US project, 1987-1991, to develop nuclear thermal rocket engines
Project Timberwind aimed to develop nuclear thermal rockets. Initial funding by the Strategic Defense Initiative from 1987 through 1991 totaled $139 million (then-year).[1] 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.
Advances in high-temperature metals, computer modelling and nuclear engineering in general resulted in dramatically improved performance. Whereas the NERVA 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 specific impulse from 930 to 1000 seconds.[citation needed]
History
In 1983, the Strategic Defense Initiative ("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.[3] 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/pebble-bed reactor, a concept developed by James R. Powell at the Brookhaven National Laboratory, 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).[4]
From 1987 to 1991 it was funded as a secret project codenamed Project Timberwind, which spent $139 million.[5] The proposed rocket project was transferred to the Space Nuclear Thermal Propulsion (SNTP) program at the Air Force Phillips Laboratory in October 1991.[6] NASA conducted studies as part of its 1992 Space Exploration Initiative (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,[4][7] after $200 million was spent.[8]
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.[13] 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.[14]
The planned ground test facilities were estimated to cost $400M of additional funding to complete in 1992.[15] 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.[14]
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.
The program had technical achievements as well, such as developing high-strength fibers, and carbide coatings for Carbon-Carbon composites. 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.[13] 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 Tungsten, which attenuates gamma rays and absorbs thermal neutrons, and Lithium Hydride, which has a large scattering cross section for fast and thermal neutrons was found to perform well with low mass compared to older Boron Aluminum Titanium Hydride (BATH) shields.[16]
Sandia National Labs was responsible for qualification of the coated particle fuel for use in the SNTP nuclear thermal propulsion concept.[15]
SNTP Comparison of Bleed and Expander Cycles
Pro
Con
Bleed Cycle
Lowest system complexity
Minimum reactor internal plumbing & manifolding
Development of reactor and balance of plant (BOP) is uncoupled
Fast startup easily achieved
Development of high temp turbine and feed lines required
Partial Flow Expander Cycle
State of the art turbine technology can be used
Higher Isp (~0.5%)
Coupled reactor and BOP development increases programmatic risk
Dedicated fuel elements to supply energy to drive the turbine are of unique design and require additional development
^Aftergood, Steven (October 2009). "Nozette and Nuclear Rocketry". Federation of American Scientists. Archived from the original on 26 May 2012. Retrieved 28 July 2012.
^ abLudewig, H. (1996), "Design of particle bed reactors for the space nuclear thermal propulsion program", Progress in Nuclear Energy, 30 (1): 1–65, doi:10.1016/0149-1970(95)00080-4
