Mercury orbiter transport study

A data base and comparative performance analyses of alternative flight mode options for delivering a range of payload masses to Mercury orbit are provided. Launch opportunities over the period 1980-2000 are considered. Extensive data trades are developed for the ballistic flight mode option utilizing one or more swingbys of Venus. Advanced transport options studied include solar electric propulsion and solar sailing. Results show the significant performance tradeoffs among such key parameters as trip time, payload mass, propulsion system mass, orbit size, launch year sensitivity and relative cost-effectiveness. Handbook-type presentation formats, particularly in the case of ballistic mode data, provide planetary program planners with an easily used source of reference information essential in the preliminary steps of mission selection and planning

Solar electric propulsion - A survey technology status and mission applications

Solar electric propulsion characteristics and capability for automated missions throughout solar syste

Error analysis of celestial-inertial navigation for low-thrust interplanetary vehicles

Error analysis of celestial-inertial navigation for low thrust electrically propelled interplanetary space vehicle

Asteroid (Flora and Eros) sample-return missions via solar electric propulsion

The characteristics and capabilities of solar electric propulsion for performing sample-return missions to the asteroids Flora and Eros are considered. Trajectory/payload analysis and mission design tradeoff options are emphasized

On the problem of comet orbit determination for spacecraft intercept missions

Optimal linear estimation of comet orbit for spacecraft intercept missio

Pioneer Mars 1979 mission options

A preliminary investigation of lower cost Mars missions which perform useful exploration objectives after the Viking/75 mission was conducted. As a study guideline, it was assumed that significant cost savings would be realized by utilizing Pioneer hardware currently being developed for a pair of 1978 Venus missions. This in turn led to the additional constraint of a 1979 launch with the Atlas/Centaur launch vehicle which has been designated for the Pioneer Venus missions. Two concepts, using an orbiter bus platform, were identified which have both good science potential and mission simplicity indicative of lower cost. These are: (1) an aeronomy/geology orbiter, and (2) a remote sensing orbiter with a number of deployable surface penetrometers

Trajectory and propulsion characteristics of comet rendezvous opportunities

Trajectory and propulsion characteristics of spacecraft rendezvous mission opportunities to comets during 1975 to 199

Analysis of an optimal celestial-inertial navigation concept for low-thrust interplanetary vehicles

Celestial-inertial navigation for interplanetary electrical propulsion vehicl

Low-thrust trajectory and payload analysis for solar system exploration utilizing the accessible regions method

Accessible regions method for delineating generalized low thrust trajectory energy requirements and payload capabilities of vehicle systems for exploration of solar syste

Low-thrust Trajectory Capabilities for Exploration of the Solar System Using Nuclear Electric Propulsion

Low-thrust trajectory requirements for solar system exploration using nuclear electric propulsio