Minimum impulse thruster valve design and development
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minimum impulse thruster valve↗
Engineering topics
Yankura, G.
Publications and source records attributed to Yankura, G..
A Propulsion System for a Scientific Micro/Nanospacecraft
A preliminary propulsion system design for a 10-100kg. micro/nanospacecraft for generic scientific missions is described. The design drives resulting in this proposed system are discussed as well as current technology developments.
Microspacecraft↗
Advanced Storable Propulsion Technologies for Low-Cost Mars Sample Return
The propulsion requirements for ascent from the surface of Mars as part of a Mars sample return mission exceed the capabilities of current state-of-the-art chemical propulsion systems.
low-cost ascent surface Mars sample return mission↗
Advanced helium regulator for a fluorine propellant system
The space storable propulsion module is an advanced high performance (375 seconds Isp minimum) planetary spacecraft propulsion system with a mission life of 5-10 years. The propellants used are liquid fluorine and amine fuel. This application requires high pressure regulator accuracy to optimize propellant depletion characteristics. An advanced regulator concept was prepared which is compatible with both fuel and oxidizer and which features design concepts such as redundant bellows, all-metallic/ceramic construction, friction-free guidance of moving parts and gas damping. Computer simulation of the propulsion module performance over two mission profiles indicated satisfactory minimization of those propellant residual requirements imposed by regulator performance variables.
Wichmann, H.↗
Survey of materials for hydrazine propulsion systems in multicycle extended life applications
An assessment is presented of materials compatibility data for hydrazine monopropellant propulsion systems applicable to the Space Shuttle vehicle missions. Materials were evaluated for application over a 10-yr/100-mission operational lifetime with minimum refurbishment. A general materials compatibility rating for a broad range of materials and several propellants based primarily on static liquid propellant immersion testing and an in-depth evaluation of hydrazine decomposition as a function of purity, temperature, material, surface conditions, etc., are presented. The most promising polymeric material candidates for propellant diaphragms and seals appear to have little effect on increasing hydrazine decomposition rates, but the materials themselves do undergo changes in physical properties which can affect their 10-yr performance in multicycle applications. The available data on these physical properties of elastomeric materials as affected by exposure to hydrazine or related environments are presented.
Coulbert, C. D.↗