Micro liquid fuel propulsion system used in micro-nano satellite

A micro-liquid, micro-nano satellite technology, applied in the field of satellite propulsion systems, to achieve the effects of light weight, low energy consumption and small size

Inactive Publication Date: 2009-06-03
GUANGZHOU INST OF ENERGY CONVERSION - CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The liquefied gas propulsion system has the advantages of simple structure, etc., but with liquefied gas as the propellant itself, it cannot have high chemical energy like single-co

Method used

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  • Micro liquid fuel propulsion system used in micro-nano satellite
  • Micro liquid fuel propulsion system used in micro-nano satellite

Examples

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[0021] Examples:

[0022] See figure 1 As shown, the liquid fuel micro propulsion system of the present invention mainly includes: a pressurized gas generator 1, a micro thruster 12, a fuel tank 4 that provides liquid fuel for the micro thruster 12, and the pressurized gas generator 1 is used for fuel The storage tank 4 is inflated and pressurized; the fuel storage tank 4 is separated by a diaphragm 5 into a liquid storage portion 42 for storing liquid fuel, and a gas storage portion 41 that communicates with the pressurized gas generator 1 through a gas pipeline 13 to reduce The amount of medicine in the pressurized gas generator is pre-filled with carbon dioxide gas in the gas storage part 41 of the fuel storage tank 4. The function of the diaphragm 5 is to separate the liquid fuel from the pressurized gas, which can make the liquid in the weightless state of space. Without entrained air bubbles, a pressure sensor 2 and a gas addition / discharge valve 3 are installed at both end...

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Abstract

The invention discloses a micro liquid fuel propulsion system used in a micro-nano satellite. The micro liquid fuel propulsion system comprises a pressurized gas generator, a micro propeller and a fuel storage tank for supplying liquid fuel to the micro propeller, the pressurized gas generator is used for inflating and pressurizing the fuel storage tank; the inside of the fuel storage tank is comparted by a diaphragm into a liquid storage part for storing the liquid fuel and a gas storage part which is communicated with the pressurized gas generator by a gas transmission pipeline, and two ends of the gas transmission pipeline are provided with a pressure sensor and a gas charge-discharge valve respectively; the liquid storage part is communicated with the micro propeller by a liquid transmission pipeline, and two ends of the liquid transmission pipeline near the liquid storage part are provided with a liquid fuel charge-discharge valve and a safety valve respectively; and the liquid transmission pipeline is further sequentially provided with a diaphragm valve, a filter and an solenoid valve. The micro liquid fuel propulsion system avoids the disadvantage of a clumsy structure of a high pressure cylinder which is used in the traditional liquid fuel satellite propulsion system for pressurizing the fuel, and can meet the requirements of the micro-nano satellite for small size, light weight and low energy consumption.

Description

technical field [0001] The invention relates to a satellite propulsion system, in particular to a micro liquid fuel propulsion system suitable for micro-nano satellites. Background technique [0002] Microsatellites have the advantages of small size, light weight, high technical content, short development period, and low development cost (tens of millions of RMB), and are a new hot spot in the development of space technology in recent years. Multiple micro-satellites can form formation flying satellites, which have a wide range of application values ​​in earth observation, stereoscopic imaging, precise positioning, atmospheric detection, astronomical observation and geophysical detection. Microsatellites can also serve as accompanying satellites, flying around space stations or other space vehicles, and providing observation and detection services. These tiny satellites all need to have good attitude control and orbit adjustment capabilities. During the development of smal...

Claims

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Application Information

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IPC IPC(8): B64G1/40F02K9/42
Inventor 岑继文徐进良
Owner GUANGZHOU INST OF ENERGY CONVERSION - CHINESE ACAD OF SCI
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