Future Expansion
There are plenty of candidates for future additions to the spacecraft simulated in Project Apollo after the basic historical Command/Service Module and Lunar Module are complete.
Spacecraft
Command/Service Module
Support may be added for the proposed Block-III CSM designed for extended orbital operations, the Block-IV CSM with batteries for power and LEM engines in place of the SPS and the Block-V intended for long duration lunar missions with one fuel cell replaced by two SNAP-27 RTGs.
In addition, the inclusion of a Block-I CSM in future versions has been discussed.
CSM Shuttle
In 1967 North American Rockwell patented a proposal to turn the Apollo CSM into something resembling a miniature space shuttle with a payload bay in the Service Module, fins on the rear, retractable wings in the bottom of the SM, and X-15 style landing gear with a nose-wheel at the front of the SM and skids at the rear:
"An aerospace vehicle comprising a substantially conical forward crew compartment or command module mated to a substantially cylindrical rearward service module. Aerodynamic fairings are provided along the midline on the sides of the cylindrical portion and a substantial distance aft thereof for providing lift at hypersonic velocities and approximately vertical fins are provided on the fairings for aerodynamic stability and control. Wings are mounted within the aerodynamic fairings at high velocities and pivotably extended therefrom at lower velocities and altitudes to provide low speed lift."
This is explained in detail in US Patent 3,576,298.
Recycled/Renovated Command Modules
In 1966 North American/Rockwell proposed to NASA that recovered CSMs should be returned to the manufacturer for re-use, this ranged from a simple renovation of the Command Module to permit it to be re-launched in a future mission, to converting it into an experiment station/airlock for use on Apollo Applications flights.
Apollo Logistics Spacecraft
This was an Apollo CSM modified to carry freight and six astronauts into orbit in support of Earth orbital Apollo Applications Program missions.
The proposed craft, like the Block IV CSMs planned for the Apollo to Venus mission replaced the fuel cells with batteries and the SPS with a single LM descent engine
Proposed launch vehicles included the Titan IIIc or Saturn Ib.
CSM Experiments Pallet
Proposed modification of the Service Module to permit a variety of Earth/Lunar orbit experiments to be carried. In a more limited form, this modification saw light as the SIM bay on Apollo 15-17.
Bell Aerospace One Man Lunar Flying Unit
Simple one manned rocket, using the remaining fuel from the LM descent stage. It was intended for scouting missions within a maximum range of 15 miles from the landing site. Could be landed either with a manned lunar mission or via an unmanned logistics vehicle.
North American/Rockwell One Man Lunar Flying Unit
Simple one manned rocket, designed by North American/Rockwell, using the remaining fuel from the LM descent stage. It was intended for scouting missions within a maximum range of 4.6 miles from the landing site. Could be landed either with a manned lunar mission or via an unmanned logistics vehicle.
Long-Range Flyer
Simple two-man rocket using fuel from the LEM. This could be used for scouting missions to sites up to around 50 miles from the main landing site, or, in an emergency, to carry two astronauts from the lunar surface to rendevouz with the CSM.
Lunar Escape System
The Lunar Escape System was a simpler folding rocket than the Long-Range Flyer, which would be carried in the descent stage of the LM to allow the astronauts to fly into an orbit where the CM Pilot could recover them in the event that the ascent stage failed to fire.
To save weight, the fuel tanks would be inflatable and a set of detachable legs would be used purely for launch, then left behind on the Moon. No life-support facilities would be included other than the astronauts' suits, and there would be no automated guidance; the astronauts would fly to orbit manually using a pre-programmed pitch program and lunar landmarks. Propulsion would be provided by a collection of CSM/LM RCS thrusters.
Lunar Shelter
North American/Rockwell patented a design for a Lunar Shelter which would use a Command Module and a Lunar Module descent stage to provide long-term accomodation for lunar astronauts on extended stays. Since there was no ascent stage, the Lunar Shelter could carry more supplies and provide more comfortable accomodation than an ascent-capable LEM. The astronauts would use their own LEM to return to orbit, which would be left on the surface in a 'hibernation' mode until the end of their stay.
Nuclear-Ion, Lunar Logistics Spacecraft
Proposed Saturn INT-21 launched Nuclear-Ion propelled Lunar Logistics Vehicle, intended to support the post Apollo manned lunar base.
Two flight modes were envisaged. In the first after reaching the moon the vehicle would separate and the cargo module would land on the lunar surface leaving the power-plant in lunar orbit. In the second the power-plant would return to Earth orbit for re-use.
Also considered was landing the complete spacecraft on the lunar surface where the power-plant would be used to provide electrical power for one of NASAs planned moonbases.
Lunar Motorbike
Little information is available, but the 'lunar motorbike' is variously claimed to have been designed as a backup in case the LRV wasn't finished in time for Apollo 15, or planned for use on Apollo 20 in addition to or as a replacement for the LRV.
Goodyear Lunar Shelter
In response to NASAs request for a means to extend the time astronauts could stay on the lunar surface the Goodyear Corporation designed an inflatable lunar shelter that could be carried folded up against the LM. It was intended to support two men on the lunar surface for eight days.
Original Saturn plans
The original Saturn-A, -B, -C and Nova designs, possibly including the earlier lunar landing plans based on multiple launches, or the single launch putting the entire CSM onto the Moon using the massive Saturn C-8 booster.
For more information see, for example, Saturn-C family and Nova family at Astronautix.com.
LM/Apollo Telescope Mount
In the original Skylab plan the Apollo Telescope Mount (ATM) was to be attached to a modified LM ascent stage and launched into orbit aboard a Saturn Ib separately from an Apollo CSM carrying the Skylab crew. After a docking and crew transfer the LM/ATM would be docked with the Skylab station.
Projects and Missions
Apollo to Venus
Phase B of the Apollo to Venus plan called for the addition of solar panels to the 'wet workshop' and the use of a Block III CSM so that the astronauts would fly the SIVB into a high altitude orbit for a year-long mission in preparation for an actual fly-by.
Phase C of the Apollo to Venus plan would use an improved version of the 'wet workshop' SIVB with a Block-IV CSM to perform the actual Venus flyby.
Wikipedia has some more information.
Apollo/Salyut/Soyuz Test Project
Early in the planning for the Apollo-Soyuz Test Project, consideration was given to have the Apollo dock with a Salyut space station to carry out the joint mission. After two days of mutual operations the Apollo would undock and carry out an Earth Resources survey of the United States before splashing down one fortnight after launch.
This wouldn't require much of a change, since the ASTP docking module should be able to dock with either: it would primarily require new scenarios and both Soyuz and Salyut from other add-ons. Furthermore, the CSM used for this mission was essentially in the J-Class configuration with SIM bay instruments, so models and animations from Apollo 15-17 could be used to represent the ASSTP Apollo.
See: Flightplan
High Orbit Laser Communications Test
To provide a possible alternative to using radio links for interplanetary communications Perkins-Elmer, a firm later involved in the construction of the Hubble Space Telescope was asked to design a laser communications system. By 1966, their work was sufficiently advanced to propose that NASA set aside an Apollo mission to test out their planned system.
A Saturn V would launch an Apollo CSM & LM into synchronous orbit where the tests were to take place. Perkins-Elmer evolved five different concepts for carrying out the communications tests, three involved using modified LMs to carry the combined laser communications unit/telescope into orbit.
High Orbit Optical Systems Experiment
A plan to place in synchronous orbit a LM whose descent stage was replaced with an optical array for the purpose of testing various advanced optical systems, such as segmented mirrors, communications lasers and stellar interferometry.
High Orbit Parabolic Antenna Test
In 1966 NASA asked Convair to research the use of Apollo systems to test out large scale space construction projects. One such project was the use of a Saturn V/CSM combination to deploy a 100ft Parabolic Antenna into a synchronous orbit so that the characteristics of the antenna could be determined under operational conditions.
Little Joe 2 Suborbital Test Flights
The original Little Joe 2 test program included not only the Launch Escape Tests, but also suborbital tests of the Service Propulsion System and Lunar Module.
Passive Communications Satellite Test
Apollo Applications studies covered a wide range of subjects, from Post-Apollo lunar exploration to Earth-Orbiting space stations. One study carried out by Goodyear looked at using Apollo to test a Passive Communications Satellite, in furtherance of the research carried out using the Echo satellites.
The uninflated satellite would be launched aboard a Saturn V and would be deployed at an altitude of 500 miles (805 km)using an Apollo CSM. After inflation and testing the Apollo crew would EVA to retrieve film cameras aboard the satellite and the S-IVb stage prior to re-entry.
This one should be fairly easy to do, as it is essentially an extension of the Apollo 7 manned mission and related models exist as part of the Apollo to Venus Phase A mission.
Perhaps of further interest is the similarity between the Goodyear satellite and some configurations of the Project Able Mirror.
Project Able LEM
A plan to use a mirror in space to light up parts of the Vietnam jungle at night. A modified LEM with a huge flexible mirror attached would be launched into space where the mirror would unfold.
A similar plan proposed using a modified LEM to fly to Soviet satellites and spray paint over their sensors: the first space vandals.
Project Icarus
Proposal to divert or destroy an incoming asteroid by launching 100 Megaton nuclear bombs on Saturn Vs.
See, for example: The Space Review: Giant Bombs on Giant Rockets, and MIT Press appear to still be selling a version of the original plan: MitPress Catalog
Project Horizon
Project Horizon, was a proposed US Army plan written up by Von Braun, it would have used multiple Saturn I (Saturn-A1) and Saturn II (Saturn-B1) launches to establish a 12 man army post on the moon.
Lunex Project
The Lunex Project was a proposed US Air Force alternative to Apollo, which would use a lifting-body re-entry vehicle and land the entire spacecraft stack on the Moon rather than having a separate lander which rendezvoused with the orbiting return craft.
Launch Vehicles
Little Joe 2
The Little Joe 2 was a solid rocket booster designed by General Dynamics/Corvair, it was used to gather flight test data on the Apollo Launch Escape and Earth Landing systems.
Saturn C-2 MLV
Proposed version of the Saturn C-2 rocket with a first stage formed from a cluster of SRBs. Capable of carrying 60,000 pounds into orbit or 18,500 pounds into an escape trajectory.
The same study also proposed a second vehicle capable of putting 130,000 pounds into orbit. This was a four stage rocket comprising a 16 SRB first stage, a 4 SRB second stage, an augmented S-II stage with six J-2 engines as a third stage and an S-II derived fourth stage fitted with two J-2 engines.
Saturn 1
The Saturn 1 was the precursor to the Saturn 1b, using an SIV stage in place of the SIVB. The SIV was smaller, with a lower fuel capacity, and used multiple RL10 engines in place of the J2 engine on the SIVB.
NASA also considered recovering the first stage of the Saturn I with a paraglider.
Saturn 1b/Centaur
Briefly known as the S-V stage the Centaur high energy booster formed part of many of the early Saturn rocket plans. Later on it was planned to fit a Centaur stage onto a standard Saturn Ib, forming a launch vehicle capable of sending a 4.4 metric ton payload on a flyby mission to Mars.
Saturn 1b MLV
As part of NASA's cost-cutting plans, they studied a 'Modified Launch Vehicle' (MLV) derivative of the Saturn 1b which would replace the S1B stage with a solid rocket that was twice the diameter of a shuttle SRB and possessing one and a half times the thrust. In essence this was a 1960s version of NASA's new 'Stick' launcher for the CEV.
See: Astronautix
See: Astronautix for details of the engine that would have been used.
Saturn 1b with multiple SRBs
Other Saturn 1b proposals would replace the S1B stage with multiple SRBs, or simply attach SRBs to the side of the S1B stage for extra thrust: that would increase payload rather then reduce cost.
Some other Saturn designs were proposed using multiple large SRBs for the first stage; one even utilising two S-II stages, one stretched with extra propellant the other using two engines rather than five.
Saturn 1 RIFT and Saturn V/Nuclear
NASA planned to develop a Nuclear-Thermal rocket stage to act as a high-energy booster for the Saturn series. The initial test series would use an S-I stage to boost the nuclear stage (Saturn-Nuclear or S-N) into a suborbital test trajectory.
Operational stages were intended to be used in conjunction with a two-stage Saturn V.
See: Astronautix
Saturn INT-21
Two-stage launcher used to launch large payloads into Earth orbit. This was used for the Skylab mission.
See: Astronautix
Saturn S-ID stage
A modified S1C stage which dropped the outer four engines in a similar manner to the Altas dropping two of its engines during launch. As well as multi-stage launchers with greater payloads, it could carry 50,000 pounds to low orbit itself with no second stage.
See Astronautix.
Saturn V-24
Saturn V with stretched stages, new toriodal aerospike engines on the upper stages, uprated F-1 engines on the first stage, and four strap-on boosters with two F-1 engines each. Capable of putting over 500,000 pounds of payload into low Earth orbit.
Skylab and Alternative Space Stations
Skylab
The NASSP 5.x Skylab sources were lost, so a new version will be required once the INT-21 support is added.
AAP Skylab
By 1968 the NASA plans for what became known as Skylab reached their final pre-Apollo Lunar Mission form. There would be eight Saturn 1b launches (two unmanned) and missions would last from 28 to 56 days.
In 1969 Hollywood took these plans and used them as the basis for the SF thriller Marooned.
Lunar Skylab
McDonnell Douglas (Seal Beach, CA) did a study on modifying the Skylab as a moon-orbiting observatory and station.
See Astronautix.
Interim Orbital Workshops
In 1971, NASA briefly looked at launching four additional Orbital Workshops after Skylab I both as a means of keeping manned spaceflight experience intact and of testing a variety of different spacecraft power systems. Launched by a Saturn INT-21, the stations would test out Solar Power, RTG power and a fully operational nuclear reactor in orbit.
Logistics support for the stations, until the space shuttle could come on line would be three or four man Apollo CSMs launched by Saturn Ibs, Saturn Ib MLVs and Titan IIIms.
Orbital Launch Facility
At the same time as the Air Force was planning its Manned Orbital Laboratory, NASA was presented with a civilian version called the Manned Orbiting Research Laboratory (MORL).
As part of NASA's post moon-landing plans, Boeing was asked to design a space station that could be used as an Orbital Launch Facility (OLF) for lunar ferry missions in support of a permanent Lunar base and manned missions to Mars and Venus.
The OLF was a nuclear powered cylindrical station built around two MORLs joined back-to-back and could be launched by a single Saturn INT-21. The station would be supported by two craft, the manned Apollo Logistics Module, a CSM modified to carry a six-man crew and logistics cannisters and an unmanned fuel tanker which would carry the fuel used by the modified S-II stage, which boosted the lunar ferries and manned expeditions out of Earth Orbit.
Baseline Orbital Workshop
The original Skylab plan envisaged launching the CSM and Orbital workshop atop a single uprated Saturn 1b. After launch the CSM would separate from the S-IVb and dock with the Airlock Module (AM) that replaced the LM atop the S-IVb stage. Once the S-IVb had been purged of its remaining fuel the astronauts would use the hydrogen tank as additional living space while in orbit. Power for the 30 day mission was to be supplied by the CSM fuel cells, with the additional reactants being carried aboard the AM.
The Phase A mission of the Manned Venus Flyby intended to use an identical spacecraft configuration.
Boeing Proposal
One element of the 1966 Planetary Joint Action Group Mars exploration plan was a Boeing designed alternate Skylab design that could be used to test out components for the Mars flyby spacecraft in addition to an Earth-Orbit science program.
Artificial Gravity Space Station
Proposed Saturn V INT-21 launched space station that would have used the spent S-II stage as a counterweight so that artificial gravity could be generated by rotating it and the crew module around a fixed hub. Two configurations were considered. The first, intended for a 9 man crew would have had the same diameter as an S-IVb stage.
The second planned configuration, which would have had a 24 man crew had the same diameter as an S-II stage.
Resupply of the stations would have been using Apollo CSMs modified into a logistics configuration.
SLA Workshop
Even as the basic design of Skylab was being finalized, an alternative design was created to enable the mission objectives to be fulfilled in a more economical fashion, should it become necessary to do so. Called the SLA Workshop, the alternate orbital laboratory was a conical vessel that would replace the CSM/SLA atop a Saturn 1b. Three variants were envisaged, one for earth resources observations, one to carry a solar telescope and finally, one carrying a standard astronomical telescope.
Emergency Escape Device
A small capsule launched on a Titan/Agena booster which could be used to rescue the crew from an Apollo Applications Program-based space station in Earth Orbit, or permanently attached to such a station as a lifeboat.
LLRV/LLTV
The Lunar Landing Research Vehicle (LLRV) and later the Lunar Landing Training Vehicle (LLTV), humorously referred to as "flying bedsteads", were created to study and analyze piloting techniques needed to fly and land the tiny Apollo Lunar Module in the moon’s airless environment.
The LLRV is already available at Orbithangar using Vinka's Spacecraft.dll. More informations can be found here: [1], [2]
Later the LLTV was used. The LLTV incorporated changes that were the result of the initial LLRV test program and their systems were more like that of the real LM. More informations can be found here: [3], [4]
Integrated Manned Programme
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NASAs ultimate Post-Apollo plan, one which would have combined the Space Shuttle with Saturn Vs to put men permanently on the Moon and send them on to Mars and Venus.
References
Here are a selection of documents with information on these spacecraft, both historical and planned:
- US Army, Project Horizon, Volume One: Summary and Supporting Considerations June 9, 1959
- US Army Ordnance Missile Command, A Lunar Exploration Program Based Upon Saturn - Boosted Systems, February 1, 1960
- Reactor in-flight test system. Volume 1 RIFT program summary, March 1961
- S. Cloverdale, Design Studies Of Very Large Solid Rockets, Final Report, April 9, 1961
- Space Systems Division, Air Force Systems Command, Lunar Expedition Plan, May 1961
- The Apollo 'A' Saturn C-1 launch vehicle system, July 17, 1961
- R.P. Smith, Project Apollo - A description of a Saturn C-3 and Nova vehicle, July 25, 1961
- Jet Propulsion Laboratory, Some interrelationships and long range implications of C-3 lunar rendezvous and solid Nova vehicle concepts, October 1961
- A.G. Orillion & G.P. Pedigo, Apollo Launch Vehicle Design, January 1, 1962
- A.I. Kaufmann Summary of Earth orbital rendezvous studies, July 1, 1962
- Direct flight Apollo study. Volume 1:Two man Apollo spacecraft, October 31, 1962
- Direct flight study using Saturn C-5 for Apollo project. Volume 1 Summary, February 1, 1963
- J.H. Semcken, Feasibility study and detailed test plans for LEM-1 and LEM-2, September 6, 1963
- Nasa support manual - Apollo description manual applicable to boilerplate 6 only, October 25, 1963
- W.F. Dankhoff, The M-1 rocket engine project, November 1963
- Final Technical Presentation Modified Apollo Logistics Spacecraft, 1963
- Apollo Systems Description: Vol 2. Saturn Launch Vehicles, February 1, 1964
- Bell Aerosystems, LLRV Weight and Balance Handbook, April 1, 1964
- N.G. Huber, Post-Saturn launch vehicle study part II condensed summary report, April 10, 1964
- North American/Rockwell, Apollo Command and Service Module System Specification (Block I) (Updated), August 28, 1964
- Orbital Payload Potential: Saturn 1B Earth Launch Vehicle Using Solid Propellant Motors, September 1964
- J.L. Sanders, Advanced post-Saturn earth launch vehicle study executive summary report, February 3, 1965
- J.W. Larson, Electrically-propelled cargo vehicle for sustained lunar supply operations, Final report, June 28, 1965
- Modified Launch Vehicle MLV Saturn V Improvement Study Composite Summary Report, July 2, 1965
- Goodyear Aerospace Corporation, Lunar Stay Time Extension Module STEM FINAL report, 21 Aug. 1964 - 20 Aug. 1965, August 1965
- J.J. Traxler, Saturn 1B Centaur propulsion systems compatibility study, August 6, 1965
- R.M. Croft, Utilization of an orbital launch facility for planetary missions, September 1965
- Orbit Launch Facility Study, VOLUME I Technical Report Summary Final, October 1965
- Orbit Launch Facility Study, VOLUME IIa Technical Report Final, October 1965
- Orbit Launch Facility Study, VOLUME IIb Technical Report Final, October 1965
- Orbit Launch Facility Study, VOLUME III OLF Study Research & Technology Implications Final Report, October 1965
- LEM utilization study for Apollo extension system missions. Volume VI - Schedule analysis Final report, October 15, 1965
- H.R. Lowery, Saturn instrument unit command system, October 22, 1965
- North American/Rockwell, Renovated Command Module Laboratory and renovated command module study Final review, January 1, 1966
- Saturn I Summary, February 15, 1966
- S.G. Embrey, The Apollo Saturn Emergency Detection System, February 17, 1966
- W.W. Hough, Apollo experiments pallet interim technical description, March 3, 1966
- 260-in.-dia motor feasibility demonstration program Final program summary report, Jun. 1963 - Apr. 1966, April 8, 1966
- General Dynamics/Convair, Little Joe 2 test launch vehicle NASA Project Apollo. Volume 1 Management, May 1, 1966
- General Dynamics/Convair, Little Joe 2 test launch vehicle NASA Project Apollo. Volume 2 - Technical summary Final report, May 1, 1966
- W.W. Hough, Study of the Apollo experiments Pallet as a support system for orbital experiments, May 20, 1966
- International Business Machines, Saturn IB 5 instrument unit instrumentation system description (S-IU-2-02 through 204 501 through 503), June 1, 1966
- J.W. Larson, Electrically-propelled cargo vehicle for sustained lunar supply operations, Summary report, June 24, 1966
- Laser Communication Satellite Experiment (LCSE), July 1, 1966
- T.C. Tweedie jr, Installation of S-027 in the IU of Mission 209, July 21, 1966
- M.S.Feldman, Saturn ib modifications required to support the orbital workshop mission, August 1966
- Optical technology Apollo extension system. Part I - Presentation, September 27, 1966
- Optical technology Apollo extension system, Part I Summary report, September 27, 1966
- Optical technology Apollo extension system, Part I. Executive summary report, September 27, 1966
- Optical technology Apollo extension system, Part I. Volume I, Book 1 of 2. Final technical report, September 27, 1966
- Optical technology Apollo extension system, Part I. Volume I, Book 2 of 2. Final technical report, September 27, 1966
- Optical technology Apollo extension system, Part I. Volume II. Final technical report, September 27, 1966
- Optical technology Apollo extension system, Part I. Volume III. Final technical report, September 27, 1966
- Optical Technology Apollo Extension System. Part II - Definition of work tasks, September 27, 1966
- G.W. Craft, A.W. Starkey, Dock concept for handling and launching large solid rocket engines applied to Saturn IB-5A launch vehicle, September 30, 1966
- PasComSat Experiment for Apollo Application Program, October 1966
- Final Report - Studies of Improved Saturn V Vehicles and Intermediate Payload Vehicles, October 7th 1966
- G.W. Craft, Saturn improvement studies A summary, October 28, 1966
- D.J. Belz, Summary description of the SAA airlock module, November 1966
- Preliminary technical data for earth orbiting space station. Volume I - Summary report, November 7, 1966
- Preliminary technical data for earth orbiting space station. Volume II - Standards and criteria, November 7, 1966
- Preliminary technical data for earth orbiting space station. Volume III - Systems, November 7, 1966
- Preliminary technical data for Earth orbiting space station. Volume IV - Configuration, integration and weights, November 7, 1966
- Feasibility Study of Utilization of LM for Project Able, December 12, 1966
- G.W. Craft, Implementing Dock Launch of MLV Saturn 1B-5A, December 29, 1966
- C.C. Ciepluch, Status of the 260-inch diameter solid rocket motor program, January 1, 1967
- Manned Venus Flyby study, Feb. 1, 1967
- J.D. Belz, Modified Saturn launch vehicles for AAP earth orbital missions, April 14, 1967
- Motor 260-SL-3 program. Volume 2 - 260-SL-3 motor propellant development Final phase report, July 14, 1967
- Aerojet-General Corporation, The M-1 rocket engine project, Final Report, August 1967
- C.D. Harris and A.A. Luoma, Static longitudinal aerodynamic characteristics of a hammerhead-shaped Little Joe II - Lunar module model at Mach 0.30 to 1.20, October 1, 1967
- Saturn 5 single launch space station and observation facility. Combined mission concept evaluation Final report, November 1967
- Large space structure experiments for AAP. Volume 5 - Parabolic antenna Final report, 15 Sep. 1966 - 15 Sep. 1967, 22 November 1967
- An Alternate Apollo Applications Program for Earth Orbit, January 1968
- L.A. Ferrara, Summary Description of the AAP Apollo Telescope Mount, April 1968
- J.J. Gabrik, A review of the Block II CM SM modifications required for AAP, November 1968
- J.B. Carpenter Jr, A study of an Extended Lunar Orbital Rendezovous ELOR mission. Volume 1 - Technical analysis Final report, January 1, 1969
- J.B. Carpenter Jr, A study of an Extended Lunar Orbital Rendezvous ELOR mission. Volume 2 - Supplemental data Final report, January 1, 1969
- J.B. Carpenter Jr, A study of an Extended Lunar Orbital Rendezvous ELOR mission. Volume 3 - Summary of results, January 1, 1969
- Lockheed, Emergency Earth Orbital Escape Device Study Vol 1. Condensed summary, January 31, 1969
- Lockheed, Emergency Earth Orbital Escape Device Study. Vol 2E. Additional study tasks, January 31, 1969
- Lockheed, Emergency Earth Orbital Escape Device Study Vol 4. Apollo Applications, January 31, 1969
- North American/Rockwell, One-man lunar flying vehicle Summary briefing, July 1, 1969
- Bell Aerospace, Study of one man lunar flying vehicle Final report, July 1, 1969
- A.W. Starkey, Summary of 260-inch solid rocket launch studies June 1965 - May 1968, August 1, 1969
- North American/Rockwell, Study of one-man lunar flying vehicle. Volume 1 - Summary Final report, August 31, 1969
- North American/Rockwell, Study of one-man lunar flying vehicle. Volume 2 - Mission analysis Final report, August 31, 1969
- North American/Rockwell, Study of one-man lunar flying vehicle. Volume 3 - Subsystem studies Final report, August 31, 1969
- North American/Rockwell, Study of one-man lunar flying vehicle. Volume 4a - Configuration design Final report, August 31, 1969
- North American/Rockwell, Study of one-man lunar flying vehicle. Volume 4b - Configuration design appendixes Final report, August 31, 1969
- North American/Rockwell, Study of one-man lunar flying vehicle. Volume 5 - Preliminary design and specifications Final report, August 31, 1969
- J.O. Mazenauer, Lunar Escape Systems (LESS) Feasibility Study - Summary Report, June 1970
- J.O. Mazenauer, Lunar Escape Systems (LESS) Feasibility Study - Final Technical Report, September 1970
- D.S. Akens, Saturn illustrated chronology: Saturn's first eleven years, April 1957 - April 1968, January 20, 1971
- George J. Hurt Jr, David B. Middleton, and Marion A. Wise, Development Of A Simulator For Studying Simplified Lunar Escape Systems, April 1971
- Study of an evolutionary interim earth orbit program, April 6, 1971
- David B. Middleton and George J. Hurt Jr, A Simulation Study Of Emergency Lunar Escape To Orbit Using Several Simplified Manual Guidance And Control Techniques, October 1971
- International rendezvous and docking mission (Apollo/Salyut/Soyuz), December 1, 1971
- H.H. Koelle, Birth, Life and Death of the Saturn Launch Vehicles, May 5, 2001
- H.H. Koelle, Nova and Beyond: A Review of Heavy Lift Launch Vehicle Concepts in the POST-SATURN Class, June 6, 2001