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Optimized configuration method for reentry and return spacecraft propulsion system

A technology of propulsion system and optimized configuration, which is applied to the propulsion system device of space navigation aircraft, space navigation aircraft, and aircraft, etc., can solve the problems of large volume, many redundancy, and difficulty in meeting the volume, space and weight of returning small satellites.

Active Publication Date: 2017-05-10
BEIJING INST OF ELECTRONICS SYST ENG
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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for optimizing the configuration of the propulsion system of a re-entry and return spacecraft, which solves the problems of the previous configuration methods, which have more redundancy, larger volume, higher weight and complex system, and it is difficult to meet the volume space and weight constraints of returnable small satellites. limit problem

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  • Optimized configuration method for reentry and return spacecraft propulsion system
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  • Optimized configuration method for reentry and return spacecraft propulsion system

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Embodiment Construction

[0059] The specific steps of a reentry and return spacecraft propulsion system optimization configuration method are as follows:

[0060] Selection of the type of propulsion system, propellant and pressurized gas in the first step

[0061] For returnable small satellites, considering that the specific impulse requirements of small satellites are not strong and the size and space are tight, a single-component liquid engine is used. Considering comprehensive performance and maturity, the propellant is DT-3, and the pressurized gas is helium.

[0062] The second step is to determine the effective propellant weight

[0063] According to the total weight M of the small satellites provided by the whole, considering the flight orbit in orbit, the gravitational constant of the earth is μ, the earth center distance is r, and the semi-major axis is a, according to formula (1) and formula (2), determine the de-orbit braking Velocity V of the front and rear tracks at the off-track point ...

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Abstract

The invention discloses an optimized configuration method for reentry and return spacecraft propulsion system, which solves a problem that a conventional configuration method is difficult to meet the configuration quality of the small-scale return spacecraft power system configuration. Based on a task analysis, in order to adapt to the characteristics of the small return spacecraft, a type of a propulsion system and a propellant is selected reasonably, a effective propellant weight is calculated, a selection of extrusion gas type is optimized, a rail control engine and a attitude control engine thrust and a number of that is preliminary determined by further analyses, the attitude control engine thrust and cylinder tank layout is determined. According to the calculated control capacity to optimize the attitude control engine thrust until the control requirements to meet the optimal system to achieve optimal configuration.

Description

technical field [0001] The invention relates to a method for optimal configuration of a propulsion system, in particular to a method for optimal configuration of a propulsion system for a reentry and return spacecraft. Background technique [0002] With the development of my country's aerospace technology, spacecraft can be divided into on-orbit spacecraft and return spacecraft according to different applications. Among them, the Shenzhou series spacecraft and returnable satellites belong to this type. The Shenzhou spacecraft is composed of three cabins: the propulsion module, the return module and the orbit module. The propulsion subsystems are respectively installed in three different compartments to achieve different functional requirements. Among them, the propulsion module system mainly realizes the momentum of orbit change maneuver, orbit maintenance, attitude stability and attitude adjustment during on-orbit flight. The return module system provides attitude contro...

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Application Information

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IPC IPC(8): B64G1/40
CPCB64G1/401
Inventor 穆育强和宇硕付仕明石凯宇晁嫣萌刘飞刘昕
Owner BEIJING INST OF ELECTRONICS SYST ENG
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