SEARCH · Engineering Papers
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
On Feb. 15, 1992 the HITEN spacecraft was inserted into orbit about the Moon. HITEN was launched on 24 January 1990, by Japan's Institute for Space and Astronautic Science (ISAS) and traversed the Earth's geotail region survived two aerobraking passes in the Earth's atmosphere (March 1991), and visited the regions near the Earth-Moon.
This paper describes the JPL discovery of an integrated trajectory, and the tracking and orbit determination suuport provided by JPL's Deep Space Network and Multimission Navigation Team in support of the final targeting for lunar insertion.
Biological experiments and effects on two primates to determine versatility of design of orbiting primate spacecraft
Linear parameter combinations for lunar orbit determination
System analysis to determine orbital parameters influence on mission scientific objectives under engineering constraints, using value function
Orbital imagery for planetary exploration - radar, visual, ultraviolet, infrared and passive microwave imaging systems
Contingency procedures for lunar orbit and transearth injection in lunar mission
Time optimal rendezvous maneuver between neighboring elliptic orbits, discussing propulsive jet system with variable thrust
Periodic orbits in highly perturbed dynamical systems, studying characteristic curves of various families in galactic-type potential
System analysis to determine orbital parameters influence on mission scientific objectives under engineering constraints, using value function
Wind tunnel tests of downwash aerodynamic surface incidence angles on Saturn S-1C booster coupled to Grumman C-4 orbiter shuttle
Safety requirements and guidelines are listed for the sortie module, upper stage vehicle, and space station for the earth orbit operations of the space shuttle program. The requirements and guidelines are for vehicle design, safety devices, warning devices, operational procedures, and residual hazards.
Current NASA planning envisions an ambitious Jupiter tour mission which will arrive at the planet in the year, 1984. The objectives of this mission are to broaden our knowledge of the outer solar system and in particular to extend our understanding of the physical processes at work in the Jupiter and Galilean satellite environment. To achieve these goals, precise spacecraft navigation is a fundamental requirement inasmuch as very near encounters with the satellites are necessary both for the planned scientific investigations and to reduce fuel requirements necessary for orbital insertion about the planet. This paper, deals with problems of producing precise spacecraft state estimates relative to the Galilean satellites, with the aid of both earth-based radio and on-board video data.
The results of the analysis conducted on the telemetry data from the prelaunch, launch, and flight activation phases of LANDSAT-2 spacecraft are presented according to subsystems and interrelationships that exist between subsystems. Subsystem characteristics are included along with the flight evaluation results. Flight data are compared to baseline data established at the 20 C plateau during thermal vacuum testing of the spacecraft. Evaluation guidelines are derived from the specifications developed from the LANDSAT program objectives: (1) acquisition of multispectral images of the surface of the earth; and (2) use of the LANDSAT-2 receiving, frequency translating, and transmitting equipment as a relay system to gather data from fixed earth-based sensor platforms which are operated by individual investigators. Data are presented on the first 50 orbits of the spacecraft.
Longitudinal and lateral-directional characteristics were obtained on several modified versions of the Rockwell International 140 A/B orbiter (0.010 scale). These modifications, designed to extend trim capability to center-of-gravity locations forward of the 65 percent fuselage station, consisted of two forebodies, two canard trimmers, and two body-wing fillets. Tests were performed over an angle-of-attack range of 12 to 36 degrees at a Reynolds number of 1.03 million based on body reference length. Data were obtained with the elevons and body flap deflected at the full-up and full-down design values. This investigation was conducted in the NASA Langley continuous flow hypersonic tunnel.
The author has identified the following significant results. Outside the U.S., various attempts were made to investigate the feasibility of utilizing orbital MSS imagery in the production of small scale land use maps. Overall, these studies are not as elaborate or extensive in their scope as the U.S. ones, and generally the non-U.S. investigators have employed nonsophisticated and less expensive techniques. A representative range of studies is presented to demonstrate the approaches and trends dealing with reprocessing, interpretation, classification, sampling, and ground truth procedures.
Tests were conducted in the LaRC 8-foot transonic pressure tunnel to determine effects of fuselage nose and wing fillet modifications on the transonic aerodynamic characteristics of a space shuttle orbiter configuration. In addition to reshaping the baseline wing planform fillet, small canards were added to the configuration. The modifications considered were of interest in extending the forward center-of-gravity boundary for the configuration.
A qualitative physical description of the orbital resonance mechanism based on a previously published (Greenberg et al. 1972; Greenberg, 1973) mathematical analysis is presented. The fundamental principles of the resonance mechanism are illustrated by an examination of the Titan-Hyperion case. More complex resonances, including Enceladus-Dione, Mimas-Tethys are considered. Resonance phenomena involving the rings of Saturn, the inner three satellites of Uranus, and the inner three Galilean satellites of Jupiter are also discussed. The role of analyses of resonance phenomena in developing theories of satellite formation and evolution is examined.