Start Date
4-1981 8:00 AM
Description
Gravity Probe-B (GP-B) is an experiment under Phase B study at Marshall Space Flight Center which is designed to measure general relativistic induced torques on a gyroscope in orbit about the earth. The measurement of the relativistic effects requires that the gyror scope be nearly perfect in spherical shape and be shielded from the influences of nonre! ati vis tic effects. To accomplish these requirements, the spacecraft design includes provisions for superconducting magnetic shields, superconducting readout electonics, drag free gyro suspension, a drag free spacecraft, and provision for gyroscope spin-up at cryogenic temperatures. The spherical rotor fabrication has resulted in advances in manufacturing and measurement techniques in order to meet the experiment requirements. An essential feature of the spacecraft system which will be launched by the Shuttle is a large volume liquid helium dewar which will supply cooling to maintain the gyros and shields at a few degrees kelvin for over a one year duration. The helium which is boiled off is used to maintain drag free control of the spacecraft. This paper will discuss the design requirements for the experiment, the essential features of the proposed spacecraft, the gyro manufacturing technology, the gas spin-up method, and the liquid helium technology.
Gravity Probe-B: the Stanford General Relativity Experiment as a Shuttle Payload
Gravity Probe-B (GP-B) is an experiment under Phase B study at Marshall Space Flight Center which is designed to measure general relativistic induced torques on a gyroscope in orbit about the earth. The measurement of the relativistic effects requires that the gyror scope be nearly perfect in spherical shape and be shielded from the influences of nonre! ati vis tic effects. To accomplish these requirements, the spacecraft design includes provisions for superconducting magnetic shields, superconducting readout electonics, drag free gyro suspension, a drag free spacecraft, and provision for gyroscope spin-up at cryogenic temperatures. The spherical rotor fabrication has resulted in advances in manufacturing and measurement techniques in order to meet the experiment requirements. An essential feature of the spacecraft system which will be launched by the Shuttle is a large volume liquid helium dewar which will supply cooling to maintain the gyros and shields at a few degrees kelvin for over a one year duration. The helium which is boiled off is used to maintain drag free control of the spacecraft. This paper will discuss the design requirements for the experiment, the essential features of the proposed spacecraft, the gyro manufacturing technology, the gas spin-up method, and the liquid helium technology.
Comments
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