LLV - LRSA Credit - © Mark Wade

Many versions of new Lunar Logistic Vehicles (LLV's) using several possible candidate propellants were studied by NASA and its contractors in the mid-1960's for post-Apollo lunar base support. By the time budget cutbacks ended such thoughts, NASA was favoring a two-stage version powered by throttleable RL10 engines burning liquid oxygen/liquid hydrogen propellants.

Limiting the propellant candidates to those being used in active NASA programs (earth storables of the N204/Aerozine 50 and cryogens of the L0X/LH2 type), the choice revolved about a tradeoff between 33% better Isp performance, poorer length to diameter configurations, and more extensive ground support requirements of LOX/LH 2 compared to N204/Aerozine 50. However, the performance increase did provide significantly larger payload capabilities, and accordingly, the cryogenic combination was chosen by NASA for the new LLV's. In addition to the conventional one stage configurations, two stage versions were also of interest. A typical two stage LLV consisted of a braking stage (LI) and a landing stage (LII). The advantages of staging were (i) payload improvement, (2) the landed vehicle had a lower center-of-gravity (reducing possible cargo unloading problems and landing gear requirements), and (3) the braking stage (LI) could be a general use propulsion stage for integration into earth orbital or planetary programs (Multi-Mission Module Concept).

Length: 7.90 m (25.90 ft). Maximum Diameter: 6.70 m (21.90 ft). Span: 21.30 m (69.80 ft). Mass: 41,000 kg (90,000 lb). Payload: 13,700 kg (30,200 lb). Main Engine Thrust: 131.210 kN (29,497 lbf). Main Engine Propellants: Lox/LH2. Main Engine Propellants: 23,500 kg (51,800 lb). Main Engine Isp: 444 sec. Electrical System: Batteries.

• LLV L-I.  Other Designations: L-I. Part of: LLV. Class: Manned. Type: Spacecraft Module. Purpose: Lunar orbit insertion of Lunar Logistics Vehicle lander and payload.

  Lunar Orbit Insertion stage for placing LLV into lunar orbit. Propulsion 2 x RL10-A3 with N2O4/MMH thrusters for orientation, midcourse, and ullage.

  Length: 2.70 m (8.80 ft). Basic Diameter: 6.70 m (21.90 ft). Maximum Diameter: 6.70 m (21.90 ft). Mass: 10,500 kg (23,100 lb). RCS Propellants: N2O4/MMH. Main Engine Thrust: 131.210 kN (29,497 lbf). Main Engine Propellants: Lox/LH2. Main Engine Propellants: 9,200 kg (20,200 lb). Main Engine Isp: 444 sec. Spacecraft delta v: 1,100 m/s (3,600 ft/sec). Electrical System: Batteries.

• LLV L-II.  Other Designations: L-II. Part of: LLV. Class: Manned. Type: Spacecraft Module. Purpose: Delivery of lunar base elements from lunar orbit to lunar surface.

  Landing stage for delivery of up to 13,400 kg payload from lunar orbit to lunar surface. Propulsion 2 x RL10-A3 with N2O4/MMH thrusters for orientation, midcourse, and ullage.

  Length: 5.20 m (17.00 ft). Basic Diameter: 6.70 m (21.90 ft). Maximum Diameter: 21.30 m (69.80 ft). Mass: 18,500 kg (40,700 lb). RCS Propellants: N2O4/MMH. Main Engine Thrust: 131.210 kN (29,497 lbf). Main Engine Propellants: Lox/LH2. Main Engine Propellants: 14,300 kg (31,500 lb). Main Engine Isp: 444 sec. Spacecraft delta v: 2,400 m/s (7,800 ft/sec). Electrical System: Batteries.

• 1969 September 1 - Soviets study NASA's ambitious plans -
  NASA gave the US President a 130-page programme outlining plans for America's future space programme. The thing read to the Soviets like a science fiction novel, with reusable space ferries, huge orbital stations and lunar bases, nuclear rocket stages, and manned Mars expeditions. There was no way the Soviet Union could compete with such a programme -- and that was leaving unconsidered the massive American military space progamme. Additional Details: Soviets study NASA's ambitious plans.