hypervelocity impact tests for spacecraft against orbital debris at hai,cardc
- Paper number
IAC-08.A6.3.4
- Author
Dr. LIU Sen, China Aerodynamics Research and Development Center, China
- Coauthor
Ms. HUANG Jie, China Aerodynamics Research and Development Center, China
- Coauthor
Mr. LI Yi, China Aerodynamics Research and Development Center, China
- Coauthor
Mr. LUO Jinyang, China Aerodynamics Research and Development Center, China
- Coauthor
Mr. XIE Aimin, China Aerodynamics Research and Development Center, China
- Coauthor
Mr. SHI Anhua, China Aerodynamics Research and Development Center, China
- Year
2008
- Abstract
Some of the capabilities of Hypervelocity Ballistics Laboratory of HAI, CARDC, have been adapted to deal with the orbital debris problems. Here in this paper are introduced the hypervelocity impact tests at this lab in recent years. Firstly, the hypervelocity ballistic range complex at this lab consists of four hypervelocity ballistic ranges. The two stage light-gas guns are of 7.6, 16, 25, 37 and 50mm calibers with the highest recorded launch velocity of 8.6km/s. The ranges are equipped with transient phenomena measurement apparatus, such as laser velocimeter, optical emission measurement system, and shadowgrapher/schliren systems. Secondly, some basic hypervelocity impact phenomena have been investigated. For the study of geometric scaling law, aluminum projectiles impact aluminum plates at 4.75 and 6.10km/s. Under the test conditions, linear scaling of the ballistic limit and backwall crater number is observed. Effect of temperature on the ballistic limit of Whipple shields has been examined. The aluminum spheres impact the shields at about 6.0km/s. Compared with room temperature results, the ballistic limits are 3.70 percent less at 150 degree and 7.49 percent larger at -110 degree centigrade. Optical spectrum has been measured for aluminum projectile impacting aluminum semi-finite target at 4.3km/s. The microwave radiation during aluminum projectile impacting aluminum and brass plates are recorded at up to 4.30km/s. Time history of debris cloud expansion is recorded with a sequenced laser shadowgrapher. The magnitude and direction of the debris clouds expansion could be analyzed. Thirdly, some components and shields of chinese spacecraft have been tested. The ballistic limit of a thermal radiator configuration is obtained through hypervelocity impacts, with impact velocities of up to 7.0km/s. Six damage modes of the low density ablative material are summarized, and the maximum damaged area diameter and crater diameter are measured. Two types of the protection configuration have been tested with aluminum spheres impacting at up to 7.0km/s, and ballistic limit curves are obtained. For the pressurized cylindrical stainless steel vessel, the ballistic limit increase with the increase of interior pressures, confirming the benefit of greater interior pressure under test condition. Three types of foamed aluminum panels have been tested, however the result is not as good as expected compared with aluminum plate of the same mass density.
- Abstract document
- Manuscript document
IAC-08.A6.3.4.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.