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Longitudinal and lateral axes orientation of uniformly rotating or rapidly rotating vehicle utilizing outputs from solar sensors and lateral magnetometer
Rubidium vapor magnetometer used for near earth orbiting spacecraft, instrumentation and in-flight performance
This paper describes a small-weight and low-power magnetometer that was designed and built for the Mars '94 mission.
We theoretically propose and discuss properties of two schemes of an all-optical self-oscillating magnetometer based on an opto-electronic oscillator stabilized with an atomic vapor cell. Proof of the principle DC magnetic field measurements characterized with 2 x 10(exp -7) G sensitivity and 1 - 1000 mG dynamic range in one of the schemes are demonstrated.
The Free-Flying Magnetometer (FFM) is an autonomous spin-stabilized sensorcraft developed at the Jet Propulsion Laboratory (JPL) for the Enstrophy sounding rocket mission.
Four Free Flying Magnetometers (FFMs) flew on the Enstrophy sounding rocket launched on February 10, 1999 from Poker Flats Research Range.
The GOES-T Goddard Magnetometer (GMAG) sensor unit (SU) thermal design was validated by SU level thermal balance (TB) testing. The correlated SU thermal model was integrated to the observatory thermal model to predict the outboard SU temperatures and operating heater duty cycles in the worst cold case and worst hot case orbits. An orbit with the highest solar beta angle (23.5°) and an orbit with the lowest solar beta angle (0°) were run for each case. A comparison in the SU temperature predictions and heater duty cycles were made. The Autumnal Equinox (AE) cold case orbit is slightly colder than the Winter Solstice (WS) cold case orbit. The WS hot case orbit is slightly warmer than the March Equinox (VE) hot case orbit. Additionally, the lunar eclipse cold case orbit was run. It is the coldest environment. Using a 23°C set point for the SU cover heater controller, there is positive heater control for all the orbits. The heater duty cycle predictions for the AE worst cold case orbit and WS worst hot case orbit were 44.4% and 33% respectively. During the lunar eclipse, the heater cycle increases to 68.8% at the end of the eclipse. The temperature predictions for the bobbins are in the 21.9°C to 22.8°C range in the AE worst cold case orbit and in the 21.8°C to 23.0°C range in the WS worst hot case orbit. The SU temperatures during nominal operation on orbit were expected to be within the design goal, despite seasonal variations in solar beta angle and solar irradiance, and no solar flux in a lunar eclipse. The maximum operating SU cover flight heater duty cycle was expected to comply with GOLD Rule 4.25. The SU thermal design is now flight proven based on its long-term (>1 year) thermal performance on orbit.
Driven magnetometer accurately measures the components of a low strength magnetic field in each of three mutually perpendicular directions. To accomplish this, it employs the principle of magnetic resonance in optically pumped rubidium vapor.
Reversing, thermal, motor-driven device positions magnetometer sensors for checking zero offset. The device alternately positions two sensors at fixed positions 90 degrees apart. The thermal motor is fabricated completely of nonmagnetic materials.
Explorer XII magnetometer records
Latitudinal cross section of ionospheric current density profile of equatorial electrojet from rocketborne magnetometers
Cryogenic magnetometer to measure rectangular component of small magnetic fields and development of magnetic shielding
Stability and temperature sensitivity tests for flux gate sensors of cryogenic magnetometer
Systems engineering data on IMP magnetometer experiment to measure magnetic field in interplanetary space
Triaxis magnetometer measurements on earth magnetic field during Gemini 10 mission
Magnetometers for measuring stable magnetic fields produced by low field superconducting shields
Critical review of argument by Fredericks et al concerning ambiguity of IMP 1 data obtained from tilted spinning fluxgate magnetometers
Multirate sampling and generalized alias as error source in spacecraft magnetometer experiments