Novel Mars spacecraft combined propulsion system

A technology of propulsion system and aircraft, applied in power plant type, rocket-type power plant, etc., can solve the problems of carrying a large amount of fuel, unable to meet the mission of Mars aircraft, and achieve the effect of reducing cost

Active Publication Date: 2018-11-20
HARBIN INST OF TECH
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  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to solve the problem that the existing propulsion system needs to carry a large amount of fuel from the earth and cannot meet the full-stage flight mission of the Mars spacecraft, the present invention provides a new type of combined propulsion system for the Mars spacecraft. The technical solution adopted is:

Method used

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  • Novel Mars spacecraft combined propulsion system
  • Novel Mars spacecraft combined propulsion system
  • Novel Mars spacecraft combined propulsion system

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specific Embodiment approach

[0016] Specific implementation method: combined Figure 1 to Figure 3 To illustrate this embodiment: a new type of Mars vehicle combined propulsion system mentioned in this embodiment includes a propeller 1 and a rocket motor 2, and the propeller 1 and rocket motor 2 are installed on the wings of the aircraft 3. Rocket engine 2 comprises oxidant storage tank 4, fuel storage tank 5, oxidant pump 6, fuel pump 7, combustion chamber 8, tail nozzle 9 and flow regulating valve 11; The output end of described oxidant storage tank 4 and fuel storage tank 5 Correspondingly connected to the input ends of the oxidant pump 6 and the fuel pump 7 respectively; flow regulating valves are provided on the pipelines connecting the oxidant storage tank 4 to the oxidant pump 6 and on the pipelines connecting the fuel storage tank 5 to the fuel pump 7 11. The fuel in the oxidant storage tank 4 and the fuel storage tank 5 is delivered to the combustion chamber 8 for combustion through the oxidant p...

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Abstract

The invention relates to a novel Mars spacecraft combined propulsion system, and relates to the technical field of Mars exploration and Mars spacecraft power. The invention aims to solve the problem that the existing propulsion system needs to carry a large amount of fuel from the earth and cannot meet the full-phase flight mission of a Mars spacecraft. The output ends of an oxidant storage tank and a fuel storage tank are correspondingly connected with the input ends of an oxidant pump and a fuel pump respectively; flow regulating valves are arranged on a pipeline for connecting the oxidant storage tank with the oxidant pump and a pipeline for connecting the fuel storage tank with the fuel pump; the fuels in the oxidant storage tank and the fuel storage tank are delivered to a combustionchamber for combustion through the oxidant pump and the fuel pump respectively, and the tail end of the combustion chamber is connected with the head end of an exhaust nozzle. According to the novel Mars spacecraft combined propulsion system provided by the invention, a propellant required by a spacecraft can be directly prepared by utilizing available resources of Mars.

Description

technical field [0001] The invention relates to a novel combined propulsion system of a Mars vehicle, and relates to the technical fields of Mars exploration and Mars vehicle power. Background technique [0002] With the improvement of human ability to enter space and the development of aerospace technology, deep space has become one of the important fields of human exploration. Mars exploration has become a hotspot in human deep space exploration in recent years. The continuous development of propulsion technology has provided the possibility for difficult space missions such as manned Mars exploration and return Mars exploration. With the continuous success of manned spaceflight and moon landing programs, the space competition goal of various countries has gradually turned to Mars. China's Mars exploration program was officially established in January 2016. Under the general goal of "serving the sustainable development of human society", the program will explore the origi...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/02
CPCB64D27/023
Inventor 秦江吕传文程昆林郭发福章思龙鲍文
Owner HARBIN INST OF TECH
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