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Future Expansion - Projectapollo Future Expansion - ProjectApollo http://nassp.sourceforge.net/wiki/Future_Expansion Future Expansion Categories: Spacecraft | Historical spacecraft | Fictional spacecraft From ProjectApollo 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. Contents 1 Spacecraft 1.1 Command/Service Module 1.2 CSM Ferry 1.3 CSM Shuttle 1.4 Command/Cryogenic Service Module 1.5 Multi-Mission Module 1.6 Recycled/Renovated Command Modules 1.7 CM Parawing 1.8 CM Land-Landing System 1.9 Apollo Logistics Spacecraft 1.10 CSM Experiments Pallet 1.11 Lunar Shelter 1.12 LM/Apollo Telescope Mount 1.13 Nuclear-Ion, Lunar Logistics Spacecraft 1.14 HL-10 Lifting Body 1.15 Emergency Escape Device 1.16 Orbital Escape Device 1.17 LLRV/LLTV 2 Lunar Mobility Aids 2.1 Lunar Motorbike 2.2 Local Scientific Survey Module (LSSM) 2.3 Bell Aerospace One Man Lunar Flying Unit 2.4 North American/Rockwell One Man Lunar Flying Unit 2.5 Long-Range Flyer 2.6 Lunar Escape System 3 Moonbases 4 Projects and Missions 4.1 Original Saturn plans 4.2 AAP Mission 1a 4.3 Apollo to Venus 4.4 AAP Venus Flyby Mission 4.5 Apollo/Salyut/Soyuz Test Project 4.6 Satellite Rendezvous and Refurbishment Missions 4.7 High Orbit Laser Communications Test 4.8 High Orbit Optical Systems Experiment 4.9 High Orbit Interferometer Test 4.10 Orbital X-Ray Telescope 4.11 High Orbit Parabolic Antenna Test 4.12 Little Joe 2 Suborbital Test Flights 4.13 Mars Excursion Module Testing 4.14 Orbiting Primate Spacecraft 4.15 Passive Communications Satellite Test 4.16 Project Able LEM 4.17 Lunar Photo-Mapping LEM 4.18 Project Icarus 4.19 Project Horizon 4.20 Lunex Project 5 Unmanned Spacecraft 5.1 High Orbit Nuclear Powered Television Satellite 5.2 Advanced Mars Probe 5.3 Jupiter Orbiting Vehicle for Exploration (JOVE) 5.4 Jupiter Orbiting Spacecraft (JOSÉ) 6 Launch Vehicles 6.1 Little Joe 2 6.2 Saturn C-2 MLV 6.3 Saturn 1 6.4 Saturn 1b/Centaur 6.5 Saturn 1b MLV 6.6 Saturn 1b with multiple SRBs 6.7 Saturn 1 RIFT and Saturn V/Nuclear 6.8 Saturn INT-21 6.9 Saturn V/J-2S 6.10 Saturn S-ID stage 6.11 Saturn S-IVC stage 6.12 Saturn Cryogenic Planetary Injection Module 6.13 Saturn V-24 7 Skylab and Alternative Space Stations 7.1 Skylab 7.2 AAP Skylab 7.3 Interim Orbital Workshops 7.4 Orbital Launch Facility 7.5 Baseline Orbital Workshop 7.6 Boeing Single Launch Space Station Proposal 7.7 Self Deploying Space Station 7.8 Lockheed Modular Space Station 7.9 Artificial Gravity Space Station 7.10 SLA Workshop 8 Integrated Manned Programme 9 References Spacecraft 1 of 21 8/17/2010 3:18 PM Future Expansion - ProjectApollo http://nassp.sourceforge.net/wiki/Future_Expansion 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 Ferry In 1965, NASA considered the possibility that the Saturn V could not be 'man-rated' in time to permit a lunar landing in the 1960's. Had this occurred an alternative mission profile was developed. An unmanned CSM/LM stack would be launched into orbit atop a Saturn V. Then a manned CSM ferry fitted with a drogue docking unit would be launched atop a Saturn 1b. The ferry would rendezvous and dock with the CSM/LM stack and after a crew transfer be jettisoned prior to the TLI burn. See: Apollo launch-vehicle man-rating. Some considerations and an alternative contingency plan. (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov /19770078693_1977078693.pdf) Beyond Apollo: RAND's Apollo backup plan (http://beyondapollo.blogspot.com/2009/06/rands-apollo-backup-plan-1965.html) 'CSM Ferry' Proposal 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 (http://patft.uspto.gov/netacgi/nph-Parser?Sect1=PTO1&Sect2=HITOFF&d=PALL& p=1&u=%2Fnetahtml%2FPTO%2Fsrchnum.htm&r=1&f=G&l=50&s1=3,576,298.PN.&OS=PN/3,576,298&RS=PN/3,576,298) . 'CSM Shuttle' proposal Command/Cryogenic Service Module In 1964 NASA conducted a preliminary study into using the RL-10 engine which powered the S-IV stage to provide power for the SM. The resulting Cryogenic Service Module would also have carried the fuel for the LM (as it was planned at that time), thus saving weight during launch. See: Analysis of a Cryogenic Service Module for the Apollo mission. (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19790076809_1979076809.pdf) and Advanced pressurization systems for cryogenic propellants. Final report, 20 Nov. 1963 - 25 Jun. 1965 (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov Cryogenic Service Module proposal /19670007276_1967007276.pdf) Multi-Mission Module In 1964 the Marshall Spaceflight Center patented the design of a booster stage that was intended to be the basis of a series of different spacecraft. In the illustration shown two such modules form the basis of a lunar logistics spacecraft. One proposed alternative use would have seen the modules used as a replacement for both the Service and Lunar modules for the Apollo missions. See: Comparative Design Study of Modular Stage Concepts - Volume III, Development Plans & Cost Analysis (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740073700_1974073700.pdf) 'Multi-Mission Module' based Apollo CSM/LM 'Multi-Mission Module' proposal Recycled/Renovated Command Modules 2 of 21 8/17/2010 3:18 PM Future Expansion - ProjectApollo http://nassp.sourceforge.net/wiki/Future_Expansion 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. Three uses for a renovated Command Module CM Parawing In the late 1960's NASA studied the possibility of replacing the parachute based Earth Descent System with a parawing based system, allowing for the possibility of bringing the Apollo CMs down on land rather than at sea. See: 1. Fixed-base visual simulation of pilot controlled descents of an advanced Apollo spacecraft with an all-flexible parawing (http://ntrs.nasa.gov/archive /nasa/casi.ntrs.nasa.gov/19690011574_1969011574.pdf) 2. Fixed-base visual simulation of obstacle avoidance during terminal descent of advanced Apollo spacecraft with an all-flexible parawing (http://ntrs.nasa.gov /archive/nasa/casi.ntrs.nasa.gov/19700026611_1970026611.pdf) 3. Wind-tunnel investigation of the static aerodynamic characteristics of an 18-foot (5.49-meter) all-flexible parawing (http://ntrs.nasa.gov/archive /nasa/casi.ntrs.nasa.gov/19670017942_1967017942.pdf) 4. Inertia tests of a 24 foot single keel parawing, model 2 (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19700011127_1970011127.pdf) Descent configuration of the CM/Parawing CM Land-Landing System One proposal for the later Apollo Extension/Apollo Applications missions was to equip the CM with a modified heat shield that would allow the CM to come down on land rather than in the ocean. See: 1. Mechanical Impact System Design for Advanced Spacecraft (MISDAS). Phase I - Design concept selection (http://ntrs.nasa.gov/archive /nasa/casi.ntrs.nasa.gov/19670005559_1967005559.pdf) 2. Mechanical Impact System Design for Advanced Spacecraft (MISDAS). Final Report (http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov /19670005572_1967005572.pdf) 3. Mechanical Impact System Design for Advanced Spacecraft (MISDAS). Application to AES SPACECRAFT (http://ntrs.nasa.gov/archive /nasa/casi.ntrs.nasa.gov/19670005610_1967005610.pdf) CM fitted with six legged land-landing system 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. See: MODAP (1963) (http://beyondapollo.blogspot.com/2009/05/modap-1963.html) Planned Apollo Logistics Module CSM Experiments Pallet Proposed modification of the Service Module to permit a variety of Earth/Lunar orbit experiments to be carried. One such experiment set evolved into the Apollo Telescope Mount fitted to Skylab.
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