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

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Chapter 8 / Simulation _ _ • Mathematical constants and WGS84 geodetic constants • System clock initialisation • Windows refresh rates • Bi-modal distribution factors (see §22.2.4.3) Program controls are customised using data read by INPUT_DATA from the external control data file as described in §8.6.4. Default initialisation ends by activating separate modules to load target, sensor, missile and trajectory optimisation data. The program is initialised by IN_CONTROL, starting with the system clocks and the printing and plotting facility (PRIPLO). The data from an external characterisation data file is read and used to overwrite previously loaded defaults with application specific data, as described in §8.6.5. If any data fails its consistency checks these are recorded and the program continues with the initialisation irrespective of the models that are to be used. If any input data faults are recorded, or inconsistencies detected in the user requirements during the initialisation process, the program is terminated with diagnostics so that the faults can be rectified. Uniquely numbered termination conditions are written to the Data Logging file described in §8.6.8. After initialisation the 16 kHz master timing loop is invoked. GMT and simulation reference times are updated using integer counter INDEXS to preserve accuracy. The system clocks are updated at the master clock rate so that precise timing can be achieved in CLOCK_UPDATE. User specified in-run real and integer variable changes are monitored and activated at the appropriate time by R_CB_CHANGE and I_CB_CHANGE respectively. Changes are applied at 1 kHz so the activation time provided should be commensurate if quantisation is to be avoided. Control is then passed to one of the Runge-Kutta state integrators (RK_*) that propagate the reference state vector at 4 kHz. The integration order is selected by setting the value of INTORD whose value is reflected in the integration module names. This parameter defaults to 2 nd order integration however, it can be changed during program initialisation and program execution. After each integration step, if the termination flag ISTOP has been set by the application models a controlled shut down is initiated. The program ends by processing the MATLAB graphics and formatted data requested. 8.6.1 Reference State Vector Integration State propagation is controlled by DX_CONTROL, as shown in shown in Figure 8-7. The integration process defined in §22.2.2 starts by resetting the integration INDEXI to 1 that identifies which pass of the state derivative is being executed. Data output from OUT_CONTROL is invoked immediately the 1 st state derivative computation in each integration period so that all data can be displayed and recorded at the current time. The process increases time locally, performs additional state derivative computations, updates the integration index, and finally collates the weighted state data. 8-10
Chapter 8 / Simulation _ _ (1) CONSTANTS Set program parameters and user independent system constants SIMULATOR DX_CONTROL (2) OPEN_IO_FILES Open I/O data files 8-11 (3) INPUT_DATA Read program contol data from external file (4) D_TARGET , (5) D_MISSILE , (6) D_OPTIMISER , (7) D_SENSORS Set default target, sensor, missile and trajectory optimiser default data subject to control data. (1) I_TIMING Set the simulation master and sub-interval clocks and associated frequencies (4) LOGIC_LOCKS Common block equivalencing and program control consistency checking 1 = STOP IN_CONTROL (2) I_PRIPLO AInitialise the automatic printing and plotting software described in Section 3.4 (5) INIT_TOP_WGT_XV Initialise the interactive X-windows interface that is described in Section 3.5 0 = LOOP ISTOP INDEXS := INDEXS + 1 Update reference and absolute TAM at 4 kHz CLOCK_UPDATE Reset the system clocks at 4 kHz R_CB_CHANGE , I_CB_CHANGE update global common block user specified changes at 1 kHz INTORD 1 2 3 4 RK_1 RK_2 RK_3 RK_4 ISTOP monitor ( 4kHz ) 1 = STOP Automatic plotting and printing final data preparation END PROGRAM (3) CHANGE_CB Read and check user provided common block change data as described in Section 3.3.3.4-7 (6) - (8) I-TARGET , I_MISSILE , I_SENSORS Initialise the target, missile and sensor models 4 kHz Integration Loop Figure 8-6 : Simulation Top-Level Infrastructure 0 = LOOP
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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 _ _ 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 / 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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5 Chapter 5 / Missile State Observe
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6 Chapter 6 / Missile Guidance _ _
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Chapter 6 / Missile Guidance _ _ 6.
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Chapter 6 / Missile Guidance _ _ As
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Chapter 6 / Missile Guidance _ _ CD
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Chapter 6 / Missile Guidance _ _ ge
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Chapter 6 / Missile Guidance _ _ ex
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Chapter 6 / Missile Guidance _ _ &
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Chapter 6 / Missile Guidance _ _ PN
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Chapter 6 / Missile Guidance _ _ ra
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Chapter 6 / Missile Guidance _ _ of
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Chapter 6 / Missile Guidance _ _ NO
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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 / WGS 84 Tar
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Appendix I / Utilities / Matrices _
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Appendix I / Utilities / Quaternion
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