Integrated configuration effects of hypersonic upper body designs on Single Stage To Orbit non-circular bodies
Abstract
The development of air breathing Single Stage To Orbit vehicles requires investigating configurations that integrate 'Tip to Tail' propulsion flowpaths, active aerodynamic control, and large propellant volumes. The selection of these configurations can vary from arrangements like a Conical Fuselage Wing Body to a Non-Circular Lifting Body. Specifically, the selection criterion relies on satisfying both the aeropropulsion requirements and the internal volume constraints needed to meet mission requirements. The focus of this paper is the relationship between aerodynamic control of the configuration and adequate propellant volume for Single Stage To Orbit vehicle mission requirements.
- Publication:
-
Aerospace Design Conference
- Pub Date:
- February 1993
- Bibcode:
- 1993asd..confU....C
- Keywords:
-
- Computer Aided Design;
- Hypersonic Vehicles;
- Launch Vehicle Configurations;
- Single Stage To Orbit Vehicles;
- Spacecraft Design;
- Aerodynamic Characteristics;
- Flow Distribution;
- Propulsion System Configurations;
- Spacecraft Performance;
- Launch Vehicles and Space Vehicles