AKA: Ballistisches Einstufiges Traeger-Aggregat III;Ballistisches Enistufiges Traeger-Aggregat III. Status: Study 1987. Payload: 17,000 kg (37,000 lb). Thrust: 1,070.00 kN (240,540 lbf). Gross mass: 780,000 kg (1,710,000 lb). Apogee: 90 km (55 mi).
The BETA III / STV-100 launch vehicle with a 100 passenger cabin had a launch mass of about 780 metric tons. 685 metric tons propellants were required for ascent, leaving a net mass of 75 metric tons, including 12.5 metric tons propellants for maneuvering, reserves and landing. The total cabin mass was estimated to be 11.6 metric tons, plus 8.4 metric tons for the passengers and crew. The cargo capability of the unmanned version would be 17 metric tons.
The cabin design featured a 6.5 m diameter pressure vessel with three levels, each one equipped with 34 seats in a circular arrangement, providing an optimum viewing opportunity for each passenger. In the center was a relatively large cylindrical zero-g exercise volume. Ample space for galleys, toilets, storage boxes and equipment was provided. On top of the passenger cabin was a cockpit with seats for the Commander and the Tourist Guide. Although the mission would be performed completely automatically a chief pilot was felt to be required for psychological reasons. In addition, three attendants would take care of the passengers. The seats would be inclined almost horizontally for the launch and landing phases. The cabin diameter is about 6.5 m.
The BETA STV-100 Mass Summary was as follows:
The total thrust level at take-off was 10700 kN, providing a launch acceleration of 1.4 g. which Koelle had found to be optimum for SSTO vehicles. 12 to 24 engines would be arranged around plug nozzle with a center engine to minimize base drag at launch and to perform orbital maneuvers (injection, retro impulses). The average specific impulse including the plug nozzle effect at ascent was assumed to be 428 sec, with 350 sec at launch and 455 s in vacuum.
During ascent the thrust level was reduced by throttling and/or cutting off selected engines in order to achieve the maximum performance and limit the thrust acceleration to some 3.5 g. Use of an optimum throttling program indicated a remarkable reduction of velocity losses and the total required velocity.
In fact the design greatly resembled the first stage of Russia's N1 moon rocket.
LEO Payload: 17,000 kg (37,000 lb) to a 90 km orbit at 6.00 degrees. Development Cost $: 2,000.000 million. Launch Price $: 2.000 million in 1969 dollars in 1969 dollars.