6 to move through the screw 7, which in turn drives the rotating platform 4 to rotate. The tilt angle of the rotating platform 4 is measured by the non-contact angular displacement sensor, and the output of the motor is adjusted accordingly. Finally, the angle of attack of the test aircraft 5 can be adjusted during the swaying test.

[0046] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0047] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for implementing a device for adjusting the angle of attack of an aircraft during a shaking test, characterized in that, A device for adjusting the angle of attack of an aircraft during a sway test, comprising a base plate (1), a rotating shaft support (2), a rotating platform (4), a threaded rotating block (6), a screw (7), a motor (8), and a motor control system, wherein: The bottom of the base plate (1) is fixed on the table surface of the vibration table (10), and the top of the base plate (1) is connected to the rotating shaft support (2); The rotating platform (4) is used to install the test aircraft (5). The two ends of the rotating platform (4) are connected to the rotating shaft support (2) and the threaded rotating block (6) respectively through the rotating shaft. One end of the screw (7) is screwed into the threaded rotating block (6), and the other end is connected to the motor (8) through a coupling. The motor (8) is connected to the motor support (9) via a rotating shaft, and the motor support (9) is fixed to the base plate (1); The motor control system drives the motor (8) to operate; The method for implementing the device for adjusting the aircraft's angle of attack during the shaking test includes the following steps: Step S1: Install the motor support (9) on the base plate (1) and install the motor (8) on the motor support (9) through the rotating shaft. Adjust the rotating shaft so that the motor (8) can rotate only around the rotating shaft. Step S2: Screw the screw (7) into the threaded rotating block (6), and install the threaded rotating block (6) on one end of the rotating platform (4) through the rotating shaft. Install the other end of the rotating platform (4) on the rotating shaft support (2) through the rotating shaft. Adjust the rotating shaft so that the threaded rotating block (6) and the rotating platform (4) can rotate around the rotating shaft only. Step S3: Adjust the installation position of the rotating shaft support (2) on the base plate (1); at the same time, connect the screw (7) and the motor (8) through the coupling. Step S4: Install the base plate (1) on the vibration table (10) and drive the motor (8) through the motor control system to output positive and negative torques. Check whether the rotating platform (4) can rotate normally. At the same time, measure the rotation angle range of the rotating platform (4) through the non-contact angular displacement sensor. If the rotation angle range does not meet the test requirements, repeat step S3 until the rotation angle range of the rotating platform (4) is greater than the angle of attack range required for the test of the aircraft (5). Step S5: Fix the test aircraft (5) on the rotating platform (4), drive the rotating platform (4) and the test aircraft (5) to rotate through the motor (8), check whether the angle of attack required for the test aircraft (5) can be met, and ensure that there is no interference between the components and the test aircraft (5) within the angle of attack range; Step S6: Start the vibration control system, drive the vibration table (10) to output swaying excitation to the test aircraft (5), and collect the vibration excitation through the acceleration sensors set on the vibration table (10) and the test aircraft (5). Through closed-loop control, the vibration table (10) outputs the desired swaying environment; at the same time, the motor control system controls the motor (8) to produce positive or negative torque, the motor (8) drives the threaded rotating block (6) to move, and then drives the rotating platform (4) to rotate. The tilt angle of the rotating platform (4) is measured by the non-contact angular displacement sensor, and the output of the motor is adjusted accordingly.

2. The method for implementing the device for adjusting the angle of attack of an aircraft in a swaying test according to claim 1, characterized in that, The device for adjusting the angle of attack of the aircraft in the shaking test also includes a vibration table (10), and the bottom of the base plate (1) is fixed on the table surface of the vibration table (10).

3. The method for implementing the device for adjusting the angle of attack of an aircraft in a swaying test according to claim 2, characterized in that, The vibration table (10) is controlled by a vibration control system, which controls the vibration table (10) to output the desired shaking environment.

4. The method for implementing the device for adjusting the angle of attack of an aircraft in a swaying test according to claim 1, characterized in that, The motor (8) drives the screw (7) to rotate forward or reverse, thereby causing the threaded block (6) to move upward or downward along the axial direction on the screw (7).

5. The method for implementing the device for adjusting the angle of attack of an aircraft in a swaying test according to claim 4, characterized in that, When the threaded rotating block (6) moves upward or downward along the axial direction on the screw (7), the motor (8) rotates on the motor support (9) through the rotating shaft.

6. The method for implementing the device for adjusting the angle of attack of an aircraft in a swaying test according to claim 1, characterized in that, The base plate (1) includes a bottom panel and a support mounting plate disposed on the bottom panel, and the pivot support (2) is fastened to the upper surface of the support mounting plate.

7. The method for implementing the device for adjusting the angle of attack of an aircraft in a swaying test according to claim 6, characterized in that, The horizontal and vertical positions of the pivot support (2) on the support mounting plate are adjustable.

8. The method for implementing the device for adjusting the angle of attack of an aircraft in a swaying test according to claim 6, characterized in that, The bottom panel is provided with multiple through holes for fastening to the vibration table (10).

9. The method for implementing the device for adjusting the angle of attack of an aircraft in a swaying test according to claim 7, characterized in that, The height between the rotating shaft support (2) and the support mounting plate is adjusted by a pad.

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