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Boeing AMLLV (Advanced Multipurpose Large Launch Vehicle)

XP67_Moonbat

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http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19750069565_1975069565.pdf

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19690030192_1969030192.pdf
 

Triton

Donald McKelvy
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Study of Advanced Multipurpose Large Launch Vehicles - Technical Report
January 1, 1968

Prepared under Contract No. NAS 2-4079
The Boeing Company
Huntsville, Alabama
for
Ames Research Center
National Aeronautics and Space Administration

Abstract
Study results are presented for a conceptual design analysis of "Advanced Multipurpose Large Launch Vehicles." This vehicle concept incorporates a single-stage-to-orbit main stage that orbits a million pound payload; and, with the addition of building block elements that include strap-on motors and a small injection stage, provides payload flexibility to nearly four million pounds. The objective was to develop practical, representative vehicle configurations through a series of design and performance trade studies, and to assess this vehicle system in terms of technology needs and implications. A vehicle family design is provided with its estimated performance and weight summaries for each possible flight configuration. Vehicle system information provided includes propulsion, pressurization, thermal, and control data. The design and performance data developed in trade studies of the design variables are presented. Both multichamber/plug and toroidal/aerospike systems were considered for main stage propulsion. The design and performance relationship between the main stage vehicle and its engine system options is stressed.

Strap-on boost assist elements investigated included various diameter solid motors and N204/UDMH pressure-fed pods. The structural impact of strap-ons to the main stage is described. The performance of the various strap-on configurations is given for both zero stage and parallel burn operation. Both the design impact and performance of the configuration with a small orbital injection stage are presented. The implications of this possible future vehicle system on technology and resources requirements are assessed to provide data for technology planning, resource estimating, and mission analysis studies.

URL:
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19750069565_1975069565.pdf
 

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Triton

Donald McKelvy
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Triton

Donald McKelvy
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Additional line drawings from Study of Advanced Multipurpose Large Launch Vehicles - Technical Report

URL:
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19750069565_1975069565.pdf
 

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Triton

Donald McKelvy
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Study of Advanced Multipurpose Large Launch Vehicles Summary Report
January 1, 1968

Prepared under Contract No. NAS 2-4079
The Boeing Company
Huntsville, Alabama
for
Ames Research Center
National Aeronautics and Space Administration


Abstract:
Study results are summarized for a conceptual design analysis of "Advanced Multipurpose Large Launch Vehicles." This vehicle concept incorporates a single-stage-to-orbit main stage that orbits a million pound payload; and, with the addition of building block elements that include strap-on motors and a small injection stage, provides payload flexibility to nearly four million pounds. The objective was to develop practical, representative vehicle configurations through a series of design and performance trade studies, and to assess this vehicle system in terms of technology needs and implications. A vehicle family design is provided with its estimated performance and weight summaries for each possible flight configuration. Vehicle system information provided includes propulsion, pressurization, thermal, and control data. The design and performance data developed in trade studies of the design variables are presented. Both multichamber/plug and toroidal/aerospike systems were considered for main stage propulsion. The design and performance relationship between the main stage vehicle and its engine system options is stressed.

Strap-on boost assist elements investigated included various diameter solid motors and N204/UDMH pressure-fed pods. The structural impact of strap-ons to the main stage is described. The performance of the various strap-on configurations is given for both zero stage and parallel burn operation. Both the design impact and performance of the configuration with a small orbital injection stage are presented. The implications of this possible future vehicle system on technology and resources requirements are assessed to provide data for technology planning, resource estimating, and mission analysis studies.

URL:
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19680010577_1968010577.pdf
 

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Donald McKelvy
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Concept for a Large Multipurpose Launch Vehicle
by Edward W Gomersall, Research Scientist, and John G Brunk, Advanced Vehicle System Manager, Launch Systems Branch, Space Division, The Boeing Company.

Mission Analysis Division, OART
Ames Research Center, NASA
Moffett Field, Calif. 94035


The key results of a NASA-sponsored study of a large multipurpose launch concept are summarized. The study evolved, through parametric performance and detailed design analyses, the characteristics of an attractive launch vehicle approach for consideration in future mission planning studies. The reported vehicle system has only two stages - a LOX/LHz main stage and a solid-motor strap-on stage. The main stage has the performance capability to fly single stage to orbit and the structural capability to accommodate strap-on stages to achieve a broad range of payload flexibility. The salient features of the vehicle system, sized to deliver one to four million pounds to low earth orbit, are described. The major resource and technology implications of the system are discussed.

URL:
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19680025115_1968025115.pdf
 

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Nik

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Wow, that's a BIG booger !!
 

Michel Van

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Here More Links from NTSR

Cost Studies of Multipurpose Large Launch Vehicles:

Volume One: Summary
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19690030191_1969030191.pdf

Volume Two: Half size (MLLV) Conceptual Design
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19690030192_1969030192.pdf

Volume Three: Resource Implication
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19690030193_1969030193.pdf

Volume Four: Baseline AMLLV Cost
Volume Five: Baseline MLLV Cost

Volume Six: Cost implications of Vehicle Size
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19690030194_1969030194.pdf

Volume Seven: Advanced Technology Implication
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19690030195_1969030195.pdf

Volume Eight: uncassified Appendices
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19700001226_1970001226.pdf

Volume Nine: Propulsion Data and Trajectories (Classifed Appendices)

Study of advanced multipurpose large launch vehicles:
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19750069565_1975069565.pdf

also (Parts of Volume Five?)
Baseline MLLV costs - Get ready or A costs, book A Final report - Document ID: 19700001823
Baseline MLLV costs - Developmental or B costs, book B Final report - Document ID: 19700001824
Baseline MLLV costs - Operational or C costs, book C Final report - Document ID: 19700001825

Nik said:
Wow, that's a BIG booger !!
there studied two size: A(dvance)MLLV and half size MLLV
all Payload in 100 n.m. 185,2 km orbit

AMLLV standard size: 266 ft x 71.6 ft ø / 81 meter x 21,8 meter ø
1.0 million lbs / 453592,0 kg

MLLV standard size: 220 ft x 56.6 ft ø / 67 meter x 17,2 meter ø
471000 lbs / 213642 kg
 

GeorgeA

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The AMLLV reference vehicle had a payload of 4 million lb. to orbit with 12 260-inch solid boosters, but a deep dive into the trade study as documented reveals that 300- to 330-inch hypergolic liquid boosters had a maximum theoretical payload of 5.2 million lbs. Other booster options, including larger solids, were examined as well. The trades involved a lot of attention to core size, core thrust, and throttling, as well as performance differences between the Pratt & Whitney version of the multichamber plug design, and the Rocketdyne toroidal aerospike.

The lineage of the concept is interesting as well. Boeing's early 60s Nova studies concentrated on parallel-staged vehicles with solid boosters and LH2 cores. An early Boeing ancestor of AMLLV was shown in the January 1966 issue of Astronautics and Aeronautics, in the article "Applying Large Solid Motors to Future Launch Vehicles". The vehicle in the article had a 36-million-lb. thrust core of 85 feet diameter and eight 260-inch boosters of up to 200 ft in length, yielding 4.2 million lbs. of payload. This basic design appeared again in the Boeing IMISCD study as a Post-Saturn variant, with a 24-million-lb. thrust, 75-ft. diameter core. The IMISCD study mentions the concurrent AMLLV study and notes the reference AMLLV vehicle was slightly smaller and perhaps more carefully optimized for generic launch missions.

The AMLLV program was envisioned as supporting 10 flights per year over a 20-year period. Depressing, huh?
 

sferrin

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IIRC Scott's article also mentions the possibility of 372" dia. solid boosters as well.
 

bobbymike

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More depressing information about a time decades ago when it seemed we wanted to take on any challenge. I say this as I watched the last shuttle flight and the end of the US manned space program.
 

FighterJock

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Anyone know the actual thrust of Boeing's large rocket? It certainly looks impressive size wise. SpaceX's Starship rocket looks small by comparison.
 

Gerald Roberts

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Inboard profile of Boeing AMLLV (Advanced Multipurpose Large Launch Vehicle) from 1968 with Saturn V for scale.

Source:
http://bbs.stardestroyer.net/viewtopic.php?f=22&t=148104&start=25

If there is actually an existing thread on this, please move.

Never heard of this before. 1968 concept using a cluster of 372" diameter solid rockets to lift 4.2 million pounds of payload.


Can't believe this video was made of my AMLLV design. Amazing.
This conceptual design was made by Boeing under contract for NASA Ames as a follow-on to the Saturn V. It was intended to make a vehicle able to launch a complete space station into orbit and then transfer it from 100nm to a 300 nm orbit. By building a modular vehicle, the launch vehicle could be tailored to whatever the payload weight was instead of trying to make the payload match the launch vehicle capability. The core areospike vehicle was made to launch the basic 1 million pound payload to 100nm. Solid rocket motors were added in pairs to reach intermediate payloads. The injection stage was also modular in design to transfer the 1 thru 4 million pound payloads from 100 to 300nm orbits. Because of the diameter, torus (donut) tanks were used with the large diameter LH2 tank able to hold the much heavier LOX tank from the inside. Extendable nozzle engines were nested in the interior to make a compact design.
A companion conceptual design was made for the launch site of this vehicle. Because the db level was so high, we choose to build a concrete launch site on the Florida continental shelf with a slit to allow the ships to bring the solid rocket motors directly to the launch gantry. It was fun to do the conceptual designs for both the vehicle and the launch site. My notes and drawings were donate to the Huntsville, AL Space and Rocket Center. Gerald Roberts
(I was the sole Boeing designer for these conceptual designs. Mr Brunk was the Boeing manager.)
 
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