Pegasus thermal design
Thermal design of micrometeoroid detector panels and electronics for Pegasus satellite
ELECTRONICS↗
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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.
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Space experiment thermal design
Thermal design of space experiment by analytical model for temperature regime acceptable to all experimental elements
Schach, M.↗
Final Thermal Design and Thermal Vacuum Testing of the StarBurst Instrument
The StarBurst Multimessenger Pioneer is a small satellite mission serving as a wide-field gamma-ray observatory designed to capture the initial emissions of short gamma-ray bursts, electromagnetic signatures of neutron star mergers. This paper presents the final thermal design and analysis of the StarBurst Instrument, comprising the bus-to-instrument interface plate, control electronics, and twelve crystal detector units, which form the core of the mission’s science capability. The passive thermal control system design requires consideration of restrictive keep-out zones, unknown orbital parameters, and narrow temperature limits of the detectors. Also summarized is the instrument level thermal vacuum cycle test, correlated model refinements, and updated model results. Following successful completion of the instrument test campaign, the hardware was integrated with the spacecraft bus for spacecraft level testing, including additional thermal vacuum testing. The results from the spacecraft level thermal vacuum test will further inform the instrument thermal model, ensuring accurate flight temperature predictions. StarBurst launches as a secondary payload in 2027 and has a mission duration of at least one year.
StarBurst↗
Guidelines for CubeSat's Thermal Design
Thermal and Fluids Analysis Workshop 2015, Silver Spring, MD. NCTS 19104-15. What does it take to thermally designlow cost, low mass cubesats? What are the differences in the approach when you compare with large scale missions?What additional risk is acceptable? What is the approach to hardware? How is the testing campaign run? These aresome of the questions that will be addressed in this course, which is designed to equip the attendees to support thedevelopment of cubesats at their organization.
0000↗
Space experiment thermal design
Thermal analysis and temperature control for spacecraft components and subsystems and thermal insulation procedures
Schach, M.↗
Thermal Design and Thermal Vacuum Testing of the StarBurst Instrument
The StarBurst Multimessenger Pioneer is a small satellite mission serving as a wide-field gamma-ray observatory designed to capture the initial emissions of short gamma-ray bursts, electromagnetic signatures of neutron star mergers. This paper presents the final thermal design and analysis of the StarBurst Instrument, comprising the bus-to-instrument interface plate, control electronics, and twelve crystal detector units, which form the core of the mission’s science capability. The passive thermal control system design requires consideration of restrictive keep-out zones, unknown orbital parameters, and narrow temperature limits of the detectors. Also summarized is the instrument level thermal vacuum cycle test, correlated model refinements, and updated model results. Following successful completion of the instrument test campaign, the hardware was integrated with the spacecraft bus for spacecraft level testing, including additional thermal vacuum testing. The results from the spacecraft level thermal vacuum test will further inform the instrument thermal model, ensuring accurate flight temperature predictions. StarBurst launches as a secondary payload in 2027 and has a mission duration of at least one year.
StarBurst↗
Final Thermal Design and Thermal Vacuum Testing of the StarBurst Instrument
Explore the source record for details and available documents.
Small Satellite↗
Thermal design and experiment thermal integration of the Long Duration Exposure Facility
The Long Duration Exposure Facility (LDEF) is a large (14 feet diameter by 30 feet long) Shuttle transported, reusable spacecraft. The LDEF can accommodate up to 13,000 pounds of experiments mounted in 86 standard trays. This paper describes the philosophy and approach used for the passive thermal design of the LDEF. Also discussed are the standardized guidelines and techniques used in the thermal design and integration of approximately 50 different thermally passive experiments. A technique for reducing multinode thermal models of experiments to 2 nodes is also presented. This approach allows the efficient thermal integration of large numbers of experiments with the LDEF spacecraft.
Greene, R. F., Jr.↗
Thermal Design and Flight Experience of the Mars Exploration Rover Spacecraft Computer-Controlled, Propulsion Line Heaters
This paper covers the design, thermal testing and flight experiences with the computer-controlled thermostats on the propulsion line heaters. Flight experience revealed heater control behavior with propellant loaded into the system and during thruster firings that was not observable during system level testing. Explanations of flight behavior, lessons learned, and suggestions for improvement of the propellant line heater design are presented in this paper.
propulsion lines↗
Thermal Design of the Thermal Infrared Spectrometer (TIRS) Instrument on PREFIRE
The Polar Radiant Energy in the Far-Infrared Experiment (PREFIRE) consists of two 6U CubeSats that each host a Thermal Infrared Spectrometer (TIRS) instrument. The CubeSats are scheduled for launch in March and October of 2023. The purpose of the TIRS instrument is to make spectrally resolved measurements of the Earth’s thermal radiation from the top of the atmosphere. PREFIRE will document, for the first time, variability in spectral fluxes from 4 to 54 microns on hourly to seasonal timescales. The primary mission is 12 months in a polar orbit with inclination of 82 to 98 at altitudes between 450 km and 650 km. The TIRS instrument is an Offner spectrometer that uses a thermopile detector array and a Schwarzchild telescope. In addition, there is a scan mirror which is periodically actuated for calibration. The instrument concept of operation is to collect radiation emitted towards zenith in a nadir sounding orientation with periodic internal and space calibrations. The TIRS thermal control architecture consists of entirely passive elements. The instrument requires all elements be maintained between 0 C and 50 C during operation for the duration of the mission. An overview of the overall thermal control design approach is presented.
Andrade, Andres↗
Solar Probe Plus MAG Sensor Thermal Design for Low Heater Power and Extreme Thermal Environment
The heater power available for the Solar Probe Plus FIELDS MAG sensor is less than half of the heritage value for other missions. Nominally the MAG sensors are in the spacecraft's umbra. In the worst hot case, approximately 200 spacecraft communication downlinks, up to 10 hours each, are required at 0.7 AU. These downlinks require the spacecraft to slew 45 deg. about the Y-axis, exposing the MAG sensors and boom to sunlight. This paper presents the thermal design to meet the MAG sensor thermal requirements in the extreme thermal environment and with low heater power. A thermal balance test on the MAG sensor engineering model has verified the thermal design and correlated the thermal model for flight temperature predictions.
Thermal design↗
Thermal design considerations
Thermal environment factors affecting electronic canister design for Pegasus satellite
THERMAL ENVIRONMENT↗
Orbital maneuvering vehicle thermal design and analysis techniques
This paper describes the OMV thermal design that is required to maintain components within temperature limits for all mission phases. A key element in the OMV thermal design is the application of a motorized thermal shade assembly that is a replacement for the more conventional variable conductance heat pipes or louvers. The thermal shade assembly covers equipment module radiator areas, and based upon the radiator temperature input to onboard computer, opens and closes the shade, varying the effective radiator area. Thermal design verification thermal analyses results are presented. Selected thermal analyses methods, including several unique subroutines, are discussed. A representation of enclosure Script F equations, in matrix form, is also included. Personal computer application to the development of the OMV thermal design is summarized.
Chapter, J.↗
Problems in the thermal design of spacecraft.
Spacecraft thermal design problems including computer programs, thermal control coatings, testing, etc
SPACECRAFT DESIGN↗
WMAP Observatory Thermal Design and On-Orbit Thermal Performance
The Wilkinson Microwave Anisotropy Probe (WMAP) observatory, launched June 30, 2001, is designed to measure the cosmic microwave background radiation with unprecedented precision and accuracy while orbiting the second Lagrange point (L2). The instrument cold stage must be cooled passively to <95K, and systematic thermal variations in selected instrument components controlled to less than 0.5 mK (rms) per spin period. This paper describes the thermal design and testing of the WMAP spacecraft and instrument. Flight thermal data for key spacecraft and instrument components are presented from launch through the first year of mission operations. Effects of solar flux variation due to the Earth's elliptical orbit about the sun, surface thermo-optical property degradations, and solar flares on instrument thermal stability are discussed.
Glazer, Stuart D.↗
Thermal Design Overview of the Mars Exploration Rover Project
Contents include the following: Mission Overview. Thermal Environments. Driving Thermal Requirements. Thermal Design Approach. Thermal Control Block Diagram. Thermal Design Description. Thermal Analysis Results Summary. Testing Plans. Issues & Concerns.
Tsuyuki, Glenn↗
Thermal design evaluation of Pegasus
Thermal design evaluation of meteoroid detector panels, louver system, and service module adaptor for Pegasus satellite
THERMAL EFFECT↗