Preliminary design of an isotope reentry vehicle /IRV/ for use with a Brayton cycle space power system.
Isotope reentry vehicle/Brayton cycle space power system design, noting blunt conical aeroshell housing of heat source capsule
Georgiev, S.↗
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Structural and decelerator design options for Mars entry.
Structural design options for decelerative aeroshell configurations for atmospheric entry on unmanned planetary explorations
Guy, L. D.↗
Tailoring polymers for entry into the atmospheres of Mars and Venus
Polymers development for ablative heat shields, aeroshell structures, antennas, insulators, electronic packaging, etc, to meet Mars and Venus atmospheric entry requirements
Nagler, R. G.↗
Gas physics environment of high altitude Jovian entry.
A description of the gas physics environment associated with high-altitude Jupiter entry is reported. Two aspects of environmental analysis are treated. First, limited discussion is devoted to prediction of the heating environment of the probe aeroshell. Prime emphasis is given to the second aspect of the analysis, a description of the gas particle probe interaction phenomena in the rarefied flow regime. Several molecular reemission models have been devised and exercised. Model selection was based upon the desire to bracket the expected reemission characteristics. Consideration was given to examining diffuse reflection as exemplified by the Maxwellian model and lobular, specular reflection as characterized by the Nocilla model. Variation of fundamental input parameters was investigated to determine particle-probe interaction sensitivity. Regardless of neutral species type, results show that the attenuation of the incoming flux of that species by reflected particles is approximately 15 per cent in the stagnation region at 200 km above the cloud tops.
Lefferdo, J. M.↗
Effects of nonequilibrium ablation chemistry on Viking radio blackout.
The length of the entry blackout period during descent of the Viking Lander into the Mars atmosphere is predicted from calculated profiles of electron density in the shock layer over the aeroshell. Nonequilibrium chemistry plays a key role in the calculation, both in the inviscid flow and in the boundary layer. This is especially true in the boundary layer contaminated with ablation material, for which nonequilibrium chemistry predicts electron densities two decades lower than the same case calculated with equilibrium chemistry.
Evans, J. S.↗
Deployment and performance characteristics of 1.5-meter supersonic attached inflatable decelerators
Attached-inflatable-decelerator (AID) canopies fabricated from lightweight Nomex cloth and tapes were deployed in a supersonic stream from the base of a 140 deg conical aeroshell. Characteristics of the deceleration system were obtained over a wide range of Mach number, dynamic pressure, and pitch angle. All models deployed rapidly by ram air and experienced only mild deployment shock loads. Steady-state drag coefficients as high as 1.3 were obtained in the supersonic stream and were relatively insensitive to Mach number, dynamic pressure, and pitch angle. All models were free of fluttering motion. Results also showed that the AID is aerodynamically more efficient without a burble fence in a supersonic stream. Though measured meridian-tape loads were higher than those predicted by theory, the ram-air deployment rates and steady-state drag coefficients were in good agreement with theory. These results indicate that the AID is a stable, efficient decelerator in a supersonic stream and its performance is readily predictable.
Bohon, H. L.↗
The Viking Mission
The Viking Mission is a scientific exploration of the planet Mars with particular emphasis on the search for life. Two unmanned spacecraft will be launched from Cape Kennedy in 1975 and will arrive at Mars in the summer of 1976. Each spacecraft will consist of an orbiter and lander. The landing sites will be preselected before launch and certified by orbital reconnaissance before landing. Soft landing on the surface will be accomplished by decelerating first on an aeroshell, then a deployed parachute and finally using terminal propulsion engines. Thirteen investigations will be performed, including mapping experiments from the orbiter, and analytical experiments on the surface which deal broadly with the biology, geosciences and atmospheric characteristics of the planet.
Martin, J. S., Jr.↗
Mars exploration with Viking
The Viking Mission is a scientific exploration of the planet Mars with particular emphasis on the search for life. Two unmanned spacecraft will be launched from Cape Kennedy in 1975 and will arrive at Mars in the summer of 1976. Each spacecraft will consist of an orbiter and lander. The landing sites will be preselected before launch and certified by orbital reconnaissance before landing. Soft landing on the surface will be accomplished by decelerating first on an aeroshell, then a deployed parachute and finally using terminal propulsion engines. Thirteen investigations will be performed, including mapping experiments from the orbiter, and analytical experiments on the surface which deal broadly with the biology, geosciences and atmospheric characteristics of the planet.
Martin, J. S., Jr.↗
Shock shapes of blunt bodies in hypersonic helium, air, and CO2 flows
A primary factor governing hypersonic flowfield characteristics of blunt vehicles entering planetary atmospheres is the normal shock density ratio. Hence, a means of duplicating or simulating the high density ratios experienced during planetary entry is needed. One facility having the capability of generating a range of hypersonic-hypervelocity flow conditions in arbitrary test gases is the expansion tube. Preliminary shock shape results obtained in the Langley 6-in. expansion tube at hypersonic conditions are presented. Normal shock density ratios from approximately 4 to 19 were generated using helium, air, and CO2 test gases at freestream velocities from 5 to 7 km/sec. Test models were a flat-faced cylinder and the Viking aeroshell.
Miller, C. G.↗
Flight tests of Viking parachute system in three Mach number regimes. 1: Vehicle description, test operations, and performance
Flight qualifications for parachutes were tested on full-scale simulated Viking spacecraft at entry conditions for the Viking 1975 mission to Mars. The vehicle was carried to an altitude of 36.6 km for the supersonic and transonic tests by a 980.000 cu m balloon. The vehicles were released and propelled to test conditions with rocket engines. A 117,940 cu m balloon carried the test vehicle to an altitude of 27.5 km and the conditions for the subsonic tests were achieved in free fall. Aeroshell separation occurred on all test vehicles from 8 to 14 seconds after parachute deployment. This report describes: (1) the test vehicle; (2) methods used to insure that the test conditions were achieved; and (3) the balloon system design and operations. The report also presents the performance data from onboard and ground based instruments and the results from a statistical trajectory program which gives a continuous history of test-vehicle motions.
Lundstrom, R. R.↗
Modern mechanisms make manless Martian mission mobile: Spin-off spells stairclimbing self-sufficiency for earthbound handicapped
Concepts were developed for three wheel chairs from progressively improving designs of a proposed unmanned roving vehicle for the surface exploration of Mars; as a spin-off, a concept for a stair-climbing wheel chair was generated. The mechanisms employed in these are described. The Mars mission is envisioned using the booster rockets and aeroshell of the Viking missions.
Sandor, G. N.↗
Buckling of structures; Proceedings of the Symposium, Harvard University, Cambridge, Mass., June 17-21, 1974
The papers deal with such topics as the buckling and post-buckling behavior of plates and shells; methods of calculating critical buckling and collapse loads; finite element representations for thin-shell instability analysis; theory and experiment in the creep buckling of plates and shells; creep instability of thick shell structures; analytical and numerical studies of the influence of initial imperfections on the elastic buckling of columns; mode interaction in stiffened panels under compression; imperfection-sensitivity in the interactive buckling of stiffened plates; buckling of stochastically imperfect structures; and the Liapunov stability of elastic dynamic systems. A special chapter is devoted to design problems, including the design of a Mars entry 'aeroshell', and buckling design in vehicle structures. Individual items are announced in this issue.
Budiansky, B.↗
Composition and structure of the Martian atmosphere - Preliminary results from Viking 1
Results from the aeroshell-mounted neutral mass spectrometer on Viking 1 indicate that the upper atmosphere of Mars is composed mainly of CO2 with trace quantities of N2, Ar, O, O2, and CO. The mixing ratios by volume relative to CO2 for N2, Ar, and O2 are about 0.06, 0.015, and 0.003, respectively, at an altitude near 135 kilometers. Molecular oxygen is a major component of the ionosphere according to results from the retarding potential analyzer. The atmosphere between 140 and 200 kilometers has an average temperature of about 180 plus or minus 20 deg K. Atmospheric pressure at the landing site for Viking 1 was 7.3 millibars at an air temperature of 241 deg K. The descent data are consistent with the view that CO2 should be the major constituent of the lower Martian atmosphere.
Nier, A. O.↗
Isotopic composition of the Martian atmosphere
Results from the neutral mass spectrometer carried on the aeroshell of Viking 1 show evidence for NO in the upper atmosphere of Mars and indicate that the isotopic composition of carbon and oxygen is similar to that of earth. Mars is enriched in N-15 relative to earth by about 75 per cent, a consequence of escape that implies an initial abundance of nitrogen equivalent to a partial pressure of at least 2 millibars. The initial abundance of oxygen present either as CO2 or H2O must be equivalent to an exchangeable atmospheric pressure of at least 2 bars in order to inhibit escape-related enrichment of O-18.
Nier, A. O.↗
Structure of the neutral upper atmosphere of Mars - Results from Viking 1 and Viking 2
Neutral mass spectrometers carried on the aeroshells of Viking 1 and Viking 2 indicate that carbon dioxide is the major constituent of the Martian atmosphere over the height range 120 to 200 kilometers. The atmosphere contains detectable concentrations of nitrogen, argon, carbon monoxide, molecular oxygen, atomic oxygen, and nitric oxide. The upper atmosphere exhibits a complex and variable thermal structure and is well mixed to heights in excess of 120 kilometers.
Nier, A. O.↗
Effect of end-ring stiffness on buckling of pressure-loaded stiffened conical shells
Buckling studies were conducted on truncated 120 deg conical shells having large end rings and many interior reinforcing rings that are typical of aeroshells used as spacecraft decelerators. Changes in base-end-ring stiffness were accomplished by simply machining away a portion of the base ring between successive buckling tests. Initial imperfection measurements from the test cones were included in the analytical model.
Davis, R. C.↗
Forebody and afterbody solutions of the Navier-Stokes equations for supersonic flow over blunt bodies in a generalized orthogonal coordinate system
A coordinate transformation, which can approximate many different two-dimensional and axisymmetric body shapes with an analytic function, is used as a basis for solving the Navier-Stokes equations for the purpose of predicting 0 deg angle of attack supersonic flow fields. The transformation defines a curvilinear, orthogonal coordinate system in which coordinate lines are perpendicular to the body and the body is defined by one coordinate line. This system is mapped in to a rectangular computational domain in which the governing flow field equations are solved numerically. Advantages of this technique are that the specification of boundary conditions are simplified and, most importantly, the entire flow field can be obtained, including flow in the wake. Good agreement has been obtained with experimental data for pressure distributions, density distributions, and heat transfer over spheres and cylinders in supersonic flow. Approximations to the Viking aeroshell and to a candidate Jupiter probe are presented and flow fields over these shapes are calculated.
Gnoffo, P. A.↗
A concept study of a remotely piloted vehicle for Mars exploration
Candidate configurations are discussed for shuttle-transported, spacecraft-deployed remotely piloted vehicles having individual aeroshells, parachutes, and scientific payloads for Mars exploration. Topics covered include aerodynamics; powerplants; structural materials; deployment and descent interface systems; payloads; secondary power; thermal control; navigation, guidance and control, communications, weight and center of gravity; performance; and flight testing. The advantages of the recommended electric-powered cruiser/lander configuration are summarized.
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