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<title>Project Timberwind</title>

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Project Timberwind

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Project Timberwind aimed to develop <a href="Nuclear_thermal_rocket" title="Nuclear thermal rocket">nuclear thermal rockets</a>. Initial funding by the <a href="Strategic_Defense_Initiative" title="Strategic Defense Initiative">Strategic Defense Initiative</a> from 1987 through 1991 totaled $139 million (then-year).<a href="#cite_note-tw_audit-1">[1]</a> The proposed rocket was later expanded into a larger design after the project was transferred to the Air Force Space Nuclear Thermal Propulsion (SNTP) program.

The program underwent an audit in 1992 due to security concerns raised by <a href="Steven_Aftergood" title="Steven Aftergood">Steven Aftergood</a>.<a href="#cite_note-tw_audit-1">[1]</a> This <a href="Special_access_program" title="Special access program">highly classified program</a> provided the motivation for starting the <a href="Federation_of_American_Scientists#Government_Secrecy" title="Federation of American Scientists">FAS Government Secrecy project</a>. Convicted spy <a href="Stewart_Nozette" title="Stewart Nozette">Stewart Nozette</a> was found to be on the master access list for the TIMBER WIND project.<a href="#cite_note-fas_nozette-2">[2]</a>

Advances in high-temperature metals, computer modelling and nuclear engineering in general resulted in dramatically improved performance. Whereas the <a href="NERVA" title="NERVA">NERVA</a> engine was projected to weigh about 6803 kg, the final SNTP offered just over 1/3 the thrust from an engine of only 1650 kg, while further improving the <a href="Specific_impulse" title="Specific impulse">specific impulse</a> from 930 to 1000 seconds.

<div class="mw-heading mw-heading2"><h2 id="History">History</h2></div>

In 1983, the <a href="Strategic_Defense_Initiative" title="Strategic Defense Initiative">Strategic Defense Initiative</a> ("Star Wars") identified missions that could benefit from rockets that are more powerful than chemical rockets, and some that could only be undertaken by more powerful rockets.<a href="#cite_note-FOOTNOTEHaslett19953-1-3">[3]</a> A nuclear propulsion project, SP-100, was created in February 1983 with the aim of developing a 100 KW nuclear rocket system. The concept incorporated a particle/<a href="Pebble-bed_reactor" title="Pebble-bed reactor">pebble-bed reactor</a>, a concept developed by <a href="James_R._Powell_(physicist)" title="James R. Powell (physicist)">James R. Powell</a> at the <a href="Brookhaven_National_Laboratory" title="Brookhaven National Laboratory">Brookhaven National Laboratory</a>, which promised a specific impulse of up to 1,000 seconds (9.8 km/s) and a thrust to weight ratio of between 25 and 35 for thrust levels greater than 89,000 newtons (20,000 lbf).<a href="#cite_note-FOOTNOTEHaslett19951–1,_2-1–2-5-4">[4]</a>

From 1987 to 1991 it was funded as a secret project codenamed Project Timberwind, which spent $139 million.<a href="#cite_note-FOOTNOTELieberman19923–4-5">[5]</a> The proposed rocket project was transferred to the Space Nuclear Thermal Propulsion (SNTP) program at the Air Force <a href="Phillips_Laboratory" title="Phillips Laboratory">Phillips Laboratory</a> in October 1991.<a href="#cite_note-FOOTNOTEHaslett19952-4-6">[6]</a> NASA conducted studies as part of its 1992 <a href="Space_Exploration_Initiative" title="Space Exploration Initiative">Space Exploration Initiative</a> (SEI) but felt that SNTP offered insufficient improvement over NERVA, and was not required by any SEI missions. The SNTP program was terminated in January 1994,<a href="#cite_note-FOOTNOTEHaslett19951–1,_2-1–2-5-4">[4]</a><a href="#cite_note-7">[7]</a> after $200 million was spent.<a href="#cite_note-FOOTNOTEHaslett19953-7-8">[8]</a>

<div class="mw-heading mw-heading2"><h2 id="Timberwind_Specifications">Timberwind Specifications</h2></div>

<div class="mw-heading mw-heading3"><h3 id="Timberwind_45_on_Timberwind_Centaur">Timberwind 45 on Timberwind Centaur</h3></div>

<ul><li>Diameter: 13.94 ft (4.25 m), Length:<a href="#cite_note-TC-9">[9]</a> 23.87 m</li>

<li>Nr of engines : 1</li>

<li>Vacuum thrust: 99208 <a href="Pound-force" class="mw-redirect" title="Pound-force">lbf</a> (441.3 kN)</li>

<li>Sea level thrust: 88305 lbf (392.8 kN)</li>

<li>Vacuum specific impulse: 1000 s</li>

<li>Sea level specific impulse: 890 s</li>

<li>Engine mass: 3300 lb (1500 kg)</li>

<li>Thrust to Weight Ratio: 30</li>

<li>Propellants: Nuclear/LH2</li></ul>

<div class="mw-heading mw-heading3"><h3 id="Timberwind_75_on_Timberwind_Titan">Timberwind 75 on Timberwind Titan</h3></div>

<ul><li>Stage Diameter: 6.1 m (20 ft) Length: 45.50 m<a href="#cite_note-TT-10">[10]</a></li>

<li>Diameter: 5.67 ft (2.03 m)</li>

<li>Nr of engines : 3 <a href="#cite_note-TT-10">[10]</a></li>

<li>Engine :

<ul><li>Vacuum thrust: 165347 lbf (735.5 kN)</li>

<li>Sea level thrust: 147160 lbf (654.6 kN)</li>

<li>Vacuum specific impulse: 1000 s</li>

<li>Sea level specific impulse: 890 s</li>

<li>Engine mass: 5500 lb (2500 kg)</li>

<li>Thrust to Weight Ratio: 30</li></ul></li>

<li>Propellants: Nuclear/LH2</li></ul>

<div class="mw-heading mw-heading3"><h3 id="Timberwind_250_stage_and_engine">Timberwind 250 stage and engine</h3></div>

<ul><li>Diameter: 28.50 ft (8.70 m). Length: 30.00 m<a href="#cite_note-TR-11">[11]</a></li>

<li>Nr of engines : 1

<ul><li>Vacuum thrust: 551,142 lbf (2,451.6 kN).</li>

<li>Sea level thrust: 429,902 lbf (1,912.0 kN)</li>

<li>Vacuum specific impulse: 1,000 s.</li>

<li>Sea level specific impulse: 780 s.</li>

<li>Engine mass: 8,300 kg (18,200 lb).</li>

<li>Thrust to Weight Ratio: 30</li></ul></li>

<li>Propellants: Nuclear/LH2</li></ul>

<div class="mw-heading mw-heading2"><h2 id="Space_Nuclear_Thermal_Propulsion_Program">Space Nuclear Thermal Propulsion Program</h2></div>

In contrast to the TIMBER WIND project, the Space Nuclear Thermal Propulsion (SNTP) program was intended to develop upper-stages for space-lift which would not operate within the Earth's atmosphere. SNTP failed to achieve its objective of flight testing a nuclear thermal upper-stage, and was terminated in January 1994.<a href="#cite_note-sntp_final-13">[13]</a> The program involved coordinating efforts across the Department of Defense, the Department of Energy, and their contractors from operating sites across the U.S. A major accomplishment of the program was to coordinate Environmental Protection Agency approvals for ground testing at two possible sites.<a href="#cite_note-final_eia-14">[14]</a>

<caption>Participating or Cooperating Agencies<a href="#cite_note-final_eia-14">[14]</a>

</caption>

<th scope="col">Name

</th>

<th scope="col">Location

</th>

<th scope="col">Responsibilities

</th></tr>

<tr>

<td><a href="Brookhaven_National_Laboratory" title="Brookhaven National Laboratory">Brookhaven National Laboratory</a>

</td>

<td>Upton, NY

</td>

<td>Reactor materials and components testing; thermal-hydraulic, and neutronic analysis; reactor design studies<a href="#cite_note-pbr_design_sntp-12">[12]</a>

</td></tr>

<tr>

<td><a href="Babcock_%26_Wilcox" title="Babcock & Wilcox">Babcock & Wilcox</a>

</td>

<td>Lynchburg, VA

</td>

<td>Reactor design testing, fabrication and assembly

</td></tr>

<tr>

<td><a href="Sandia_National_Labs" class="mw-redirect" title="Sandia National Labs">Sandia National Labs</a>

</td>

<td>Albuquerque, NM

</td>

<td>Nuclear safety, nuclear instrumentation and operation, reactor control system modeling, nuclear testing

</td></tr>

<tr>

<td><a href="Aerojet" title="Aerojet"> Aerojet Propulsion Division</a>

</td>

<td>Sacramento, CA

</td>

<td>Fuel element alternate materials development

</td></tr>

<tr>

<td><a href="Hercules_Aerospace" class="mw-redirect" title="Hercules Aerospace"> Hercules Aerospace Corporation</a>

</td>

<td>Magna, UT

</td>

<td>Design and fabrication of engine lower structure and nozzle

</td></tr>

<tr>

<td><a href="Garrett_AiResearch" title="Garrett AiResearch">Garrett Fluid Systems Division</a>

</td>

<td>Tempe, AZ and San Tan, AZ

</td>

<td>Design and fabrication of attitude control system, propellant flow control system and turbopump assembly

</td></tr>

<tr>

<td><a href="Garrett_AiResearch" title="Garrett AiResearch">AiResearch Los Angeles Division of Allied Signal</a>

</td>

<td>Torrance, CA

</td>

<td>Turbine wheel testing

</td></tr>

<tr>

<td><a href="Grumman" title="Grumman"> Grumman Space Electronics Division</a>

</td>

<td>Bethpage, NY

</td>

<td>Vehicle design and fabrication, systems integration

</td></tr>

<tr>

<td><a href="Raytheon" title="Raytheon">Raytheon Services Nevada</a>

</td>

<td>Las Vegas, NV

</td>

<td>Facility and Coolant Supply System (CSS) engineering, facility construction management

</td></tr>

<tr>

<td>Reynolds Electrical and Engineering Company, Inc

</td>

<td>Las Vegas, NV

</td>

<td>Facility construction

</td></tr>

<tr>

<td>Fluor-Daniel, Inc.

</td>

<td>Irvine, CA

</td>

<td>Effluent Treatment System (ETS) engineering

</td></tr>

<tr>

<td><a href="Sandia_National_Labs" class="mw-redirect" title="Sandia National Labs">Sandia National Labs</a>

</td>

<td>Saddle Mountain Test Site or QUEST or LOFT Sites

</td>

<td>Test site preparation, planning and performance of engine ground tests, nuclear component testing

</td></tr>

<tr>

<td>[REDACTED]

</td>

<td>Washington, DC

</td>

<td>Program management

</td></tr>

<tr>

<td><a href="United_States_Department_of_Energy" title="United States Department of Energy">DoE Headquarters</a>

</td>

<td>Washington, DC

</td>

<td>Program management, nuclear safety assurance

</td></tr>

<tr>

<td><a href="Nevada_National_Security_Site" class="mw-redirect" title="Nevada National Security Site">DoE Nevada Test Site</a>

</td>

<td>Las Vegas, NV

</td>

<td>Ground testing

</td></tr>

<tr>

<td><a href="Idaho_National_Laboratory" title="Idaho National Laboratory">DoE Idaho National Engineering Lab</a>

</td>

<td>Idaho Falls, ID

</td>

<td>Ground testing

</td></tr>

<tr>

<td><a href="Phillips_Laboratory" title="Phillips Laboratory">U.S. Air Force Phillips Lab</a>

</td>

<td>Albuquerque, NM

</td>

<td>Program management

</td></tr>

<tr>

<td><a href="United_States_Army_Corps_of_Engineers" title="United States Army Corps of Engineers">U.S. Army Corps of Engineers</a>

</td>

<td>Huntsville, AL

</td>

<td>ETS engineering management

</td></tr>

<tr>

<td><a href="Los_Alamos_National_Laboratory" title="Los Alamos National Laboratory">Los Alamos National Laboratory</a>

</td>

<td>Los Alamos, NM

</td>

<td>Fuels and materials testing

</td></tr>

<tr>

<td><a href="Marshall_Space_Flight_Center" title="Marshall Space Flight Center">Marshall Space Flight Center</a> (NASA)

</td>

<td>Huntsville, AL

</td>

<td>Material and component simulation/testing

</td></tr>

<tr>

<td><a href="Western_Range_(USAF)" class="mw-redirect" title="Western Range (USAF)">Western Test Range/Western Space & Missile Center (USAF)</a>

</td>

<td>Vandenberg AFB, CA

</td>

<td>Program review

</td></tr>

<tr>

<td><a href="Arnold_Engineering_Development_Complex" title="Arnold Engineering Development Complex">Arnold Engineering Development Center</a>

</td>

<td>Manchester, TN

</td>

<td>Hydrogen flow testing

</td></tr>

<tr>

<td>UNC Manufacturing Company

</td>

<td>Uncasville, CT

</td>

<td>Materials manufacturing

</td></tr>

<tr>

<td><a href="Grumman" title="Grumman">Grumman Corporation - Calverton Facility</a>

</td>

<td>Long Island, NY

</td>

<td>Hydrogen testing

</td></tr></tbody></table>

The planned ground test facilities were estimated to cost $400M of additional funding to complete in 1992.<a href="#cite_note-gao_nukerock_cost-15">[15]</a> Fewer than 50 sub-scale tests were planned over three to four years, followed by facility expansions to accommodate five to 25 1000 second full-scale tests of a 2000MW engine.<a href="#cite_note-final_eia-14">[14]</a>

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</style><blockquote class="templatequote">Initially, PIPET [Particle Bed Reactor Integral Performance Element Tester] was envisioned as a small, low-cost, SNTP-specific experiment for testing and qualifying PBR fuel and fuel elements. The demands by other agencies, DOE and NASA, resulted in a national test facility for NTP fuel, fuel elements, and engines. Its size out grew the SNTP Program's ability to secure the funds for such a large construction project. Though the demands were placed upon the SNTP Program to expand the facility's scope and the SNTP Program's management tried to coordinate tri-agency, DoD-DOE-NASA, support and funding, adequate funding support for the national ground test facility was not obtained. </blockquote><div class="templatequotecite">— SNTP Final Report, <a href="#cite_note-sntp_final-13">[13]</a></div>

The program had technical achievements as well, such as developing high-strength fibers, and carbide coatings for <a href="Reinforced_carbon%E2%80%93carbon" title="Reinforced carbon–carbon">Carbon-Carbon composites</a>. The hot-section design evolved to use all Carbon-Carbon to maximize turbine inlet temperature and minimize weight. Carbon-Carbon has much lower nuclear heating than other candidate materials, so thermal stresses were minimized as well. Prototype turbine components employing a 2-D polar reinforcement weave were fabricated for use in the corrosive, high-temperature hydrogen environment found in the proposed particle bed reactor (PBR)-powered engine.<a href="#cite_note-sntp_final-13">[13]</a> The particle bed reactor concept required significant radiation shielding, not only for the payload, electronics and structure of the vehicle, but also to prevent unacceptable boil-off of the cryogenic propellant. A propellant-cooled, composite shield of <a href="Tungsten" title="Tungsten">Tungsten</a>, which attenuates gamma rays and absorbs thermal neutrons, and <a href="Lithium_hydride" title="Lithium hydride">Lithium Hydride</a>, which has a large scattering cross section for fast and thermal neutrons was found to perform well with low mass compared to older <a href="Boron_Aluminum_Titanium_Hydride" class="mw-redirect" title="Boron Aluminum Titanium Hydride">Boron Aluminum Titanium Hydride</a> (BATH) shields.<a href="#cite_note-pbr_shield-16">[16]</a>

<a href="Sandia_National_Labs" class="mw-redirect" title="Sandia National Labs">Sandia National Labs</a> was responsible for qualification of the coated particle fuel for use in the SNTP nuclear thermal propulsion concept.<a href="#cite_note-gao_nukerock_cost-15">[15]</a>

<caption>SNTP Comparison of Bleed and Expander Cycles

</caption>

<th>

</th>

<th scope="col">Pro

</th>

<th scope="col">Con

</th></tr>

<tr>

<th scope="row">Bleed Cycle

</th>

<td><div><ol><li>Lowest system complexity</li><li>Minimum reactor internal plumbing & manifolding</li><li>Development of reactor and balance of plant (BOP) is uncoupled</li><li>Fast startup easily achieved</li></ol></div></td>

<td>Development of high temp turbine and feed lines required

</td></tr>

<tr>

<th scope="row">Partial Flow Expander Cycle

</th>

<td><div><ol><li>State of the art turbine technology can be used</li><li>Higher Isp (~0.5%)</li></ol></div>

</td>

<td><div><ol><li>Coupled reactor and BOP development increases programmatic risk</li><li>Dedicated fuel elements to supply energy to drive the turbine are of unique design and require additional development</li></ol></div>

</td></tr></tbody></table>

<div class="mw-heading mw-heading2"><h2 id="References">References</h2></div>

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</style><cite id="CITEREFLieberman1992" class="citation web cs1">Lieberman, Robert (December 1992). <a rel="nofollow" class="external text" href="http://www.fas.org/sgp/othergov/dod/tw.pdf">"Audit Report on the TIMBER WIND Special Access Program"</a> (PDF). Department of Defense. <a rel="nofollow" class="external text" href="https://web.archive.org/web/20120520082710/http://www.fas.org/sgp/othergov/dod/tw.pdf">Archived</a> (PDF) from the original on 20 May 2012. Retrieved 28 July 2012.</cite>

</li>

<li id="cite_note-fas_nozette-2"><a href="#cite_ref-fas_nozette_2-0">^</a> <cite id="CITEREFAftergood2009" class="citation web cs1">Aftergood, Steven (October 2009). <a rel="nofollow" class="external text" href="http://www.fas.org/blog/secrecy/2009/10/nozette.html">"Nozette and Nuclear Rocketry"</a>. Federation of American Scientists. <a rel="nofollow" class="external text" href="https://web.archive.org/web/20120526091729/http://www.fas.org/blog/secrecy/2009/10/nozette.html">Archived</a> from the original on 26 May 2012. Retrieved 28 July 2012.</cite>

</li>

<li id="cite_note-FOOTNOTEHaslett19953-1-3"><a href="#cite_ref-FOOTNOTEHaslett19953-1_3-0">^</a> <a href="#CITEREFHaslett1995">Haslett 1995</a>, p. 3-1.

</li>

<li id="cite_note-FOOTNOTEHaslett19951–1,_2-1–2-5-4">^ <a href="#cite_ref-FOOTNOTEHaslett19951–1,_2-1–2-5_4-0">a</a> <a href="#cite_ref-FOOTNOTEHaslett19951–1,_2-1–2-5_4-1">b</a> <a href="#CITEREFHaslett1995">Haslett 1995</a>, pp. 1–1, 2-1–2-5.

</li>

<li id="cite_note-FOOTNOTELieberman19923–4-5"><a href="#cite_ref-FOOTNOTELieberman19923–4_5-0">^</a> <a href="#CITEREFLieberman1992">Lieberman 1992</a>, pp. 3–4.

</li>

<li id="cite_note-FOOTNOTEHaslett19952-4-6"><a href="#cite_ref-FOOTNOTEHaslett19952-4_6-0">^</a> <a href="#CITEREFHaslett1995">Haslett 1995</a>, p. 2-4.

</li>

<li id="cite_note-7"><a href="#cite_ref-7">^</a> <cite id="CITEREFMillerBennett1993" class="citation journal cs1">Miller, Thomas J.; Bennett, Gary L. (1993). "Nuclear propulsion for space exploration". Acta Astronautica. 30: 143–149. <a href="Bibcode_(identifier)" class="mw-redirect" title="Bibcode (identifier)">Bibcode</a>:<a rel="nofollow" class="external text" href="https://ui.adsabs.harvard.edu/abs/1993AcAau..30..143M">1993AcAau..30..143M</a>. <a href="Doi_(identifier)" class="mw-redirect" title="Doi (identifier)">doi</a>:<a rel="nofollow" class="external text" href="https://doi.org/10.1016%2F0094-5765%2893%2990106-7">10.1016/0094-5765(93)90106-7</a>. <a href="ISSN_(identifier)" class="mw-redirect" title="ISSN (identifier)">ISSN</a> <a rel="nofollow" class="external text" href="https://search.worldcat.org/issn/0094-5765">0094-5765</a>.</cite>

</li>

<li id="cite_note-FOOTNOTEHaslett19953-7-8"><a href="#cite_ref-FOOTNOTEHaslett19953-7_8-0">^</a> <a href="#CITEREFHaslett1995">Haslett 1995</a>, p. 3-7.

</li>

<li id="cite_note-TC-9"><a href="#cite_ref-TC_9-0">^</a> <a rel="nofollow" class="external text" href="https://web.archive.org/web/20061018195321/http://www.astronautix.com/lvs/timntaur.htm">Timberwind Centaur</a>

</li>

<li id="cite_note-TT-10">^ <a href="#cite_ref-TT_10-0">a</a> <a href="#cite_ref-TT_10-1">b</a> <a rel="nofollow" class="external text" href="https://web.archive.org/web/20061018193800/http://www.astronautix.com/lvs/timtitan.htm">Timberwin Titan</a>

</li>

<li id="cite_note-TR-11"><a href="#cite_ref-TR_11-0">^</a> <a rel="nofollow" class="external text" href="https://web.archive.org/web/20080708221621/http://www.astronautix.com/lvs/timrwind.htm">Timberwind rocket</a>

</li>

<li id="cite_note-pbr_design_sntp-12">^ <a href="#cite_ref-pbr_design_sntp_12-0">a</a> <a href="#cite_ref-pbr_design_sntp_12-1">b</a> <cite id="CITEREFLudewig1996" class="citation cs2">Ludewig, H. (1996), "Design of particle bed reactors for the space nuclear thermal propulsion program", Progress in Nuclear Energy, 30 (1): 1–65, <a href="Doi_(identifier)" class="mw-redirect" title="Doi (identifier)">doi</a>:<a rel="nofollow" class="external text" href="https://doi.org/10.1016%2F0149-1970%2895%2900080-4">10.1016/0149-1970(95)00080-4</a></cite>

</li>

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<div class="mw-heading mw-heading2"><h2 id="External_links">External links</h2></div>

<ul><li><a rel="nofollow" class="external text" href="https://web.archive.org/web/20061105180112/http://www.astronautix.com/engines/timind45.htm">Encyclopedia Astronautica link about the Timberwind 45</a></li>

<li><a rel="nofollow" class="external text" href="https://web.archive.org/web/20061207202619/http://astronautix.com/engines/timind75.htm">Encyclopedia Astronautica link about the Timberwind 75</a></li>

<li><a rel="nofollow" class="external text" href="https://web.archive.org/web/20080602060358/http://www.astronautix.com/engines/timnd250.htm">Encyclopedia Astronautica link about the Timberwind 250</a></li>

<li><a rel="nofollow" class="external text" href="https://apps.dtic.mil/sti/citations/ADA305996">Space Nuclear Thermal Propulsion Program Final Report</a></li></ul></div><div><div class="zim-footer">

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