Refilling gas storage type solid propellant power device

A solid propellant and power device technology, applied in jet propulsion devices, rocket engine devices, machines/engines, etc., can solve problems such as separation difficulties, achieve simple ignition methods, save structural materials, and have low strength design requirements.

Inactive Publication Date: 2019-09-03
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It is very difficult to separate the two processes by conventional means

Method used

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  • Refilling gas storage type solid propellant power device
  • Refilling gas storage type solid propellant power device
  • Refilling gas storage type solid propellant power device

Examples

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Embodiment Construction

[0029] The idea, specific structure and technical effects of the present invention will be further described below in conjunction with the accompanying drawings and embodiments, so as to understand the purpose, features and effects of the present invention.

[0030] Such as figure 1 As shown, a reloaded gas-storage solid rocket motor includes: charge storage chamber rotating motor 1, first charge push rod 2, charge storage chamber 3, second charge push rod 4, pulse charge 5. Main charge 6, charge loader 7, residual gas release device 8, gas storage chamber 9, pressure measurement and control device 10, igniter 11, nozzle seal 12, valve control nozzle 13. The remaining gas release device 8 is connected to the charge loader 7 through a pipeline, the opening at the front head of the gas storage chamber 9 is connected to the charge loader 7 to form a closed space, and the tail is connected to the controllable nozzle 13 . The main charge 6 is designed as an internal combustion tub...

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Abstract

The invention relates to a refilling gas storage type solid propellant power device, and belongs to the technical field of solid rocket engines and solid fuel gas generators. The refilling gas storagetype solid propellant power device adopts the following technical approaches that firstly, pulse pressurization is adopted, wherein multiple stages of pulse explosive columns are used for continuously filling to achieve combustion, and the combustion process is not required to be stopped; and secondly, a gas storage link is added, wherein a charge combustion process and a spray pipe exhaust working process are separated, and are independent respectively. Charge combustion is only used for pressurizing a fuel gas storage box without simultaneously exhausting gas, and exhaust working enables aworking medium and energy of the refilling gas storage type solid propellant power device to be from the fuel gas storage tank, and at the moment, explosives are not required to be charged for simultaneous combustion. According to the refilling gas storage type solid propellant power device, a traditional combustion-release process is changed into combustion-gas storage-release process so that theproblem caused by the fact that the solid propellant combustion process is difficult to interrupt can be well solved; and according to the refilling gas storage type solid propellant power device, two technical approaches of gas storage link and pulse pressurization are combined, so that active startup and shutdown and multiple times of start of the solid propellant power device are truly realized.

Description

technical field [0001] The invention relates to a reloaded gas storage type solid propellant power device, which belongs to the technical field of solid rocket motors and solid gas generators. Background technique [0002] Solid propulsion methods are widely used. For example, solid rocket motors are selected as power devices for most missiles and rockets due to their simple structure, low cost, good reliability, and fast response. However, power plants using solid propellants also have inherent disadvantages, typically manifested in poor controllability, and it is difficult to achieve thrust control similar to liquid rocket engines. [0003] In order to improve performance and expand the scope of application, researchers have conducted related research on the thrust controllability of solid propellant power plants, and have made progress in the fields of thrust vector control, variable thrust engines, and attitude-orbit control gas valves. However, the development of the m...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/24
CPCF02K9/24
Inventor 章玮奇魏志军夏定国孙烨真张璐佳
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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