Controllable Solid Propulsion for Launch Vehicle and Spacecraft Application
- Paper number
IAC-06-C4.2.04
- Author
Mr. John Napior, Aerojet, United States
- Year
2006
- Abstract
Aerojet, a leading propulsion company in the United States, has been developing controllable solid propellant propulsion systems for a wide variety of applications for over 10 years, including systems in production. Controllable solid propulsion systems provide variable thrust capability with high turn down ratios by changing the nozzle throat area and the motor’s operating pressure. Aerojet has developed numerous controllable systems with single and multiple variable thrust nozzles for axial propulsion rocket motors and attitude control systems, respectively. Recently, Aerojet has started work on controllable thrust systems for crew launch vehicles and spacecraft applications in support of NASA’s Space Exploration program. This paper will provide an overview of Aerojet’s controllable thrust capabilities and how they are being applied to crew abort systems on launch vehicles and landing rockets for spacecraft. This is the first time that this information will be provided in support of a technical conference.
- Abstract document
- Manuscript document
IAC-06-C4.2.04.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.