Wasp
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- 11 January 2010
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I'm searching for any bit of information about the EMW A11 rocket stage project, that was thought up by the advanced developement group of Peenemünde during the late years of the war, but never (at last not that we know of) reached a detailed developement stage.
The A11 stage should have been mated with the A9/A10 to create a three-stage rocket, that would have been estimated to be able putting a payload of 500kg into a low 300km orbit.
Further information are pretty scarce about this project.
The measures available should be:
Height: 25m
Diameter: 8,10m
Span: 15,30m or 16,10m
Mass: 586,000 kg
Thrust: 11,700.00 kn
no. of engines: 6
However all these measures (taken from http://www.astronautix.com/lvs/a9a10a11.htm and repeated through other sources in the web) seem not really confirmed and somewhat doubtful. I.e. the diameter of 8,10m, yet the A 10 with a span of 9m should be totally encased. That's hardly possible with 8,10m, isn't it?
There is an illustriation (see attachement below) that is stated as a drawing from 1946 for the US Army done based on the information Wernher von Braun gave them about the A9/10/11 project.
Another big question is the number and configuration of the engines. It's stated that it should be six A10 engines. However the recent Anigrand release incorporated 8 (don't know where they possibly got that info from). Also the six engined design has the open question of direction control. Should it have been achieved through giant graphit paddles like in the case of the one engined A4 or A10 (seems unpractically to me), or like planned in the early developement stages of the A10 with six engines, through direct control of the thrust of the single rocket engines (reducing thrust on one side would turn the rocket etc.)?
I also attached a drawing of the princilple of a six-engined rocket like the A10.
However I'm wondering if the plan for directional control through the thrust itself, which is basically a sound idea, would still work if all six single thrusts are combined by leading them through a venturi chamber shown?
Any help or opinion is appreciated.
Thanks!
The A11 stage should have been mated with the A9/A10 to create a three-stage rocket, that would have been estimated to be able putting a payload of 500kg into a low 300km orbit.
Further information are pretty scarce about this project.
The measures available should be:
Height: 25m
Diameter: 8,10m
Span: 15,30m or 16,10m
Mass: 586,000 kg
Thrust: 11,700.00 kn
no. of engines: 6
However all these measures (taken from http://www.astronautix.com/lvs/a9a10a11.htm and repeated through other sources in the web) seem not really confirmed and somewhat doubtful. I.e. the diameter of 8,10m, yet the A 10 with a span of 9m should be totally encased. That's hardly possible with 8,10m, isn't it?
There is an illustriation (see attachement below) that is stated as a drawing from 1946 for the US Army done based on the information Wernher von Braun gave them about the A9/10/11 project.
Another big question is the number and configuration of the engines. It's stated that it should be six A10 engines. However the recent Anigrand release incorporated 8 (don't know where they possibly got that info from). Also the six engined design has the open question of direction control. Should it have been achieved through giant graphit paddles like in the case of the one engined A4 or A10 (seems unpractically to me), or like planned in the early developement stages of the A10 with six engines, through direct control of the thrust of the single rocket engines (reducing thrust on one side would turn the rocket etc.)?
I also attached a drawing of the princilple of a six-engined rocket like the A10.
However I'm wondering if the plan for directional control through the thrust itself, which is basically a sound idea, would still work if all six single thrusts are combined by leading them through a venturi chamber shown?
Any help or opinion is appreciated.
Thanks!