Integrated active and passive whole-satellite vibration isolation device

Abstract

The invention discloses an integrated active and passive whole-satellite vibration isolation device, belonging to the technical field of aerospace. A scheme 1 is characterized in that a plurality of actuator support spring leaves are all detachably connected with the lower end surface of a satellite; the plurality of actuator support spring leaves are all detachably connected with the upper end surface of an adapter; a plurality of actuators are all arranged in the adapter in a mode of being perpendicular to the bottom surface of the adapter; the upper end of each actuator is detachably connected with an extended end of one corresponding actuator support spring leaf; the lower end of each actuator is connected with one corresponding actuator support bracket; and a plurality of actuator support brackets are all arranged in the adapter and detachably connected with the adapter. A scheme 2 is different from the scheme 1 in that a plurality of satellite support spring leaves are additionally arranged, the plurality of satellite support spring leaves and the plurality of actuator support spring leaves are all arranged on the same circumference alternately and sequentially, and the plurality of satellite support spring leaves are all detachably connected with the lower end surface of the satellite. The integrated active and passive whole-satellite vibration isolation device can meet the requirement of carrying out vibration isolation design under the condition that a satellite-rocket interface is not changed.

Description

technical field [0001] The invention relates to a whole-satellite vibration isolation device, in particular to a whole-satellite vibration isolation device for isolating the vibration transmission between a carrier rocket and a spacecraft during the launch phase of a spacecraft, and belongs to the field of aerospace technology. Background technique [0002] During the launching process, the spacecraft has to bear the effects of various quasi-static loads and timely changing loads. These loads mainly include the noise directly acting on the fairing on the surface of the spacecraft and the noise, random vibration, and explosion shocks transmitted to the spacecraft through the star-rocket connection adapter. The vibration transmitted to the surface of the spacecraft through the star-rocket connection adapter mainly comes from the random excitation of noise, the thrust pulsation caused by the unstable combustion of the rocket engine, the unbalanced rotation of the rotating parts...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to propose an active-passive integrated whole-satellite vibration isolation device to solve the problem of large vibration of the spacecraft during launch, and to overcome the design difficulties caused by only taking vibration isolation measures for the relevant components inside the spacecraft in the traditional way, Disadvantages such as high cost, and the need to change the interface of the star and arrow to overcome the existing whole-satellite vibration isolation device, the additional mass is too large, and the reliability is low.

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