| With the development of technical along with the aerospace rapidly, the space deployable structure be used in more and more in aerospace. It is folded during launching, and is deployed to keep in working state in the orbit. Usually, the work appearance stability is requested of the Unfold structure. It is a work request When the temperature changes , the variation of their shapes should be very little.The carriage of Satellite in the space orbit circulate changes with the time and space. So variety makes heat outside the space that be absorbed by satellite that take place variety continuously. It Make the satellite be placed in different carriage become a different temperature steps degree. Whether foldable structure can normal work in continuously the variety of the temperature become more and more important. Imitate the space environment starts experiment to consume a funds very expensive, so it is Necessary that to carry on hot analysis before shoot. It Provide a beneficial basis for the structure design, at the same time economize a funds.The spatial quantity of heat the secondary planet absorbs is varying according to the pose of the secondary planet, so the orbital parameter pertinent to the heat should be calculated first. Based on the aerospace theory, this paper programmed and calculated the orbital parameter pertinent to the heat.According to the radiant heat analyse, aiming at the special work condition, it needs to calculate the coefficient of the radiant heat transfer angle to calculate the aerospace external flow heat. This paper calculated solar coefficient of the radiant heat transfer angle, earth's infrared coefficient of the radiant angle and earth's albedo oefficient of different locations, and gained their numerical values.The secondary planet will enter earth's shadow area when circulating on the orbit, in this area the secondary planet will only absorb earth's infrared heat, the temperature of the secondary planet will hugely change because of the change. Therefor, it's very important for the heat analyse to calculate the time when the secondary planet enters the shadow and the time the secondary planet circulates on the orbit. This paper calculated the two times above using the program.The software ANSYS is an universal finite element software, it has powerful analysis coincidence function. For radiant heat analysis, software ANSYS has several radiant heat analysis elements, satisfied designing needs. In chapter 3, this paper made temperature field analysis using ANSYS/ Thermals element, and in chapter 4, this paper made heat coincidence analysis using coincidence element. Because of the particularity of radiant diathermancy, this paper adopted indirect method to analyse heat coincidence combining to the characteristic of software ANSYS. In chapter 3, this paper processed the calculatation of temperature grads, aiming at two antenna outspread frameworks of different carriages. And got the infections the solar radiate, earth's infrared radiate, earth's albedo to the antenna outspread frameworks of different carriages, than estimated the advantages and the disadvantages of the two frameworks. The temperature grads results was to be used in chapter 4.The special expandedness frameworks requires pimping distortion out of temperature change. So it's necessary to process heat stress analysis using the results of temperature grads. And calculate the distortion out of temperature change. Using software ANSYS, this paper brought to bear the results of temperature grads to configurable model, and gained the heat distortion of the two frameworks. Than we could get the better one comparing the results of the two frameworks. The distortion is the basis for design. |
PDF Full Text Request