Accession Number : ADA467749


Title :   Investigation of Advanced Propellants to Enable Single Stage to Orbit Launch Vehicles


Descriptive Note : Master's thesis


Corporate Author : AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV


Personal Author(s) : Mossman, Jason


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a467749.pdf


Report Date : 30 Oct 2006


Pagination or Media Count : 91


Abstract : Single-Stage-To-Orbit (SSTO) launch vehicles designs offer the promise of reduced complexity and cost compared to multi-stage vehicles, as only one stage need be developed, produced, and maintained. Despite well-funded development efforts, no SSTO vehicles have been fielded to date. Existing chemical rocket and vehicle technologies do not enable feasible SSTO designs. In the future, new propellants with advanced properties could enable SSTO launch vehicles. A parametric sizing study was conducted to determine the rocket propulsion performance required. Bulk density, specific impulse, and main propulsion thrust-to-weight level were varied to determine the sensitivity of SSTO vehicle size to these parameters. Advanced propellants including strained-ring hydrocarbons and polynitrogen compounds are evaluated for their suitability in SSTO applications.


Descriptors :   *LAUNCH VEHICLES , *ROCKET PROPULSION , PROPELLANTS , SPECIFIC IMPULSE , PROPULSION SYSTEMS , THRUST


Subject Categories : Rocket Engines
      Unmanned Spacecraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE