This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
A Two Stage-to-Orbit High Staging Mach Number Design Concept
Technical Paper
2000-01-5605
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
This paper presents a Mach 23 staged two stage-to-orbit launch vehicle candidate. Previously, two stage-to-orbit launch vehicles considered subsonic, supersonic and hypersonic staging options. Studies have shown that performance optimized two stage launch vehicles have first stage performance capabilities that vary widely depending on the propulsion and type of fuel used in the first and second stage. A Mach 23 performance capable first stage could fly around the world and return from the takeoff site using a boost-glide-skip trajectory profile. A Mach 23 staged first stage would be significantly less difficult to develop compared to a single stage-to-orbit launch vehicle. The usable propellant fraction for the Mach 23 rocket-based combined cycle engine powered first stage presented in this paper is 0.614 and the payload fraction is 0.033.
Previous work by the authors has shown that a Mach 23 staged vehicle is close to the performance optimum when the operational orbit of the payload is considered as the performance requirement for a two-stage-to-orbit vehicle. A Mach 23 first stage capable launch vehicle can operate from a single launch site without the need for down-range recovery sites and a means of returning to the launch site. During each flight the first stage returns directly to the take-off site on an unpowered boost-glide-skip trajectory.
Recommended Content
Technical Paper | The Joint Services Advanced Vertical Lift Aircraft (JVX) Propulsion System |
Technical Paper | History of Ice Protection System Design at Bell Helicopter |
Technical Paper | Method to evaluate takeoff distance for nose-gear light aircrafts |
Citation
Chase, R., McKinney, L., and Froning, M., "A Two Stage-to-Orbit High Staging Mach Number Design Concept," SAE Technical Paper 2000-01-5605, 2000, https://doi.org/10.4271/2000-01-5605.Also In
References
- AIAA-96-4519 “Aerospace Plane Trajectory Optimization for Sub-Orbital Boost-Glide Flight,” November 1996
- STAIF 97 “Upper-Stage Options for Reusable Launch Vehicle Pop-Up Missions,” January 1997
- AIAA 97-2972 “Comments on Upper Stage Applications for a Military Space Plane,” Chase R. July 1997
- AIAA 97-5630 “A Military Space Plane Candidate,” Chase R. McKinney L. Froning H. October 1997
- ANSER Technical Report 97-1 “An Advanced Highly Reusable Space Transportation System Definition and Assessment Study,” Chase R. Boyd R. Dr. Czysz P. Dr. Fronning H. Lewis M. Dr. McKinney L. September 1997
- AIAA 95-3124 “The Strutjet Engine: The Overlooked Option for Space Launch,” Siebenhaar A. Bulman M. July 1995
- STAIF 97 “Upper-Stage Options for Reusable Launch Vehicle Pop-Up Missions,” November 1996
- IAF-90-191 “A Comparison of Fully Reusable Winged Single-Stage and Two-Stage Launch Vehicles with Different Propulsion Concepts,” October 1990
- 709-02-CR “Earth-to-Orbit Reusable Launch Vehicles, A Comparative Assessment,” February 1978