Experimental technique to simulate orbital-debris impact on space shields at impact velocities over 10 km/s

Conference · Thu Dec 31 04:00:00 EST 1992

OSTI ID:10155806

Chhabildas, L C; Boslough, M B

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
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
360103
42 ENGINEERING
420500
ACCELERATION
ALUMINIUM
IMPACT TESTS
LAUNCHING
MATERIALS TESTING
MECHANICAL PROPERTIES
PLATES
SHIELDING
SIMULATION
SPACE VEHICLES
TITANIUM