Shuttle Orbiter stellar-inertial reference system
Previously cited in issue 19, p. 2997, Accession no. A82-38963
Smith, F. E.↗
Engineering topics
Blucker, T. J.
Publications and source records attributed to Blucker, T. J..
Shuttle orbiter stellar-inertial reference system
The Space Shuttle stellar-inertial reference system is a velocity and attitude data source during flight operations. An overview of the reference system is presented as well as specifics discussing design concepts, functional operation, and performance capabilities. Techniques for star sighting and inertial measurement unit alignment and calibration are described, and alignment accuracy, star tracker capability, and gyro and accelerometer accuracy are discussed, with emphasis on flight test results. Test programs have confirmed that the system meets performance requirements such as being accurate to within 0.26 degree at the 400,000 foot altitude entry interface in order to execute an accurate touchdown, as well as demonstrating reusability, payload capability, and operational flexibility. Growth possibilities, such as the implementation of rendezvous target tracking, are discussed.
Smith, F. E.↗
Position determination from star-gravity measurements
Position determination on planetary surface from gravity and star line-of-sight direction measurements, presenting numerical results for Apollo lunar landing missions
Blucker, T. J.↗
A method for star vector determination from alignment optical telescope sighting
A method is described for determining the measured star vector in LM body coordinates when the measurement data consist of a spiral measurement, a cusor measurement, and a time associated with each measurement. The method is defined from alignment optical telescope (AOT) sightings from the LM on the lunar surface. This formulation will be coded into the real-time computer complex off-line AOT and gravity (AOT+G) bench program, the Gravity-Optics LM Attitude and Position (GOLAP) program.
Crigler, S. W.↗
Sun compass error model
An error model is described for the Apollo 15 sun compass, a contingency navigational device. Field test data are presented along with significant results of the test. The errors reported include a random error resulting from tilt in leveling the sun compass, a random error because of observer sighting inaccuracies, a bias error because of mean tilt in compass leveling, a bias error in the sun compass itself, and a bias error because the device is leveled to the local terrain slope.
Blucker, T. J.↗
A method for lunar roving vehicle position determination from three landmark observations with a sun compass
A simplified method is described for determining the position of the lunar roving vehicle on the lunar surface during Apollo 15. The method is based upon sun compass azimuth measurements of three lunar landmarks. The difference between the landmark azimuth and the sun azimuth is measured and the resulting data are voice relayed to the Mission Control Center for processing.
Blucker, T. J.↗
Verification of the Kalman filter equations used in the LM AGS
Kalman filter equations for processing rendezvous radar data in lunar module abort guidance system
Blucker, T. J.↗
Apollo CSM and LM onboard navigation system constraints
Apollo CSM and LM onboard navigation system constraints
Blucker, T. J.↗