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The Mars Project
About this book
This classic on space travel was first published in 1953, when interplanetary space flight was considered science fiction by most of those who considered it at all. Here the German-born scientist Wernher von Braun detailed what he believed were the problems and possibilities inherent in a projected expedition to Mars.
Today von Braun is recognized as the person most responsible for laying the groundwork for public acceptance of America's space program. When President Bush directed NASA in 1989 to prepare plans for an orbiting space station, lunar research bases, and human exploration of Mars, he was largely echoing what von Braun proposed in The Mars Project.
Today von Braun is recognized as the person most responsible for laying the groundwork for public acceptance of America's space program. When President Bush directed NASA in 1989 to prepare plans for an orbiting space station, lunar research bases, and human exploration of Mars, he was largely echoing what von Braun proposed in The Mars Project.
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Yes, you can access The Mars Project by Wernher Von Braun,Henry J. White in PDF and/or ePUB format, as well as other popular books in Biological Sciences & Military & Maritime History. We have over one million books available in our catalogue for you to explore.
Information
A
THREE-STAGE FERRY VESSELS
1. COMPILATION OF MAIN DATA WITH SYMBOL MEANINGS
TABLE 1. ORBIT OF DEPARTURE
| Period of revolution | T1 | 2 hr |
| Orbital radius | RS,E | 8,110 km |
| Altitude above earth's surface | yS,E | 1,730 km |
| Orbital velocity | vci,1 | 7.07 km/sec |
TABLE 2. FIRST STAGE
| Thrust (at expansion to an exit pressure equal to the ambient pressure) | FI | 12,800 t |
| Take-off weight | W0,I | 6,400 t |
| Empty weight | WE,I | 700 t |
| Final weight (1st stage empty; 2d and 3d stages full) | W1,I | 1,600 t |
| Mass ratio | EI | 4 |
| Ratio of empty weight of 1st stage to propellant weight | kI | 0.146 |
| Propellant weight | WP,I | 4,800 t |
| Rate of propellant flow |  | 55.81 t/sec |
| Exhaust velocity | uI | 2,250 m/sec |
| Nozzle exit pressure | Pe,I | 0.7 kg/cm2 |
| Nozzle exit area | Ae,I | 224 m2 |
| Initial acceleration (absolute) | a0,I | 18.64 m/sec2 |
| Take-off acceleration (relative) | at0,I | 8.83 m/sec2 |
| Final acceleration (absolute) | a1,I | 87.0 m/sec2 |
| Burning time | tI | 84 sec |
| Cut-off altitude | yI | 40 km |
| Cut-off velocity | VI | 2,350 m/sec |
| Cut-off distance | xI | 50 km |
| Angle of elevation at cut-off | φI | 20.5° |
| Distance between take-off and landing (1st stage) | xL,I | 304 km |
| Length of 1st stage (without fins) | LI | 29 m |
| Diameter of 1st stage | DI | 20 m |
Note: 1 t = 1 metric ton = 1,102 short tons
TABLE 3. SECOND STAGE
| Thrust | FII | 1,600 t |
| Initial weight | W0,II | 900 t |
| Empty weight | WE,II | 70 t |
| Final weight (2d stage empty; 3d stage full) | W1,II | 200 t |
| Mass ratio | EII | 4.5 |
| Ratio empty weight 2d stage to propellant weight | kII | 0.10 |
| Propellant weight | WP,II | 700 t |
| Rate of propellant flow | | 5.6 t/sec |
| Exhaust velocity | uII | 2,800 m/sec |
| Nozzle exit pressure | pe,II | 24.11 g/cm2 |
| Nozzle exit area | Ae,II | 300 m2 |
| Initial acceleration (absolute) | a0,II | 17.4 m/sec2 |
| Final acceleration (absolute) | a1,II | 78.8 m/sec2 |
| Burning time | tII | 124 sec |
| Cut-off altitude | yII | 64 km |
| Cut-off velocity | vII | 6,420 m/sec |
| Cut-off distance (from take-off) | xII | 534 km |
| Angle of elevation at cut-off | φII | 2.5° |
| Distance between take-off and landing (2d stage) | xL,II | 1,459 km |
| Length of 2d stage | LII | 14 m |
| Aft diameter of 2d stage | DII | 20 m |
| Front diameter of 2d stage | DIII | 9.8 m |
TABLE 4. THIRD STAGE (MANEUVER OF ASCENT)
| Thrust | FIII | 200 t |
| Initial weight | W0,III | 130 t |
| Empty weight without payload | WE,III | 22 t |
| Final weight after maneuver of ascent | W1,III | 78.5 t |
| Ratio empty weight of 3d stage to its total | ||
| propellant load | kIII | 0.265 |
| Propellant load (total) | WP,III | 83 t |
| Propellant load (maneuver of ascent) | WP,III,01 | 51.5 t |
| Rate of propellant flow | | 702 kg/sec |
| Exhaust velocity | uIII | 2,800 m/sec |
| Nozzle exit pressure | pe,III | 10 g/cm2 |
| Nozzle exit area | Ae,III | 74 m2 |
| Initial acceleration (absolute) | a0,III | 15.1 m/sec2 |
| Final acceleration (absolute) | a1,III | 25.0 m/sec2 |
| Burning time | tIII,01 | 73 sec |
| Cut-off altitude | yIII | 102 km |
| Cut-off velocity | vIII | 8,260 m/sec |
| Cut-off distance from take-off | xIII | 1,054 km |
| Angle of elevation at cut-off | φIII | 0° |
TABLE 5. THIRD STAGE (MANEUVER OF ADAPTATION)
| Thrust | FIII | 200 t |
| Initial weight | W1,III | 78.5 t |
| Final weight after adaptation maneuver | W2,III | 66.6 t |
| Burning time | tIII,12 | 17 sec |
| Velocity increment for adaptation | vIII,12 | 460 m/sec |
TABLE 6. THIRD STAGE (RETURN MANEUVER IN THE ORBIT)
| Thrust (half-throttle) | ½FIII | 100 t |
| Initial weight | W3,III | 32.2 t |
| Final weight (landing weight) | W4,III | 27 t |
| Landing payload | WN,III,34 | 5 t |
| Burning time | tIII,34 | 14.8 sec |
| Velocity decrement for return maneuver | vIII,34 | 480 m/sec |
| Altitude of perigee of landing ellipse | yp | 80 km |
| Landing speed | vL | 105 km/h |
TABLE 7. THIRD STAGE (DIMENSIONS)
| Length of body | LIII | 15 m |
| Aft diameter | DIII | 9.8 m |
Table of contents
- Cover Page
- Title Page
- Copyright Page
- Contents
- Foreword
- Preface to the 1962 Edition
- Introduction
- A: Three-Stage Ferry Vessels
- B: Space Ships
- C: Landing Boats
- D: Ferry Flights and General Logistics
- E: Power Plant Performance
- F: Interplanetary Radio Communication