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Portable nano-satellite atmospheric-pressure thermal test measurement and control system

A measurement and control system and micro-nano-satellite technology, which is applied in the direction of temperature control, measuring device, and heat measurement using electric methods, to achieve the effects of convenient implementation, simple structure, and low cost

Active Publication Date: 2016-07-20
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology

[0005] The technical problem to be solved by the present invention is to provide a portable system and method for micro-nano satellites to realize auxiliary external heat flow simulation control and pollution measurement in the external field atmospheric pressure environment, so as to meet the safety, Demand for high flexibility and certain expansion capabilities

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Embodiment Construction

[0017] The portable micro-nano-satellite atmospheric pressure thermal test measurement and control system of the present invention will be described in detail below with reference to the accompanying drawings, but the description is only exemplary and is not intended to limit the protection scope of the present invention.

[0018] Fig. 1 is a schematic diagram of the connection between the portable micro-nano satellite atmospheric pressure thermal test measurement and control system and atmospheric equipment of the present invention, as figure 1 As shown, the system is arranged outside the spacecraft thermal test equipment 101 in the outer field, and is composed of an auxiliary external heat flow simulation system 110 for spacecraft vacuum thermal tests, a temperature measurement system 111 and a pollution measurement system 112; In the equipment 101, a temperature sensor 104 is fixed on the surface of the test piece, and a heating device 103 (infrared quartz lamp is shown in t...

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Abstract

The invention discloses a portable nano-satellite atmospheric-pressure thermal test measurement and control system. The system includes an auxiliary external flux simulation system, a temperature measuring system, and a pollution measuring system which are used in spacecraft vacuum thermal tests. The auxiliary external flux simulation system generates a predetermined flux density through a temperature controlling instrument and a power supply passing a test piece local heater. The temperature measuring system obtains test piece surface temperature by means of a platinum resistor. The pollution measuring system includes a balance frequency and a glass test piece contaminant capacity measuring system. According to the invention, the system can simulate external flux imposed on the nano-satellite in orbit under atmospheric pressure, measures corresponding thermal property and contaminant capacity, and conducts atmospheric-pressure thermal tests of the nano-satellite in a rapid and convenient manner. The system has a high reliability and flexibility, can effectively reduce test expenditure and test period, and increases production efficiency.

Description

technical field [0001] The invention belongs to the technical field of spacecraft ground test verification, and in particular relates to a portable integrated atmospheric pressure thermal test measurement and control method and system for a micro-nano satellite. The auxiliary external heat flow control simulation of the micro-nano satellite is realized in the atmospheric pressure thermal test through the portable measurement and control system , The function of temperature measurement and pollution measurement of each stand-alone equipment in the test piece. Background technique [0002] With the diversification of my country's aerospace missions and the development of aerospace models, the application of micro-nano satellites is becoming more and more extensive. The circulation equipment cooperates with the test measurement and control system for verification. [0003] In recent years, the number of newly built atmospheric pressure thermal cycle equipment has gradually incr...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01K7/18G05D23/19G01N33/00G01M99/00
CPCG01K7/18G01M99/002G01N33/00G05D23/19
Inventor 尚永红龚喆王晶杨晓宁杨勇李西园张皓马昆
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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