Location
Cocoa Beach, FL
Start Date
5-4-1965 8:00 AM
Description
This paper discusses the capability of nuclear pulse propulsion in performing manned missions to Mars and other planets using a single-stage vehicle. Recently declassified descriptive data on a 10-meter-diam nuclear pulse propulsion module design (Saturn V compatible) is summarized and a typical complete exploration vehicle employing the module is described. The specific impulse of the propulsion module is 2,500 sec, its dry weight 200,000 Ib.
The mission versatility of this single vehicle design is emphasized. The same propulsion module, and essentially the same overall vehicle design, are shown capable of performing single-stage missions requiring velocity increments ranging from under 40,000 ft/sec to over 114,000 ft/sec. Total payloads ranging from 100,000 to 500,000 Ib are considered.
For a minimal Mars landing mission, roughly comparable to those proposed for less-capable, multi-staged propulsion systems, an earth-orbit departure weight of 6^0,000 Ib is indicated. A higher payload and propellant loading of the same vehicle, however, is considered preferable. Performing a complete Mars surface excursion mission in 200 to 250 days is shown as one optional way of exploiting the vehicle's capability. Carrying a considerably larger personnel complement, including scientists as well as astronauts, is another- Consistent with the latter idea> two reference design missions, presented in detail, employ retrothrust to return the vehicle to an elliptical earth orbit, avoiding the typically necessary atmospheric reentry maneuver as the final task of a long mission.
A Mars mission capability supported by a single launch, using a Saturn first stage, is also described. In this instance nuclear pulse propulsion is begun suborbitally, starting at an altitude greater than 50 nautical miles.
The major system advantages and systems problems are outlined and briefly discussed. Finally, a series of artist's conceptions of the major operational steps is presented.
Manned Planetary Exploration Capability Using Nuclear Pulse Propulsion
Cocoa Beach, FL
This paper discusses the capability of nuclear pulse propulsion in performing manned missions to Mars and other planets using a single-stage vehicle. Recently declassified descriptive data on a 10-meter-diam nuclear pulse propulsion module design (Saturn V compatible) is summarized and a typical complete exploration vehicle employing the module is described. The specific impulse of the propulsion module is 2,500 sec, its dry weight 200,000 Ib.
The mission versatility of this single vehicle design is emphasized. The same propulsion module, and essentially the same overall vehicle design, are shown capable of performing single-stage missions requiring velocity increments ranging from under 40,000 ft/sec to over 114,000 ft/sec. Total payloads ranging from 100,000 to 500,000 Ib are considered.
For a minimal Mars landing mission, roughly comparable to those proposed for less-capable, multi-staged propulsion systems, an earth-orbit departure weight of 6^0,000 Ib is indicated. A higher payload and propellant loading of the same vehicle, however, is considered preferable. Performing a complete Mars surface excursion mission in 200 to 250 days is shown as one optional way of exploiting the vehicle's capability. Carrying a considerably larger personnel complement, including scientists as well as astronauts, is another- Consistent with the latter idea> two reference design missions, presented in detail, employ retrothrust to return the vehicle to an elliptical earth orbit, avoiding the typically necessary atmospheric reentry maneuver as the final task of a long mission.
A Mars mission capability supported by a single launch, using a Saturn first stage, is also described. In this instance nuclear pulse propulsion is begun suborbitally, starting at an altitude greater than 50 nautical miles.
The major system advantages and systems problems are outlined and briefly discussed. Finally, a series of artist's conceptions of the major operational steps is presented.
