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definitions and mathematical correction factors which obscure actual performance results and complicate qualitative comparison of competitive propellants. An industry survey determined desirable standard motor system parameters and prevailing practices. From industry, best practice such as 1,000 psi combustion pressure and 15 degree nozzle exit half-angle expanded to local ambient pressure, were adopted in the motor and system design as far as possible. Other system parameters were selected by the assigned design engineer/manager; 2Lt H. Gale. Eight months after assignment, first firing was in
September, 1961. Twelve firings of two propellants were made for motor and system evaluation. All objectives were successfully achieved or exceeded. Calibration firings established the confidence level and accuracy of the system prior to evaluation of industry propellants.
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cartridge case, on the OD, burning only on the two outer ends and the central bore, and is dimensioned so the burning area does not change significantly (< 3% in the original BATES motor) through the burn, generating a flat-topped thrust curve (neutral burn) to minimize propellant characterization
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consists of one or more cylindrical grain segments with the outer surface inhibited, but free to burn both on the segment ends and the cylindrical core. Such grains are very easy to cast, while allowing for the user to configure a progressive, regressive, or neutral thrust curve by changing various
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in 1959 through the early 1960s, used for almost forty years thereafter, and again beginning in 2010. Then through 2016. According to this reference, a single propellant grain weighing 68 to 70 pounds was used in the original AFRL BATES motor design. An AFRL BATES propellant grain is inhibited,
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Abstract: A reproducible, accurate, ballistic evaluation system for solid propellants was developed. Particular attention centered on an accuracy level of 0.5 percent or better on specific impulse (Isp). Evaluation of new propellants by their manufacturers had resulted in a multiplicity of
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Development and
Evaluation of the USAF Ballistic Test Evaluation System for Solid Rocket Propellants Accession Number : AD0276424: Technical documentary report : TEST GROUP (DEVELOPMENT) (6593RD) EDWARDS AFB
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In 2016 the AIR FORCE published through DTIC an overview the included a summary of BATES use.
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The first official description of the BATES system was published by and available from the
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234:"The History of the BATES Motors at the Air Force Rocket Propulsion Laboratory"
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239:. AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST (1998).
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dimensions. The neutral BATES length is calculated by the equation
264:"AFRL test marks return to 'in-house' rocket fuel development"
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An official press release in 1964 included BATES information.
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This article is about AFRL BATES. For other uses, see
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63:In modern usage, BATES often refers to a type of
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134:{\displaystyle L={\frac {1}{2}}(3D_{g}+d_{c})}
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39:United States Air Force Research Laboratory
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47:costs and simplify the data analysis.
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243:from the original on October 9, 2012
52:Defense Technical Information Center
28:BAllistic Test and Evaluation System
442:. You can help Knowledge (XXG) by
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293:Gale, Harold W. (April 1962).
270:. US Air Force. Archived from
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406:Richard Experimental Rocketry
380:Richard Experimental Rocketry
402:"Rocket motor design charts"
161:is the length of the grain,
438:This rocketry article is a
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376:"RNX Composite Propellant"
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232:Geisler, R.; Beckman, C.
301:(Report). Archived from
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18:Bates (disambiguation)
308:on February 1, 2017.
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208:{\displaystyle d_{c}}
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181:{\displaystyle D_{g}}
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262:Thuloweit, Kenji.
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65:solid-fuel rocket
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32:solid rocket
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324:"- YouTube"
73:BATES grain
483:Categories
411:30 January
360:2022-06-02
219:References
35:propellant
241:Archived
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329:YouTube
67:motor
354:(PDF)
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71:. A
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