Study of heat shielding requirements for manned Mars landing and return missions Final report
Heat shielding and material testing for manned Mars landing and hyperbolic reentry missions
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Heat shielding and material testing for manned Mars landing and hyperbolic reentry missions
Project Fire was undertaken by the National Aeronautics and Space Administration to measure the total and radiative heating experienced by a blunt body reentering the earth's atmosphere at 11 300 meters per second. This report presents a photographic record of the Fire II spacecraft during its reentry. The photographs were clear enough to establish the times of major events, and they show that adequate-separation was maintained between the reentry package and the spent Antares. This report also identifies operational problems encountered in spacecraft reentry at hyperbolic velocities and presents the solutions satisfactorily employed.
Environmental and ablative materials performance affecting heat shielding requirements of slender and blunt vehicles during hyperbolic reentry
Calculated ablative quantities for nylon phenolic heat shielding materials of hyperbolic reentry vehicles
Apollo command module, biconic and cone hyperbolic reentry vehicles engineering, discussing L/D ratio, heat protection and weight
Reentry flight corridor depth reduction as result of inadequate flight data at hyperbolic speeds, noting overshoot limit and inverted attitude
Reentry flight corridor depth reduction as result of inadequate flight data at hyperbolic speeds, noting overshoot limit and inverted attitude
Optimum trajectory control for minimum heating paths during manned vehicle reentry at hyperbolic speeds
Optimum navigation measurements for satellite orbit and hyperbolic free fall reentry
Manned space vehicle reentry at circular to hyperbolic velocities, considering deceleration, corridor width, heating, heat protection, vehicle weight, lateral ranging, and landing factors
Minimization of total heat input for manned vehicles entering atmosphere at hyperbolic speeds
Optimum entry vehicle design using aerobreaking for manned earth entry at hyperbolic speeds, examining blunted conic, biconic and tetrahedral configurations
Optimum entry vehicle design using aerobreaking for manned Earth entry at hyperbolic speeds, examining blunted conic, biconic and tetrahedral configurations
Vehicles for circular and hyperbolic entry by manned spacecraft
Multipurpose manned reentry vehicle capable of entry at circular to hyperbolic velocities - design study
Recently, Li and Sanders have introduced a class of finite difference schemes to approximate generally discontinuous solutions to hyperbolic systems of conservation laws. These equations have the form together with relevant boundary conditions. When modelling hypersonic spacecraft reentry, the differential equations above are frequently given by the compressible Euler equations coupled with a nonequilibrium chemistry model. For these applications, steady state solutions are often sought. Many tens (to hundreds) of super computer hours can be devoted to a single three space dimensional simulation. The primary difficulty is the inability to rapidly and reliably capture the steady state. In these notes, we demonstrate that a particular variant from the schemes presented can be combined with a particular multigrid approach to capture steady state solutions to the compressible Euler equations in one space dimension. We show that the rate of convergence to steady state coming from this multigrid implementation is vastly superior to the traditional approach of artificial time relaxation. Moreover, we demonstrate virtual grid independence. That is, the rate of convergence does not depend on the degree of spatial grid refinement.
Body shape, entry angle and velocity, and weight to area ratio effects on radiative heating rates and total heat input of vehicles entering the earths atmosphere at hyperbolic velocities