A multi-stage vibration isolation system for optical remote sensing satellite and its design method

Abstract

A multi-stage vibration isolation system for optical remote sensing satellites and a design method thereof. The present invention relates to the field of spacecraft vibration control, and specifically to the field of micro-vibration suppression of optical remote sensing satellites. In order to solve the problem of poor vibration isolation effect of existing micro-vibration suppression technology for optical remote sensing satellites, the present invention provides a multi-stage vibration isolation system for optical remote sensing satellites, the system comprising: a satellite platform, a flywheel vibration isolation device and a camera vibration isolation device; the satellite platform comprises: N structural members and N-1-level vibration isolation devices, the N structural members and the N-1-level vibration isolation devices are arranged alternately, adjacent structural members and vibration isolation devices are fixedly connected, and N is an integer greater than 2; the flywheel vibration isolation device is fixedly connected to the first structural member; the camera vibration isolation device is fixedly connected to the Nth structural member. The present invention has good application prospects for micro-vibration suppression of remote sensing satellites.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft vibration control, and in particular to the field of micro-vibration suppression of optical remote sensing satellites. Background Art

[0002] With the rapid development of optical remote sensing satellites and related technologies, the attitude accuracy, stability and resolution of satellite optical remote sensing cameras have been continuously improved, and the requirements for micro-vibration suppression of remote sensing satellites have become increasingly higher. During the on-orbit operation phase, the wide-band, small-amplitude disturbances generated by the on-board moving parts (such as flywheels, control moment gyroscopes, solar wing drive mechanisms, etc.) will cause the transfer function of the optical remote sensing camera to decrease, thereby causing a decrease in image quality. Among them, the flywheel is one of the main vibration sources causing disturbances to the satellite platform. Therefore, it is necessary to reduce the micro-vibration interference generated by the flywheel to ensure the control accuracy and imaging quality of the optical remote sensing camera.

[0003] At present, in terms of micro-vibration suppression, a two-stage vibration isolation method is mainly used to provide an ultra-quiet environment for optical remote sensing cameras. After the flywheel and the camera are installed on the whole satellite through the vibration isolation device, their frequencies may be coupled with the satellite platform structure frequency, resulting in a greatly reduced vibration isolation effect. Especially for high-resolution optical remote sensing cameras, the efficiency of medium and high frequency vibration isolation from the flywheel to the optical remote sensing camera is extremely high, and the two-stage vibration isolation system may not achieve the vibration isolation effect. There is an urgent need for a multi-stage vibration isolation system to focus on the vibration isolation of the medium and high frequency disturbances transmitted from the flywheel to the optical remote sensing camera. Summary of the invention

[0004] In order to solve the problem of poor vibration isolation effect of existing optical remote sensing satellite micro-vibration suppression technology, the present invention provides a multi-stage vibration isolation system for optical remote sensing satellites, the system comprising: a satellite platform, a flywheel vibration isolation device and a camera vibration isolation device;

[0005] The satellite platform comprises: N structural members and N-1 level vibration isolation devices, wherein the N structural members and the N-1 level vibration isolation devices are arranged alternately, and adjacent structural members and vibration isolation devices are fixedly connected, and N is an integer greater than 2;

[0006] The flywheel vibration isolation device is fixedly connected to the first structural member;

[0007] The camera vibration isolation device is fixedly connected to the Nth structural member.

[0008] Furthermore, the flywheel vibration isolation device, the camera vibration isolation device and the vibration isolation device are passive vibration isolation devices.

[0009] Furthermore, the N structural members are cabin plate structures composed of honeycomb sandwich panels.

[0010] Furthermore, the vibration isolation device adopts a viscoelastic damping material vibration isolator or a fluid damping vibration isolator.

[0011] A design method for a multi-stage vibration isolation system on an optical remote sensing satellite, wherein the multi-stage vibration isolation system is the multi-stage vibration isolation system described in the above method, the optical remote sensing satellite is a whole satellite equipped with the multi-stage vibration isolation system, the optical remote sensing satellite is provided with a flywheel and an optical remote sensing camera, the flywheel is fixedly connected to a flywheel vibration isolation device of the multi-stage vibration isolation system, and the optical remote sensing camera is fixedly connected to a camera vibration isolation device of the multi-stage vibration isolation system, and the method comprises the following steps:

[0012] Step 1: obtaining the perturbation frequency domain distribution characteristics of the flywheel in the optical remote sensing satellite, and using this as the input condition of the finite element model of the whole satellite;

[0013] Step 2: Establishing the whole satellite finite element model, the initial state of the whole satellite finite element model is set as follows: setting the flywheel vibration isolation device and the camera vibration isolation device to a vibration isolation state, and setting the remaining vibration isolation devices to a rigid body state;

[0014] Step 3: Calling finite element software to calculate and optimize the whole satellite finite element model;

[0015] Step 4: For the whole satellite finite element model described in step 2, obtain the vibration magnitude transmitted from the flywheel to the optical remote sensing camera, and determine whether the vibration magnitude meets the index requirements;

[0016] If it is satisfied, the N value of the multi-stage vibration isolation system is i, the initial value of i is 1, and the design of the multi-stage vibration isolation system is completed;

[0017] If not satisfied, proceed to step 5;

[0018] Step 5: Start the i-th level vibration isolation device, so that the i-th level vibration isolation device is no longer a rigid body, set the design variables of the vibration isolation device of this level, and at the same time, i is incremented by 1, and return to execute step 3.

[0019] Furthermore, the acquisition of the flywheel disturbance frequency domain distribution characteristics is achieved through a KistlerTable measurement system.

[0020] Furthermore, the model of the KistlerTable measurement system is HR-FP3406.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. Based on the two-stage vibration isolation from the vibration source flywheel to the satellite platform and then to the optical remote sensing camera, the present invention adds a preset multi-stage vibration isolation device inside the satellite platform in the initial design stage, so as to avoid the subsequent change of the satellite platform design based on the strict micro-vibration suppression requirements, thereby affecting the satellite envelope, weight and other satellite indicators, and improve the iteration efficiency in the satellite development process;

[0023] 2. The present invention uses the flywheel disturbance characteristics as input and combines the vibration magnitude index requirements of the optical remote sensing camera to start the internal vibration isolation device of the satellite platform step by step, conducts large system micro-vibration simulation analysis, and comprehensively considers all aspects of the micro-vibration influence, effectively avoiding the loss of vibration isolation function due to coupling resonance between the vibration source flywheel, the optical remote sensing camera and the satellite structure, and realizes efficient isolation of the medium and high frequency disturbances transmitted to the optical remote sensing camera by the flywheel. The design method is universal and can meet the micro-vibration suppression requirements of different optical remote sensing cameras;

[0024] 3. The present invention arranges the flywheel and the optical remote sensing camera at both ends of the system through layout design. The interfaces of the components of the satellite platform are clear, which greatly extends the transmission path of the flywheel disturbance, increases the transmission links, increases the transmission interfaces, accelerates the attenuation of medium and high frequency vibrations, and greatly reduces the medium and high frequency disturbances transmitted to the optical remote sensing camera. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic structural diagram of a multi-stage vibration isolation system for an optical remote sensing satellite according to the first embodiment;

[0026] Figure 2 A flow chart of a method for designing a multi-stage vibration isolation system for an optical remote sensing satellite as described in Embodiment 5.

[0027] Figure numerals: 1. Satellite platform; 2. Flywheel; 3. Optical remote sensing camera; 4. Flywheel vibration isolation device; 5. Camera vibration isolation device; 101. Structural member; 1001. Vibration isolation device. DETAILED DESCRIPTION

[0028] Implementation method 1: Combination Figure 1 To illustrate this embodiment, a multi-stage vibration isolation system for an optical remote sensing satellite is provided, the system comprising: a satellite platform 1, a flywheel vibration isolation device 4 and a camera vibration isolation device 5;

[0029] The satellite platform 1 comprises: N structural members 101 and N-1 level vibration isolation devices 1001, wherein the N structural members 101 and the N-1 level vibration isolation devices 1001 are arranged alternately, and adjacent structural members 101 and vibration isolation devices 1001 are fixedly connected, and N is an integer greater than 2;

[0030] The flywheel vibration isolation device 4 is fixedly connected to the first structural member 101;

[0031] The camera vibration isolation device 5 is fixedly connected to the Nth structural member 101 .

[0032] Figure 1The schematic diagram of the structure of the present embodiment shows that the satellite platform comprises N structural members 101, and a set of vibration isolation devices 1001 is preset between adjacent structural members 101, so as to avoid the subsequent change of the satellite platform design based on more stringent micro-vibration suppression requirements, thereby affecting the whole satellite indicators such as the satellite envelope and weight, thereby improving the iteration efficiency in the satellite development process; the satellite platform includes a total of N-1 levels of vibration isolation devices 1001, and the vibration isolation devices 1001 inside the satellite platform are started step by step according to the needs until the requirements are met, thereby realizing efficient isolation of the medium and high frequency disturbances transmitted to the optical remote sensing camera by the flywheel.

[0033] Implementation method 2: This implementation method further limits the multi-stage vibration isolation system for an optical remote sensing satellite described in implementation method 1, and the flywheel vibration isolation device 4, the camera vibration isolation device 5 and the vibration isolation device 1001 are all passive vibration isolation devices.

[0034] The vibration isolation device 1001 is preferably a metal rubber or silicon rubber vibration isolation device with a simple structure and reliable system. A passive vibration isolation device is a vibration isolation device that does not require external energy input, and it achieves vibration isolation and vibration reduction through structural design and material selection.

[0035] Implementation method three: This implementation method further limits the multi-stage vibration isolation system for an optical remote sensing satellite described in implementation method one. In this implementation method, the N structural members 101 are all cabin plate structures composed of honeycomb sandwich panels.

[0036] The cabin structure of the honeycomb sandwich panel is composed of multiple honeycomb sandwich panels. This structure has the characteristics of light weight, high strength and good rigidity. The honeycomb core material of the honeycomb sandwich panel can effectively disperse and absorb impact force and improve the impact resistance of the structure. At the same time, the panel of the honeycomb sandwich panel can be selected from different materials as needed to meet different requirements, such as carbon fiber panels for light weight and high strength, and aluminum panels for high thermal conductivity.

[0037] Embodiment 4: This embodiment further limits the multi-stage vibration isolation system for an optical remote sensing satellite described in Embodiment 1, and the vibration isolation device 1001 is a viscoelastic damping material isolator or a fluid damping isolator.

[0038] Viscoelastic damping material isolators utilize the fact that when viscoelastic damping materials are subjected to alternating stress, the friction between internal molecules converts mechanical energy into heat energy and dissipates it, thereby exerting damping characteristics. It mainly adjusts the local stiffness of the satellite, adjusts the system damping, and improves the vibration isolation efficiency through the high-energy-consuming structure formed by the function of metal materials.

[0039] Fluid damping vibration isolator is a device that uses the viscous damping characteristics of fluid to achieve vibration isolation. By adjusting the fluid viscosity, flow area, fluid pressure and other parameters of the vibration isolator, the damping and stiffness characteristics of the damper can be changed, and the characteristics of large damping at resonance and small damping at high frequency can be used to simultaneously improve the vibration isolation efficiency in the resonance amplification area and high frequency area.

[0040] Implementation method five: combining Figure 2 This embodiment is described. A design method for a multi-stage vibration isolation system on an optical remote sensing satellite is provided. The multi-stage vibration isolation system is the multi-stage vibration isolation system described in any one of the first to fourth embodiments. The optical remote sensing satellite is a whole satellite equipped with the multi-stage vibration isolation system. A flywheel 2 and an optical remote sensing camera 3 are provided on the optical remote sensing satellite. The flywheel 2 is fixedly connected to a flywheel vibration isolation device 4 of the multi-stage vibration isolation system. The optical remote sensing camera 3 is fixedly connected to a camera vibration isolation device 5 of the multi-stage vibration isolation system. The method comprises the following steps:

[0041] Step 1: obtaining the perturbation frequency domain distribution characteristics of the flywheel 2 in the optical remote sensing satellite, and using this as the input condition of the finite element model of the whole satellite;

[0042] Step 2: Establish the whole satellite finite element model. The initial state of the whole satellite finite element model is set as follows: the flywheel vibration isolation device 4 and the camera vibration isolation device 5 are set to the vibration isolation state, and the remaining vibration isolation devices 1001 are set to the rigid body state;

[0043] Step 3: Calling finite element software to calculate and optimize the whole satellite finite element model;

[0044] Step 4: For the whole satellite finite element model described in step 2, obtain the vibration magnitude transmitted from the flywheel 2 to the optical remote sensing camera, and determine whether the vibration magnitude meets the index requirements.

[0045] If it is satisfied, the N value of the multi-stage vibration isolation system is i, the initial value of i is 1, and the design of the multi-stage vibration isolation system is completed;

[0046] If not satisfied, proceed to step 5;

[0047] Step 5: Start the i-th level vibration isolation device 1001, so that the i-th level vibration isolation device 1001 is no longer a rigid body, set the design variables of the vibration isolation device 1001 of this level, and at the same time, i is incremented by 1, and return to execute step 3.

[0048] Figure 2 A schematic diagram of the process of this embodiment is shown.

[0049] Embodiment 6: This embodiment further limits the design method of a multi-stage vibration isolation system on an optical remote sensing satellite described in embodiment 5, and the acquisition of the frequency domain distribution characteristics of the flywheel disturbance is achieved by a KistlerTable measurement system.

[0050] The KistlerTable measurement system described in this embodiment is implemented using a test system model HR-FP3406.

Claims

1. A design method for a multi-stage vibration isolation system on an optical remote sensing satellite, characterized in that: The multi-stage vibration isolation system comprises: a satellite platform (1), a flywheel vibration isolation device (4) and a camera vibration isolation device (5); The satellite platform (1) comprises: N structural members (101) and N-1 level vibration isolation devices (1001), wherein the N structural members (101) and the N-1 level vibration isolation devices (1001) are arranged alternately, and adjacent structural members (101) and vibration isolation devices (1001) are fixedly connected, and N is an integer greater than 2; The flywheel vibration isolation device (4) is fixedly connected to the first structural member (101); The camera vibration isolation device (5) is fixedly connected to the Nth structural member (101); The optical remote sensing satellite is a whole satellite equipped with the multi-stage vibration isolation system. A flywheel (2) and an optical remote sensing camera (3) are arranged on the optical remote sensing satellite. The flywheel (2) is fixedly connected to a flywheel vibration isolation device (4) of the multi-stage vibration isolation system. The optical remote sensing camera (3) is fixedly connected to a camera vibration isolation device (5) of the multi-stage vibration isolation system. The method comprises the following steps: Step 1: obtaining the perturbation frequency domain distribution characteristics of the flywheel (2) in the optical remote sensing satellite, and using this as an input condition for the finite element model of the entire satellite; Step 2: Establishing the whole-satellite finite element model, wherein the initial state of the whole-satellite finite element model is set as follows: setting the flywheel vibration isolation device (4) and the camera vibration isolation device (5) to a vibration isolation state, and setting the remaining vibration isolation devices (1001) to a rigid body state; Step 3: Calling finite element software to calculate and optimize the whole satellite finite element model; Step 4: for the whole satellite finite element model in step 2, obtain the vibration magnitude transmitted from the flywheel (2) to the optical remote sensing camera, and determine whether the vibration magnitude meets the index requirements; If it is satisfied, the N value of the multi-stage vibration isolation system is i, the initial value of i is 1, and the design of the multi-stage vibration isolation system is completed; If not satisfied, proceed to step 5; Step 5: Start the i-th level vibration isolation device (1001), so that the i-th level vibration isolation device (1001) is no longer a rigid body, set the design variables of the i-th level vibration isolation device (1001), and at the same time, i is incremented by 1, and return to execute step 3.

2. The design method of a multi-stage vibration isolation system on an optical remote sensing satellite according to claim 1, characterized in that: The flywheel vibration isolation device (4), the camera vibration isolation device (5) and the N-1 level vibration isolation device (1001) are all passive vibration isolation devices.

3. The design method of a multi-stage vibration isolation system on an optical remote sensing satellite according to claim 1, characterized in that: The N structural members (101) are all cabin plate structures composed of honeycomb sandwich panels.

4. The design method of a multi-stage vibration isolation system on an optical remote sensing satellite according to claim 1, characterized in that: The vibration isolation device (1001) adopts a viscoelastic damping material vibration isolator or a fluid damping vibration isolator.

5. The design method of a multi-stage vibration isolation system on an optical remote sensing satellite according to claim 1, characterized in that: The acquisition of the frequency domain distribution characteristics of the flywheel (2) disturbance is achieved by using a KistlerTable measurement system.

6. The method for designing a multi-stage vibration isolation system on an optical remote sensing satellite according to claim 5, characterized in that: The model of the KistlerTable measurement system is HR-FP3406.

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