An axial vibration damping device for calming an on-orbit target
By designing an axial vibration damping device and utilizing a combination of spring stiffness and mass blocks, a two-degree-of-freedom undamped vibration model was constructed, solving the axial vibration problem of the target spacecraft, achieving vibration suppression and energy transfer, and improving the stability and accuracy of the spacecraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-08
- Publication Date
- 2026-07-10
AI Technical Summary
Existing technologies have failed to effectively suppress the periodic vibrations and energy transfer experienced by the target spacecraft along the axial direction, affecting the spacecraft's pointing accuracy and the performance of its internal instruments.
An axial vibration damping device for stabilizing on-orbit targets is adopted, comprising a structural frame assembly and a spring-mass assembly. By designing the parameters of the spring stiffness and the mass block, a two-degree-of-freedom undamped vibration model is constructed to achieve vibration suppression and energy transfer.
It effectively suppresses the axial vibration of the target spacecraft, reduces the impact of periodic interference on the spacecraft, and improves pointing accuracy and the stability of internal instruments.
Smart Images
Figure CN122359458A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of space robot research and engineering, specifically to an axial vibration reduction device for stabilizing on-orbit targets. Background Technology
[0002] When a servicing spacecraft performs an on-orbit capture mission, axial contact and collision between the capture mechanism and the target spacecraft are unavoidable, leading to undesirable periodic vibrations in the axial direction. Furthermore, the target spacecraft itself is constantly subjected to periodic excitations from loads such as the control moment gyroscope and reaction flywheel, which can impair its pointing accuracy and affect the performance of its internal precision instruments. However, current research typically focuses only on suppressing the disturbances of external excitations on the servicing spacecraft and its base, neglecting vibration reduction methods for the target spacecraft as the primary vibration system. Therefore, to ensure the safety of the target spacecraft and suppress the negative impact of axial periodic disturbances on its operation, an axial vibration reduction device for stabilizing the on-orbit target is proposed to reduce the disturbances caused by axial periodic disturbances, thereby achieving stable capture. Summary of the Invention
[0003] This invention addresses the challenge of a target spacecraft subjected to external axial periodic disturbance forces after capture. To solve the problem of the target spacecraft's own inability to suppress vibration and transfer energy, an axial vibration reduction device for stabilizing on-orbit targets is proposed.
[0004] To achieve the above objectives, the present invention adopts the following technical solution:
[0005] An axial vibration damping device for stabilizing an on-orbit target mainly includes a structural frame assembly and a spring-mass assembly.
[0006] The structural frame assembly mainly consists of a capture mechanism connecting bracket (201), a vibration damping device frame (202), slider one (301), slide rail one (302), slider two (303), slider three (304), slide rail two (305), and slider four (306). The spring mass assembly includes a mass block (204), spring two (203), and spring one (205).
[0007] Furthermore, slide rail one (302) and slide rail two (305) are respectively installed on the upper and lower inner sides of the vibration damping device frame (202). Slider one (301) and slider four (306) are respectively installed on the upper and lower outer sides of the capture mechanism connecting bracket (201), and are respectively connected to slide rail one (302) or slide rail two (305) as sliding pairs. Slider two (303) and slider three (304) are respectively installed on the upper and lower outer sides of the mass block (204), and are respectively connected to slide rail one (302) or slide rail two (305) as sliding pairs.
[0008] Furthermore, the axial vibration damping device (102) for stabilizing the on-orbit target is connected to the spacecraft base (101) or the capture mechanism (103) through the vibration damping device frame (202) or the capture mechanism connecting bracket (201), respectively. The target spacecraft (104), the spacecraft base (101) and the capture mechanism (103) are the external systems of the present invention.
[0009] Furthermore, the masses of spring 2 (203), spring 1 (205), slider 1 (301), slider 2 (303), slider 3 (304), and slider 4 (306) are ignored. After capture, the target spacecraft (104), capture mechanism (103), and capture mechanism connecting bracket (201) are considered as a whole, with a mass of m. t The mass of the mass block (204) is set as m. d The vibration damping device frame (202), slide rail one (302), slide rail two (305), and spacecraft base (101) are fixedly connected as a whole, with a mass of m. b Set the stiffness of spring 2 (203) to k2, and the stiffness of spring 1 (205) to k1. Target spacecraft (104) / m t The vibration displacement is x2, and the mass block is (204) / m. d The vibration displacement is x1.
[0010] Furthermore, assume that the axial harmonic disturbance force on the target spacecraft (104) is F = Asinωt.
[0011] Furthermore, when When the frequency ω of the external disturbance force approaches zero, the vibration displacement x2 of the target spacecraft (104) approaches zero, meaning the vibration of the target spacecraft is reduced. In summary, by comprehensively assessing the frequency of the external axial disturbance force in the mechanical environment of the target spacecraft in advance, and by rationally designing the stiffness of spring two (203) and spring one (205) as well as the mass of the mass block (204), the frequency of the disturbance force can be reduced. The vibration of the target spacecraft (104) in the vicinity is transferred to the mass block (204) by the vibration energy input by the external disturbance force.
[0012] The technical solution provided by this invention has the following characteristics compared with the prior art:
[0013] After the target is captured in orbit, traditional vibration reduction methods typically focus only on the disturbances caused by external excitations to the servicing spacecraft and its base, rarely considering reducing the vibration of the target spacecraft as a primary objective. Therefore, this invention addresses the situation where the target spacecraft is subjected to periodic axial disturbances by introducing a two-degree-of-freedom undamped vibration model, thereby achieving vibration suppression and energy transfer of the target spacecraft under axial harmonic disturbances after capture. Attached Figure Description
[0014] Figure 1 This is a schematic diagram of the overall three-dimensional structure of a specific embodiment of the present invention;
[0015] Figure 2 This is a three-dimensional structural schematic diagram of the axial vibration reduction device for stabilizing on-orbit targets according to the present invention.
[0016] Figure 3 This is a top view schematic diagram of the axial vibration reduction device for stabilizing on-orbit targets according to the present invention.
[0017] Figure 4 This is a schematic diagram of the equivalent mechanical principle of the present invention.
[0018] The labels in the attached diagram are explained as follows:
[0019] Spacecraft base (101), axial vibration damping device for stabilizing on-orbit targets (102), capture mechanism (103), target spacecraft (104), capture mechanism connecting bracket (201), vibration damping device frame (202), spring two (203), mass block (204), spring one (205), slider one (301), slide rail one (302), slider two (303), slider three (304), slide rail two (305), slider four (306). Detailed Implementation Plan
[0020] The following is in conjunction with the appendix Figures 1-4 The present invention will be further described as follows:
[0021] An axial vibration damping device for stabilizing an on-orbit target mainly includes a structural frame assembly and a spring-mass assembly.
[0022] The structural frame assembly mainly consists of a capture mechanism connecting bracket (201), a vibration damping device frame (202), slider one (301), slide rail one (302), slider two (303), slider three (304), slide rail two (305), and slider four (306). The spring mass assembly includes a mass block (204), spring two (203), and spring one (205).
[0023] Furthermore, slide rail one (302) and slide rail two (305) are respectively installed on the upper and lower inner sides of the vibration damping device frame (202). Slider one (301) and slider four (306) are respectively installed on the upper and lower outer sides of the capture mechanism connecting bracket (201), and are respectively connected to slide rail one (302) or slide rail two (305) as sliding pairs. Slider two (303) and slider three (304) are respectively installed on the upper and lower outer sides of the mass block (204), and are respectively connected to slide rail one (302) or slide rail two (305) as sliding pairs.
[0024] Furthermore, the axial vibration damping device (102) for stabilizing the on-orbit target is connected to the spacecraft base (101) or the capture mechanism (103) through the vibration damping device frame (202) or the capture mechanism connecting bracket (201), respectively. The target spacecraft (104), the spacecraft base (101) and the capture mechanism (103) are the external systems of the present invention.
[0025] Furthermore, since the masses of spring 1 (203), spring 2 (205), slider 1 (301), slider 2 (303), slider 3 (304), and slider 4 (306) are relatively small compared to other components, their masses are ignored. After capture, the target spacecraft (104), capture mechanism (103), and capture mechanism connecting bracket (201) are considered as a whole, with a mass of m. t The mass of the mass block (204) is set as m. d The vibration damping device frame (202), slide rail one (302), slide rail two (305), and spacecraft base (101) are fixedly connected as a whole, with a mass of m. b Set the stiffness of spring 2 (203) to k2, and the stiffness of spring 1 (205) to k1. Target spacecraft (104) / m t The vibration displacement is x2, and the mass block is (204) / m. d The vibration displacement is x1.
[0026] Furthermore, assume that the harmonic disturbance force experienced by the target spacecraft (104) is F = Asinωt.
[0027] Furthermore, assume m b >>m t And m b >>m d Therefore, the post-capture composite system containing the axial vibration damping device for stabilizing on-orbit targets described in this invention can be equivalent to, for example: Figure 4 The dynamics of the two-degree-of-freedom undamped forced vibration system shown is as follows: The dynamic equations of this system can be expressed as:
[0028] Furthermore, let its particular solution be: Furthermore, we can obtain a system of non-homogeneous equations concerning amplitudes A1 and A2: Solving this equation yields the expressions for amplitudes A1 and A2: Where: f(ω) 2 )=[(k1+k2)-m d ω 2 ](k2-m t ω 2 )-k2 2 .
[0029] Furthermore, when At that time, it can be obtained A2 = 0. Therefore: x2 = 0. Therefore, at this point, the target spacecraft has a velocity of (104) / m. t Although subjected to the disturbance force F=Asinωt, no vibration occurs, while the mass block (204) generates forced vibration with the same phase as the disturbance force. This is equivalent to applying the disturbance force to the mass block (204), while the target spacecraft (104) avoids external interference. In summary, by comprehensively assessing the frequency of the external axial disturbance force in the mechanical environment of the target spacecraft (104) in advance, and by rationally designing the stiffness of spring two (203) and spring one (205) as well as the mass block (204), the square root of the ratio of the sum of the stiffnesses of spring two (203) and spring one (205) to the mass block's mass can be made to approach the frequency of the external disturbance force. This reduces the frequency of the disturbance force. The vibration of the target spacecraft (104) in the vicinity is transferred to the mass block (204) by the vibration energy input by the external disturbance force.
Claims
1. An axial vibration damping device for stabilizing an on-orbit target, comprising a structural frame assembly and a spring-mass assembly, characterized in that: The structural frame assembly mainly consists of a capture mechanism connecting bracket, a vibration damping device frame, slider one, slide rail one, slider two, slider three, slide rail two, and slider four; the spring mass assembly includes a mass block, spring two, and spring one; slide rail one and slide rail two are respectively installed on the upper and lower inner sides of the vibration damping device frame; slider one and slider four are respectively installed on the upper and lower outer sides of the capture mechanism connecting bracket, and are respectively connected to slide rail one or slide rail two as sliding pairs; slider two and slider three are respectively installed on the upper and lower outer sides of the mass block, and are respectively connected to slide rail one or slide rail two as sliding pairs.
2. The axial vibration damping device for stabilizing an on-orbit target according to claim 1, characterized in that: By comprehensively assessing the frequency of the external axial periodic disturbance force in the mechanical environment of the target spacecraft in advance, and by rationally designing the stiffness of spring 2 and spring 1 as well as the mass of the mass block, the square root of the ratio of the sum of the stiffness of spring 2 and spring 1 to the mass of the mass block approaches the frequency of the external disturbance force. Under this condition, the axial vibration reduction device for stabilizing on-orbit targets can reduce the forced vibration amplitude of the target spacecraft under the action of external disturbance force and transfer the vibration energy input by the external disturbance force to the mass block.
3. The axial vibration damping device for stabilizing an on-orbit target according to claim 1, characterized in that: The axial vibration damping device for stabilizing the on-orbit target is connected to the external spacecraft base via a vibration damping device frame; the axial vibration damping device for stabilizing the on-orbit target is connected to the external capture mechanism via a capture mechanism connecting bracket.