Accession Number:

AD0392295

Title:

HYBRID PROPULSION SYSTEM FOR AN ADVANCED ROCKET-POWERED TARGET MISSILE.

Descriptive Note:

Final rept. 1 Jun 66-1 Mar 68,

Corporate Author:

UNITED TECHNOLOGY CENTER SUNNYVALE CALIF

Personal Author(s):

Report Date:

1968-08-01

Pagination or Media Count:

372.0

Abstract:

A demonstration program has been completed to determine the feasibility of a low-cost hybrid propulsion system for an advanced rocket-powered target vehicle. During a 21-month program a flightweight hybrid propulsion system was designed, fabricated, and successfully tested in numerous static firings at ambient conditions, temperature extremes of -65 F to 165 F and at altitude conditions in the AFRPL altitude facility. The final system design demonstrated step-thrust operation over an 81 thrust range which was provided on-command from boost thrust to sustain thrust. The sustain thrust level is selected prior to system firing by setting a flow control valve which provides dial-a-thrust flexibility. The final phase of the program involved flight tests with a target vehicle airframe which demonstrated the hybrid propulsion system capability to provide command step-thrust operation, powered flight times approaching 5 min, and reliable operation following aircraft launch at 49,000 ft, Mach 1.5. Author

Subject Categories:

  • Pilotless Aircraft
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE