Suspension support two-stage composite on-orbit free boundary simulation method

Abstract

The application discloses a suspension support two-stage composite on-orbit free boundary simulation method, which comprises a spacecraft upper assembly, a spacecraft lower assembly, a rigid suspension frame, a rigid foundation, an elastic suspension spring, a spacecraft upper assembly limiting block, a spacecraft switching auxiliary arm, a spacecraft lower assembly limiting block and an elastic support spring, the spacecraft lower assembly is connected with the rigid foundation through a spacecraft lower assembly support block, and the spacecraft upper assembly is connected with the spacecraft lower assembly through a spacecraft upper assembly support block. In the application, the on-orbit free boundary state of a two-section spacecraft is simulated through the combined action of suspension and support; the rigidity and deformation of the suspension spring and the support spring are set, so that the overall gravity of the spacecraft is unloaded, and the demand of the free boundary condition simulation of the spacecraft on the ground for micro-vibration and other dynamic experiments is met; the spacecraft upper and lower assemblies are unloaded step by step and the relative position is kept unchanged through the cooperation of the spring, the limiting block and the support block.

Description

Technical Field

[0001] This invention relates to the field of spacecraft dynamics testing technology, and in particular to a method for simulating on-orbit free boundaries using a two-stage composite suspension support system. Background Technology

[0002] Spacecraft operate in a free-boundary state during orbit. To conduct various experiments on the ground to simulate spacecraft behavior in space, obtain various dynamic characteristics of the spacecraft, and provide support for spacecraft design and development, a ground-based free-boundary simulation method must be designed. Ideally, when conducting micro-vibration experiments on the ground, no constraint forces should be applied to the spacecraft after unloading its gravity, leaving it in a suspended state. However, due to the presence of ground gravity, only approximate methods can be used to simulate the free-boundary conditions during orbital flight. Therefore, an on-orbit free-boundary simulation method must be proposed, allowing the spacecraft's upper and lower components to be unloaded step-by-step while maintaining their relative positions, thus addressing the ground-based testing requirements for verifying the spacecraft's on-orbit dynamic characteristics and micro-vibration environment. Summary of the Invention

[0003] The purpose of this invention is to propose a suspension-supported dual-stage composite on-orbit free boundary simulation method to solve the above-mentioned problems.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] The suspension support dual-stage composite on-orbit free boundary simulation method includes the upper spacecraft component, the lower spacecraft component, the rigid suspension frame, the rigid foundation, the elastic suspension spring, the upper spacecraft component limiting block, the spacecraft transfer auxiliary arm, the lower spacecraft component limiting block, and the elastic support spring.

[0006] Preferably, the lower spacecraft assembly is connected to a rigid foundation via a lower spacecraft assembly support block, and the upper spacecraft assembly is connected to the lower spacecraft assembly via an upper spacecraft assembly support block.

[0007] Preferably, a vibration reduction and isolation device is provided between the upper and lower components of the spacecraft, and four spacecraft transfer auxiliary arms arranged in the circumferential direction are connected to the outer walls of both the upper and lower components. The weight of the upper component is G1, and the weight of the lower component is G2.

[0008] Preferably, it includes the following steps:

[0009] S1. The spacecraft is hoisted into place;

[0010] S2. The limiting device is fixed in place;

[0011] S3, G1, gravity of components on the spacecraft being suspended and unloaded;

[0012] S4, supporting the gravity of the unloaded spacecraft's lower components, G2;

[0013] S5. Conduct experiments.

[0014] Preferably, the process of suspending and unloading the gravity G1 of the spacecraft components in step S3 includes the following steps:

[0015] S3.1 Assemble the elastic suspension springs. Four sets of elastic suspension springs are set up along the circumferential direction of the outer perimeter of the spacecraft components.

[0016] S3.2. Raise the top of the elastic suspension spring so that the tension of each spring reaches 0.225G1. At this point, 90% of the weight of the spacecraft components has been unloaded.

[0017] S3.3 Remove the component support blocks on the spacecraft. At this time, the remaining 10% of the gravity is borne by the component limiting blocks on the spacecraft.

[0018] S3.4 Continue to lift the top of the elastic suspension spring so that the tension of each spring reaches 0.25G1. At this time, the spacecraft component limit block no longer provides support force to the spacecraft component, the spacecraft transfer auxiliary arm does not contact the spacecraft component limit block, and the spacecraft component is completely unloaded by gravity.

[0019] Preferably, the step S4 of supporting the gravity G2 of the unloading spacecraft's lower components includes the following steps:

[0020] S4.1 Assemble the elastic support springs. A total of eight sets of elastic support springs are set along the circumferential direction of the bottom of the spacecraft's lower components.

[0021] S4.2 Lift the bottom of the elastic support spring so that the tension of each spring reaches 0.1125G2, at which point 90% of the weight of the spacecraft's lower components has been unloaded;

[0022] S4.3 Remove the support block of the lower component of the spacecraft. At this time, the remaining 10% of the gravity is borne by the limiting block of the lower component of the spacecraft.

[0023] S4.4 Continue to raise the bottom of the elastic support spring so that the tension of each spring reaches 0.125G2. At this time, the spacecraft lower component limit block no longer provides support force to the spacecraft lower component, the spacecraft transfer auxiliary arm does not contact the spacecraft lower component limit block, and the spacecraft lower component is completely unloaded by gravity.

[0024] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0025] 1. This application achieves the simulation of the free boundary state of a two-section spacecraft in orbit through the combined action of suspension and support; by setting the stiffness and deformation of the suspension spring and support spring, the overall gravity of the spacecraft is unloaded, which meets the requirements for simulating the free boundary conditions when the spacecraft is conducting micro-vibration and other dynamic experiments on the ground; through the coordinated use of springs, limit blocks and support blocks, the upper and lower components of the spacecraft are unloaded step by step while maintaining their relative positions. Attached Figure Description

[0026] Figure 1 This diagram illustrates the structure of the suspension-supported dual-stage composite on-orbit free boundary simulation before unloading, according to an embodiment of the present invention.

[0027] Figure 2 A schematic diagram of the structure of the suspension support dual-stage composite on-orbit free boundary simulated unloading provided according to an embodiment of the present invention is shown.

[0028] Legend:

[0029] 1. Upper spacecraft component; 2. Vibration reduction and isolation device; 3. Upper spacecraft component support block; 4. Lower spacecraft component; 5. Lower spacecraft component support block; 6. Rigid suspension frame; 7. Rigid foundation; 8. Elastic suspension spring; 9. Upper spacecraft component limiting block; 10. Spacecraft transfer auxiliary arm; 11. Lower spacecraft component limiting block; 12. Elastic support spring. Detailed Implementation

[0030] 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.

[0031] Please see Figure 1-2 The present invention provides a technical solution:

[0032] The suspension-supported two-stage composite on-orbit free boundary simulation method includes an upper spacecraft component 1, a lower spacecraft component 4, a rigid suspension frame 6, a rigid foundation 7, an elastic suspension spring 8, an upper spacecraft component limiting block 9, a spacecraft transfer auxiliary arm 10, a lower spacecraft component limiting block 11, and an elastic support spring 12. The lower spacecraft component 4 is connected to the rigid foundation 7 via a lower spacecraft component support block 5, and the upper spacecraft component 1 is connected to the lower spacecraft component 4 via an upper spacecraft component support block 3. A vibration reduction and isolation device 2 is provided between the upper spacecraft component 1 and the lower spacecraft component 4. Four spacecraft transfer auxiliary arms 10 arranged in the circumferential direction are connected to the outer walls of both the upper spacecraft component 1 and the lower spacecraft component 4. The gravity of the upper spacecraft component 1 is G1, and the gravity of the lower spacecraft component is G2.

[0033] Specifically, such as Figure 1 and Figure 2 As shown, the suspension-supported two-stage composite on-orbit free boundary simulation method includes the following steps:

[0034] S1. The spacecraft is hoisted into place, and the lower component support block 5 of the spacecraft is installed. The lower surface of the lower component support block 5 is fixedly connected to the rigid foundation 7. At least three lower component support blocks 5 should be selected, and it is recommended to select four to eight. The entire spacecraft is hoisted onto the lower component support block 5.

[0035] S2. The limiting device is fixed in place, fixing the upper component limiting block 9 of the spacecraft to the rigid suspension frame 6, and limiting the spacecraft transfer auxiliary arm 10 to restrict the position of the upper component 1 of the spacecraft. There are four upper component limiting blocks 9 in total, distributed around the periphery of the upper component 1 of the spacecraft. The lower component limiting block 11 of the spacecraft is fixed to the rigid suspension frame 6, and limiting the spacecraft transfer auxiliary arm 10 to restrict the position of the lower component 4 of the spacecraft. There are four lower component limiting blocks 11 in total, distributed around the periphery of the lower component 4 of the spacecraft.

[0036] S3, G1, gravity of components on the spacecraft being suspended and unloaded;

[0037] S4, supporting the gravity of the unloaded spacecraft's lower components, G2;

[0038] S5. Conduct the test. Based on the limit and unloading status detected by the force sensor and displacement sensor, and after checking that everything is correct, install the modal test exciter; conduct micro-vibration test or other dynamic experiments; after the test is completed, organize and record the data.

[0039] Specifically, such as Figure 1 and Figure 2 As shown, step S3, which involves suspending and unloading the gravity G1 of a component on the spacecraft, includes the following steps:

[0040] S3.1 Assemble the elastic suspension springs 8. There are four sets of elastic suspension springs 8, which are arranged along the circumferential direction of the outer periphery of the spacecraft component 1.

[0041] S3.2. Lift the top of the elastic suspension spring 8 so that the tension of each spring reaches 0.225G1. At this time, ninety percent of the weight of the spacecraft component 1 has been unloaded.

[0042] S3.3 Remove the component support block 3 on the spacecraft. At this time, the remaining 10% of the gravity is borne by the component limiting block 9 on the spacecraft.

[0043] S3.4 Continue to lift the top of the elastic suspension spring 8 so that the tension of each spring reaches 0.25G1. At this time, the spacecraft component limiting block 9 no longer provides support force for the spacecraft component 1, the spacecraft transfer auxiliary arm 10 does not contact the spacecraft component limiting block 9, and the spacecraft component 1 is completely unloaded by gravity.

[0044] Specifically, such as Figure 1 and Figure 2 As shown, step S4, supporting the unloading of the spacecraft's lower component gravity G2, includes the following steps:

[0045] S4.1 Assemble the elastic support springs 12. There are eight sets of elastic support springs 12, which are arranged along the circumferential direction of the bottom of the lower component 4 of the spacecraft.

[0046] S4.2, Raise the bottom of the elastic support spring 12 so that the tension of each spring reaches 0.1125G2, at which point 90% of the weight of the lower component 4 of the spacecraft has been unloaded;

[0047] S4.3 Remove the spacecraft lower component support block 5. At this time, the spacecraft lower component limiting block 11 will bear the remaining 10% of the gravity.

[0048] S4.4 Continue to raise the bottom of the elastic support spring 12 so that the tension of each spring reaches 0.125G2. At this time, the spacecraft lower component limit block 11 no longer provides support for the spacecraft lower component 4, the spacecraft transfer auxiliary arm 10 does not contact the spacecraft lower component limit block 11, and the spacecraft lower component 4 is completely unloaded by gravity.

[0049] Thus, the gravity unloading of the entire spacecraft was completed by using a two-stage composite action of suspension and support, which approximately simulated the free boundary conditions of the spacecraft during its orbital flight.

[0050] This application achieves the simulation of the free boundary state of a two-section spacecraft in orbit through the combined action of suspension and support. By setting the stiffness and deformation of the elastic suspension spring 8 and the elastic support spring 12, the overall gravity of the spacecraft is unloaded, which meets the requirements for simulating the free boundary conditions when the spacecraft is conducting micro-vibration and other dynamic experiments on the ground. Through the coordinated use of springs, limit blocks and support blocks, the upper and lower components of the spacecraft are unloaded step by step while maintaining their relative positions.

[0051] The above description of the embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for simulating the free boundary of a two-stage composite suspension support system in orbit, characterized in that: It includes the upper spacecraft component (1), the lower spacecraft component (4), the rigid suspension frame (6), the rigid foundation (7), the elastic suspension spring (8), the upper spacecraft component limiting block (9), the spacecraft transfer auxiliary arm (10), the lower spacecraft component limiting block (11), and the elastic support spring (12). The lower component (4) of the spacecraft is connected to the rigid foundation (7) via the lower component support block (5), and the upper component (1) of the spacecraft is connected to the lower component (4) via the upper component support block (3). A vibration damping and isolation device (2) is provided between the upper component (1) and the lower component (4) of the spacecraft. Four spacecraft transfer auxiliary arms (10) arranged circumferentially are connected to the outer walls of both the upper component (1) and the lower component (4). The gravity of the upper component (1) is... G 1. The gravity of the lower component of the spacecraft is G 2.

2. The suspension-supported dual-stage composite on-orbit free boundary simulation method according to claim 1, characterized in that, Includes the following steps: S1. The spacecraft is hoisted into place; S2. The limiting device is fixed in place; S3, Suspension and unloading of spacecraft components (1) Gravity G 1; S4, Supporting the unloading of spacecraft lower components (4) gravity G 2; S5. Conduct experiments.

3. The suspension-supported dual-stage composite on-orbit free boundary simulation method according to claim 2, characterized in that, In step S3, the gravity of components on the spacecraft is suspended and unloaded. G 1. Includes the following steps: S3.1 Assemble the elastic suspension springs (8). There are four sets of elastic suspension springs (8) arranged along the circumferential direction of the outer periphery of the spacecraft component (1). S3.2, Raise the top of the elastic suspension spring (8) so that the tension of each spring reaches 0.

225. G 1. At this point, ninety percent of the gravity of the spacecraft's component (1) has been removed; S3.3 Remove the support block (3) on the spacecraft components. At this time, the remaining 10% of the gravity is borne by the limiting block (9) on the spacecraft components. S3.4 Continue to lift the top of the elastic suspension spring (8) so that the tension of each spring reaches 0.

25. G 1. At this time, the spacecraft component limiting block (9) no longer provides support for the spacecraft component (1), the spacecraft transfer auxiliary arm (10) does not contact the spacecraft component limiting block (9), and the spacecraft component (1) is completely unloaded by gravity.

4. The suspension-supported dual-stage composite on-orbit free boundary simulation method according to claim 2, characterized in that, In step S4, the gravity of the components under the support of the spacecraft is unloaded. G 2 includes the following steps: S4.1 Assemble the elastic support springs (12). Eight sets of elastic support springs (12) are set along the circumferential direction of the bottom of the lower component (4) of the spacecraft. S4.2, Raise the bottom of the elastic support spring (12) so that the tension of each spring reaches 0.1125. G 2. At this point, ninety percent of the gravity of the lower component (4) of the spacecraft has been unloaded; S4.3 Remove the spacecraft lower component support block (5), at which point the spacecraft lower component limiting block (11) will bear the remaining 10% of the gravity. S4.4 Continue to raise the bottom of the elastic support spring (12) so that the tension of each spring reaches 0.

125. G 2. At this time, the spacecraft lower component limiting block (11) no longer provides support for the spacecraft lower component (4), the spacecraft transfer auxiliary arm (10) does not contact the spacecraft lower component limiting block (11), and the spacecraft lower component (4) is completely unloaded by gravity.

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