Cryogenic propellant on-orbit thermal protection device and its design method, spacecraft

A low-temperature propellant and thermal protection technology, which is applied to space vehicle propulsion system devices, space vehicle heat protection devices, space flight vehicles, etc., and can solve problems such as zero evaporation and storage of propellants in orbit.

Active Publication Date: 2021-09-28
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0005] The invention provides a low-temperature propellant on-orbit heat protection device and its design method, and a spacecraft, which solves the problem that the existing passive heat insulation protection cannot achieve zero evaporation storage of propellant on orbit without using a refrigerator technical problem

Method used

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  • Cryogenic propellant on-orbit thermal protection device and its design method, spacecraft
  • Cryogenic propellant on-orbit thermal protection device and its design method, spacecraft
  • Cryogenic propellant on-orbit thermal protection device and its design method, spacecraft

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Embodiment Construction

[0036] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0037] refer to figure 1 , the preferred embodiment of the present invention provides an on-orbit heat protection device for low-temperature propellant, which includes a storage tank for storing propellant, and above the storage tank is installed a A protection device for heat dissipation, the protection device includes a first support 3 arranged on the storage tank, the top of the first support 3 is provided with a protective cover for blocking solar radiation, and the protective cover is made of heat insulating material.

[0038] In this embodiment, the protective cover is made of multi-layer polyimide film material. The first support member 3 is a support bar arranged on the storage tank, ...

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Abstract

The invention discloses a low-temperature propellant on-orbit heat protection device, a design method thereof, and a spacecraft. The low temperature propellant on-orbit heat protection device is provided with a protection device above the storage tank, and the protection device includes: a first support on the storage tank, and a protective cover for blocking solar radiation is provided on the top of the first support , The protective cover is made of heat insulating material. The present invention realizes shielding of solar radiation by setting up a protective cover. In addition, the outer space is used as a cooling environment, and the solar radiation energy absorbed by the protective cover dissipates heat to the outside in the form of thermal radiation, thereby realizing zero-zero propellant on-orbit. Evaporative storage solves the problem that the existing passive protection and heat insulation cannot achieve zero evaporation storage of propellant in orbit, greatly improves the storage efficiency and safety of the storage tank, and makes the application range of low-temperature propellant wider. The present invention also provides a design method of the above-mentioned cryogenic propellant on-orbit thermal protection device. The present invention also provides a spacecraft comprising the above-mentioned low-temperature propellant on-orbit heat protection device.

Description

technical field [0001] The invention relates to the fields of manned spaceflight and deep space exploration, in particular to a low-temperature propellant on-orbit thermal protection device and a design method thereof. In addition, the present invention also relates to a spacecraft comprising the above-mentioned low-temperature propellant on-orbit heat protection device. Background technique [0002] Future exploration missions will use more and more low-temperature propellants. If the goal of zero-evaporation storage of low-temperature propellants can be achieved, the storage efficiency and safety of the storage tank will be greatly improved, and the application range of low-temperature propellants will be wider. , increase the flight distance of the spacecraft of the same quality level, and greatly save costs. [0003] There are two main methods of traditional cryogenic propellant on-orbit storage heat protection schemes: passive heat insulation protection and active cool...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/58B64G1/40
CPCB64G1/402B64G1/58
Inventor 黄奕勇宋嘉政陈小前张翔陈勇吴宗谕
Owner NAT UNIV OF DEFENSE TECH
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