Accession Number : ADA207584

Title :   Hybrid Electric Chemical Propulsion,

Corporate Author : AEROSPACE CORP EL SEGUNDO CA AEROPHYSICS LAB

Personal Author(s) : Pollard, James E ; Cohen, Ronald B

PDF Url : ADA207584

Report Date : 01 Apr 1989

Pagination or Media Count : 27

Abstract : A spacecraft propulsion concept that uses a combination of electrical energy and chemical energy for thrust is explored using thermodynamic modeling calculations. The essence of this concept consists of adding a carefully chosen amount of O2 or F2 oxidizer to the propellant flow of a conventional H2 electrothermal thruster. A general method is given for selecting the Fuel: oxidizer ratio so as to optimize the thruster performance for any set of mission constraints. Auxiliary propulsion, Chemically augmented electrothermal thrusters, Electric propulsion, Spacecraft propulsion. (mjm)

Descriptors :   *CHEMICAL REACTIONS, *ELECTRIC PROPULSION, *HYBRID PROPULSION, AUXILIARY, CHEMICALS, COMPUTATIONS, ELECTRICITY, ENERGY, FLOW, FUELS, MISSIONS, MODELS, OXIDIZERS, PERFORMANCE(ENGINEERING), PROPELLANTS, PROPULSION SYSTEMS, RATIOS, SPACE PROPULSION, SPACECRAFT, THERMODYNAMICS, THRUSTERS

Subject Categories : Liquid Propellant Rocket Engines
      Electricity and Magnetism

Distribution Statement : APPROVED FOR PUBLIC RELEASE