Nitrogen cold gas micro propulsion device adopting ring storage tank

Abstract

The invention discloses a nitrogen cold gas micro propulsion device adopting a ring storage tank, comprising a propellant storage tank, a high-pressure charging valve, a high-pressure pressure reducer, a low-pressure pressure reducer, a high-pressure latching valve, a thruster, a high-pressure sensor and a filter. The micro propulsion device is used for attitude control on a micro satellite as well as maintenance and control on a track; nitrogen is used as a propellant, therefore, the nitrogen cold gas micro propulsion device has no toxicity and pollution; and the micro propulsion device has the advantages of simple structure, low quality, low power consumption and high reliability. The micro propulsion device is installed on an installation baffle, thereby being convenient to install andreplace; and the micro propulsion device has no excessive connection and interference with other parts of the satellite, thereby being convenient to replace and repair.

Description

technical field [0001] The invention belongs to the technical field of cold air micro-propulsion, and relates to a nitrogen-air-cooled micro-propulsion device suitable for micro-satellites, in particular to a nitrogen-air-cooled micro-propulsion device using a ring storage tank. Background technique [0002] The air-cooled micro-propulsion system refers to the cold-air propulsion system used for micro-satellites. Usually, satellites with a weight of 100kg to 500kg are called small satellites, satellites with a weight of 10kg to 100kg are called microsatellites, and satellites with a weight of 10kg or less are called nanosatellites. satellite. Satellites below 1kg are called pico-satellites. Microsatellites refer to satellites with a weight in the range of 10kg to 500kg. The main features of microsatellites are tight development schedule (short cycle), small shape, strong function and low cost. Over the past ten years, high-performance modern micro-satellites from various ...

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Problems solved by technology

Although the nozzle is light in weight, the weight of the whole system is moderate due to the need to equip high-pressure gas cylinders (storage tanks) and distribution delivery systems, and because a large number of gas cylinders are required to store the propellant (gas state), the system is in volume The utilization rate is not high. The output thrust range of a typical cold air propulsion system is 5mN to 250N. When the nozzle area ratio is 100, the specific impulse of nitrogen varies from 45s to 74s, depending on the thrust of the nozzle (thruster). size, because as the volume of the thruster decreases, the losses in the nozzle will increase

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