Orbital Relative Motion and Terminal Rendevouz (Spacecraft Guidance Applications)

Description

Preface Contents Chapter 1: The Second-Order Analytic Approximation to the Solution of the Euler-Hill Equations of Relative Motion 1.1 Introduction 1.2 Derivation of the Equations of Motion in Rotating Rectangular Coordinates for an Elliptic Orbit 1.3 The Second-Order Approximation to the Euler-Hill Equations of Relative Motion References Chapter 2: Analytic Solutions for the Perturbed Motion of a Spacecraft in Near-Circular Orbit, Under the Influence of the J2 a... 2.1 Introduction 2.2 Zonal Harmonics Perturbation Acceleration Components in Euler-Hill Frame 2.3 General Solution of Perturbed Motion Due to J2 in Local Euler-Hill Frame 2.4 General Solution of Perturbed Motion Due to J3 in Local Rotating Euler-Hill Frame 2.5 General Solution of Perturbed Motion Due to the Combined Effect of J2 and J3, in the Euler-Hill Frame 2.6 Refined Analytic Description of Perturbed Motion Due to J2 Starting from Any Desired Epoch on a Near-Circular Orbit 2.7 General Solution of Perturbed Motion Due to J2 2.8 Construction of the Reference Orbit and Generation of the Initial Conditions for Forward Propagation 2.9 Numerical Results 2.10 Comparison of First-Order Analytic Orbit Theory Due to J2 Perturbation with the Numerically Integrated Solution 2.11 Choice of Reference Orbit and Generation of Corresponding Initial Position and Velocity Components to Start the Analytic ... 2.12 Accuracy Assessments 2.13 Analytic Description of Perturbed Motion Due to J3: Comparison with the Numerically Integrated Solution 2.14 General Solution of Perturbed Motion Due to J3 2.15 General Solution of Perturbed Motion Due to J2 and J3 2.16 Numerical Results 2.17 Conclusion References Chapter 3: Analytic Solutions for the Perturbed Motion of a Spacecraft in Near-Circular Orbit, Under the Influence of the Luni... 3.1 Introduction 3.2 Third Body Perturbation Acceleration Components in Euler-Hill Frame 3.3 General Solution of Perturbed Motion Due to Solar Gravity in Rotating Euler-Hill Frame 3.4 General Solution of Perturbed Motion Due to Lunar Gravity in Rotating Euler-Hill Frame 3.5 Comparison of Analytic Solution of Perturbed Motion Due to Luni-Solar Gravity with the Numerically Integrated Solution 3.6 Third Body Gravity Acceleration and Equations of Relative Motion 3.7 Results References Chapter 4: Effect of Luni-Solar Gravity Perturbations on a Near-Circular Orbit: Third-Body Orbit Eccentricity Considerations 4.1 Introduction 4.2 General Form of Third-Body Perturbation Acceleration Components in Rotating Frame 4.3 Derivation of the General Solution Reference Chapter 5: Effect of Atmospheric Drag Perturbation on Circular Orbits: Atmosphere Rotation Considerations 5.1 Introduction 5.2 Derivation of the Expression for the Air Relative Velocity in Rotating and Inertial Systems 5.3 General Solution of Perturbed Motion Due to Atmospheric Drag from a Rotating Atmosphere 5.4 Analytic Solution of Perturbed Motion in Near-Circular Orbit Due to Atmospheric Drag from a Rotating Oblate Atmosphere wit... 5.4.1 Introduction 5.4.2 Derivation of a Suitable Expression for the Atmospheric Density 5.4.3 General Solution of Perturbed Motion Due to Atmospheric Drag from a Rotating Oblate Atmosphere with Day-to-Night Density... 5.5 Effect of Atmospheric Drag Perturbation from an Exponential Rotating Atmosphere on Circular Orbits: Comparison with Numeri... 5.5.1 Introduction 5.5.2 General Solution of Perturbed Motion Due to Atmospheric Drag 5.5.3 Numerical Results References Chapter 6: Analytic Solution of Terminal Rendezvous in Near-Circular Orbit Around the Oblate Earth: The Computation of the Sta... 6.1 Introduction 6.2 Equations of Relative Motion Around the Spherical Earth 6.3 Equations of Relative Motion around the Oblate Earth 6.4 Generation of Initial Conditions and Rendezvous Equations 6.5 Numerical Results 6.6 Optimization of Interception Time for Minimum - DeltaV Rendezvous 6.7 Conclusion References Chapter 7: Techniques of Accurate Analytic Terminal Rendezvous in Near-Circular Orbit 7.1 Introduction 7.2 Equations of Relative Motion 7.3 Generation of Initial Conditions and Rendezvous Equations 7.4 Description of Rendezvous Algorithm 7.5 Numerical Results 7.6 Conclusion References Chapter 8: Coplanar Two-Impulse Rendezvous in General Elliptic Orbit with Drag 8.1 Introduction 8.2 General Analysis 8.3 Analytic Solution of the Two-Impulse Coplanar Rendezvous in Vacuum for Target in Circular Orbit 8.4 Numerical Solution of the Two-Impulse Coplanar Rendezvous in Vacuum with Reference in Circular Orbit 8.5 Numerical Solution of the Two-Impulse Coplanar Rendezvous with Drag with Reference Attached to Passive Vehicle in General ... 8.6 Conclusion References Chapter 9: The Analysis of the Relative Motion in General Elliptic Orbit with Respect to a Dragging and Precessing Coordinate ... 9.1 Introduction 9.2 Euler´s Exact Form of the Components of Inertial Acceleration Along Rotating Axes and Its Extension to Orbital Motion 9.3 The Treatment of the Drag and Oblateness Accelerations 9.4 Conclusion References Chapter 10: The Algorithm of the Two-Impulse Time-Fixed Noncoplanar Rendezvous with Drag and Oblateness Effects 10.1 Introduction 10.2 Initialization and Rendezvous Algorithm Description 10.3 Numerical Results 10.4 Conclusion References Chapter 11: The Analysis and Implementation of In-Plane Stationkeeping of Continuously Perturbed Walker Constellations 11.1 Introduction 11.2 Geometry of Symmetric Walker Constellation 11.3 Perturbation of the Satellite Orbits 11.4 Relative Motion with Respect to Precessing Frames 11.5 In-plane Maneuvering for Targeting to Center of Rotating Frame 11.6 Conclusion References Chapter 12: The Mathematical Models of the Jet Propulsion Laboratory (JPL) Artificial Satellite Analysis Program (ASAP) 12.1 Introduction 12.2 Cowell´s Method of Special Perturbation 12.3 Central Body Disturbing Function 12.4 Third-Body Disturbing Function 12.5 Equations of Motion Due to Air Drag References Index