Mechanism-type separation nut and joint unlocking mechanism of satellite and launch vehicle composed of mechanism-type separation nut

A separate nut and mechanism technology, which is applied in the aerospace field, can solve the problems of increased weight of power supply equipment, large satellite impact, and low reliability, and achieve the effects of avoiding superposition and amplification, small working impact, and high synchronization

Active Publication Date: 2019-01-18
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In summary, the point device based on pyrotechnic separation nut has a great impact on the impact of the satellite, and even affects the function of some instruments and equipment on the satellite.
[0004] Secondly, according to the load and specifications of the satellite-rocket separation surface, a single satellite-rocket separation surface generally requires 4, 6 or even more than 8 connection unlocking points. Only when all pyrotechnics are unlocked can the satellite be separated into orbit. The reliability model In order to be connected in series, the comprehensive unlocking reliability decreases significantly with the increase of the number of pyrotechnics, and the unlocking of all pyrotechnics at the same time puts forward higher requirements on the power supply equipment of the rocket, and leads to an increase in the weight of the power supply equipment, which responds to the carrying capacity.
[0005] In addition, the working method of the pyrotechnic separation nut is the detonation of the main charge to achieve unlocking. As a one-time use product, it can only be judged indirectly through the ignition test of other products of the same batch, the structure of the product itself, and the quality of the charge. It is no longer possible to verify the unlocking function of this product before flying
[0006] Finally, some satellite models have dual-star parallel launch, synchronously unlocking the launching requirements of orbiting accompanying flight, which leads to the addition of high synchronization requirements in the case of high requirements for reliability and power supply capacity of the launch mission. The pyrotechnic separation nuts are ignited independently, and the synchronization is difficult to meet the satellite unlocking accuracy requirements
[0007] In summary, there are more and more restrictions on the application of pyrotechnic separation nuts in the field of star-arrow multi-point connection unlocking, and there are disadvantages such as large impact, low reliability, high power supply requirements, undetectable and low synchronization.

Method used

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  • Mechanism-type separation nut and joint unlocking mechanism of satellite and launch vehicle composed of mechanism-type separation nut
  • Mechanism-type separation nut and joint unlocking mechanism of satellite and launch vehicle composed of mechanism-type separation nut

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Experimental program
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Embodiment

[0091] see figure 1 , the mechanism-type separation nut 1 of this embodiment includes the following components:

[0092] The central bearing rod 11 is a rod-shaped structure, and the upper end of the top is provided with an external hexagonal reaction moment loading interface; the middle section of the structure is a threaded section, which is connected to the satellite side structure through nuts; the lower section is an inner concave section, the upper side of the notch is a horizontal plane, and the lower side is The oblique cone surface has the function of guiding and positioning, and is used for the embedding of multi-lobes 12 to realize the limitation and connection;

[0093] Multi-petal 12, which is composed of four sub-petals cut by annular petals. The inner contour of the petals is consistent with the concave mating surface 1101 of the central bearing rod 11. The upper surface is a horizontal plane, and the lower surface is a conical surface. The structure is embedde...

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Abstract

The invention discloses a mechanism-type separation nut and a joint unlocking mechanism of a satellite and a launch vehicle composed of the mechanism-type separation nut. The joint unlocking mechanismof the satellite and the launch vehicle further comprises a multi-link transmission mechanism, Spring power and lock release, A mechanism-type separation nut is use for connecting satellite, and thatunlocking power source of the plurality of mechanism-type separation nut is provided by a remotely positioned spring power device, and the power is remotely transmitted by a multi-link transmission mechanism, and the locking release device locks the satellite-arrow connection unlocking mechanism before unlocking, and reliably releases the locking power at the unlocking time. The satellite-arrow connection unlocking mechanism of the invention has the functions of connection and unlocking, simultaneously has the characteristics of low impact, multi-point synchronous unlocking, main device can be detected and non-destructively and quickly installed and reset, small power supply demand and high reliability.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and relates to a connection unlocking scheme applied to satellites and launch vehicles, including a mechanism-type separation nut and a star-rocket connection unlocking mechanism composed of it, which is especially suitable for pairs using point-type connection unlocking devices. Shock-sensitive dual-satellite synchronization connection unlocked. Background technique [0002] At present, the point device based on pyrotechnic separation nut has the advantages of mature technology, compact structure and high reliability, and has been widely used in the connection unlocking between satellites and launch vehicles. With the development of the aerospace industry, satellites put forward higher and higher requirements for the unlocking impact of the connection point. The source of the unlocking impact mainly comes from two aspects: 1) the instantaneous deflagration work of the main charge of the pyrot...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/641B64G1/645
Inventor 李新宽张醒王金童秦震沈征辉李昊朱亮聪丁关锦冯淑红
Owner SHANGHAI AEROSPACE SYST ENG INST
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