Accession Number : ADA454615


Title :   THRUST AUGMENTED NOZZLE (TAN) the New Paradigm for Booster Rockets


Descriptive Note : Technical Paper Preprint


Corporate Author : AEROJET SACRAMENTO CA


Personal Author(s) : Bulman, Melvin J


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a454615.pdf


Report Date : 12 Jul 2006


Pagination or Media Count : 10


Abstract : Rocket-powered launch vehicles require high thrust when taking off and high vacuum specific impulse (Isp) later in the mission. These two requirements are in conflict since a large area ratio nozzle operating at sea-level pressure is less efficient in producing thrust and the jet may separate from the nozzle causing destructive forces. Aerojet's Thrust Augmented Nozzle (TAN) concept overcomes these conventional engine limitations by injecting additional propellants and combusting in the nozzle. The TAN concept represents no less than a change in the rocket propulsion paradigm. Higher thrust to weight of the engine can reduce the engine weight, which can be traded directly for increased payload. Launch vehicle mission effective Isp can be significantly improved by using TAN to safely fill a high area ratio nozzle at sea level while significantly increasing thrust. The thrust augmenting propellants can be different from the core engine, enabling the benefits of dual fuels on mission performance. Possibly the most important benefit of TAN is increased engine system reliabilities by operating the engine core at a reduced chamber pressure and making up the required thrust by operating TAN. This paper describes the TAN concept, and how it overcomes these classic booster engine problems as supported by test results and a representative simulated mission.


Descriptors :   *BOOSTER ROCKET ENGINES , *LAUNCH VEHICLES , *THRUST AUGMENTOR NOZZLES , *SPECIFIC IMPULSE , SIMULATION , RATIOS , SYMPOSIA , COMBUSTION PRODUCTS , PERFORMANCE(ENGINEERING) , SEA LEVEL , PROPELLANTS , WEIGHT , BAROMETRIC PRESSURE


Subject Categories : Rocket Engines
      Unmanned Spacecraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE