In recent years, a number of technology and operational features have emerged which have had an impact on the design of control systems for tactical missiles. These have required the closer tuning of autopilots to both the guidance loop and the aerodynamic limits and, at the same time, new design and assessment methods have also been developed for control systems. It is the purpose of this paper to bring these developments together and show how the various aspects contribute to the overall design process which enables a missile autopilot to reach maturity.
MetcalfeH.From Rheintochter to Rapier, 1992, Royal Aeronautical Society).
6.
MarkhamK. C.IMPACT: A computer program to aid missile system design. Aeronaut. J., January 1990.
7.
NeslineF. W.NeslineM. L.How autopilot requirements constrain the aerodynamic design of homing missiles. American Control Conference Proceedings, 1984, pp. 716–730.
8.
NeslineF. W.NeslineM. L.How autopilot requirements constrain the aerodynamic design of homing missiles. American Control Conference Proceedings, June 1984, pp. 716–730.
9.
NeslineF. W.NeslineM. L.Wing size v radome compensation in aerodynamic controlled radar homing missiles. J. Guidance, Control and Dynamics, 1986, 9(6), 645–649.
10.
NeslineF. W.ZarchanP.Missile guidance design trade-offs for high altitude air defence. J. Guidance, Control and Dynamics, 1983, 6, 207–212.
11.
NeslineF. W.ZarchanP.Miss distance dynamics in homing missiles. AIAA Guidance and Control Conference Proceedings, August 1984, pp. 84–98.
12.
NeslineF. W.ZarchanP.Radome induced miss distance in aerodynamically controlled homing missiles. AIAA Guidance and Control Conference Proceedings, August 1984, pp. 99–115.
13.
NeslineF. W.ZarchanP.Line of sight reconstruction for faster homing guidance. J. Guidance, Control and Dynamics, 1985, 8, 3.
14.
NeslineF. W.ZarchanP.Digital homing guidance—stability-v-performance trade-offs. J. Guidance, Control and Dynamics, 1985, 8, 255.
15.
RusnakK. I.LeviM.Modern guidance law for high-order autopilot. J. Guidance, Control and Dynamics, 1991, 14(5), 1056–1058.
16.
YuenW. R.LinC. F.Optimal controller for homing missiles. J. Guidance, Control and Dynamics, 1985, 8(3), 408–411.
17.
ZarchanP.Complete statistical analysis of non-linear missile guidance systems—SLAM. J. Guidance and Control, 1979, 2(1), 71–78.
18.
BlackelockJ. H.Automatic control of aircraft and missiles, 1991, John Wiley, Chichester).
19.
McCormicB. W, Aerodynamics, aeronautics and flight mechanics, 1979, John Wiley, Chichester).
20.
SpearmanF. R. J.The derivation and use of aerodynamic transfer functions for airframes. J. R. Aeronaut. Soc., November 1955.
21.
AlbanesW.Design of guidance and control digital autopilots. J. Guidance and Control, 1981, 4(2), 126–133.
22.
ArrowA.WilliamsD. E.Comparison of classical and modern missile autopilot design and analysis techniques. J. Guidance, Control and Dynamics, 1989, 12(2), 220–227.
23.
FlemingR. J.IrwinG. W.Filter controllers for bank-to-turn CLOS guidance. IEE Proc., January 1987, 134(D1), 17–25.
24.
HortonM. P.A study of autopilots for the adaptive control of tactical guided missiles. MSc thesis, University of Bath, 1992.
25.
JohnsonC. D.Discrete-time disturbance-accommodating control theory with applications to missile digital control. J. Guidance and Control, 1981, 4(2), 116–125.
26.
KaufmannW. A.Airframe dynamics and flight control of the Phoenix missile. AGARD Flight Mechanics Panel, May 1979.
27.
NeslineF. W.NabbfieldN. C.Design of digital autopilots for homing missiles. AGARD Flight Mechanics Panel, May 1979.
28.
NeslineF. W.NeslineM. L.Homing missile autopilot response sensitivity to stability derivative variations. IEEE Decisions and Control Conference Proceedings, December 1984, pp. 1116–1121.
29.
ChristopherP. A. T.Roll-attitude control of a missile having strong aerodynamic non-linearities. Int. J. Control, 1980, 31(2), 209–218.
30.
ParksN. E.RobertsA. P.WilsonH.Roll loop design for bank-to-turn guidance by polynomial methods. IEE Proc., November 1993, 140(D6), 435–441.
31.
RoddyD. J.IrwinG. W.WilsonH.Approaches to roll loop design for BTT CLOS guidance. IEE Proc, 1985, 132(D6), 268–275.
32.
BenshabatD. G.ChaitY.Application of quantitative feedback theory to class of missiles. J. Guidance, Control and Dynamics, 1993, 16(1), 47–52.
33.
BossertD. E.Design of robust quantitative feedback theory controllers for pitch attitude hold systems. J. Guidance, Control and Dynamics, 1994, 17(1), 217–219.
34.
BrierleyS. D.LongchampR.Application of sliding-mode control to air-air interception problem. IEEE Trans, on Aerospace and Electronic Systems, 1990, 26(2), 306–325.
35.
HydeR. A.GloverK.The application of scheduled H controllers to VSTOL aircraft. IEEE TAC, July 1993, 38(7).
36.
JacksonP.Applying μ-synthesis to missile autopilot design. Proceedings of Twenty-ninth Conference on Decision and control, December 1990.
37.
LinC.-F.LeeS. P.Robust missile autopilot design using a generalised singular optimal control technique. J. Guidance, Control and Dynamics, 1985, 8(4), 498–507.
38.
NeslineF. W.ZarchanP.Robust instrumentation for homing missile flight control. AIAA Guidance and Control Conference, August 1980.
39.
NeslineF. W.ZarchanP.Why modern controllers can go unstable in practice. J. Guidance, Control and Dynamics, 1984, 7(4), 4495–4500.
40.
NeslineF. W.WellsB. H.ZarchanP.A combined optimal/classical approach to robust missile autopilot design. J. Guidance and Control, 1981, 4(3), 316–322.
41.
ReichertR. T.Application of H control to missile autopilot design. AIAA Guidance, Navigation and Control Conference, 1989.
42.
ReichertR. T.YostD. J.Modern robust controllers for missile autopilot design. AGARD Missile Interceptor Guidance Systems Technology, 1989–90.
43.
SeftonJ. A.GloverK.Pole/zero cancellation in the general H problems with reference to a two block design. Systems and Control Lett., 1990, 14.
44.
WiseK. A.Missile autopilot robustness to uncertain aerodynamics: Stability hypersphere radius calculation. J. Guidance, Control and Dynamics, 1991, 14(1), 166–175.
45.
WiseK. A.Missile autopilot robustness using the real multiloop stability margins. J. Guidance, Control and Dynamics, 1993, 16(2), 354–362.
46.
BradshawA.CorniseliJ. M.Use of modern control concepts to decouple missile roll and lateral dynamics at high incidence. Department of Aeronautical and Mechanical Engineering, University of Salford, January 1988.
47.
FortescneP. W.Pitch/yaw coupling due to roll of an axisym-metric missile with autopilot. Aeronaut. Q., May 1982, 33, 124–139.
48.
FortescueP. W.BeloE. M.Control decoupling analysis for gyroscopic effects in rolling missiles. J. Guidance, Control and Dynamics, 1989, 12(6), 798–805.
49.
GuelmanM.Absolute stability of symmetric highly manoeuvrable missiles. J. Guidance, Control and Dynamics, 1985, 8(5), 660–662.
50.
MurphyC. H.Symmetric missile dynamic instabilities. J. Guidance and Control, 1981, 4(5), 464–471.
51.
ShinarJ.MerhavS. J.Effects of periodic roll rate in missiles with proportional navigation. J. Spacecraft and Rockets, September 1976, 13(9), 547–556.
52.
BurginG. H.SchnetzierS. S.Artificial neural networks in flight control and flight management systems. National Aerospace Control Conference, May 1990.
53.
FeteihS.BreckenridgeG.Neural network based estimator for a maneuvering aircraft. American Control Conference, June 1993.
54.
GoldenthalW.FarrellJ.Application of neural networks to automatic control. AIAA Guidance, Navigation and Control Conference, August 1990.
55.
HaC. M.Neural networks approach to AIAA aircraft control design challenges. AIAA Guidance, Navigation and Control Conference, August 1991.
56.
JonesL. C.The development of neural network autopilots for a tactical missile. RAeS Conference on The role of intelligent systems in defence, 27–28 March1995.
57.
LightbodyG.IrwinG. W.Neural model reference adaptive control and application to a BTT-CLOS guidance system. IEEE Conference on Neural Networks, 1994.
58.
LinseD. J.StengelR. F.Identification of aerodynamic coefficients using computational neural networks. J. Guidance, Control and Dynamics, 1993, 16(6).
59.
MacLeanD.MatsudaH.Use of neural networks in a flight control system. IM&C Conference on Control applications of neural networks, September 1994.
60.
NarendraK. S.ParthasarathyK.Identification and control of dynamical systems using neural networks. IEEE Trans. on Neural Networks, March 1990, 1(1).
61.
PorterN. D.Further investigations into an adaptive autopilot control system for a tail controlled missile based on a variation of the model reference technique. Royal Aircraft Establishment, technical memo DW8, September 1977.
62.
PriceC. F.KoenigsbergW. D.Adaptive control and guidance for tactical missiles, 1970, The Analytic Science Corporation).
63.
PriceC. F.KoenigsbergW. D.Adaptive control with explicit parameter identification for tactical missiles, 1971, The Analytic Science Corporation).
64.
ShammaJ. S.CloutierJ. R.Gain-scheduled autopilot design using linear parameter varying transformations. J. Guidance, Control and Dynamics, 1993, 16(2), 256–263.
65.
TroudetT.GargS.MerrillW. C.Neural network application to aircraft control system design. AIAA Guidance, Navigation and Control Conference, August 1991.
66.
WarwickK.IrwinG. W.HuntK. J. (Eds) Neural networks for control and systems, IEE Control Engineering Series 46, 1992, pp. 51–71 (Peter Peregrinus Limited).
67.
WharingtonJ. M.DengateR. C.An algorithm for indirect adaptive flight control using neural networks, Vol. 6, Part 1, 1993 (TEA).
