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Deceleration control method for recoverable sounding rocket

A sounding rocket and deceleration control technology, which is applied to the system of space flight vehicle returning to the earth's atmosphere, space navigation equipment, space navigation aircraft and other directions, can solve the problems that cannot be changed with time, and no deceleration control method has been seen.

Active Publication Date: 2019-01-18
NAT SPACE SCI CENT CAS
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0004] According to the information currently available in China, the deployment angle of sounding rocket mechanical deployment deceleration technology is a fixed value, that is, it cannot change with time, and there is no related deceleration control method of mechanical deployment

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  • Deceleration control method for recoverable sounding rocket
  • Deceleration control method for recoverable sounding rocket
  • Deceleration control method for recoverable sounding rocket

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Embodiment Construction

[0047] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0048] Generally speaking, after re-entering the atmosphere, the aerodynamic reducer develops the resistance surface in an inflated manner, which is characterized by a faster speed and generates aerodynamic heat.

[0049] Therefore, the present invention proposes the following hypothesis: the peripheral gas is regarded as an ideal gas form, that is, the peripheral gas does not undergo ionization and chemical reactions, and the change of the flow field caused by structural deformation is not considered. When in the reentry process, the speed of the reducer is double the speed of sound compared with the speed of sound. Observe the aerodynamic state and evaluate the aerodynamic effect. When the effective resistance area of ​​the reducer remains unchanged, the analysis of the spread angle of the reducer can tell whether the flow field around the ...

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Abstract

The invention discloses a deceleration control method of a recoverable sounding rocket, The method comprises: (1) designing a deployment angle of a recoverable sounding rocket reducer varying with time below a first height, so that the speed of the sounding rocket when it descends to the second altitude range falls within the range of the set speed, the overload on the arrow body in the descendingprocess does not exceed the designated overload, and the structural stress of the reducer is always smaller than the allowable stress of the material in the unfolding process; Step 2) When the recoverable sounding rocket returns and when it reaches the first altitude, the recoverable sounding rocket reducer is deployed according to the deployment angle designed in Step 1). The deceleration control method of the invention ensures that the overload on the arrow body in the descending process does not exceed 10g all the time, and the load is not damaged due to excessive overload; the structuralstress of the reducer is always less than the allowable stress of the material during the unfolding process, and the reducer structure will not be damaged.

Description

technical field [0001] The invention relates to the field of sounding rockets, in particular to a deceleration control method for a returning sounding rocket. Background technique [0002] The flying height of the sounding rocket is between the air balloon and the satellite, and it is the only tool capable of in-situ detection at a height of 40 to 300 kilometers in space. Developed countries are very concerned about the research of sounding rockets, including the exploration of its technical updates. For example, the National Aeronautics and Space Administration (NASA) and the European Space Agency (ESA) both have a large number of research topics and experimental projects related to sounding rockets. In the research of the recovery system, in order to improve the success rate of the recovery task, it is necessary to base it on multiple tests. However, the test requires a lot of manpower and material resources, and the entire test cycle is also long. At this time, the addi...

Claims

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Application Information

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IPC IPC(8): B64G1/22B64G1/62
CPCB64G1/222B64G1/62
Inventor 杨剑宇杨萱
Owner NAT SPACE SCI CENT CAS
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