Performance Of A Two-Stage Launcher Using Hydrogen
Report Number: AEDC TDR 62-32
Author(s): Stephenson, W. B., Knapp, R. E.
Corporate Author(s): ARO, Inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1962-03
Pages: 58
Contract: AF 40(600)-800
DoD Project: 8950
DoD Task: 89600
Identifier: AD0273528
Abstract:
A procedure is outlined for computing the performance of two-stage, light-gas launchers using hydrogen as a propellant. A method in general dimensionless terms is developed by which the launch velocity for this type of launcher may be computed. The effects of piston weight and velocity, as well as preheating of the pump tube gas, are determined. Experimental results using both unheated and heated hydrogen are compared with theoretical calculations of velocity. Since the important physical variables -- piston mass, velocity, pump tube geometry, initial pump tube pressure, piston reversal, initial projectile movement, and heat losses -- are included, a design optimization has been made, and limits to the launch velocity were estimated.
Provenance: IIT
Author(s): Stephenson, W. B., Knapp, R. E.
Corporate Author(s): ARO, Inc.
Laboratory: Arnold Engineering Development Center
Date of Publication: 1962-03
Pages: 58
Contract: AF 40(600)-800
DoD Project: 8950
DoD Task: 89600
Identifier: AD0273528
Abstract:
A procedure is outlined for computing the performance of two-stage, light-gas launchers using hydrogen as a propellant. A method in general dimensionless terms is developed by which the launch velocity for this type of launcher may be computed. The effects of piston weight and velocity, as well as preheating of the pump tube gas, are determined. Experimental results using both unheated and heated hydrogen are compared with theoretical calculations of velocity. Since the important physical variables -- piston mass, velocity, pump tube geometry, initial pump tube pressure, piston reversal, initial projectile movement, and heat losses -- are included, a design optimization has been made, and limits to the launch velocity were estimated.
Provenance: IIT