From “Astronautics at Armstrong Whitworth’s” by HR Hilton
In reference to diagrams “but to obtain good definition, all edges and the nose of the vehicle are shown completely sharp. Optimum resistance to heating effects would, of course, require a blunted nose and substantial edge radii.”
Trailing edge control design.
Wing area – 332 sq ft
Wing structure weight at 5 lb/sq ft = 1,660 lb
Fins 140 lb
Capsule, including 2 pilots, instruments, etc. 2,000 lb
Retro rockets, fuel and tanks. 200 lb
Control actuator, power supplies, etc. 120 lb
= 4,120 lb
Wing loading – 12.4 lb/sq ft
Theoretical AW design for booster.
100 ft tall (ref RAF Flying Review 1959) Total weight 160 tons
First stage 133.5 tons. Of which 120 tons is oxidiser and fuel.
41 ft long 13 ft diameter.
Fully gimballed motor unit – sea level thrust of 450,00 lb.
Propellant specific impulse of 270 lb/sec mass ratio of 4.0
Height and spedd of burn out 40 miles and 9,700 ft/sec at 40 degree to the horizontal
Burning time 161 sec.
Image stage jettisoned.
Second stage 22.07 tons of which 19.85 tons of propellants same as first stage.
Gimballed motor of 69,400 lb thrust for 173 sec.
To height of 75 miles speed 21,000 ft/sec 3 degrees.
Coasting for several minutes to above 80 miles while ground computers take readings and calculate third stage burn time.
Third stage gimballed motor thrust of 30,000 lb same “species” of propellants.
Speed 26,640 ft/sec at burn out.