Engineering topics
Publications and source records attributed to Levin, G. M..
The Orbital Refueling System (ORS); force torque sensor; Plasma Motor/Generator (PMG) proof of function; voice controlled system; infrared intercommunications; superfluid helium on orbit transfer; laser docking sensor; and the Small Expendable Deployment System (SEDS) are summarized.
The Flight Demonstration Program was initiated by the Office of Space Flight in October 1983. The purposes of this program are to conduct an ongoing series of flight demonstrations which demonstrate critical enabling technology to potential Shuttle users and at the same time provide hands on experience to NASA engineers. Flight demonstrations are selected through a peer review process in response to an annual solicitation issued by the Flight Demonstration Office at NASA Headquarters. As of July 1985 one major flight demonstration has been successfully conducted, two flight demonstrations are scheduled to fly in November on STS 61-B, and five flight demonstrations are in various stages of development and planned to be flown during the next three years.
Seven scientific instruments are presently being studied for use with the Large Space Telescope (LST). These instruments are the F/24 Field Camera, the F/48-F/96 Planetary Camera, the High Resolution Spectrograph, the Faint Object Spectrograph, the Infrared Photometer, and the Astrometer. These instruments are being designed as facility instruments to be replaceable during the life of the Observatory.
In order that the LST meet its scientific objectives and also be a National Astronomical Space Facility during the 1980's and 1990's, broad requirements have been levied by the scientific community. These scientific requirements can be directly translated into design requirements and specifications for the scientific instruments. The instrument ensemble design must be consistent with a 15-year operational lifetime. Downtime for major repair/refurbishment or instrument updating must be minimized. The overall efficiency and performance of the instruments should be maximized. Modularization of instruments and instrument subsystems, some degree of on-orbit servicing (both repair and replacement), on-axis location, minimizing the number of reflections within instruments, minimizing polarization effects, and simultaneous operation of the F/24 camera with other instruments, are just a few of the design guidelines and specifications which can and will be met in order that these broader scientific requirements be satisfied.-
Jovian turbopause probe mission, discussing atmospheric composition measurements and nonsurvivable system concept
Mission planning for Jovian turbopause probe
Venus atmosphere exploration by multiple entry probe, describing spacecraft system design, launch and earth-Venus transfer trajectory, approach and entry sequence, etc
Entry vehicle design for planetary exploration using nonsurviving needle-nosed probe for data collection on Mars atmosphere composition, pressure and density
Mars atmosphere models for entry vehicle design