A system and method for testing the anti-torsion of the satellite-rocket separation interface under a vibration environment

Abstract

The present invention discloses a system and method for torsion resistance test of satellite-rocket separation interface under a vibration environment. The system is characterized in that its test piece includes a satellite, a rocket compartment, and a satellite-rocket connection device, and its test equipment includes a vibration table, a fixed bracket, a torque transmission device, a power source device, and a fixed pulley. Two tooling points are set at the front and rear symmetrical positions of the structure of the satellite. The fixed bracket is set at the tangent position of the tooling point and the satellite side plate. The fixed pulley is installed on the fixed bracket, and the upper end height of the fixed pulley is flush with the tooling point. One end of the torque transmission device is fixed to the tooling point, and the other end is connected to the power source device at the end through the fixed pulley to complete the loading of the torque. The present invention is direct, effective, and reliable, filling the blank of satellite-rocket torsion resistance test in the domestic aerospace field, making up for the shortcomings of traditional static load assessment, and can be widely used in the design of satellite-rocket separation interface torsion resistance test under different load conditions and different satellite-rocket combination configurations.

Description

Technical Field

[0001] The present invention relates to the technical field of torsion testing in a vibration environment, and in particular to a system and method for testing the anti-torsion of a satellite-rocket separation interface in a vibration environment. Background Art

[0002] The connection, unlocking and separation of the satellite and rocket are key nodes in the space launch process. During the flight of the rocket, the rotation of the rocket will generate corresponding torque on the satellite. In a complex vibration environment, the torsion resistance of the satellite-rocket separation device to the satellite-rocket separation interface is tested. The conventional satellite-rocket torsion test is to apply opposite tangential forces with hydraulic equipment at symmetrical positions on the outer diameter of the satellite to simulate the torsional load of the satellite and perform a static test on the torsion resistance of the satellite-rocket separation device.

[0003] With the change of rocket support form, the vibration environment during flight tends to be more complicated. The torsional resistance of the satellite-rocket interface cannot be evaluated under simple static test conditions. In order to fill the gap in test methods in this field and to evaluate the reliability of the torsional margin of the satellite-rocket separation device under a vibrating state, the best way is to conduct a torsional resistance test of the satellite-rocket interface on a vibration table. However, conventional hydraulic equipment cannot be used in a vibration environment. It is urgent to find a test method for torsional torque testing of the satellite-rocket separation interface under a vibration environment. Summary of the invention

[0004] The technical problem solved by the present invention is that a method for testing the torsion resistance of the satellite-rocket separation interface under a vibration environment is proposed, as the static test scheme cannot cover the torsion resistance assessment requirements of the satellite-rocket separation interface under a complex environment. The method comprises the following steps:

[0005] The present invention is direct, effective and reliable, filling the gap in satellite-rocket torsion resistance testing in the domestic aerospace field. The method considers conducting torsion resistance testing experiments simultaneously under a vibration environment, replacing a single static test, making up for the shortcomings of traditional static load assessments, and can more realistically simulate the torsion load conditions of the satellite-rocket separation interface in flight. It can be widely used in the design of satellite-rocket separation interface torsion resistance tests under different load conditions and with different satellite-rocket combination configurations. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] Figure 1 A side view of the arrangement of a satellite-rocket separation interface anti-torsion test system under a vibration environment provided by an embodiment of the present invention;

[0007] Figure 2 A top view of the arrangement of the satellite-rocket separation interface anti-torsion test system under a vibration environment provided in an embodiment of the present invention.

[0008] Description of reference numerals:

[0009] 1: Satellite; 2: Rocket compartment; 3: Satellite-rocket connection unlocking device; 4: Vibration table; 5: Torque transmission device; 6: Fixed pulley; 7: Power source device; 8: Fixed bracket; 9: Tooling point. DETAILED DESCRIPTION

[0010] The present invention will be described in more detail below with reference to the accompanying drawings showing embodiments of the present invention. In order to achieve a full and complete disclosure and to fully understand the scope of the present invention to those skilled in the art.

[0011] The following is a further description of the satellite-rocket separation interface anti-torsion test system and method under a vibration environment provided by the present invention in conjunction with the accompanying drawings and embodiments.

[0012] Figure 1 and Figure 2 They are respectively a side view and a top view of the arrangement of the satellite-rocket separation interface anti-torsion test system under a vibration environment provided by an embodiment of the present invention. Figures 1-2 As shown, a test piece of a satellite-rocket separation interface anti-torsion test system under a vibration environment provided by an embodiment of the present invention includes a satellite 1, a rocket compartment 2 and a satellite-rocket connection device 3, and the test equipment includes a vibration table 4, a torque transmission device 5, a power source device 7, a fixed pulley 6, etc.

[0013] The satellite-rocket separation interface anti-torsion test method under a vibration environment of the present invention comprises:

[0014] Step 1: Use the satellite-rocket connection unlocking device 3 to connect the satellite 1 (structural component) with the rocket compartment 2 to form a satellite-rocket assembly, and load the satellite-rocket connection unlocking device with a corresponding preload force according to the load requirements;

[0015] Step 2: Fix the satellite-rocket assembly on the vibration table 4 to prepare the torsional load to be applied to the satellite;

[0016] Step 3: The torsional load application step includes: setting two tooling points 9 at the front and rear symmetrical positions outside the satellite 1 structure, setting two fixed brackets 8 at the tangent positions of the tooling points 9 and the side panels of the satellite 1, mounting a fixed pulley 6 on the fixed bracket 8, the fixed pulley 6 is horizontal with the tooling point 9, fixing one end of the torque transmission device 5 with the tooling point 9, and connecting one end with the power source device 7 at the end through the fixed pulley 6 to complete the torque loading;

[0017] Step 4: Start the vibration table 4 to apply vibration conditions to the satellite-rocket combination, complete the anti-torsion test of the satellite-rocket separation interface under the vibration environment, and determine whether the satellite-rocket docking surface is twisted after the test.

[0018] The force source device 7 can be a weight counterweight to achieve the corresponding load conditions. The position of the fixed pulley 6 can be ensured by the fixed bracket 8 to ensure that the upper end height of the fixed pulley 6 is flush with the tooling point 9; the torque transmission device 5 can be a flexible material such as a steel cable but is not limited to a steel cable, and the counterweight of the force source device 7 can be adjusted to achieve different torque transmission.

[0019] When the torsional load is applied, the force value of the force source device is adjusted to achieve a thorough analysis of the torsional margin. By adjusting the difference between the two forces, the bending moment condition can be applied simultaneously with the torque condition.

[0020] The satellite torsion force application points are two tooling points 9, with parallel and opposite directions. The relationship between torque and force source device is: M 扭矩 =(F 力源装置1 +F 力源装置2 )×L 两工装点直线 .

[0021] By changing the tension ratio of the power source device, a bending moment can be applied to the satellite-rocket separation surface at the same time. The relationship between the bending moment and the power source device is: M 弯矩 =|F 力源装置1 -F 力源装置2 |×H 工装点-星箭面 .

[0022] The satellite torsion judgment method in step 4 may be to draw vertical lines above and below the docking surface before step 4 or other obvious judgment methods. Step 4 judges whether the satellite is torsion, and multiple groups of tests may be performed in sequence to complete the critical torsion moment of whether the satellite is torsion or not. At this time, the anti-torsion margin coefficient is obtained by testing.

[0023] The satellite-rocket separation interface torsion resistance test method under a vibration environment provided by the present invention assesses the satellite-rocket separation interface torsion resistance reliability in a flight state in an intuitive manner.

[0024] As an optimized test method, the present invention aims at the anti-torsion test demand of the satellite-rocket separation interface under a vibration environment. By applying parallel and opposite lateral tensions to the outside of the satellite, it can be equivalent to the torque condition of the satellite; by changing the tension ratio, the test piece can be further provided with bending moment conditions according to experimental needs; by using flexible materials such as steel cables as torque transmission devices, it can better match the vibration environment assessment and avoid rigid damage; by adjusting the counterweight as a force source device with weights, it is simple and efficient; the vibration test assessment rather than static load assessment is more intuitive and realistic, and is not limited to a single static load condition.

[0025] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0026] It should be noted that the above is only an illustrative description and explanation of the present invention, and those skilled in the art should understand that any modification and replacement of the present invention belongs to the protection scope of the present invention.

Claims

1. A satellite-rocket separation interface anti-torsion test system under a vibration environment, characterized in that: The test piece includes a satellite, a rocket compartment, and a satellite-rocket connection unlocking device. The test equipment includes a vibration table, a fixed bracket, a torque transmission device, a power source device, and a fixed pulley. The satellite-rocket connection unlocking device connects the satellite and the rocket compartment to form a satellite-rocket assembly. The satellite-rocket assembly is placed on the vibration table. Two tooling points are set at the front and rear symmetrical positions on the outside of the satellite structure, the fixed bracket is set at the tangent position between the tooling point and the satellite side panel, the fixed pulley is installed on the fixed bracket, and the upper end height of the fixed pulley is flush with the tooling point, one end of the torque transmission device is fixed to the two tooling points, and the other end is connected to the power source device at the end through the fixed pulley to complete the loading of the torque, and the satellite torsion force application points are the two tooling points, and the directions are parallel and opposite.

2. The satellite-rocket separation interface anti-torsion test system under a vibration environment according to claim 1 is characterized in that: The torque transmission device is a steel cable of flexible material.

3. The satellite-rocket separation interface anti-torsion test system under a vibration environment according to claim 1 is characterized in that: The force source device is a weight counterweight.

4. A method for testing the anti-torsion of the satellite-rocket separation interface under a vibration environment, characterized in that: The satellite-rocket separation interface anti-torsion test system under a vibration environment according to any one of claims 1 to 3 comprises the following steps: Step 1: Use the satellite-rocket connection unlocking device to connect the satellite and the rocket compartment to form a satellite-rocket assembly, and load the satellite-rocket connection unlocking device with corresponding preload force according to the load requirements; Step 2: Fix the star-rocket assembly on the vibration table; Step 3: Fix one end of the torque transmission device to the tooling point, and connect the other end to the force source device at the end through a fixed pulley; Step 4: Start the vibration table to apply vibration conditions to the satellite-rocket combination to complete the torsional resistance assessment of the satellite-rocket separation interface under the vibration environment.

5. The method for testing the anti-torsion of the satellite-rocket separation interface under a vibration environment according to claim 4, characterized in that: In step 3, the relationship between the torque and the power source device is: 扭矩 =(F 力源装置1 +F 力源装置2 )×L 两工装点直线 .

6. The method for testing the anti-torsion of the satellite-rocket separation interface under a vibration environment according to claim 4, characterized in that: According to the experimental requirements, in step 3, by changing the tension ratio of the power source device, a bending moment is applied to the satellite-rocket separation surface. The relationship between the bending moment and the power source device is: M 弯矩 =|F 力源装置1 -F 力源装置2 |×H 工装点-星箭面 .

7. The method for testing the anti-torsion of the satellite-rocket separation interface under a vibration environment according to claim 4, characterized in that: Before step 4, draw vertical lines above and below the docking surface, and after step 4, perform satellite torsion interpretation.

8. The method for testing the anti-torsion of the satellite-rocket separation interface under a vibration environment according to claim 4, characterized in that: After step 4, the torsion of the satellite is judged, and multiple groups of tests are carried out in sequence to complete the critical torsional moment of whether the satellite is torsion or not. At this time, the anti-torsion margin coefficient is obtained by testing.

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