Title

Performance Of A Two-Stage Launcher Using Hydrogen

Date

1962

Index Abstract

Coming Soon

Photo Quality

Not Needed

Report Number

AEDC TDR 62-32

Creator

Stephenson, W. B.

Knapp, R. E.

Corporate Author

ARO, Inc.

Laboratory

Arnold Engineering Development Center

Extent

58

Identifier

AD0273528

Access Rights

ASTIA

Distribution Classification

1

Contract

AF 40(600)-800

DoD Project

8950

DoD Task

89600

DTIC Record Exists

No

Distribution Change Authority Correspondence

None

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.

Report Availability

Full text available

Date Issued

1962-03

Publisher

Arnold Air Force Station, TN : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force

Provenance

IIT

Type

report

Format

1 online resource