This timeline was generated on the Integrated Mission Program (IMP). All burn events over 2 seconds are finite with IMP solving a two point boundary value setup for begin burn time, burn time and control angles. Perigee and apogee shown above are mean orbital values. Significant events are listed. Each finite thrust event has two lines. The first is the beginning time showing the initial conditions, thrust and ISP used. The second has the end burn conditions and the delta v and time of burn. This case is an abort from the 750 x 750 phasing abort, using the taxi's main engines. An abort using the Reaction Control System (RCS) was also investigated but required a large increase in RCS propellant and was abandoned.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Human Mars Mission Performance Crew Taxi Profile


    Contributors:

    Publication date :

    1999-10-07


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Manned Mars mission crew factors

    Santy, Patricia A. | NTRS | 1986


    Manned MARS Mission Crew Factors

    P. A. Santy | NTIS | 1986