Approved for public release; distribution is unlimited.ii REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)September 2008 ARL-TR-4611 SPONSOR/MONITOR'S ACRONYM(S) 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTSpin-stabilized artillery munitions were originally designed to provide precise ballistic fire on long-range targets. Today the challenge is to utilize these ballistic munitions in military operations in urban terrain environments where significantly higher levels of precision are required to minimize collateral damage. One strategy is to retrofit these munitions with some level of low-cost precision. Unique challenges arise when munitions designed to be ballistically precise are guided. Projectile flight is often stabilized by a high spin rate, which induces complex dynamics. Flight mechanics are further aggravated by adding a control mechanism. The goal of this study was to provide a fundamental understanding of various control mechanism strategies for spin-stabilized projectiles. Flight control systems were developed and executed in a six degree-of-freedom simulation. Formulating a generalized model of a control mechanism allowed investigation of parameters such as control force magnitude, control axial location, control lift-to-drag ratio, and control force duration. Results showed that control authority linearly related to control force magnitude. Maximal control authority was obtained by placing the control mechanism at the rear of the projectile. The variation with axial location was also determined since these results were valuable for instances when the control was unable to be located near the projectile base. A lower lift-to-drag ratio of the control mechanism decreased control authority and maximum range. Lastly, the trade-offs associated with continuous and pulsed flight control systems were quantified. Physical explanations for the simulation results were provided. SUBJECT TERMSflight dynamics, precise muni...
Approved for public release; distribution is unlimited.ii REPORT DOCUMENTATION PAGE Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) ARL-TR-3589 SPONSOR/MONITOR'S ACRONYM(S) 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES* Georgia Tech Research Institute, Smyrna, GA 30080 † Georgia Institute of Technology, Atlanta, GA 30332 ABSTRACTThe focus of this report is to provide a technical and programmatic summary of a Defense Advanced Research Projects Agency effort to explore the feasibility of producing steering forces on a spinning projectile using microadaptive flow control (MAFC). The report discusses the theoretical foundation for the flow control mechanism, the multidisciplinary modeling technology developed, the flight control technology required to enable the MAFC on spinning projectiles, iii
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