Author: G

National Archives Collection

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Image credit: General Dynamics / Convair
Images: National Archives

Space Tug Maintenance Concept

19710008955

The overall view shows a Cislunar Shuttle being approached by an unmanned maintenance Tug. The Tug has three replacement modules attached to a turntable assembly. The first view shows an expanded section of the Cislunar Shuttle with the Tug approaching. The Tug will be docked with the Cislunar Shuttle using a standard docking mechanism. The second small view shows the Tug harddocked to the Cislunar Shuttle. A module is being removed from the Shuttle. The third small view shows the turntable rotated and a module being installed in the Cislunar Shuttle. After the operation is completed the two vehicles are demated and the Tug backed off as depicted in the lower illustration.

Image credit: NASA
File source: NASA NTRS

MT70-6335 6-25-70

19710008955

Shown here is an artist’s concept of a manned Space Tug servicing a communications satellite. Servicing of satellites will be economical and desirable in many cases in the future. However, the satellites will have to be designed to permit servicing. Existing satellite systems which are designed without consideration of inspace maintenance probably could not be effectively serviced even by a highly sophisticated maintenance kit used in conjunction with a manned Tug.

Image credit: NASA
File source: NASA NTRS

SPS Space Transportation

Heavy-Lift Launch Vehicle (HLLV)

The reference HLLV is a two-stage, vertical takeoff, horizontal landing (VTOHL), fully reusable winged launch vehicle. The launch configuration and overall geometry are detailed in Figure 1. The vehicle uses sixteen CH4/02 engines on the booster (first stage) and 14 standard SSME’S on the orbiter (second stage). The booster engines employ a gas generator cycle and provide a vacuum thrust of 9.79X1O6 newtons each. The orbiter SMME’s provide a thrust of 2.O9x1O6 newtons each at 100% power level. The gross liftoff weight of the HLLV is 11,040 metric tons with a payload to LEO of 424 metric tonnes.

Figure 1. Reference Two-Stage Winged Orbiter Vehicle

Personnel Launch Vehicle (PLV)

The PLV provides for the transportation of personnel and priority cargo between Earth and low orbit. The reference vehicle is derived from the current Space Shuttle system. It incorporates a winged fly-back booster instead of the solid rocket boosters and has a personnel compartment in the orbiter payload bay capable of transporting 75 passengers. The overall configuration and vehicle characteristics are shown in Figure 2. The passenger module is also shown in the figure.

Figure 2. Personnel Launch Vehicle

Personnel Orbital Transfer Vehicle (POTV)

The functions of the POTV are to deliver personnel and cargo from LEO to GEO and to return personnel from GEO to LEO. The reference vehicle is a two-stage (common stage) LO2/LH2 configuration as illustrated in Figure 3.

Figure 3. Reference LO2/LH2 Common Stage POTV

Heavy-Lift Launch Vehicle (HLLV)

VTO/HL HLLV Concept – Series Burn (Reference Concept)
VTO/HL HLLV Concept – Parallel Burn
HTO/SSTO HLLV Concept
SB/VTO/HL HLLV (Small Payload Option)
PB/VTO/HL HLLV (Small Payload Option)

Personnel Orbital Transfer Vehicle (POTV)

As previously stated, the reference POTV concept utilized a two (common) stage propulsive element to transport crew and crew supplies and priority cargo to GEO. The stages are fueled in LEO and are capable of a roundtrip mission.

Orbital Crew Rotation/Resupply POTV Configuration

Earth-to-Orbit Systems

 A PB/VTO/HL HLLV configuration is shown in Figure 1.2-1 in the launch. configuration. As shown, both stages have common body diameter, wing and vertical stabilizer; however, the overall length of the second stage (orbiter)is approximately 5 m greater than the first stage (booster). The vehicle gross lift off weight (GLOW) is 7.14 million kg with a payload capability of 230,000 kg to the referenced earth orbit.

Figure 1.2-1. PB/VTO/HL HLLV Launch Configuration

An alternate (smaller payload) configuration of more conservative design (i.e, more closely resembling the STS configuration) is depicted in the launch configuration, Figure 1.4-1. This configuration was adopted to permit the use of documented STS aerodynamic and performance data to address certain specific technical issues relative to VTO/HL vehicle concepts.

Figure 1.4-1. PB/VTO/HL HLLV Mated System and Attach Structure

19820007651

Image credit: NASA
File source: NASA NTRS

SOC Concept Analysis

SOC BASIC ELEMENTS
SOC COMMUNICATIONS
SOC OPERATIONS FACILITIES
CONSTRUCTION AND FLIGHT SUPPORT OPERATIONS
Habitat Module Configuration
SOC Initial Concept
Platform Construction
OTV Retrieval and Assembly
Current Configuration
Manned Geosynchronous Mission

19800015850

Image credit: NASA
Image source: NASA NTRS

OTV Vehicle Studies Overview

MARTIN MARIETTA SPACE BASED OTV

PAYLOAD 12,000 UP/10,000 DN

BOEING SPACE BASED OTV

BALLUTE BRAKED

UNIQUE FEATURES

  • BALLUTE
    • NEXTEL/CS 105
    • 1500°F BACKWALL
    • 1 USE
  • HEATSHIELD-RSI
    • 20 USES
  • NO INITIAL ON-ORBIT ASSEMBLY

STAGE WEIGHT

  • DRY 9189
  • MAIN PROP 63890
  • OTHER FLUIDS 1,061
  • START BURN 74,190

GENERAL DYNAMICS MODULAR SPACE-BASED OTV

19880006549

Image credit: NASA

Image source: NASA NTRS

MOTV Vehicle Description

Duration:
Operations:		7-14 Days
45° Traverse to visit 4 satellites
CREW MODULE
Ignition Weight:
Payload
Dimensions
Crew Size:		11000 lb
2000 lb
15′ D x 15′ L
4
STAGE 1
Dry Weight:
Prop. Wt. (LO2/LH2)
Prop. System
Dimensions		4759 lbs
54733 lbs
RL-10 Cat 2B (2) @ 459 Isp
15′ D x 33′ L
STAGE 2
Same as Stage 1

19800015850

Image credit: NASA
File source: NASA NTRS