Comparison of small water-graphite nuclear rocket stages with chemical upper stages for unmanned missions
Small water-graphite nuclear rocket stages compared with chemical upper stages for use in unmanned spacecraft
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Small water-graphite nuclear rocket stages compared with chemical upper stages for use in unmanned spacecraft
Cement materials to attach thermocouple to stainless steel tubing in nuclear rocket engine nozzle, considering thermal conductivity, bond and tensile and compressive strengths
Variable property heat transfer equations and their applicability to nozzle of nuclear rocket Phoebus 2
Crew radiation dosage from fission fragments in plume from gas core nuclear rocket
Solid core nuclear reactor engine variables, considering specific impulse, engine weight, operating life and engine thrust
Feasibility of supporting liquid fuel on solid wall in radiating liquid core nuclear rocket concept
Effect of turbulent mixing on average fuel temperatures in gas-core nuclear rocket engine
Recirculation zone in fluid mechanics experiments on cylindrical cavity simulating gas core nuclear rocket as heavy gas reservoir, discussing flow patterns
Engine thrust, specific impulse, and uranium loss rate effects on gaseous fueled nuclear rocket engine weight
Radiation hazard from backflow of fission fragments from plume of gas-core nuclear rocket
Nozzle and cavity wall cooling limitations on specific impusle of gas-core nuclear rocket engine
Design, development, and characteristics of open cycle, gas core nuclear rocket engine
The problem of on-line digital computer control of the NERVA nuclear rocket engine is considered. Proposed is a method of State Dependent State Variable Feedback (SDSVF) as a practical approach to the control of NERVA and other complex nonlinear and/or time-varying systems. The difficulties inherent in other design methods are avoided by defining the optimal closed loop system in terms of a desired transfer function, rather than a performance index to maximize or minimize.
NASA has initiated planning and critical technology development for nuclear rocket propulsion systems for Space Exploration Initiative missions to the moon and to Mars. Interagency agreements are being negotiated between NASA, the Department of Energy, and the Department of Defense for joint technology development activities. This paper summarizes the activities of the NASA project planning team in FY 1990 that led to the draft Nuclear Propulsion Project Plan, outlines the FY 1991 Interagency activities, and describes the current status of the project plan.
An arc-heater driven hyperthermal convective environments simulator was recently developed and commissioned for long duration hot hydrogen exposure of nuclear thermal rocket materials. This newly established non-nuclear testing capability uses a high-power, multi-gas, wall-stabilized constricted arc-heater to produce hightemperature pressurized hydrogen flows representative of nuclear reactor core environments, excepting radiation effects, and is intended to serve as a low-cost facility for supporting non-nuclear developmental testing of hightemperature fissile fuels and structural materials. The resulting reactor environments simulator represents a valuable addition to the available inventory of non-nuclear test facilities and is uniquely capable of investigating and characterizing candidate fuel/structural materials, improving associated processing/fabrication techniques, and simulating reactor thermal hydraulics. This paper summarizes facility design and engineering development efforts and reports baseline operational characteristics as determined from a series of performance mapping and long duration capability demonstration tests. Potential follow-on developmental strategies are also suggested in view of the technical and policy challenges ahead. Keywords: Nuclear Rocket Engine, Reactor Environments, Non-Nuclear Testing, Fissile Fuel Development.
Linear optimal feedback control theory for nuclear rocket dynamics and control problems
Interfacial stability at thin flexible partition between fuel and propellant flows for gas core nuclear rockets
Effect of buoyancy on fuel containment in open-cycle gas-core nuclear rocket engine