Cutaway of 1946 and
Credit: © Mark Wade
German winged orbital launch vehicle. Von Braun's 1952 design for a reusable space launcher used the same mass and performance calculations done in 1948. However the large parachute cannisters were replaced by deployable drag skirts. This allowed the design to be substantially less squat and more elegant than the 1948 version  but still fatter than the sleek paintings that appeared in print!
For the drawings and paintings to illustrate the 1952 Colliers series and subsequent books, the 1948 version was found to be too dumpy and squat to inspire. Therefore, Von Braun, in collaboration with artist Rolf Klep, sketched a much more elegant tapered launch vehicle design. The still somewhatsquat official version became even more stretched and elegant looking in the artist's renderings. This can be contrasted with Von Braun's Redstone, then already in design, which used the uninspiring but efficient cylindrical body that would be the basis of his later Jupiter and Saturn rockets. One can only conclude that Von Braun went along with the artist's desires for a more glamorouslooking rocket ship.
The base diameter of the first stage remained the same, but those of the upper stages were drastically reduced. To make more room for engines in the base, the parachute package was changed from a centrallylocated canister to a steelmesh circular drag brake, stored along the outer fuselage. The engine concept was now changed from an annular nozzle to separate conventional bellnozzle engines. Since the first stage diameter was the same, and the parachute canister that took up half its diameter was deleted, there was enough room in the first stage for 52 such engines. However there were real problems in using the 1948 calculations for the upper stages.
The second stage diameter was reduced from 20 m to 13.5 m. There was simply not enough base area for the total nozzle area indicated in Von Braun's original calculations. This could have been remedied if the chamber pressure was increased, as was clearly possible by 1952. However that should have resulted in a higher specific impulse, but the 1948 calculations were used 'asis'. Klep's illustrations showed Redstonetype lowexpansion ratio engines, inconsistent with the area ratio calculated in 1948 and needed for the high engine performance.
Similarly, the third stage diameter was reduced from 9.8 m to 5.8 m, with the same logical problem, since in the original calculation the nozzle occupied the entire base of the third stage.
LEO Payload: 25,000 kg (55,000 lb) to a 1,730 km orbit at 23.50 degrees.
Stage Data  Von Braun 1952
 Stage 1. 1 x Von Braun 19521. Gross Mass: 5,500,000 kg (12,100,000 lb). Empty Mass: 700,000 kg (1,540,000 lb). Thrust (vac): 141,286.300 kN (31,762,424 lbf). Isp: 257 sec. Burn time: 84 sec. Isp(sl): 217 sec. Diameter: 20.00 m (65.00 ft). Span: 37.00 m (121.00 ft). Length: 36.50 m (119.70 ft). Propellants: Nitric acid/Hydrazine. No Engines: 51. Status: Study 1952.
 Stage 2. 1 x Von Braun 19522. Gross Mass: 770,000 kg (1,690,000 lb). Empty Mass: 70,000 kg (154,000 lb). Thrust (vac): 16,271.100 kN (3,657,889 lbf). Isp: 298 sec. Burn time: 124 sec. Diameter: 13.50 m (44.20 ft). Span: 13.50 m (44.20 ft). Length: 20.70 m (67.90 ft). Propellants: Nitric acid/Hydrazine. No Engines: 34. Status: Study 1952.
 Stage 3. 1 x Von Braun 19523. Gross Mass: 105,000 kg (231,000 lb). Empty Mass: 22,000 kg (48,000 lb). Thrust (vac): 2,033.800 kN (457,216 lbf). Isp: 296 sec. Burn time: 105 sec. Diameter: 5.80 m (19.00 ft). Span: 48.00 m (157.00 ft). Length: 23.40 m (76.70 ft). Propellants: Nitric acid/Hydrazine. No Engines: 5. Status: Study 1952.
AKA: A12.
Status: Study 1952.
Gross mass: 6,400,000 kg (14,100,000 lb).
Payload: 25,000 kg (55,000 lb).
Height: 97.00 m (318.00 ft).
Diameter: 20.00 m (65.00 ft).
Thrust: 119,300.00 kN (26,819,700 lbf).
Apogee: 1,730 km (1,070 mi).
More...  Chronology...
Associated Countries
Associated Engines

Von Braun2 Notional Nitric acid/UDMH rocket engine. 461.5 kN. A11, Von Braun studies 19431952. Isp=286s. More...

Von Braun3 Notional Nitric acid/UDMH rocket engine. 392.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle. More...

Von Braun1 Notional Nitric acid/UDMH rocket engine. 3057.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle. More...
See also

Von Braun In 1948, with the US Army's V2 test project winding down, Wernher Von Braun was ensconced in isolated Fort Bliss. He had, unusually, some time on his hands. He occupied himself by writing a novel concerning an expedition to Mars, grounded on accurate engineering estimates. As an appendix to the novel he documented his calculations. More...

Winged In the beginning, nobody (except Jules Verne) thought anybody would be travelling to space and back in ballistic cannon balls. The only proper way for a space voyager to return to earth was at the controls of a real winged airplane. More...
Associated Manufacturers and Agencies

Von Braun American manufacturer of rockets and spacecraft. Von Braun, USA. More...
Bibliography

Von Braun, Wernher, and Ley, Willy, La Conquista del Espacio, Espasacalpe, SA, Madrid, 1966.
Associated Stages

Von Braun 19521 Nitric acid/Hydrazine propellant rocket stage. Loaded/empty mass 5,500,000/700,000 kg. Thrust 141,286.30 kN. Vacuum specific impulse 257 seconds. More...

Von Braun 19522 Nitric acid/Hydrazine propellant rocket stage. Loaded/empty mass 770,000/70,000 kg. Thrust 16,271.10 kN. Vacuum specific impulse 298 seconds. More...

Von Braun 19523 Nitric acid/Hydrazine propellant rocket stage. Loaded/empty mass 105,000/22,000 kg. Thrust 2,033.80 kN. Vacuum specific impulse 296 seconds. More...
Von Braun 1952 Chronology
1952 February 11  .
Launch Vehicle:
Von Braun 1952.
 Collier's Man Will Conquer Space Soon  .
Nation: USA. Related Persons: von Braun; Ley. Summary: Collier's magazine published papers from First Symposium on Space Flight, under the title "Man Will Conquer Space Soon.". This was an important step in the popularization of the idea of manned space flight..
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