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Old 01-30-2019, 11:38 PM
luke strawwalker's Avatar
luke strawwalker luke strawwalker is offline
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Continued...

First, a cutaway showing the interior of the Mission Module (MM). Solar panels provide electricity, the MM provides living and work space for the crew during the mission. The CSM is powered down, only powered up during the midcourse corrections, since it provides all propulsion. Navigation would be done by ground tracking backed up by onboard sextant navigation done by the crew for the inputs for the guidance computer on the CM...

Second, The launch configuration of the Venus flyby mission with the MM under the LM panels on top of the S-IVB in place of the LM, and after transposition and docking to the MM after the S-IVB burn to put them into elliptical orbit. This would be how the spacecraft remained configured throughout the mission (unless it had to jettison the MM for an abort) until shortly before reentry back at Earth after the mission.

Third, the trajectory and timeline of the mission, from launch, through the first 100 nautical mile circular "parking orbit" (used for phase adjusting the spacecraft to the precise time and position for the second burn), the burn to the 70,000 nautical mile elliptical 48 hour orbit which provided most of the velocity needed to reach Venus before discarding the S-IVB stage, the transposition and docking with the MM and its solar arrays and communications antenna deployments, checkout and inspection, before arriving at the apogee of the 70,000 n. mi orbit the next day, where the SM would perform maneuvers to adjust the trajectory and phasing of the orbit in preparation for the main Trans-Venus Injection, a burn of the SM SPS for an additional 3,000 fps velocity needed to reach Venus, conducted 24 hours later during the perigee of the orbit at 100 nautical miles above Earth, to gain maximum advantage of the Oberth effect, which would place the spacecraft on course for Venus.

Fourth, the actual flight path of the spacecraft toward Venus on the flyby. Launch would have been on 5 April 1972, actually heading outbound from the Sun and Earth about 1/3 of the way toward Mars in a heliocentric orbit before swinging back inward past Earth's orbit and down toward Venus's orbit, rendezvousing with Venus in a flyby on 23 August 1972, and continuing on past the planet heading back "up" towards Earth, arriving back at Earth on 30 March, 1973 (the day after my second birthday!)

Fifth, Periapsis at Venus (closest approach altitude above Venus during the flyby) versus velocity of the reentry back at Earth... As well as the required velocity from the S-IVB and SM's SPS to achieve the required velocity to Trans-Venus Injection... The closer the approach, the more velocity required of the launch vehicle, and of course it also affected the timing of the launch as well, as indicated at the bottom of the chart...

Sixth, the Apollo Service Module performance requirements for various Trans-Venus Injection trajectories and velocities depending on the trajectory chosen and closest approach to Venus (periapsis)...

Later! OL J R
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