Responsive, low-Cost Launch of Nanosatellites and Technology Demonstrations
- Paper number
IAC-10.D2.7.4
- Author
Mr. Steve Cook, Dynetics, United States
- Coauthor
Mr. Mark Fisher, Dynetics, United States
- Year
2010
- Abstract
Nanosatellites are emerging as key assets for a broad array of missions including space weather, communications, Earth observation and technology demonstrations for a wide variety of customers including the Department of Defense (DoD), NASA, the National Science Foundation (NSF), and universities. Currently, nanosatellites are launched as secondary payloads on large launch vehicles. While these launches are adequate for test demonstrations, the nanosat’s orbital location is confined to the primary payload’s orbital destination. More importantly, these launches are scheduled years in advance, requiring research to be placed on hold awaiting a launch – a particular problem for university faculty. In order to maximize the benefit of the next generation of nanosats, Dynetics recognizes that a dedicated, low cost, small payload launch system is needed to ensure rapid deployment and precise placement of nanosatellites and demonstration of advanced technologies such as advanced hypersonic systems, orbital systems, etc. Dynetics, in support of the U.S. Army’s Space and Missile Defense Command (SMDC), is currently developing the Multipurpose NanoMissile System (MNMS) to address these needs. Unlike past attempts in the arena of low cost, small launchers, the MNMS system is designed from the start to meet a low cost, responsive mission set. It is not simply a scaled down model of an expensive launch system. MNMS utilizes: \begin{itemize}\item Lowest cost materials (steel instead of aluminum)\end{itemize} \begin{itemize}\item Pressure-fed propellants instead of turbopumps. \end{itemize} \begin{itemize}\item Reliability & low part count over performance\end{itemize} \begin{itemize}\item Modular assembly for “made to order” capability\end{itemize} \begin{itemize}\item COTS wireless electronic component connectivity\end{itemize} \begin{itemize}\item Rapid validation through extensive tests\end{itemize} \begin{itemize}\item Safe fuel & oxidizer: ethane & nitrous oxide\end{itemize} \begin{itemize}\item “Ship & shoot” approach\end{itemize} \begin{itemize}\item Minimal range requirements\end{itemize} Through innovative, cost-driven, minimalist design, the MNMS team has applied lean, entrepreneurial practices to the challenges of space launch. The MNMS uses non-toxic liquid propellants that do not require cryogenic cooling below 0°F. These propellants, which remain liquid at non-cryogenic temperature under their own significant vapor pressure, eliminate the needfor turbopumps or complex tank pressurization hardware. The self-pressurizing nitrous oxide and ethane propellants used for all three main stages are storable, commonly available and easily handled. The rocket motor is submerged in the nitrous tank to reduce interstage mass and simplify propellant feeds for the motor and Liquid Injection Thrust Vector Control (LITVC). The use of propulsion modules with common components decreases the production costs of the MNMS...- Abstract document
- Manuscript document
IAC-10.D2.7.4.pdf (🔒 authorized access only).
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