Title

Hybrid Rockets for Advanced Missions

Description

With the successful demonstration of the ability to scale hybrid propulsion systems from laboratory engines to the 40,000 lb thrust level and the flight testing of a series of air launched target missiles covering the altitude range from 50,000 to 80,000 ft, hybrid propulsion technology has been brought to the point where it is realistically available for practical application to advanced missiles. The work completed over the period of six years has demonstrated effective practical solutions to the classic problems in design and operation, and has verified the basic advantages originally predicted for hybrid rockets. Detailed studies for many advanced upper stage requirements such as the Jupiter probe missioin have shown that a high energy space storable hybrid stage using propellants composed of lithium and a hydrocarbon binder in combination with fluorine/oxygen mixtures has the potential to outperform existing LOX-hydrogen stages which are suitable modified. In addition, cost studies have indicated that both development and recurring costs for the hybrid stage should be substantially less than for the deep cryogenic stage. Other advantages of significant interest are freedom from acoustic combustion instability, reduced sensitivity in the tolerances of certain critical components, and safety in handling. These characteristics make the hybrid a prime competitor for any new advanced upper stage or for an existing stage requiring modification.

Creator

Altman, David

Ordahl, D. D.

Publisher

Arlington, VA : Air Force Office of Scientific Research

Date

1969

Format

5 pages ; 28 cm.

Type

article

Date Issued

1969-12

Corporate Author

United Technology Center, Division of United Aircraft Corporation

Report Number

AFOSR 69-2951TR p. 132-136

Distribution Conflict

No

Index Abstract

Contrails only

Photo Quality

Not Needed

Distribution Classification

1

Report Availability

Full text available by request

Abstract

With the successful demonstration of the ability to scale hybrid propulsion systems from laboratory engines to the 40,000 lb thrust level and the flight testing of a series of air launched target missiles covering the altitude range from 50,000 to 80,000 ft, hybrid propulsion technology has been brought to the point where it is realistically available for practical application to advanced missiles. The work completed over the period of six years has demonstrated effective practical solutions to the classic problems in design and operation, and has verified the basic advantages originally predicted for hybrid rockets. Detailed studies for many advanced upper stage requirements such as the Jupiter probe missioin have shown that a high energy space storable hybrid stage using propellants composed of lithium and a hydrocarbon binder in combination with fluorine/oxygen mixtures has the potential to outperform existing LOX-hydrogen stages which are suitable modified. In addition, cost studies have indicated that both development and recurring costs for the hybrid stage should be substantially less than for the deep cryogenic stage. Other advantages of significant interest are freedom from acoustic combustion instability, reduced sensitivity in the tolerances of certain critical components, and safety in handling. These characteristics make the hybrid a prime competitor for any new advanced upper stage or for an existing stage requiring modification.

Identifier

AD0703442