The configuration selected, provided the lightest practical lunar launch stage. The Apollo vehicle recommended was readily adaptable to lunar landing missions.
The design selected involved a multiple tank system with the lunar landing units jettisoned prior to takeoff. 31 38 3. Another possible approach technique was the direct approach to the moon's surface without any intermediate parking orbit.
Similarly, midcourse guidance would correct for deviations in the earth-moon trajectory so that the spacecraft would arrive at the required location with the required velocity for entry into the lunar orbit. Juli 1969 statt - ein Mensch betrat erstmalig den Mond.
Status: Study 1962.Height: 14.10 m (46.20 ft).. Command, mission, and propulsion modules were designed primarily for lunar orbit, with flexibility and growth potential built in for more advanced missions (such as a lunar landing) with the same basic vehicle …
Mondspaziergang. The aerodynamic fairing surrounding the tanks for earth launch provided an excellent meteorite shield. Mond Mondlandung. This ellipse was entered by applying a small decrement of velocity somewhere between a quarter revolution and a half revolution from the landing area. During the final approach, the landing area was surveyed for possible obstacles, and any necessary maneuvering to avoid these was performed. The circumlunar version would have a total length of 14.1 m. The M-3 vehicle with foldable wings was one logical evolution from the M-2. Eventually, the requirement to re-enter, fly in, and land at an existing airport, or to ferry vehicles from one base to another would be justifiable. Overall length was minimized by the internal conical tie-in structure inside the tank. 19 28 1. These goals were not entirely compatible, and the resulting material represented a compromise solution to the problem. Elimination of long inter-stage adapters; duplicate application of the lunar launch engine for landing, reliability inherent with multiple tanks, protection afforded the internally mounted take-oft tank, and ease of manufacture all contributed to establishing this preference. Ferry flights would be powered and fuelled by detachable engines and fuel pods. Apollo 14: Start: 31.1.1971.
The clustered, pressure-stabilized, cylindrical tanks provided an ideal combination of light weight, reliability, and ease of manufacture. Elementary experiments that would evolve into rendezvous, docking, artificial gravity, maneuverable landing, and an eventual lunar landing were foreseen. The primary change was replacement of the circumlunar propulsion module with a larger, dual-purpose system. Stability and control testing of the M-1 shape would yield applicable data for reducing flap size, weight, and cross coupling effects.
29 28 7. Roter Apollo. After entering the lunar orbit, prior to the descent to the surface, the orbit would be accurately established by observations with an altimeter and horizon scanner.
Attitude control was provided by the existing engines mounted on the mission module during takeoff and by the two 4K engines during landing. The reduction in gravity losses by increasing thrust was offset by the higher weight of the propulsion system. The powered descent time was the order of six minutes. It was most efficient to use liquid hydrogen as fuel for both the launch and landing stages because: The airlock could be jettisoned to lighten the return take-off load.
The latter were attached to the mission module, and were available on the return trip to earth, after the landing tanks have been jettisoned.