SASSTO

SASSTO (Saturn Application Single-Stage-to-Orbit) combined launch vehicle and spacecraft. Only 62.3 ft (19m.) tall, a single plug-nozzle engine would serve both as launch vehicle and for soft-landing back on Earth after an orbital mission. The craft – seen here with a Gemini two-man capsule – would be recovered intact and could be used repeatedly. It would be a particularly appropriate for ferry missions into Earth-orbit including the emergency rescue of astronauts.

  1. Optional fairing around the two-man Gemini Capsule;
  2. Gemini adapter section;
  3. Transition support structure;
  4. Orbit injection / retro and control propellant tanks (6);
  5. Toroidal liquid-oxygen tank;
  6. Annular combustion chamber;
  7. Truncated plug nozzle and re-entry heat shield;
  8. Attitude-control system (4);
  9. Retractable landing legs (4);
  10. Spherical liquid-hydrogen propellant tank.

Text from Frontiers of Space by Philip Bono & Kenneth Gatland, 1969

SASSTO at Astronautix

Philip Bono at Astronautix

Image credit: Douglas

Image source(s):

SDASM Archives

Numbers Station

Skylab by Neil Jacobe

B&W (As seen in Roundup dated Nov. 24, 1967)
NOV. 67 S-67-51373

MANNED SPACE CENTER, HOUSTON, TEXAS

ORBITAL WORKSHOP — Artist’s concept showing how a Saturn S-IVB stage will appear when converted to the Apollo Applications Orbital Workshop. Launched fully fueled with airlock and docking adaptor attached, the S-IVB’s liquid hydrogen tank becomes a shirtsleeve environment workshop after the fuel has been depleted. At left is an Apollo Command and Service Module launched separately and docked into one of the docking adaptor’s ports. The Apollo Telescope Mount is shown docked into one of the side ports. The ATM will be joined to the cluster in a second phase of the program. Solar cell “wings” to provide power fold outward from the S-IVB after orbit is achieved. McDonnell Douglas Corporation’s Missile and Space Systems Division is making the S-IVB orbital workshop modifications under contract to NASA Marshall Space Flight Center and McDonnell Astronautics Company is developing the airlock under contract to MSC. (MCDONNELL DOUGLAS PHOTOGRAPH)

Look closely and you’ll notice subtle differences between this version of the painting and a colour rendering found in the SDASM Archives I’ve shared before.

If you’re interested in seeing more of Jacobe’s work, his artwork for the Douglas MOL can be found here. The images are small and plastered with watermarks, so it’s a bit of a tease but they are beautiful.

Skylab at Astronautix

Image credit: NASA

Image source: Numbers Station

Apollo Flight Configuration

The Saturn V configuration is shown in inches and meters as illustrated by the Boeing Company. The Saturn V vehicle consisted of three stages: the S-IC (first) stage powered by five F-1 engines, the S-II (second) stage powered by five J-2 engines, the S-IVB (third) stage powered by one J-2 engine. A top for the first three stages was designed to contain the instrument unit, the guidance system, the Apollo spacecraft, and the escape system. The Apollo spacecraft consisted of the lunar module, the service module, and the command module. The Saturn V was designed perform lunar and planetary missions and it was capable of placing 280,000 pounds into Earth orbit.

Saturn V at Astronautix

Image credit: NASA

Image source: NASA MSFC

Saturn V Apollo

Saturn V at Astronautix

Image credit: NASA

Image source: NASA MSFC

Mercury Space Capsule

Project Mercury at Astronautix

Image credit: NASA

Image source: Numbers Station

532 Flyback Booster

Shuttle Program at Astronautix

Grumman & Boeing Phase B at PM View

Image credit: Grumman

Image source: NASA NTRS

Inside Deimos

ROMBUS

Configuration for a manned Mars mission (Project Deimos).

  1. Six man Mars landing capsule;
  2. Pressurized tunnel;
  3. Toroidal living compartment;
  4. Liquid hydrogen tanks (8);
  5. Spherical liquid oxygen tank
  6. Booster centerbody.

Project Deimos – Mars Landing Module

  1. Earth-return capsule;
  2. Command centre and pressurized tunnel;
  3. Separation joint, for return to Mars orbit;
  4. Mars landing propellant tanks(6);
  5. Ground access hatch;
  6. Mars-launch platform;
  7. Payload and power supply equipment compartment;
  8. Mars-launch propellant tank;
  9. Landing and take-off rocket motor;
  10. Jettisonable closure panel;
  11. Mars-entry heat shield;
  12. Extensible landing gear(4);
  13. Altitude-control system quads (4).

Text from Frontiers of Space by Philip Bono & Kenneth Gatland, 1969

Project Deimos at Astronautix

Philip Bono at Astronautix

Image credit: Douglas

Image source: Numbers Station

Pegasus Cutaway & Plan

Pegasus Intercontinental Passenger Rocket

  1. Forward pressure dome;
  2. Two-man crew compartment;
  3. Re-entry stabilization fines (2);
  4. Cargo compartment;
  5. Aft pressure dome;
  6. Pressurized cabin for passengers (170);
  7. Deck structure (4) with passenger couches (43 each).

Pegasus during atmospheric re-entry uses the LH2-cooled plug nozzle as a heat shield. The ballistic transport would convey 172 passengers and freight 7,456 miles (12,000 km.) in 39 min. without exceeding an acceleration of 3g during ascent or re-entry. At the arrival spaceport it would hover on rocket thrust during a soft landing in the vertical attitude.

Pegasus Passenger Compartment

  1. Four-level passenger access doors (3);
  2. Stairways (2) connecting four passenger decks;
  3. Double-wall acoustic damping structure;
  4. Luggage racks (9);
  5. Re-entry stabilization fins (2).

Text from Frontiers of Space by Philip Bono & Kenneth Gatland, 1969

Pegasus at Astronautix

Image credit: Douglas / Blandford Press

Image source(s):

Numbers Station

SDASM Archives

518 Flyback Booster

Shuttle Program at Astronautix

Grumman & Boeing Phase B at PM View

Image credit: Grumman

Image source: NASA NTRS

518 Structural Arrangement

Shuttle Program at Astronautix

Grumman & Boeing Phase B at PM View

Image credit: Grumman

Image source: NASA NTRS