Range complex Ames Research Center

1 range complex

1.1 ames vertical gun range
1.2 hypervelocity free-flight range
1.3 electric arc shock tube

range complex
ames vertical gun range

the ames vertical gun range (avgr) designed conduct scientific studies of lunar impact processes in support of apollo missions. in 1979, established national facility, funded through planetary geology , geophysics program. in 1995, increased scientific needs across various disciplines resulted in joint core funding 3 different science programs @ nasa headquarters (planetary geology , geophysics, exobiology, , solar system origins). in addition, avgr provides programmatic support various proposed , ongoing planetary missions (e.g. stardust, deep impact).

using 0.30 cal light-gas gun , powder gun, avgr can launch projectiles velocities ranging 500 7,000 m/s (1,600 23,000 ft/s). varying gun’s angle of elevation respect target vacuum chamber, impact angles 0° 90° relative gravitational vector possible. unique feature extremely important in study of crater formation processes.

the target chamber approximately 2.5 meters (8 ft 2 in) in diameter , height , can accommodate wide variety of targets , mounting fixtures. can maintain vacuum levels below 0.03 torrs (4.0 pa), or can filled various gases simulate different planetary atmospheres. impact events typically recorded high-speed video/film, or particle image velocimetry (piv).

hypervelocity free-flight range

the hypervelocity free-flight (hff) range comprises 2 active facilities: aerodynamic facility (hffaf) , gun development facility (hffgdf). hffaf combined ballistic range , shock-tube driven wind tunnel. primary purpose examine aerodynamic characteristics , flow-field structural details of free-flying aeroballistic models.

the hffaf has test section equipped 16 shadowgraph-imaging stations. each station can used capture orthogonal pair of images of hypervelocity model in flight. these images, combined recorded flight time history, can used obtain critical aerodynamic parameters such lift, drag, static , dynamic stability, flow characteristics, , pitching moment coefficients. high mach number (m > 25) simulations, models can launched counter-flowing gas stream generated shock tube. facility can configured hypervelocity impact testing , has aerothermodynamic capability well. hffaf configured operate 1.5 inches (38 mm) light-gas gun in support of continuing thermal imaging , transition research nasa s hypersonics program.

the hffgdf used gun performance enhancement studies, , occasional impact testing. facility uses same arsenal of light-gas , powder guns hffaf accelerate particles range in size 3.2 25.4 millimeters (0.13 1.00 in) diameter velocities ranging 0.5 8.5 km/s (1,500 28,000 ft/s). of research effort date has centered on earth atmosphere entry configurations (mercury, gemini, apollo, , shuttle), planetary entry designs (viking, pioneer venus, galileo , msl), , aerobraking (afe) configurations. facility has been used scramjet propulsion studies (national aerospace plane (nasp)) , meteoroid/orbital debris impact studies (space station , rlv). in 2004, facility utilized foam-debris dynamics testing in support of return flight effort. of march 2007, gdf has been reconfigured operate cold gas gun subsonic cev capsule aerodynamics.

electric arc shock tube

the electric arc shock tube (east) facility used investigate effects of radiation , ionization occur during high velocity atmospheric entries. in addition, east can provide air-blast simulations requiring strongest possible shock generation in air @ initial pressure loading of 1 standard atmosphere (100 kpa) or greater. facility has 3 separate driver configurations, meet range of test requirements: driver can connected diaphragm station of either 102 millimeters (4.0 in) or 610 millimeters (24 in) shock tube, , high-pressure 102 millimeters (4.0 in) shock tube can drive 762 millimeters (30.0 in) shock tunnel. energy drivers supplied 1.25-mj-capacitor storage system.