Orbit deploying device for cubic micro-nano satellite
A micro-nano satellite and cube technology, applied in the aerospace field, can solve the problems of difficult assembly, poor bearing capacity, easy deformation, etc., and achieve the effects of preventing satellite oscillation, good vibration reduction effect and light weight
Pending Publication Date: 2021-11-26
CHANGGUANG SATELLITE TECH CO LTD
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Problems solved by technology
[0005] The purpose of the present invention is to propose an orbit deployer for cube micro-nano satellites, which solves the problems of poor carrying capacity, easy deformation, difficult assembly, uncontrollable distance tolerance between orbits and vibration conditions in the prior art. Problem with satellites oscillating in the separation mechanism causing damage
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[0043] Embodiments of the present invention will be further described below in conjunction with the accompanying drawings.
[0044] See attached figure 1 - attached Figure 8 , an orbit deployer for cube micro-nano-satellites of the present invention includes a cabin body 13 and an ejection mechanism 16 arranged in the cabin body 13;
[0045]The cabin body 13 at least includes a hatch door 1306 that is arranged on one end of the cabin body 13 and is rotatably connected to the cabin body 13, and the other side of the hatch door 1306 is a free end; the hatch door 1306 is closed relative to the cabin body 13 , locked by closing the locking mechanism 14, when the hatch door 1306 is opened relative to the cabin body 13, it is locked by the in-position locking mechanism 15, and the inner surface of the hatch door 1306 is away from the side that is rotationally connected with the cabin body 13, up and down respectively A wedge block 1307 is provided, and the two wedge blocks 1307 c...
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The invention discloses an orbit deploying device for a cubic micro-nano satellite, belongs to the technical field of aerospace, and aims at solving the problems that in the prior art, the bearing capacity is poor, deformation is prone to occurring, the assembly difficulty is large, the distance tolerance between orbits cannot be controlled, and the satellite is damaged due to oscillation in a separation mechanism under the vibration working condition. The device comprises a cabin body and an ejection mechanism arranged in the cabin body; the cabin body at least comprises a cabin door which is arranged at one end of the cabin body and rotationally connected with the cabin body, the cabin door is locked through a closing locking mechanism when being closed relative to the cabin body and is locked through an in-place locking mechanism when being opened, and a wedge-shaped block is arranged on the upper portion and the lower portion of the side, away from the side rotationally connected with the cabin body, of the inner surface of the cabin door respectively; the ejection mechanism comprises a pushing plate in sliding fit with the cabin body and a cylindrical spiral spring arranged between the pushing plate and the other end face of the cabin body, wedge-shaped faces are arranged at the three corners of the inner surface of the pushing plate, and the wedge-shaped faces are matched with wedge-shaped blocks on the cabin door to press the cubesat on the bottom face and the side face of the cabin body.
Description
technical field [0001] The invention belongs to the field of aerospace technology, and in particular relates to an orbit deployer for cube micro-nano satellites. Background technique [0002] The orbit deployer is one of the star-rocket separation mechanisms, mainly used for the separation of the star and rocket of the cube star. The size of the cube star is 1U~16U (1U is a standard unit, the size is 100mm×100mm×100mm, and the weight is about 1kg) , CubeSats at home and abroad are mainly 1U ~ 6U, 12U and 16U cubesats are relatively rare. For the satellite-rocket separation mechanism of cube satellites, there are mature standard products abroad, but they are expensive, the quality of the separation mechanism itself is relatively large, and it can only adapt to standard-type cube satellites. For some convex satellites equipped with cameras or antennas For cubesats with larger envelopes, standard products cannot meet their needs. [0003] The Chinese patent publication number...
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IPC IPC(8): B64G1/64
CPCB64G1/641
Inventor 李佳乐赵相禹张道威谷松臧宏达赵春娟程浩
Owner CHANGGUANG SATELLITE TECH CO LTD