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Kohlhase, C. E.

Publications and source records attributed to Kohlhase, C. E..

8 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1977

Voyager mission description

The Voyager project, which involves the 1977 launch of two advanced three-axis attitude stabilized spacecraft for the exploration of the Jovian and Saturnian systems, as well as interplanetary space, is discussed. The missions include investigation of the gravitational fields, atmospheric dynamics and magnetospheres of Jupiter and Saturn, the atmospheres, surface composition and features of Titan, the Io flux tube, the Great Red Spot of Jupiter, and earth occultation by Saturn's rings. To reduce energy required to reach Saturn, gravity-assist swingbys of Jupiter will be employed; a continuation to Uranus by the second satellite may be implemented by reliance on gravity-assist at Saturn.

Kohlhase, C. E.↗
NASA NTRS1977

Mariner Jupiter/Saturn 1977 mission design tradeoffs

The considered MJS77 project involves the launching of two spacecraft during a one-month launch period which opens on August 20, 1977. Each Mariner craft will perform a flyby mission through the Jupiter and Saturn planetary systems. The targets of the missions are discussed and a spacecraft description is presented. The mission design factors are considered, taking into account details concerning the trajectory selection process, the MJS77 mission module, the remote sensing capability of MJS77 science instruments, and the targeting option of a possible continuation of the mission to Uranus. Attention is given to the search for attractive trajectory candidates, the relationship between Saturn arrival data and Jupiter arrival dates of special interest, and observation sequences.

Kohlhase, C. E.↗
NASA NTRS1975

Autonomous navigation preparations for future unmanned space missions

In order to prepare for the era of autonomous navigation, this paper first examines existing techniques for spacecraft navigation by describing the basic elements of the Mark-I and II navigation technologies. The remainder of the paper deals with identification of criteria which necessitate onboard navigation, and with promising solutions now under consideration. An attractive solution possibility is proposed which utilizes narrow-angle optics, a charge-coupled device area-array image sensor, a small advanced onboard flight computer, and a simplified set of software algorithms. Onboard commands would be derived and sent to the appropriate spacecraft attitude control, propulsion, and science platform pointing subsystems. The proposed autonomous navigation system does not address all mission options, but focuses primarily on precision approach trajectory control and adaptive science instrument pointing for asteroid, cometary, and outer planet satellite missions.

Kohlhase, C. E.↗
NASA NTRS1973

Mariner/Jupiter/Saturn navigation in the presence of massive planetary satellites

Orbit determination accuracies attainable during a Mariner/Jupiter/Saturn encounter have been established by means of covariance analyses. Advanced earth-based multistation radiometric data, optical data consisting of star/satellite pictures provided by a narrow-angle TV camera on board the spacecraft, and batch sequential filtering methods were employed. An evaluation of sequential filter sensitivities to errors in modeling small nongravitational spacecraft accelerations is presented. Selected covariances developed in the orbit determination analysis are used in an investigation of the trajectory correction costs associated with a close Ganymede encounter. The 99 percentile Delta V contours in the Ganymede aiming plane are obtained for satellite encounters before or after Jupiter closed approach, and the sources of the dominant contributions to the Delta V costs are identified.

Hildebrand, C. E.↗
NASA NTRS1972

Navigation of 1975 Mars Viking mission.

This paper describes the Viking mission objectives and overall navigation profile from trans-Mars injection through the post-landing station-keeping phase. Included are interplanetary trajectory corrections, Mars orbit insertion, satellite orbit trims to acquire the landing site, lander separation and deorbit, entry, landing, and, finally, orbiter station keeping with the lander. The broad spectrum of navigation activities has strongly influenced the design of the Viking spacecraft and mission. The paper discusses fuel requirements to account for trajectory dispersions and uncertainties, requirements for navigation hardware and software, expected inflight uncertainties, satellite orbit adjustment for landing site acquisition, lander targeting techniques, lander trajectory reconstruction, and lander position determination.

Kohlhase, C. E.↗