The large spacecraft structure would generate thermal-induced vibration in orbit under specific condition, which will affect the performance of the payload. In order to predict the occurrence of thermal-induced vibration of the spacecraft structure in orbit, it is necessary to carry out tests in the ground simulated vacuum and low temperature environment. The vibration displacement of structure should be measured by laser displacement meter during the test. Due to the special environment such as vacuum, low temperature environment, it is necessary to improve the laser displacement meter. The effect of internal and external pressure difference during pumping is eliminated by design the venting holes. Ensures the temperature uniformity and operating temperature range of the laser displacement meter by thermal control design, to reduce the measurement error caused by the thermal deformation of the sensor. The adaptive design ensures that the laser displacement meter can work normally under vacuum and low temperature environment, and the measurement accuracy is better than 5μm.
To satisfy the application of fiber grating sensor technology in high vacuum thermal environment, FBG on sleeve compactly single model fiber with two typical different kind of connection such as fiber splicing and optical fiber connector are researched. Influence of the different connection to the characteristic of FBG reflectance spectrum in high vacuum thermal environment is analyzed and verified. First, experimental program of influence on FBG reflection spectrum characteristics is designed. Then, a hardware-in-the-loop detection platform is set up. Finally, the influence of temperature and vacuum on the reflection peak power of FBG with two typical different connections under high vacuum thermal environment is studied and verified. Experimental results indicate that: when vacuum varied from normal pressure to 10-4Pa level and then return to normal pressure, temperature of two different single-mode optical fiber connection dropped to -196 ̊C from room temperature and then returned to room temperature, after 224 hours, the peak power of the FBG reflectance spectrum did not change. It provided the experimental basis for the application of optical fiber sensing technology in high vacuum (pressure about 10-4Pa level) and thermal environment (-196 ̊C temperature cycle).
In order to verify the performance of space deployable structures before launch, separation and deployment tests should be carried out in large space environment simulation chamber, in which a simulated on-orbit environment can be achieved. In separation and deployment tests, high-speed camera system is often employed to capture the test image. The high-speed camera system is also exposed to the cryogenic and vacuum environment in large space environment simulation chamber. Consequently, cryogenic and vacuum adaptability of the system should be very strong to withstand the extreme environment in space environment simulation chamber. A common solution is using optical chamber. The equipment was set in a pressurized chamber which can insulate inner environment from the outer vacuum environment, and the gas in the chamber can also help to heat convection, therefore heat generated by the device can be transferred to the chamber wall. This paper aims to explore the thermal design of optical chamber for high-speed camera or other special equipment used in extreme environment. Using rule number analysis method, Heat transfer model in vacuum and ambient environment had been built to analyze the characteristics of heat transfer under different thermal power, characteristic length, and environment. recommended limits were delivered by the rule number analysis. CFD method was applied to verify the rule number analysis above. The two methods above reached a similar result, which demonstrated the effectiveness of the analysis.
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