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The Martin X-23A PRIME (Precision Reentry Including Maneuvering reEntry) (SV-5D) is a small lifting-body re-entry vehicle tested by the United States Air Force in the mid-1960s. Unlike ASSET, primarily used for structural and heating research, the X-23A PRIME was developed to study the effects of maneuvering during re-entry of Earth's atmosphere, including cross-range maneuvers up to from the ballistic track.

Design

Each X-23A was constructed from titanium, beryllium, stainless steel, and aluminum. The craft consisted of two sections—the aft main structure and a removable forward "glove section". The structure was completely covered with a Martin-developed ablative heat shield thick, and the nose cap was constructed of carbon phenolic material.

Aerodynamic control was provided by a pair of lower flaps, and fixed upper flaps and rudders. A nitrogen-gas reaction control system was used outside the atmosphere. At Mach 2 a drogue ballute deployed and slowed the vehicle's descent. As it deployed, its cable sliced the upper structure of the main equipment bay, allowing a recovery chute to deploy. It would then be recovered in midair by a specially-equipped JC-130B Hercules aircraft.

|prime units?=kts

|length ft= 6

|length in= 8

|span ft= 3

|span in= 10

|height ft= 2

|height in= 10

|gross weight lb= 894

|eng1 name=Nitrogen gas reaction control thrusters

|max speed kts=14388

|max speed note=

|max speed mach=25

|range miles=

|range km=

|more performance=

  • Hypersonic L/D Ratio: 1:1

|avionics=

See also

References

  • Encyclopedia Astronautica
  • Video Atlas X-38 Prototype Arrival (PRIME/X-23), Unloading, Mating and Launch