Experimental technique to simulate orbital-debris impact on space shields at impact velocities over 10 km/s
With the development of a new HyperVelocity Launcher, HVL, at Sandia, it is now possible to perform experiments over the velocity range of 7 to 12 km/s. This velocity range has not been previously accessible for gram-size plates. This meets the requisite mass-velocity criteria established for the orbital debris environment. In this paper, the technique employed to launch thin flier plates to velocities not previously accessible on a two-stage light-gas gun is reported. In particular, this technique has been used on a two-stage light-gas gun to launch nominally 0.5 to 1.0-mm thick aluminum, titanium, and magnesium flier plates intact to velocities up to 12.2 km/s. Since the mass-velocity capability of the newly developed HVL meets the average specifications of the space debris environment, it is expected to be a useful tool to evaluate the effects of debris impact on space structures and debris shields. Examples of a plate impact i.e., orbital debris impact on a thin Whipple shield are presented in this paper.
- Research Organization:
- Sandia National Labs., Albuquerque, NM (United States)
- Sponsoring Organization:
- USDOE, Washington, DC (United States)
- DOE Contract Number:
- AC04-76DP00789
- OSTI ID:
- 10155806
- Report Number(s):
- SAND-92-2460C; CONF-9304135-1; ON: DE93011619
- Resource Relation:
- Conference: 1. European conference on space debris,Darmstadt (Germany),5-8 Apr 1993; Other Information: PBD: [1992]
- Country of Publication:
- United States
- Language:
- English
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