Integrated shock absorbing vibrating isolation device for stellite

A technology of vibration reduction and vibration isolation and satellite, which is applied in the directions of transportation and packaging, spring/shock absorber, vibration suppression adjustment, etc. It can solve the problem of not increasing the lateral swing of the satellite, different vibration isolation frequency requirements, and not allowing the lateral support of the satellite to be reduced Torsional rigidity and other issues to achieve the effect of reducing launch costs

A technology of vibration reduction and vibration isolation and satellite, which is applied in the directions of transportation and packaging, spring/shock absorber, vibration suppression adjustment, etc. It can solve the problem of not increasing the lateral swing of the satellite, different vibration isolation frequency requirements, and not allowing the lateral support of the satellite to be reduced Torsional rigidity and other issues to achieve the effect of reducing launch costs

CN1911734AInactive Publication Date: 2007-02-14郑钢铁 +3
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  • Integrated shock absorbing vibrating isolation device for stellite
  • Integrated shock absorbing vibrating isolation device for stellite
  • Integrated shock absorbing vibrating isolation device for stellite

Examples

Experimental program
Comparison scheme
Effect test

specific Embodiment approach 1

[0010] Specific implementation mode one: (see Figure 1 to Figure 8 ) This embodiment is composed of the connecting structural member of the satellite, the vibration damping and vibration isolation device and the connecting structural member of the carrier; the connecting structural member of the satellite is connected with the connecting structural member of the carrier through the vibration damping and vibration isolation device and the sliding structural member.

[0011] The invention decomposes the vibration from the launch vehicle into vibration components in a transverse plane perpendicular to the axis of the launch vehicle or longitudinal vibration components parallel to the axis of the launch vehicle, and performs vibration reduction and isolation respectively.

specific Embodiment approach 2

[0012] Specific implementation mode two: (see figure 1 ) This embodiment is made up of the connecting structural member 1 of the satellite, the longitudinal vibration-reducing vibration-isolating device 3 and the connecting-structural member-4 of the vehicle; 3 and the longitudinal sliding constraint matching surface 3-4; the bottom of the connecting structural member 1 of the satellite and the bottom of the connecting structural member 1 of the vehicle are connected through parallel longitudinal elastic elements 3-2 and longitudinal damping elements 3-3 Connection: The outer surface of the connecting structural member 1 of the satellite and the inner surface of the connecting structural member 4 of the vehicle are connected through the longitudinal sliding constraint mating surface 3-4.

[0013] The connecting structural member 1 of the satellite and the connecting structural member 4 of the vehicle together constitute a longitudinal sliding restraint pair, so that the connec...

specific Embodiment approach 3

[0014] Specific implementation mode three: (see figure 2 ) The present embodiment is made up of the connecting structural member 1 of the satellite, the connecting structural member 2 of the lateral vibration-reducing vibration-isolating device 2 and the carrier; 2. The lateral sliding restraint matching surface 2-3 and the lateral sliding structural member 2-4 are composed; the outer surface of the connecting structural member 1 of the satellite is fixedly connected with the inner side of the lateral sliding structural member 2-4, and the lateral sliding structural member 2-4 The inner surface of the connecting structural member 2 6 of the outer surface and the carrier is connected by multiple groups of parallel transverse elastic elements 2-1 and transverse damping elements 2-2, and the upper and lower sides of the lateral sliding structural member 2-4 and the carrier The inner surfaces of the connecting structural member 2 6 are connected through the lateral sliding constr...

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Abstract

The present invention is overall satellite vibration reducing isolator and aims at solving the problem that the overall satellite vibration reducing isolator has different longitudinal and transverse vibration isolating frequencies and the requirement of no reduction in transverse torsional rigidity of satellite support. The present invention resolves the vibration caused by the carrier rocket into one transverse vibration component and one longitudinal vibration component for subsequent separated vibration reduction and isolation. The overall satellite vibration reducing isolator includes satellite connect member, vibration reducing and isolating mechanism and carrier connecting member. The present invention makes it possible to use precise elements in space craft and lower satellite launching cost via reducing vibration of satellite.

Description

technical field [0001] The invention relates to a vibration damping and isolating device. Background technique [0002] The dynamic environment in which a satellite is launched is the harshest. Therefore, ensuring that the satellite can not be damaged in the dynamic environment of the launch process is the main research direction of the current satellite structural strength design. Usually, the strength of the satellite itself is improved, but the quality of the spacecraft is increased, which increases the launch cost, and the increased quality is useless in the normal operation of the spacecraft in orbit. The satellite adapter is the connection part between the satellite and the launch vehicle. The existing satellite adapter is a section of conical shell structure with bolt holes at both ends to connect with the satellite connection interface and the vehicle connection interface respectively. The overall satellite vibration reduction and isolation device is a modification...

Claims

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Application Information

Patent Timeline
14 Feb 2007
Publication
CN1911734A
IPC
B64G1/22
CPC
B64G1/641; F16F15/022
Inventors
郑钢铁; 刘丽坤