Thermodynamic Considerations in Bipropellant Blowdown Systems
Author:
Affiliation:
1. Lockheed Missiles & Space Co., Inc., Sunnyvale, California
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/3.55537
Reference5 articles.
1. Feasibility of simple bipropellant blowdown systems
2. Evaluation of Bipropellant Pressurization Concepts for Spacecraft
3. Prediction of a propellant tank pressure history using state space methods
4. Ring, E., Rocket Propellant and Pressurization Systems, Prentice-Hall, Englewood Cliffs, N.J., 1964, pp.223-225.
5. 5Kreith, F., Principles of Heat Transfer, Intext Educational Publishers, New York, N.Y., 1973, pp.402-407.
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1. Development and Validation of Fluid/Thermodynamic Models for Spacecraft Propulsion Systems;Journal of Propulsion and Power;2001-05
2. Design and development of a large bipropellant blowdown propulsion system;Journal of Propulsion and Power;1995-09
3. Design and development of a large bipropellant blowdown propulsion system;29th Joint Propulsion Conference and Exhibit;1993-06-28
4. Mathematical modelling of the unified bipropellant propulsion system;Acta Astronautica;1992-11
5. A performance computing and monitoring method for monopropellant propulsion systems;28th Joint Propulsion Conference and Exhibit;1992-07-06
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