Influence of control strategy on stability of dual-spin projectiles with fixed canards
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摘要
Existing literature has shown that the control force at the nose could cause dynamic instability for controlled projectiles. To lower the adverse impact on the dual-spin projectile with fixed canards under the premise of meeting guidance system requirements, the influence of control moment provided by a motor on the flight stability is analyzed in this paper. Firstly, the effect of the rolling movement on stability is analyzed based on the stability criterion derived using the Hurwitz stability theory. Secondly, the evaluation parameters combining the features of different control periods that could assess the variation of stability features after the motor torque are obtained. These effective formulas are used to indicate that, to reduce the flight instability risks, the stabilized rolling speed of roll speed keeping period should be as small as possible; the variation trend of motor torque during the rolling speed controlling period and the roll angle of the forward body during roll angle switching period are recommended corresponding to the projectile and trajectory characteristics. Moreover,detailed numerical simulations of 155 mm dual-spin projectile are satisfactory agreement with the theoretical results.
Existing literature has shown that the control force at the nose could cause dynamic instability for controlled projectiles. To lower the adverse impact on the dual-spin projectile with fixed canards under the premise of meeting guidance system requirements, the influence of control moment provided by a motor on the flight stability is analyzed in this paper. Firstly, the effect of the rolling movement on stability is analyzed based on the stability criterion derived using the Hurwitz stability theory. Secondly, the evaluation parameters combining the features of different control periods that could assess the variation of stability features after the motor torque are obtained. These effective formulas are used to indicate that, to reduce the flight instability risks, the stabilized rolling speed of roll speed keeping period should be as small as possible; the variation trend of motor torque during the rolling speed controlling period and the roll angle of the forward body during roll angle switching period are recommended corresponding to the projectile and trajectory characteristics. Moreover,detailed numerical simulations of 155 mm dual-spin projectile are satisfactory agreement with the theoretical results.
Existing literature has shown that the control force at the nose could cause dynamic instability for controlled projectiles. To lower the adverse impact on the dual-spin projectile with fixed canards under the premise of meeting guidance system requirements, the influence of control moment provided by a motor on the flight stability is analyzed in this paper. Firstly, the effect of the rolling movement on stability is analyzed based on the stability criterion derived using the Hurwitz stability theory. Secondly, the evaluation parameters combining the features of different control periods that could assess the variation of stability features after the motor torque are obtained. These effective formulas are used to indicate that, to reduce the flight instability risks, the stabilized rolling speed of roll speed keeping period should be as small as possible; the variation trend of motor torque during the rolling speed controlling period and the roll angle of the forward body during roll angle switching period are recommended corresponding to the projectile and trajectory characteristics. Moreover,detailed numerical simulations of 155 mm dual-spin projectile are satisfactory agreement with the theoretical results.
引文
[1] Moorhead S. Precision guidance kits(PGKs)improving the accuracy of conventional cannon rounds. Field Artill 2007:31-3. Jan.-Feb.
[2]Grignon C, Cayz.ac R, Hed.dadj S.Improvement of artillery projectile accuracy.In:Proc., 23rd international symposium on ballistics. Tarragona, Spain:International Ballistics Committee; 2007. p. 747-54.
[3] Knudson A, Moratz M, Altamura F. The future of fun-fired precision munitions(GFPM). Army AL T 2008:22-5. Jan.-March.
[4] Montalvo C, Costello M. Effect of canard stall on projectile roll and pitch damping. Proc. IME G J, Aero. Eng. 2011;225(No.9):703-16.
[5] Cooper G, Fresconi F, Costello M. Flight stability of an asymmetric projectile with activation canards. J Spacecraft Rockets 2012;49(No,1):130—5.
[6] Rogers J, Costello M. Course correction fuze concept analysis for in-service155mm spin-stabilized gunnery projectiles. In:AIAA guidance, navigation and control conference and exhibit, Honolulu, Hawaii, USA; 2008. p. 18-21.
[7] Costello M, Peterson A. Linear theory of a dual-spin projectile in atmospheric flight. J Guid Contr Dynam 2000;23(No.5):789—97.
[8] Wernert P. Stability analysis for canard guided dual-spin stabilized projectiles.In:AIAA atmospheric flight mechanics conference and exhibit, Chicago, USA;2009. p. 10-3.
[9] Dalin Z, Shenging T, Jie G, Rui C. Flight stability of a dual-spin projectile with canards. J Aero Eng 2014;0(No.0):1-14.
[10] Ollerenshaw D, Costello M. Simplified projectile swerve solution for general control inputs. J Guid Contr Dynam 2008;31(No.5):1259-65.
[11] Fresconi F, Plostins P. Control mechanism strategies for spin-stabilized projectiles. Proc IME G J. Aero. Eng. 2010;224(No.9):979-91.
[12] Chang Sijiang. Dynamic response to canard control and gravity for a dual-spin projectile. J Spacecraft Rockets 2016;53(No.3):558-66.
[13] Theodoulis S, Fassmann V, Wernert P, et al. Guidance and control design for a class of spin-stabilized fin-controlled projectiles. J Guid Contr Dynam2013;36(No.2):517-31.
[14] Fresconi Frank. Guidance and control of a projectile with reduced sensor and actuator requirements. J Guid Contr Dynam 2011;34(No.6):1757-66.
[15] John C,Thomas B, William F. Fixed canard 2-D guidance of artillery projectiles.Jan. 2006. US Patent, No.6981672, filed 3.
[16] Je S, Jung H, Park M, Cho T. A study on the aero dynamic characteristics for a spin-stabilized projectile with PGK. In:Proc 26th international symposium on ballistics, miami, USA; 2011. p. 578-86.
[17] Murphy CH. Angular motion of spinning almost symmetric missiles. J Guid Contr Dynam 1979;2(No.6):504-10.
[18] Murphy CH. Instability of controlled projectiles in ascending or descending flight J Guid Contr Dynam 1981;4(No.1):66-9.
[19] Wang Y, Cheng J, Yu J, Wang X. Influence of yawing force frequency on angular motion and ballistic characteristics of a dual-spin projectile. Defence Technology 2016;12(No.2):124-8.
[2]Grignon C, Cayz.ac R, Hed.dadj S.Improvement of artillery projectile accuracy.In:Proc., 23rd international symposium on ballistics. Tarragona, Spain:International Ballistics Committee; 2007. p. 747-54.
[3] Knudson A, Moratz M, Altamura F. The future of fun-fired precision munitions(GFPM). Army AL T 2008:22-5. Jan.-March.
[4] Montalvo C, Costello M. Effect of canard stall on projectile roll and pitch damping. Proc. IME G J, Aero. Eng. 2011;225(No.9):703-16.
[5] Cooper G, Fresconi F, Costello M. Flight stability of an asymmetric projectile with activation canards. J Spacecraft Rockets 2012;49(No,1):130—5.
[6] Rogers J, Costello M. Course correction fuze concept analysis for in-service155mm spin-stabilized gunnery projectiles. In:AIAA guidance, navigation and control conference and exhibit, Honolulu, Hawaii, USA; 2008. p. 18-21.
[7] Costello M, Peterson A. Linear theory of a dual-spin projectile in atmospheric flight. J Guid Contr Dynam 2000;23(No.5):789—97.
[8] Wernert P. Stability analysis for canard guided dual-spin stabilized projectiles.In:AIAA atmospheric flight mechanics conference and exhibit, Chicago, USA;2009. p. 10-3.
[9] Dalin Z, Shenging T, Jie G, Rui C. Flight stability of a dual-spin projectile with canards. J Aero Eng 2014;0(No.0):1-14.
[10] Ollerenshaw D, Costello M. Simplified projectile swerve solution for general control inputs. J Guid Contr Dynam 2008;31(No.5):1259-65.
[11] Fresconi F, Plostins P. Control mechanism strategies for spin-stabilized projectiles. Proc IME G J. Aero. Eng. 2010;224(No.9):979-91.
[12] Chang Sijiang. Dynamic response to canard control and gravity for a dual-spin projectile. J Spacecraft Rockets 2016;53(No.3):558-66.
[13] Theodoulis S, Fassmann V, Wernert P, et al. Guidance and control design for a class of spin-stabilized fin-controlled projectiles. J Guid Contr Dynam2013;36(No.2):517-31.
[14] Fresconi Frank. Guidance and control of a projectile with reduced sensor and actuator requirements. J Guid Contr Dynam 2011;34(No.6):1757-66.
[15] John C,Thomas B, William F. Fixed canard 2-D guidance of artillery projectiles.Jan. 2006. US Patent, No.6981672, filed 3.
[16] Je S, Jung H, Park M, Cho T. A study on the aero dynamic characteristics for a spin-stabilized projectile with PGK. In:Proc 26th international symposium on ballistics, miami, USA; 2011. p. 578-86.
[17] Murphy CH. Angular motion of spinning almost symmetric missiles. J Guid Contr Dynam 1979;2(No.6):504-10.
[18] Murphy CH. Instability of controlled projectiles in ascending or descending flight J Guid Contr Dynam 1981;4(No.1):66-9.
[19] Wang Y, Cheng J, Yu J, Wang X. Influence of yawing force frequency on angular motion and ballistic characteristics of a dual-spin projectile. Defence Technology 2016;12(No.2):124-8.