Advanced product development
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Advanced Projects Design Team Team-X↗
Engineering topics
Miyake, R. N.
Publications and source records attributed to Miyake, R. N..
The Technology Development Status of the Solar Probe
The continuing development of new spacecraft technologies promises to enable the Solar Probe to be the first mission to travel in the atmosphere or corona of the Sun. The most significant technology challenge is the thermal shield that would protect the spacecraft from the flux of 3000 Suns (400 W/cm**2) at the perihelion radius of 4 solar radii while allowing the spacecraft subsystems to operate at near room temperature.
Solar↗
Lightweight composite mirror analysis and testing
The Jet Propulsion Laboratory InterDisciplinary Model for precision composite structures is described along with the HAVOC composite computer code used to study laminate mirror facesheets. The composite mirror panel thermal behavior is described in addition to structural and optical characteristics. Environmental mirror performance testing and performance test/prediction correlation are covered.
Helms, R. G.↗
Large Deployable Reflector (LDR) thermal characteristics
The thermal support group, which is part of the lightweight composite reflector panel program, developed thermal test and analysis evaluation tools necessary to support the integrated interdisciplinary analysis (IIDA) capability. A detailed thermal mathematical model and a simplified spacecraft thermal math model were written. These models determine the orbital temperature level and variation, and the thermally induced gradients through and across a panel, for inclusion in the IIDA.
Miyake, R. N.↗
Large deployable reflector thermal characteristics in low earth orbits
Preliminary results are presented from the development of a thermal analytical tool capable of analyzing the orbital thermal characteristics of a Large Deployable Reflector (LDR) spaceborne astronomical instrument for observations in the 30-micron to 1-mm range. This LDR thermal analytical tool is a 9X6-node reflector thermal model to be used in conjunction with the thermal analyzer program SINDA, as well as the orbital heat flux program TRASYS for the computation of solar and IR radiation and orbit-related input data.
Wu, Y. C.↗
Starprobe thermal shield system design concepts
The mission goals, flight trajectory, and material durability requirements for the NASA Starprobe spacecraft are reviewed. The spacecraft will use a Jovian gravity assist to pass within four solar radii of the sun to study fields and particles near the sun, perform experiments dealing with relativity and gravity, and observe the structure of the solar atmosphere from the photosphere to the corona. Constraints on the system size and mass design are given, and the system is noted to be required to withstand 2500 K at perihelion, thermally insulate the instrument payload, have a tube for optical measurements, and provide protection from meteorite damage. A secondary shield is also required to dispense thermal radiation that passes the primary shield and could endanger the payload. Design options are discussed, along with temperature control requirements and a conical carbon-carbon primary shield with mass-loss rate characteristics sufficient to meet a 2.5 mg/sec criterion.
Maag, C. R.↗
System requirements of Starprobe thermal shield
The mission of the Starprobe Spacecraft is to do in situ exploration of the solar corona to four solar radii. A thermal shield is required to protect the spacecraft equipment from a 3000 sun incident solar energy level caused by this close approach to the sun. The thermal shield requirements discussed include configuration, material requirements, temperature level, penetrations, outgassing and mass loss, and contamination as referenced to spacecraft mission parameters. Further, the size of the spacecraft will be limited by the space transport system orbiter payload bay dimensions, thus defining the upper limit of the relative sizes and locations of the heat shield and spacecraft equipment.
Miyake, R. N.↗