Ablation analysis and test for the outstanding obstical of manned spacecraft
- Paper number
IAC-06-C2.7.01
- Author
Prof. Guoting Wu, China Academy of Space Technology (CAST), China
- Year
2006
- Abstract
The returned module(RM) of <SHENZHOU> manned spacecraft is linked with the orbiter module(OM) and boost module (BM) by a kind of linkers which will leave several outstanding obstacles on the thermal-protection surface of the RM after it being separated from the spacecraft. These outstanding obstacles must be burned out as earlier as possible during the RM atmospherically re-entry, to avoid the over-heating causing by obstacles’ flow disturbing. In the design of the part, the main difficulties are: 1) how to determine the temperature, at which the outstanding obstacle is burned out; and 2) how the ground tests to be proceeded and to get the real performance in the re-entry flight from the results of tests. In order to solve the difficulties above, a set of design proceeding is developed using analysis and tests repetitively. In the analysis, the temperature rise of the obstacle is calculated with the base of non-disturbing heating flux density on the smooth surface and considering the distribution along the highness and around circle of the obstacle. In the tests, such parameters as local non-disturbing heating flux density on the smooth surface, local gas dynamical shear force, and total pressure of gas are simulated. With the design proceeding, the material and dimensions of the outstanding obstacles of the linkers are determined, and the ablative behavior of the obstacle is predicated. The performance of the linkers has been verified by the successful flights of "SZ-1" to "SZ-6", therefore the technique of the ablative analyses and test on the outstanding obstacle is also verified.
- Abstract document