Spacecraft propellant management method

A management method and propellant technology, applied in jet propulsion devices, machines/engines, rocket engine devices, etc., can solve the problems of reducing the carrying capacity of the spacecraft and increasing the structural mass of the spacecraft, to meet the requirements of multiple starts, simplify the Control system design to ensure the effect of reliable work

A management method and propellant technology, applied in jet propulsion devices, machines/engines, rocket engine devices, etc., can solve the problems of reducing the carrying capacity of the spacecraft and increasing the structural mass of the spacecraft, to meet the requirements of multiple starts, simplify the Control system design to ensure the effect of reliable work

CN107327355AActive Publication Date: 2017-11-07BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Spacecraft propellant management method
  • Spacecraft propellant management method
  • Spacecraft propellant management method

Examples

Experimental program
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Embodiment 1

[0066] In this example, the spacecraft propellant selects unsymmetrical dimethylhydrazine and dinitrogen tetroxide, the storage tank 1 volume is 700L, the storage tank 1 height is 1300mm, and the starting basket device volume is 20L (outer frame 3 volume+exhaust pipe 4 Volume), the height of the exhaust pipe 4 is 150mm. Because parameters such as surface tension coefficient and density of unsymmetrical dimethyl hydrazine and dinitrogen tetroxide are different, the apertures of the first through holes 7 in the starter basket devices in the two kinds of propellant storage tanks are different, and the apertures of the second through holes 8 are also different. different.

[0067] In this example, during the first ignition of the main engine of the spacecraft, the axial overload of the spacecraft is 0.1g. Under this overload, the propellant at the top of the tank can theoretically move from the top of the tank to the bottom of the tank in 1.63s. , the propellant storage flow rate...

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Abstract

The invention relates to a spacecraft propellant management method. In the method, the idea that a starting basket device is arranged in a propellant storage box is proposed for the first time, the spacecraft repeated starting propellant management requirement is met through retention and refilling, the starting basket device is of a structural design comprising an outer frame and an exhaust pipe. A propellant is stored inside through the outer frame, gas in the outer frame is exhausted through the exhaust pipe, repeated filling of the propellant is achieved, and therefore the engine repeated starting requirement is met. The structural mode of the outer frame and the exhaust pipe is optimally designed. The method is applicable to repeated starting spacecraft propellant management in the space microgravity environment, it is ensured that liquid drained out of the storage box contains no gas, the problem that too many attitude-control propellant is consumed for deposition is avoided, and meanwhile the structural weight of the propellant is reduced.

Description

technical field [0001] The invention relates to a spacecraft propellant management method, in particular to a space vehicle that starts multiple times in space, and belongs to the technical field of propellant management. Background technique [0002] For launch vehicles, satellites and other spacecraft, it is necessary to complete orbit change, orbit adjustment or position maintenance, requiring multiple starts in a microgravity environment, and there are problems in the management of liquid propellants. Propellant management is a problem that must be considered when the spacecraft is in taxiing, cold separation and other weightless conditions. It mainly ensures the separation of gas and liquid in the storage tank, so that the exhaust of the storage tank can be carried out reliably and the propellant can sink to the bottom reliably, so as to prevent the storage tank from being supplied to the engine. Gas inclusions in the propellant. [0003] At present, launch vehicles an...

Claims

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Application Information

Patent Timeline
07 Nov 2017
Publication
CN107327355A
IPC
F02K9/56
CPC
F02K9/56
Inventors
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