Thesis - Leigh Moody.pdf - Bad Request - Cranfield University

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Chapter 6 / Missile Guidance _ _ the basic PN demand is optimal and no further control effort is required once a collision course is established. The difference between normalised and traditional PN is in the velocity scaling. Normalised PN is scaled using the closing speed whilst traditional PN is scaled by missile speed. The acceleration demand is applied normal to the missile-target LOS for True PN, and normal to the missile velocity vector for PPN. The four variants in the basic PN demand are therefore, Normalised - True PN PN S SL Traditional - True PN PN m 6-16 XS m, t ( ) T ZS YS ω , − α : = λ ⋅ P& ⋅ ω S SL Normalised - Pure PN PN m XMV o, m A, S A, S ( ) T ZS YS − ω , α : = λ ⋅ P& ⋅ ω MV SL Traditional - Pure PN PN m XS m, t A, S A, S ( ) T ZS YS ω , − α : = λ ⋅ P& ⋅ ω MV SL m XMV o, m A, S A, S ( ) T ZS YS − ω , α : = λ ⋅ P& ⋅ ω A, S A, S Equation 6.5-14 Equation 6.5-15 Equation 6.5-16 Equation 6.5-17 Although the speed advantage required for Traditional PN can be relaxed for Normalised PN, the later is prone to acceleration limiting and incidence drag induced speed loss. Although Shukla [S.1] showed that PPN is superior to TPN, PPN is rarely used as it requires missile incidence as well as seeker data. In its basic form TPN requires only seeker data, and ideally a measurement of closing speed. The closing speed and LOS rate are obtained directly from the missile observer states, P 2 m, t ⋅ T B S P m, t ⋅ ω S A, S ⋅ P& : = − P • P& XS t : = A m, t A m, t B A B A ( TA ⋅ Pm, t ) × ( TA ⋅ P& m, t ) Equation 6.5-18 Equation 6.5-19 Expanding the Normalised TPN demand in terms of polar dynamics,
Chapter 6 / Missile Guidance _ _ PN α B SL : = λ m S TB ⋅ P& XS o, m ( 1 ) ⋅ ⎛ ⎜ ⎜ ⎜ ⎝ T S B − T 6-17 ( ) ( ) ⎟ ( ) ( ) ⎟⎟ S ⎞ ⎛ S S 9 , − T Ψ ⋅ Θ ⎞ B 8 & ⎟ ⎜ A cos A ⎟ ⋅ ⎜ S S ⎟ ⎜ S 6 , T 5 − Θ& B B ⎠ ⎝ A ⎠ Equation 6.5-20 For a seeker with an inner pitch, and an outer yaw gimbal, the elemental Euler rotational matrices defined in §16.1 combine to give, S B : S S [ Θ ] ⋅ [ ] T = Ψ B B Equation 6.5-21 In terms of the direction cosines from Missile Body to Seeker LOS axes, PN α B SL : = λ m ⋅ P& XS t ⋅ ⎛ ⎜ ⎜ ⎜ ⎝ − Ψ& S A ⋅ cosΘ Ψ& S A S A ⋅ cosΘ ⋅ tan Θ 6.5.2.2 Missile Acceleration Augmented PN Guidance S B S A ⋅ sec Ψ ⋅ tan Ψ S B S B − Θ& S A ⋅ secΘ S B ⎞ ⎟ ⎟ ⎟ ⎠ Equation 6.5-22 Modifying TPN to account for the missile longitudinal acceleration results in Ideal TPN (ITPN) and is important during the boost phase of larger missiles engaging short-range targets. Inserting the relevant direction cosines for a seeker with an inner pitch and outer yaw gimbal into this component of the PN guidance command, PN α B MA : = − T &P & XB o, m S B ( 1 ) ⋅ ⎛ ⎜ ⎜ ⎜ ⎝ T S B − T Expanding, and using the results of §6.5.2, PN PN α α B MA B MA XB Po, m S B S ( 9 ) , − T ( 8 ) S B & : = − T ⋅ XB o, m ( 1 ) S ( 6 ) , T ( 5 ) B B ⎞ ⎛ T ⎟ ⎜ ⎟ ⋅ ⎜ ⎟ ⎜ ⎠ ⎝ T ( ( ) ( ) ) T S S T 4 , T 7 B B S B S B ( ) T S S S − tan Ψ , tan Θ ⋅ sec : = & P& ⋅ Ψ B B ( 2 ) ⎞ ( ) ⎟⎟⎟ 3 ⎠ Equation 6.5-23 Equation 6.5-24 B Equation 6.5-25
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CRANFIELD UNIVERSITY LEIGH MOODY SE
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ABSTRACT When considering advances
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Contents _ _ LIST OF CONTENTS 1 INT
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Contents _ _ 8.2 The Scope of Moder
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Contents _ _ 17.4 Inertial Velocity
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Tables _ _ LIST OF TABLES Table 1-1
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Figures _ _ LIST OF FIGURES Figure
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Figures _ _ Figure 5-1 : Centralise
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Figures _ _ Figure 19-3 : Air Densi
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Acronyms _ _ Acronyms And Abbreviat
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Acronyms _ _ HDOP - NAVSTAR GPS Hor
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Acronyms _ _ RCS - Radar Cross Sect
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Glossary _ _ GLOSSARY A challenge w
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Glossary _ _ 0.1 Predicate Calculus
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Glossary _ _ ]A,B] Real number rang
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Glossary _ _ 0.9 Matrix Operators [
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Glossary _ _ 0.14.2 Special Vectors
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Glossary _ _ P C a , b ≡ XC YC ZC
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Glossary _ _ V ≡ V : = V • V Th
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Glossary _ _ 0.16.4 Matrix Partitio
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Glossary _ _ Only the subset of qua
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Glossary _ _ 0.19 Systeme Internati
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1 Chapter 1 / Introduction _ _ Chap
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Chapter 1 / Introduction _ _ Wherea
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Chapter 1 / Introduction _ _ • Cr
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Chapter 1 / Introduction _ _ genera
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Chapter 1 / Introduction _ _ radar
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Chapter 1 / Introduction _ _ simple
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Chapter 1 / Introduction _ _ optimi
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Chapter 1 / Introduction _ _ 1.3.9
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2 Chapter 2 / Target Modelling _ _
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Chapter 2 / Target Modelling _ _ 2.
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Chapter 2 / Target Modelling _ _
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Chapter 2 / Target Modelling _ _ t
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Chapter 2 / Target Modelling _ _ P&
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Chapter 2 / Target Modelling _ _ GO
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Chapter 2 / Target Modelling _ _ th
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Chapter 2 / Target Modelling _ _
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Chapter 2 / Target Modelling _ _ VX
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Chapter 2 / Target Modelling _ _ ma
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3 Chapter 3 / Sensors _ _ Chapter 3
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Chapter 3 / Sensors _ _ 3.1 Simulat
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Chapter 3 / Sensors _ _ Table 3-4 :
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Chapter 3 / Sensors _ _ Reference D
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Chapter 3 / Sensors _ _ 3.2-9 s s i
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Chapter 3 / Sensors _ _ 3.2-11 t o
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Chapter 3 / Sensors _ _ Figure 3-5
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Chapter 3 / Sensors _ _ Table 3-7 :
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Chapter 3 / Sensors _ _ IF ϕ LIM
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Chapter 3 / Sensors _ _ The phase e
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Chapter 3 / Sensors _ _ Taking expe
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Chapter 3 / Sensors _ _ Expressing
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Chapter 3 / Sensors _ _ INPUT; AA,
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Chapter 3 / Sensors _ _ The functio
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Chapter 3 / Inertial Navigation _ _
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Chapter 3 / Sensors / Gyroscopes _
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Chapter 3 / Sensors / Accelerometer
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Chapter 3 / Sensors / Barometric Al
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Chapter 3 / Sensors / Barometric Al
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Chapter 3 / Sensors / Radar Altimet
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Chapter 3 / Sensors / Radar _ _ 3.8
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Chapter 3 / Sensors / Radar _ _ LF
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Chapter 3 / Sensors / Radar _ _ ( )
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Chapter 3 / Sensors / Radar _ _ S :
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Chapter 3 / Sensors / Radar _ _ SN
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Chapter 3 / Sensors / Radar _ _ 2
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Chapter 3 / Sensors / Radar _ _ ⎛
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Chapter 3 / Sensors / Seeker _ _ 3.
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Chapter 3 / Sensors / Seeker _ _ 5
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Chapter 3 / Sensors / Seeker _ _
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Chapter 3 / Sensors / Seeker _ _ th
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Chapter 3 / Sensors / Seeker _ _ Th
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Chapter 3 / Sensors / Seeker _ _ Th
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Chapter 3 / Sensors / Fins _ _ 3.10
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Chapter 3 / Sensors / Fins _ _ thro
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Chapter 3 / Sensors / NAVSTAR GPS _
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Chapter 3 / Sensors / Helmet Mounte
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Chapter 3 / Sensors / Helmet Mounte
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Chapter 3 / Sensors / Air Data Syst
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Chapter 4 / Target Tracking _ _ 3.1
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Chapter 4 / Target Tracking _ _ Ine
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Chapter 4 / Target Tracking _ _ ran
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Chapter 5 / Missile State Observer
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Page 259 and 260: Chapter 5 / Missile State Observer
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8 Chapter 8 / Simulation _ _ Chapte
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Chapter 8 / Simulation _ _ 8.1 The
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Chapter 8 / Simulation _ _ 8.3 The
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Chapter 8 / Simulation _ _ Having p
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Chapter 8 / Simulation _ _ 8.5.1 Gl
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Chapter 8 / Simulation _ _ (1) CONS
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Chapter 8 / Simulation _ _ 8.6.2 Ou
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Chapter 8 / Simulation _ _ The file
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Chapter 8 / Simulation _ _ • The
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Chapter 8 / Simulation _ _ comprehe
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Chapter 8 / Simulation _ _ WIN_RATE
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Chapter 8 / Simulation _ _ for this
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Chapter 8 / Simulation _ _ with the
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Chapter 8 / Simulation _ _ Figure 8
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Chapter 8 / Simulation _ _ Table 8-
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Chapter 8 / Simulation _ _ 8.8 Disc
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9 Chapter 9 / Performance _ _ Chapt
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Chapter 9 / Performance _ _ 9.1 Air
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Chapter 9 / Performance _ _ XM ( >
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Chapter 9 / Performance _ _ 9.3 PN
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Chapter 9 / Performance _ _ The eff
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Chapter 9 / Performance _ _ VXMVOM
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Chapter 9 / Performance _ _ VXMVOM
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Chapter 9 / Performance _ _ 9.4 CLO
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Chapter 9 / Performance _ _ AR_BOM
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Chapter 9 / Performance Chapter 9 /
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Initially the position error falls
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values of CN are not always a relia
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crude initialisation introduces err
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9.5.3 Singer Filter Tuning The Sing
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9.6.2 CLOS Study The CLOS study sho
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Chapter 10 / Conclusions _ _ 10-2
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Chapter 10 / Conclusions _ _ 10.3 T
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Chapter 10 / Conclusions _ _ 10.7 M
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Chapter 11 / Future Research _ _ 11
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Chapter 11 / Future Research _ _
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Chapter 11 / Future Research _ _ To
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References _ _ B.4 BAZARAA M.S., SH
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References _ _ F.1 FOX J.E., “A C
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References _ _ H.5 #HULL D.G., RADK
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References _ _ L.2 LOOZE D.P., HSU
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References _ _ N.4 NABAA N., BISHOP
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References _ _ R.3 RUSNACK I., “O
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References _ _ S.15 SINGER R.A.,
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References _ _ Y.2 YUAN P., CHERN J
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Bibliography _ _ B.13 BABA Y., YAMA
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Bibliography _ _ B.40 BECKER J.C.,
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Bibliography _ _ C.33 CORTINA E., O
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Bibliography _ _ E.8 ERSHOV A.A.,
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Bibliography _ _ G.34 GUTMAN P., VE
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Bibliography _ _ H.35 HUSSAIN A.M.,
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Bibliography _ _ K.14 KATZIR S., CL
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Bibliography _ _ L.19 LEFAS C.C,
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Bibliography _ _ M.16 MAYNE D.Q., P
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Bibliography _ _ P.1 PAINTER J.H.,
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Bibliography _ _ R.32 RONG LI X., Z
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Bibliography _ _ S.47 SPEYER J.L.,
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Bibliography _ _ V.5 VIAN J.L., MOO
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Bibliography _ _ W.29 WATSON G.A.,
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Appendix A / Geometric Points _ _ 1
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Appendix A / Geometric Points _ _ 1
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Appendix B / Frames of Reference _
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Appendix C / Axis Transforms _ _ 16
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Appendix C / Axis Transforms _ _ YP
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Appendix C / Axis Transforms _ _ B
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Appendix C / Axis Transforms _ _ YB
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Appendix C / Axis Transforms _ _ Us
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Appendix C / Axis Transforms _ _ No
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Appendix C / Axis Transforms _ _ B
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Appendix C / Axis Transforms _ _
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Appendix D / Point Mass Dynamics _
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Appendix E / Earth Geometry _ _ 18-
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Appendix E / Earth Geometry _ _ ELL
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Appendix E / Earth Geometry _ _ (dx
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Appendix E / Earth Geometry _ _ Int
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Appendix E / Earth Geometry _ _ 18.
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Appendix E / Earth Geometry _ _ 19-
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Appendix E / Earth Geometry _ _ P S
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Appendix E / Earth Geometry _ _ 19.
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Appendix E / Earth Geometry _ _ ∂
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Appendix G / Gravity _ _ 20-2
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Appendix G / Gravity _ _ g : = g +
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Appendix G / Gravity _ _ d −6 2
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Appendix G / Gravity _ _ 20-8
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Appendix H / Steady State Tracking
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Appendix I / Utilities _ _ 22.1-2
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Appendix I / Utilities _ _ Cartesia
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Appendix I / Utilities _ _ Matrix P
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Appendix I / Utilities _ _ 22.1-8
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Appendix I / Utilities / General Ut
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Appendix I / Utilities / WGS 84 Tar
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Appendix I / Utilities / Axis Trans
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Appendix I / Utilities / Point Mass
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Appendix I / Utilities / Earth, Atm
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Appendix I / Utilities / Earth, Atm
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Appendix I / Utilities / Digital Ma
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Appendix I / Utilities / Digital Fi
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Appendix I / Utilities / Matrices _
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Appendix I / Utilities / Quaternion
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Appendix I / Utilities / Trigonomet
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Appendix I / Utilities / Vectors _
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Appendix I / Utilities / Covariance
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