NAR Pogo Vehicle North American version of the one-man lunar pogo. Credit: via Jean-Christophe Carbonel |
Status: Study 1966. Gross mass: 82 kg (180 lb). Unfuelled mass: 49 kg (109 lb). Specific impulse: 290 s.
It relied on manual control obtained by thruster gimballing for pitch and roll, and jetavators for yaw. Communication was limited to the PLSS VHF line of sight, voice system. Navigation and guidance was done visually with aids such as maps and a sextant to determine initial flight direction. The F1B had a fueled mass of 82 kg, a range of 20 km, and would take $11.1 million and 24 months to develop.
LFV Concepts Summary Pogo Single-Crew Surface to Surface F1A F1B F1C Fueled Mass(kg) 64 82 310 Range(km) 8 20 170 Crew Size 1 1 1 Development Cost($M) 10.6 11.1 13.4 Development Time(Mos) 24 24 24 Multiman Surface to Surface F2A F2B F2C F2D F3A F3B F3C F3D Fueled Mass(kg) 288 392 530 788 529 1074 2066 4209 Range(km) 20 50 100 200 50 200 400 800 Crew Size 2 2 2 2 3 3 3 3 Development Cost($M) 29.1 29.5 30.1 30.9 30.8 32.7 36.8 44.5 Development Time(Mos) 42 42 42 42 42 42 42 42 Surface to Lunar Orbit F2E F3E Fueled Mass(kg) 1106 1476 Crew Size 2 3 Development Cost($M) 33.0 34.8 Development Time(Mos) 42 42
Crew Size: 1.
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