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Parametric trade studies on a shuttle 2 launch system architecture
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Morris Sr., W. Douglas Talay, Theodore A. Stanley, Douglas O. Cruz, Christopher I. Naftel, J. Christopher Lepsch, Roger A. |
| Copyright Year | 1991 |
| Description | A series of trade studies are presented on a complementary architecture of launch vehicles as a part of a study often referred to as Shuttle-2. The results of the trade studies performed on the vehicles of a reference Shuttle-2 mixed fleet architecture have provided an increased understanding of the relative importance of each of the major vehicle parameters. As a result of trades on the reference booster-orbiter configuration with a methane booster, the study showed that 60 percent of the total liftoff thrust should be on the booster and 40 percent on the orbiter. It was also found that the liftoff thrust to weight ratio (T/W) on the booster-orbiter should be 1.3. This leads to a low dry weight and still provides enough thrust to allow the design of a heavy lift architecture. As a result of another trade study, the dry weight of the reference booster-orbiter was chosen for a variety of operational considerations. Other trade studies on the booster-orbiter demonstrate that the cross feeding of propellant during boost phase is desirable and that engine-out capability from launch to orbit is worth the performance penalty. Technology assumptions made during the Shuttle-2 design were shown to be approx. equivalent to a 25 percent across the board weight reduction over the Space Shuttle technology. The vehicles of the Shuttle-2 architecture were also sized for a wide variety of payloads and missions to different orbits. Many of these same parametric trades were also performed on completely liquid hydrogen fueled fully reusable concepts. If a booster-orbiter is designed using liquid hydrogen engines on both the booster and orbiter, the total vehicle dry weight is only 3.0 percent higher than the reference dual-fuel booster-orbiter, and the gross weight is 3.8 percent less. For this booster-orbiter vehicle, a liftoff T/W of 1.3, a thrust of about 60 percent on the booster, and a Mach staging number of 3 all proved to be desirable. This modest dry weight increase for a liquid hydrogen fueled Shuttle-2 system should be more than offset by the elimination of the entire hydrocarbon engine development program and the savings in operation cost realized by the elimination of an entire fuel type. |
| File Size | 3106099 |
| Page Count | 58 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910008867 |
| Archival Resource Key | ark:/13960/t89h0jz23 |
| Language | English |
| Publisher Date | 1991-03-01 |
| Access Restriction | Open |
| Subject Keyword | Launch Vehicles And Space Vehicles Hydrogen Engines Engine Design Space Shuttles Spacecraft Launching Propulsion System Configurations Supersonic Speed Payload Integration Weight Reduction Launch Vehicle Configurations Booster Rocket Engines Liquid Hydrogen Spacecraft Configurations Spacecraft Design Thrust-weight Ratio Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
