Near space aerocraft and thermal control system thereof

A near-space, thermal control system technology, applied in the field of near-space vehicles, can solve the problems of complex passive temperature control measures and high thermal control costs, and achieve the effects of simple structure, stable temperature and simple thermal control methods

Active Publication Date: 2017-04-05
DONGGUAN FRONTIER TECH INST +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The purpose of the present invention is to overcome the deficiencies of the above-mentioned prior art, and provide a near-space vehicle and its thermal control system, which solves the current technology of complex passive temperature control measures for near-space vehicles and brings relatively large thermal control costs question

Method used

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  • Near space aerocraft and thermal control system thereof
  • Near space aerocraft and thermal control system thereof

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Embodiment Construction

[0014] In order to make the object, technical solution and advantages of the present invention more clear, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0015] It should be noted that when an element is described as being “fixed” or “disposed on” another element, it may be directly on the other element or there may be an intervening element at the same time. When an element is described as being "connected to" another element, it can be directly connected to the other element or intervening elements may also be present.

[0016] It should also be noted that the orientation terms such as left, right, up, down, top, and bottom in this embodiment are only relative concepts or refer to the normal use state of the product, and should not be regarded ...

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Abstract

The invention discloses a near space aerocraft and a thermal control system thereof. The thermal control system of the near space aerocraft comprises a shrinkage capsule with expansion and shrinkage functions; the shrinkage capsule is arranged on the outer surface of a near space aerocraft shell; the surface, relative to a contact surface of the outer surface of the near space aerocraft shell, of the shrinkage capsule is also provided with a phase-change heat absorbing part used for absorbing radiant heat in a near space aerocraft cabin; the outside of the phase-change heat absorbing part is also provided with a first radiation coating; and the first radiation coating is used for absorbing the radiant heat in the near space aerocraft cabin and conducting the radiant heat to the phase-change heat absorbing part. The thermal control system disclosed by the invention is capable of keeping the temperature inside the near space aerocraft cabin relatively stable as well as simple in structure and thermal control way. The near space aerocraft disclosed by the invention is low in cost because of adopting passive thermal control and capable of effectively keeping the temperature inside the near space aerocraft cabin relatively stable so that equipment in the cabin can normally work.

Description

technical field [0001] The invention belongs to the technical field of near-space vehicles, and in particular relates to a thermal control system of a near-space vehicle and a near-space vehicle containing the thermal control system. Background technique [0002] Near space is a new space developed by the human economy, and near space vehicles will reside in this area for a long time in the future. Whether the equipment cabin of the aircraft can provide a relatively stable temperature environment determines the basic conditions for the normal operation of the equipment in the cabin. [0003] Because the ambient temperature in the airtight cabin of the aircraft is affected by the ambient temperature in the adjacent space, solar radiation, infrared radiation and solar reflection, and the heating of equipment in the cabin, the temperature may be too high during the day and too cold at night. In the external environment where the heat of electronic equipment is difficult to dis...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/46B64G1/58
Inventor 不公告发明人
Owner DONGGUAN FRONTIER TECH INST
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