Parallel type satellite-rocket interface vibration reduction method

Abstract

The invention discloses a parallel type satellite-rocket interface vibration reduction method which comprises the following steps: determining an allowable installation space of a vibration damper, and selecting the shape of the vibration damper; the performance of the shock absorber is determined according to the shape of the shock absorber and the external load environment condition; determining the mounting position of the shock absorber; and the installation number of the shock absorbers is determined. The problem that the satellite branch frequency is greatly reduced due to a traditional series vibration reduction scheme is solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace systems, and in particular relates to a parallel satellite-rocket interface vibration reduction method. Background Art

[0002] During the launch of a rocket, due to external aerodynamic forces and engine thrust, a severe vibration environment will be generated and transmitted to the satellite through the satellite-rocket interface, which can easily cause the failure of the satellite's structure and equipment. Due to the limitations of the structural form, the vibration environment will be significantly amplified, further increasing the environmental adaptability risk of the satellite. Therefore, it is necessary to take active control measures for the vibration environment at the satellite-rocket interface, reduce the vibration environment at the satellite-rocket interface, and eliminate the environmental adaptability risk of the satellite.

[0003] At present, most of the rocket-satellite interface vibration reduction technologies are based on the series structure scheme, such as Figure 1 As shown in the figure, satellites and rockets are usually connected via satellite adapters and transition brackets. The serial satellite-rocket vibration reduction technology generally connects a vibration reduction system in series between the transition bracket and the satellite adapter. This solution will cause a certain loss of stiffness, resulting in a decrease in the frequency of the transition bracket, satellite and satellite adapter assembly, affecting the safety of the dynamic clearance between the satellite and the fairing. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a parallel satellite-rocket interface vibration reduction method, and to solve the problem of excessive reduction in satellite branch frequency caused by traditional series vibration reduction schemes.

[0005] The object of the present invention is achieved through the following technical scheme: a parallel satellite-rocket interface vibration reduction method, comprising: determining the allowable installation space of the shock absorber and selecting the shape of the shock absorber; determining the shock absorber performance according to the shock absorber shape and external load environmental conditions; determining the shock absorber installation position; determining the number of shock absorbers to be installed.

[0006] In the above-mentioned parallel satellite-rocket interface vibration reduction method, the allowable installation space for the vibration absorber is determined including: the satellite bracket installation envelope space is occupied by the satellite protrusion, and the vibration absorber is only allowed to be installed on the transition bracket; since the transition bracket is a skin truss structure, the vibration absorber needs to be screwed to the ring frame during installation.

[0007] In the above-mentioned parallel satellite-rocket interface vibration reduction method, the shape of the vibration absorber is a cylindrical vibration absorber.

[0008] In the above-mentioned parallel satellite-rocket interface vibration reduction method, the external load environment condition is a low-frequency vibration external load environment condition of 5Hz to 100Hz.

[0009] In the above-mentioned parallel satellite-rocket interface vibration reduction method, the performance of the shock absorber is: the maximum damping force of the shock absorber is 9500N, the damping coefficient of the shock absorber is 700000Ns / m, and the telescopic stroke of the damping rod of the shock absorber is 10mm.

[0010] In the above-mentioned parallel satellite-rocket interface vibration reduction method, the vibration absorber is installed at the following position: the vibration absorber is installed between the two ring frames of the transition bracket.

[0011] In the above-mentioned parallel satellite-rocket interface vibration reduction method, determining the number of shock absorbers to be installed includes: determining the number of shock absorbers to be installed based on a preset carrying capacity and a preset vibration reduction requirement.

[0012] In the above-mentioned parallel satellite-rocket interface vibration reduction method, the preset vibration reduction requirements are: longitudinal vibration reduction efficiency is 35%-40%, and lateral vibration reduction efficiency is 20%-25%.

[0013] In the above-mentioned parallel satellite-rocket interface vibration reduction method, the number of vibration absorbers installed is 8.

[0014] In the above-mentioned parallel satellite-rocket interface vibration reduction method, 8 vibration absorbers are evenly distributed along the circumference of the ring frame.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] The present invention solves the problem of stiffness loss in traditional series vibration reduction solutions by installing vibration reduction dampers in parallel at transition brackets, and can achieve more than 30% attenuation of the satellite-rocket interface vibration environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0018] Figure 1 It is a schematic diagram of the principle of the tandem satellite-rocket vibration reduction technology in the prior art;

[0019] Figure 2 It is a schematic diagram of the principle of the parallel satellite-rocket vibration reduction technology provided by an embodiment of the present invention;

[0020] FIG3( a ) is a schematic diagram of a rectangular parallelepiped shock absorber provided in an embodiment of the present invention;

[0021] FIG3( b ) is a schematic diagram of a parallel vibration damper for a satellite adapter provided in an embodiment of the present invention;

[0022] FIG4( a ) is a schematic diagram of a cylindrical vibration damper provided in an embodiment of the present invention;

[0023] FIG. 4( b ) is a schematic diagram of a parallel vibration damper for a transition bracket provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0024] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to be able to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features described in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0025] This embodiment provides a parallel satellite-rocket interface vibration reduction method, the method comprising:

[0026] Determine the allowable installation space for the shock absorber and select the shape of the shock absorber;

[0027] Determine the performance of the shock absorber according to the shock absorber shape and external load environment conditions;

[0028] Determine the installation position of the shock absorber;

[0029] Determine the number of shock absorbers to be installed.

[0030] Determine the allowable installation space for the shock absorber including: the satellite bracket installation envelope space is occupied by the satellite protrusion, and the shock absorber is only allowed to be installed on the transition bracket; since the transition bracket is a skin truss structure, the shock absorber needs to be screwed to the ring frame during installation.

[0031] The shock absorber has a cylindrical shape.

[0032] The external load environment condition is a low-frequency vibration external load environment condition of 5Hz to 100Hz.

[0033] The performance of the shock absorber is as follows: the maximum damping force of the shock absorber is 9500N, the damping coefficient of the shock absorber is 700000Ns / m, and the telescopic stroke of the damping rod of the shock absorber is 10mm.

[0034] The installation position of the shock absorber is: install the shock absorber between the two ring frames of the transition bracket.

[0035] Determining the number of shock absorbers to be installed includes: determining the number of shock absorbers to be installed according to a preset carrying capacity and a preset vibration reduction requirement.

[0036] The preset vibration reduction requirements are: longitudinal vibration reduction efficiency is 35%-40%, and lateral vibration reduction efficiency is 20%-25%.

[0037] The number of vibration dampers installed is 8. The 8 vibration dampers are evenly distributed along the circumference of the ring frame.

[0038] The parallel satellite-rocket interface vibration reduction method does not change the satellite branch structure nor add a series vibration reduction system. It is generally achieved by installing vibration reducers in parallel on the transition bracket or satellite bracket, such as Figure 2 As shown, the problem of excessive reduction in satellite branch frequency caused by the traditional series vibration reduction solution is solved, ensuring efficient vibration reduction at the system resonance frequency while achieving integrated load-bearing and vibration reduction. The specific method is as follows:

[0039] Step 1: Determine the allowable installation space of the shock absorber and select the shape of the shock absorber;

[0040] According to the installation space allowed by the arrow body, a shock absorber shape that is easy to install is selected. Common shapes include rectangular parallelepiped and cylindrical shapes, as shown in Figures 3(a), 3(b), 4(a) and 4(b);

[0041] Step 2: Design the vibration damping parameters of the shock absorber according to the shock absorber shape and external load environment conditions to determine the shock absorber performance;

[0042] The vibration reduction of the satellite-rocket interface generally focuses on the vibration reduction effect in the low-frequency vibration environment of 5Hz to 100Hz. The vibration dampers currently used in the satellite-rocket interface generally include viscous dampers, magnetorheological dampers, electrorheological dampers and particle dampers. For viscous dampers, magnetorheological dampers and electrorheological dampers, it is necessary to carry out parameter optimization design of maximum damping force, damping coefficient and extension stroke of damping rod according to the external load environmental conditions. For particle dampers, it is necessary to carry out optimization design of particle material, size and filling rate, and finally determine the use parameters of various dampers in the low-frequency vibration environment of 5Hz to 100Hz.

[0043] Step 3: Carry out the optimal design of the shock absorber installation position and determine the shock absorber installation position;

[0044] Conduct dynamic characteristic analysis of the satellite, satellite adapter and transition bracket assembly to obtain the transfer characteristics of each section. Optimize the design of the shock absorber installation position based on the vibration characteristics of the assembly and determine the shock absorber installation position. Generally, the closer the shock absorber installation position is to the maximum vibration position of the satellite assembly, the better. If the shock absorber cannot be installed at the maximum vibration position of the assembly due to installation space limitations, other suitable locations can be selected for installation.

[0045] Step 4: Carry out optimization design of the number of shock absorbers to be installed and determine the number of shock absorbers to be installed.

[0046] According to the carrying capacity and vibration reduction requirements, carry out the optimization design of the number of shock absorbers to be installed and determine the number of shock absorbers to be installed;

[0047] Complete the production and assembly of the shock absorber: According to the shock absorber shape determined in step one, the shock absorber parameters determined in step two, the shock absorber installation position determined in step three, and the shock absorber installation direction determined in step four, complete the production and assembly of the shock absorber.

[0048] The parallel design embodiment using viscous damper for vibration reduction is as follows:

[0049] Step 1: Select the shape of the shock absorber: The installation envelope of the satellite bracket is occupied by the satellite protrusion, and the shock absorber is only allowed to be installed on the transition bracket. The transition bracket is a skin truss structure, and the shock absorber needs to be screwed to the ring frame when installed. Based on this, the cylindrical shock absorber is designed according to the ring frame spacing.

[0050] Step 2: Determine the performance of the shock absorber: According to the cylindrical shock absorber shape and the low-frequency vibration external load environmental conditions of 5Hz to 100Hz, the parameters of the shock absorber are designed. The shock absorber parameters are finally designed to have a maximum damping force of 9500N, a damping coefficient of 700000Ns / m, and a damping rod telescopic stroke of 10mm.

[0051] Step 3: Determine the installation position of the vibration damper: Carry out dynamic characteristic analysis of the satellite, satellite adapter and transition bracket assembly to obtain the transfer characteristics of each section. The closer to the satellite, the larger the vibration mode of the assembly, but limited by the requirement in step 1 that the vibration damper is only allowed to be installed on the transition bracket, the damper is installed between the two ring frames of the transition bracket.

[0052] Step 4. Determine the number of dampers to be installed: According to the carrying capacity and vibration reduction requirements, the number of shock absorbers to be installed is optimized. A single viscous damper weighs 4.75kg, and the total weight when 8 dampers are installed is 38kg. While meeting the carrying capacity requirements, the longitudinal vibration reduction efficiency reaches 37%, and the lateral vibration reduction efficiency reaches 23%, meeting the vibration reduction requirements.

[0053] In order not to affect the stiffness of the transition bracket, satellite and satellite adapter assembly, the present invention proposes a serial satellite-rocket interface vibration reduction method, such as Figure 2 As shown, a vibration absorber (damper) is installed on the transition bracket or the satellite bracket (in the present invention, the vibration absorber is installed on the transition bracket because there is not enough space on the satellite adapter), so as to solve the problem of excessive reduction in satellite branch frequency caused by the traditional series vibration reduction scheme.

[0054] This embodiment solves the problem of stiffness loss in traditional series vibration reduction solutions by installing vibration-reducing dampers in parallel at the transition bracket, and can achieve an attenuation of the satellite-rocket interface vibration environment of more than 30%.

[0055] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A parallel satellite-rocket interface vibration reduction method, characterized in that include: Determine the allowable installation space for the shock absorber and select the shape of the shock absorber; Determine the performance of the shock absorber according to the shock absorber shape and external load environment conditions; Determine the installation position of the shock absorber; Determine the number of shock absorbers to be installed.

2. The parallel satellite-rocket interface vibration reduction method according to claim 1, characterized in that: Determine the allowable installation space for the shock absorber including: The satellite bracket installation envelope space is occupied by the satellite protrusion, and the vibration damper is only allowed to be installed on the transition bracket; Since the transition bracket is a skin truss structure, the shock absorber needs to be screwed to the ring frame during installation.

3. The parallel satellite-rocket interface vibration reduction method according to claim 2, characterized in that: The shock absorber has a cylindrical shape.

4. The parallel satellite-rocket interface vibration reduction method according to claim 1, characterized in that: The external load environment condition is a low-frequency vibration external load environment condition of 5Hz to 100Hz.

5. The parallel satellite-rocket interface vibration reduction method according to claim 1, characterized in that: The performance of the shock absorber is as follows: the maximum damping force of the shock absorber is 9500N, the damping coefficient of the shock absorber is 700000Ns / m, and the telescopic stroke of the damping rod of the shock absorber is 10mm.

6. The parallel satellite-rocket interface vibration reduction method according to claim 1, characterized in that: The installation position of the shock absorber is: install the shock absorber between the two ring frames of the transition bracket.

7. The parallel satellite-rocket interface vibration reduction method according to claim 1, characterized in that: Determining the number of shock absorbers to be installed includes: determining the number of shock absorbers to be installed according to a preset carrying capacity and a preset vibration reduction requirement.

8. The parallel satellite-rocket interface vibration reduction method according to claim 7, characterized in that: The preset vibration reduction requirements are: longitudinal vibration reduction efficiency is 35%-40%, and lateral vibration reduction efficiency is 20%-25%.

9. The parallel satellite-rocket interface vibration reduction method according to claim 7, characterized in that: The number of shock absorbers installed is 8.

10. The parallel satellite-rocket interface vibration reduction method according to claim 9, characterized in that: The eight vibration dampers are evenly distributed along the circumference of the ring frame.

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