Idea Shuttle payloads that never flew

I had planned to cover another student designed OTV for this post, but this Solar Array is rather more interesting. The first volume of the Final Report covers testing, including a shuttle mission to do so and details of a power module based around the arrays.

Multi 100kW Solar Array for Low Earth Orbit (1983)

A preliminary design effort directed toward a low concentration ratio photovoltaic array system capable of delivering multihundred kilowatts (300 kW to 1000 kW range) in low earth orbit is described. The array system consists of two or more array modules each capable of delivering between 113 kW to 175 kW using silicon solar cells or gallium arsenide solar cells, respectively. The array module deployed area is 1320 square meters and consists of 4356 pyramidal concentrator elements. The module, when stowed in the Space Shuttle's payload bay, has a stowage volume of a cube with 3.24 meters on a side. The concentrator elements are sized for a geometric concentration ratio (GCR) of six with an aperture area of .25 sq. m. The structural analysis and design trades leading to the baseline design are discussed. It describes the configuration, as well as optical, thermal and electrical performance analyses that support the design and overall performance estimates for the array are described.
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Low Concentration Ratio Solar Array For Low Earth Orbit Multi-100kW Application Final Report, Vol.1: Design, Analysis & Developmental Tests

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19830028277_1983028277.pdf

Low Concentration Ratio Solar Array For Low Earth Orbit Multi-100kW Application Final Report, Vol.2: Drawings

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19830027827_1983027827.pdf

Low Concentration Ratio Solar Array For Low Earth Orbit Multi-100kW Application Final Report, Mid-Term Report

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19830012089_1983012089.pdf

For any first time readers of this thread, I'd advise you start with the OP as there are many interesting things to discover.
 
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Lightside Atmospheric Revitalization System (LARS) (1980)

A closed-loop atmosphere revitalization system was studied as a replacement to the present baseline UGH system for extended duration shuttle missions. The system consists of three subsystems: a solid amine water desorbed regenerable carbon dioxide removal system, a water vapor electrolysis oxygen generating system, and a Sabatier reagtor carbon dioxide reduction system.

The system is called the Lightside Atmospheric Revitalization System (LARS), since it is designed for use on a solar powered shuttle vehicle. The majority of the system's power requirements are utilized on the sun side of each orbit, when solar power is available.
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Lightside Atmospheric Revitalization System, Study Report

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810012202_1981012202.pdf

The most interesting thing about this 'add-on kit' is that it was specifically designed to work with the Power Extension Package modelled by Donamy.

[ame="http://www.orbithangar.com/searchid.php?ID=5592"]http://www.orbithangar.com/searchid.php?ID=5592[/ame]
 
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Superfluid Helium Tanker (1988)

Proposed carrier for Superfluid Helium to be used to re-supply orbiting infra-red telescopes and experiments such as the [ame=http://en.wikipedia.org/wiki/Alpha_Magnetic_Spectrometer]Alpha Magnetic Spectrometer[/ame]. Was designed to use a wide range of launch vehicles including the space shuttle.



Superfluid Helium Tanker Study

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19890010811_1989010811.pdf
 
The day of passenger space travel is approaching, first to Low Earth Orbit and then to circumlunar distances. Details of the NASA citizen-in-space project are reviewed, along with a report on the Shuttle Passenger Module studied by a major travel agency. Passenger flight into Earth orbit, weekend stays in a globe-circling vacation spa, and eventual translunar excursions are considered in an evolutionary way.
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http://www.spacefuture.com/archive/the_space_tourist.shtml
 
With the NTRS back online but all the interesting content missing.



I think the above image would make an interesting new space shuttle 'skin'.
 
I still have not checked all the links to see if the documents in earlier posts in this thread are still available. But I found this blog post with an interesting shuttle based Mars mission.


...the NASA flyby plan aimed to counter a possible Soviet manned Mars flyby. He cited a 1984 CIA memorandum that suggested (without citing much in the way of proof) that the Soviet Union might attempt such a mission in the late 1990s to garner international prestige.

NASA’s manned Mars flyby would be based on Space Shuttle, Space Station, and Lunar Base hardware expected to be operational in the late 1990s. Space Shuttle Orbiters would deliver to NASA’s low-Earth orbit (LEO) Space Station an 18-ton Mission Module (MM) and a pair of empty expendable propellant tanks with a mass of 11.6 tons each. The MM, derived from a Space Station module, would include a 3,000-pound radiation shelter, 7,000 pounds of science equipment, and 2,300 pounds of food and water.
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D.F.S Portree, Beyond Apollo

http://www.wired.com/wiredscience/2012/06/shuttle-era-manned-mars-flyby-1985/


Later:

Ok,

I've done a check of the links on page five of this thread and the following items still have links to their NTRS documentation:

Multi 100kW Solar Array for Low Earth Orbit (1983)
Lightside Atmospheric Revitalization System (LARS) (1980)
Superfluid Helium Tanker (1998)

The GEOSEL (AKA Space:1989) transportation system material is still offline as of this date. (11/01/14)

Later:

I've checked page four of the thread and the documentation for the following are still available either in whole or part.

Manned Orbital Facility (1975)
Space Operations Center (1979)
Manned Orbital Facility User Guide (1976 ?)
In-space propellant logistics. (1972)
In-space propellant systems safety. (1972) (Vol. 1 is not online)
ReUseable Space Tug, North American/Rockwell (1971) (Vol. 3 is not online)
30/20 Ghz Demonstration System SSUS-D/BSE, Final Report (1981)
Space Tug Point Study, North American/Rockwell (1972)
Space Construction System Analysis (1979)
Lens Antenna Deployment Demonstration (1985-1989)

The following documents are not online as of this date (12/01/14).

Space Tug (Cryogenic), Convair Proposal
Space Tug (Cryogenic), McDD Proposal
 
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A check of the links on page 3 of the thread shows that the following posts still have links to the online documents, where multiple different documents are in the same post, the link to that post will be in the first document title.

Phase A Reaction Control System Design For The Large Space Telescope (LST)
Scientific Instrument Package For The Large Space Telescope (Part of Post 31)
Erectable Space Platform For Space Sciences And Applications
Conceptual Design Study. Science & Application Space Platform (SASP)
AAFE Large Deployable Antenna Development Program: Executive Summary
Study Of Shuttle Imaging Microwave System Antenna. Vol. I: Conceptual Design
The Microwave Radiometer Spacecraft: A Design Study
Shuttle Infrared Telescope Facility (SIRTF, 1976)
Atmospheric Science Facility (Part of Post 42)
Bioresearch Module (Part of Post 42)
Hughes: 30/20GHZ Technology Satellite
Ion beam plume and efflux characterization flight experiment study

The following documents are not online as of this date (16/01/2014):

An analysis of the Large Space Telescope (LST) application to solar system observations (Part of Post 31)
Integrated Control/Display Station For Teleoperator And Experiments


Hughes: Severe Storms Observing Satellite (SSOS aka StormSat) (1976)

The STORMSAT spacecraft and its primary sensors, the Advanced Atmospheric Sounding and Imaging Radiometer (AASIR) and Microwave Atmospheric Sounding Radiometer (MASR), will be used to provide the data base to enhance understanding of mesoscale weather phenomena, The primary data provided by STORMSAT will be visible images, infrared images,infrared temperature and humidity sounding, and microwave temperature and humidity sounding. These data will be processed into visible and infrared pictures, vertical temperature and humidity profiles, and possibly precipitation estimates. These data are currently being provided by a combination of polar orbiting and geostationary satellites, but not with the time and/or space resolution needed for mesoscale observation.
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Severe Storms Observing Satellite (STORMSAT), Final Report



 
A check of the links on page 2 of the thread shows that the following posts still have links to the online documents, where multiple different documents are in the same post, the link to that post will be in the first document title.

Power system interface and umbilical system study
Satellite power system salvage and disposal alternatives (Part of Post 18)
Satellite Power Systems (SPS). LSST systems and integration task for SPS flight test article (Part of Post 18)
Laser Data Transfer Flight Experiment
Research & Applications Module
 (The Executive Summary Report is not online.)
25-100kW Orbital Power Module
Large Space Telescope
Mission requirements for a manned earth observatory
Planetary/DoD Entry Technology Flight Experiments
Preliminary Design Study, Shuttle Modular Scanning Spectroradiometer, Final Report (Part of Post 26)
Convair: Large Space Structures Fabrication Experiment

Convair: Space Construction Automated Fabrication Experiment (SCAFE) (Part 4, Volume 1 of the report is not online)
Convair: Space Construction Experiment (SCE)


The following documents are not online as of this date (17/01/2014):

Very Large Space Telescope
The 12 Person Space Station & Logistics Module

Grumman: Manned Orbital Transfer Vehicle (1979)

1979 design for a Manned Orbital Transfer Vehicle. The documentation online lacks the executive summary, but does have a full list of 'generic missions'.

Manned Orbital Transfer Vehicle (MOTV): Volume 2, Mission Handbook
Manned Orbital Transfer Vehicle (MOTV): Volume 3, Program Requirements Document
Manned Orbital Transfer Vehicle (MOTV): Volume 4, Supporting Analysis
Manned Orbital Transfer Vehicle (MOTV): Volume 5, Turnaround Analysis
Manned Orbital Transfer Vehicle (MOTV): Volume 6, Five Year Program Plan





Later:

Located further documents relating to the Grumman MOTV.

Manned Geosynchronous Mission Requirements & Systems Analysis Study, Vol. 1, Executive Summary
Manned Geosynchronous Mission Requirements & Systems Analysis Study Extension, Vol. 1, Executive Summary
Manned Geosynchronous Mission Requirements & Systems Analysis Study Extension, 3rd Quarterly Review
Manned Orbital Transfer Vehicle Capabilities Handbook and User Guide
Manned Geosynchronous Mission Requirements & Systems Analysis Study Add-On, Final Briefing
 
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A check of the links on page 1 of the thread shows that the following posts still have links to the online documents, where multiple different documents are in the same post, the link to that post will be in the first document title.

Small Astronomy Payloads
Atmospheric, Magnetospheric and Plasmas in Space (AMPS) payload (Part of Post 4)
Astronomical Observatory for Shuttle, Phase A Study(Part of Post 4)
Spacelab Payload Accommodation Handbook (Appendix B Only) (Part of Post 4)
Guntersville Workshop on Solar-Terrestrial Studies
National Oceanic Satellite
A concept study of a remotely piloted vehicle for Mars exploration (Part of Post 8)
Modular Reflector Concept Study (Part of Post 8)
Exotic Particles In The Cosmic Rays Payload (EPIC)



The following documents are not online as of this date (18/01/2014):

Report of the facility definition team spacelab UV optical telescope facility
Astrophysics Near-Term Program. Project Concept Study: Starlab
Spacelab payload accommodation handbook. Main volume
Biomedical Experiments Scientific Satellite
Payload Installation & Deployment Aid (PIDA)


Module for Automatic Dock and Detumble (MADD) (1973)

RPV for space rescue designed by the Aerospace Engineering Department of Penn State. Designed for the ASTP style of docking collar, could be easily modeled with both that and the design of docking collar used on the ISS.

The Module for Automatic Dock and Detumble (MADD) is an automated device for bringing a passive, tumbling space base under control in an orbital rescue situation. The conceptual design of-such a device reslulted from a consideration of tumbling motion analyses, and mission constraints. Specific topics of investigation include orbit and, attitude dynamics and detumble profiles. Position and attitude control systems for the various phases of operation were developed. Dynamic motion of a passive vehicle with MADD attached is considered as an example application and to determine control requirements. Since time is a critical factor in rescue operations, it is essential to execute the detumbling maneuver in a minimum of time. Optimization of the MADD thrusting, sequence has also been investigated. Results indicate the control torque must be directed opposite to the angular momentum vector for the assumptions used here.
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Module for Automatic Dock and Detumble (MADD) for Orbital Rescue Operations



 
Convair - Orbital Propellant Transfer Experiment (1980)

Proposed 1985 space shuttle mission to test out a method for refuelling Orbital Transfer Vehicles.

The primary objective of this study was to provide the NASA Lewis Research Center with a conceptual design and development plan for a large scale orbital propellant transfer experiment. The scope of this effort was twofold. First, OTV configurations, operatlons and requirements planned for the period from the 1980's to the 1990's were reviewed and a propellant transfer experiment was designed that would support the needs of these advanced OTV operational concepts. Second, an experiment development plan was prepared to aid NASA LeRC in the preparation of an overall integrated propellant management technology plan for all NASA centers.
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Conceptual Design Of An Orbital Propellant Transfer Experiment, Vol. II, Study Results








 
Here are three pallet based experiments related to cryogenic storage.

McDonnell-Douglas: Spacelab Cryogenic Management Experiment (1976)

In order to demonstrate the desirability and feasibility of subcritical cryogenic fluid orbital storage and supply, the conceptual design of a Spacelab cryogen management experiment was performed. The conceptual design includes a description of the experimental apparatus, definition of supporting requirements, procedures, data analysis, and a cost estimate. The experiment was conceived as a LH2 tank 1.06 m (41. 7 in. ) in diameter with a screen device and helium pressurization system for LH2 supply, and a high-performance thermal control system consisting of a vapor-cooled shield thermodynamic vent system, multilayer insulation,and vacuum jacket. The experiment could be mounted on the ESA pallet and flown with Spacelab in the STS Orbiter payload bay, or alternatively, could be mounted in the bay next to the Spacelab ingress/egress tunnel. The complete experiment package in the payload bay, including fluids and pallet mounting supports, weighs 162 kg.
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Design and Evaluation of Thermodynamic Vent/Screen Baffle Cryogenic Storage System
Spacelab Cryogenic Management Experiment, Special Report




Beech Aircraft Corporation: Cryogenic Fluid Management Experiment (1981)

This study presents the conceptual design of a Spacelab experiment to develop the technology associated with low-gravity propellant management. The proposed facility consists of a supply tank, receiver tank, pressurization system, instrumentation and supporting hardware. A phased approach was assumed for the facility with Phase I concentrating on technology issues related to the supply tank and Phase II concentrating on technology issues related to the receiver tank.
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Conceptual Design of an In-Space Cryogenic Fluid Management Facility, Executive Summary
Conceptual Design of an In-Space Cryogenic Fluid Management Facility




Martin-Marietta: Cryogenic Fluid Management Experiment (1981)

Cryogenic liquid storage and supply systems will play an important role in meeting mission requirements of future NASA and DOD payloads. A first step in the development of spacecraft subcritical cryogenic storage systems is to obtain engineering data on the performance of these systems. The Cryogenic Fluid Management Experiment (CFME) is the first Space Shuttle flight system designed to characterize subcritical liquid hydrogen storage and expulsion i n the low-g space environment. The experiment utilizes a fine-mesh screen fluid management device to accomplish gas-free liquid expulsion and a thermodynamic vent system (TVS) to intercept heat leak and control tank pressure.
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Conceptual Design and Analysis of Orbital Cryogenic Liquid Storage and Supply Systems
Cryogenic Fluid Management Experiment

 
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I've just finished checking the links on an earlier post relating to an unflown shuttle experiment I linked to in the Op. This post dealt with the idea of adding a dedicated materials processing segment to the Spacelab module. All the documentation links in the post still point to the correct documents.

Early Spacelab Materials Processing Kit





McDonnell-Douglas: Auxiliary Payload Power System (1976)

Proposed add-on kit to allow the testing of materials processing in space. Document while only covering the preliminary design is the only one relating to this project available.

Auxiliary Payload Power System Study For Space Processing Applications Payloads. Preliminary Requirements Study

 
Perkins-Elmer: Deepsky Ultra-Violet Survey Telescope (1977)

Proposed wide field UV telescope designed for a solo flight mission. The shuttle markings shown on the artists impression (as mentioned earlier) would make for an interesting alternate shuttle skin.

Design Study of the Deepsky UltraViolet Survey Telescope







 
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McDonnell-Douglas: Space Shuttle Orbiter TPS Repair Kit (1979)

This report was prepared by the McDonnell-Douglas Astronautics Company (MDAC) for the National Aeronautics and Space Administration Johnson Space Center (NASA-JSC) in accordance with Contract NAS9-15971. It documents the results of a 2 and a half month program entitled Tile Protective System Flight Repair Kit Conceptual Design, which has as its major objective the conceptual development of a TPS Flight Repair Kit for use by the Shuttle crew for the on-orbit repair of any damage to the Orbiter TPS during launch.
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http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19800005922.pdf
 
Hamilton Standard: Portable Oxygen Subsystem (1975)

Like the item in the previous post this is equipment designed for use with the Space Shuttle rather than a payload, but one that could be added to the UMMUs.

Hamilton Standard has developed a Portable Oxygen Subsystem (POS) for use in the Space Shuttle Orbiter System. This development effort was conducted under Contract NAS 9-14458 to NASA's Johnson Space Center. The scope of this program included the selection, design, fabrication, and test of a POS which meets the Shuttle objectives of long life, low cost and minimum maintenance.

The POS is a rebreather type system which provides a revitalized breathing gas supply to a crewman for denitrogenization, emergency IV activity, and/or emergency rescue.
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http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19760009714.pdf


 
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Andy44 said:
"POS" ha. I'm guessing that had it continued they'd have changed the acronym early on.
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Probably to Emergency Oxygen Subsystem (EOS), then again I have seen an Apollo era document which referred to a software package called SMASHIN (The last word was 'Nefariousness'... :lol: )

Later:

Garret Airesearch - Portable(Emergency) Oxygen Subsystem (POS/EOS) - 1975

This report describes the concept selection, design, fabrication, and testing of a Portable Oxygen Subsystem (POS) for use in Space Shuttle operations. Tradeoff analyses were conducted to determine the POS concept for fabrication and testing, The fabricated POS was subjected to unmanned and manned tests to verify compilance with the Statement of Work requirements. The POS used in the development program described herein met requirements for the three operationl modes -- prebreathing, contaminated cabin, and Personnel Rescue System operations.
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http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19760009713.pdf
 

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TEAL RUBY

2599e.jpg


Unflown IR surveillance test satellite. Canceled after over a decade of development.

http://thespacereview.com/article/2599/1
 
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