Space Plasma Active Experiment Experimental Research And Engineering Prototype Development

Space exploration is the direct detection of space environment byman-made spacecraftsuch as rockets,satellites,planetsand spacecrafts. Theseare usually passive detection of space environmental changes and disturbances.Disturbances of nature are usually unpredictable. Compared to the passive way,space plasma active experiment is artificial destruction of the physicalequilibrium of the space environment, and observation of its dynamic process ofrestoring balance. This method is beneficial to highlight one or a few parametersamong many physical parameters to discover their rules.This paper describes ground experiments of Barium release system inspace plasma active experiment on the basis of prior research on space plasmaactive experiment abroad and the preliminary work for active experiment beforein our country. In the laboratory, we investigated the heating and release methodof Barium, and conducted a study on the ignition system and we found that moreeasily ignited when the chemicals have certain resistance, and ignition energyobtained by experiment is about 22 Joule.Wemeasured the titanium and carboncombustion temperature, the maximum combustion temperature was up to 2600Kelvin in the atmosphere. On this basis, we designed the scaled releaseexperiment in vacuum, meanwhile, schemes for measuring combustiontemperature and pressure in vacuum were determined too.This paper also gives the thermal design for the Barium release module. Inspace physics active experiment, the experimental device continues to fly inspace until the time to release after separation with the launch vehicle. Duringflight the device's attitude can't be controlled. In order to make the circuit in theelectronic control box to work properly, surface coating must be applied to theelectronic control box to control the temperature in an ideal range. This papercalculated the temperature of electronic control box under this condition, andresults show that solar radiation heat flux and electric heat inside the control boxare main reasons for the temperature change. As the attitude of the electroniccontrol box is uncertain, solar radiation will directly affect its temperature, so coating needs to meet the requirements of different situations. The results showthat total reflection coating with low surface absorption rate (α= 0.15) and corresponding surface emissivity (e = 0.16) can control the box temperaturechange within a very small range, ensuring the circuit inside in the normal scopeof working temperature.