Venus halo - Photometric evidence for ice in the Venus clouds

Venus halo and photometric evidence for ice in Venus cloud

Cost effective alternative to low irradiance measurements

Martin Marietta's Space Simulation Laboratory (SSL) has a Thermal Environment Simulator (TES) with 56 individually controlled heater zones. The TES has a temperature range of approximately minus 129 C to plus 149 C. Because of the ability of TES to provide complex irradiance distributions, it is necessary to be able to measure a wide range of irradiance levels. SSL currently uses ambient temperature controlled radiometers with the capacity to measure sink irradiance levels of approximately 42.6 mw/sq cm, sink temperature equals 21 C and up. These radiometers could not be used to accurately measure the lower irradiance levels of the TES. Therefore, it was necessary to obtain a radiometer or develop techniques which could be used to measure lower irradiance levels

Transfer orbit stage mechanisms thermal vacuum test

A systems level mechanisms test was conducted on the Orbital Sciences Corp.'s Transfer Orbit Stage (TOS). The TOS is a unique partially reusable transfer vehicle which will boost a satellite into its operational orbit from the Space Shuttle's cargo bay. The mechanical cradle and tilt assemblies will return to earth with the Space Shuttle while the Solid Rocket Motor (SRM) and avionics package are expended. A mechanisms test was performed on the forward cradle and aft tilting assemblies of the TOS under thermal vacuum conditions. Actuating these assemblies under a 1 g environment and thermal vacuum conditions proved to be a complex task. Pneumatic test fixturing was used to lift the forward cradle, and tilt the SRM, and avionics package. Clinometers, linear voltage displacement transducers, and load cells were used in the thermal vacuum chamber to measure the performance and characteristics of the TOS mechanism assembly. Incorporation of the instrumentation and pneumatic system into the test setup was not routine since pneumatic actuation of flight hardware had not been previously performed in the facility. The methods used are presented along with the problems experienced during the design, setup and test phases

The 1969 opposition effect of Mars - Full disc, Syrtis Major and Arabia

Photometric analysis of brightness surge on Mars surfac

Moon - Optical properties of Apollo 11 samples

Optical properties of lunar powder samples from Tranquility Bas

Optical properties of Apollo 12 moon samples

Optical measurements on Apollo 12 soil samples from lunar mare surface

Unfolding the air vanes on a supersonic air-launched missile

ASALM (Advanced Strategic Air-Launched Missile) is a supersonic air vehicle designed to be air-launched from a carrier aircraft. The four aft aerodynamic control vanes are folded to maximize the number of missiles carried on-board. The unfolding (erection) system must be small, energetic, fast, and strong. The materials selected and problems that arose during development of the unfolding system are described

A photogeologic comparison of Skylab and LANDSAT images of southwestern Nevada and southeastern California

There are no author-identified significant results in this report

The Influence of Topography on the Formation of Temporary Bright Patches on Mars

Influence of topography on formation of bright patches on Mar

Physical properties of the Apollo 12 lunar fines

Optical and radio frequency electrical properties and grain size analyses of Apollo 11 and 12 lunar soil sample