Cislunar Space Beginner's GuideCislunar Space Beginner's Guide
  • Satellite Simulation
Cislunar Glossary
Resources & Tools
Space News
AI Q&A
Home
Gitee
GitHub
  • 简体中文
  • English
  • Satellite Simulation
Cislunar Glossary
Resources & Tools
Space News
AI Q&A
Home
Gitee
GitHub
  • 简体中文
  • English
  • Site map

    • Home (overview)
    • What is cislunar space
    • Spacecraft trajectories
    • Directions & labs
    • Glossary · terms & definitions
    • Data & code
    • Space industry archive
  • Cislunar glossary (terms & definitions)

    • Cislunar Space Glossary
    • Fundamentals

      • Adaptive Grid Subdivision
      • Amplitude Parameter & Phase Parameter (振幅参数与相位参数)
      • Augmented Earth-Moon Model
      • Augmented State Vector
      • Chebyshev Polynomial
      • Coast Arc
      • Collinear Lagrange Point
      • Conjugate Point, Extremal, and Second-Order Optimality Conditions
      • Control Regularization
      • Declination Deviation
      • Delta-V Budget
      • Delta-v (Δv)
      • Dimensionality Reduction
      • Dynamic Reference Catalog
      • Energy Minimization
      • Entrywise Leading Order Interpolation
      • Equation of Motion and State Equation
      • Electric Propulsion (EP / Low-Thrust Propulsion)
      • Global Analysis of Invariant Objects
      • Post-Newtonian Parameter, gamma
      • Gauss-Legendre Collocation Method
      • Global Search
      • Gravitational Asymmetry at Libration Points
      • Gravitational Light Deflection
      • Gravitational Potential
      • Gravity Field Model
      • Gravity Gradient Matrix
      • Grid Search Method
      • Grid Search
      • Heterogeneous Constellation
      • Hidden-Genes Genetic Algorithm
      • High-Fidelity Simulation
      • Ill-Conditioned State Transition Matrix
      • Inertial Reference Frames (ECI / EME2000 / GCRF / MCI / LME2000)
      • Invariant Torus & Quasi-Periodic Tori (Invariant Torus & Quasi-Periodic Tori)
      • Jacobi Field
      • Jacobian Matrix
      • L3 Point
      • L4 Point
      • L5 Point
      • Lambert's Problem
      • Libration Point
      • Lindstedt-Poincaré Method
      • Line of Nodes of the Lunar Orbit
      • Linearization
      • Lorentz Contraction
      • Linear Time-Periodic System
      • Lunar Equatorial Plane
      • Lunar Orbit Eccentricity (月球轨道偏心率)
      • Lunar Sub-Satellite Track
      • Mapped Adjoint Control Transformation, MACT
      • Method of Variation of Constants
      • Multi-Body Dynamical Environment
      • Multi-Conic Method
      • Nondimensionalization (Normalized Units)
      • Non-Dominated Sorting Genetic Algorithm II
      • Numerical Ephemeris (and the Full Ephemeris Model)
      • Orbital Axis Slewing
      • Orbital Perturbations
      • Orthogonal coordinate system
      • Osculating Orbital Elements (吻切轨道根数)
      • Out-of-Plane Difference
      • PDF Transformation Rule
      • Position Angle
      • Precession-Nutation Matrix
      • Precomputed Variational Data
      • Reconstructed Harmonic Balance Method
      • Richardson Third-Order Analytical Approximation
      • Richardson Third-Order Analytical Solution
      • Richardson Third-Order Expansion
      • Right Ascension Deviation
      • Runge-Kutta Method
      • Shape Parameter (形状参数)
      • Slack Variable
      • Small Denominator
      • Staggered Optimization
      • A 6x6 matrix describing how perturbations propagate from initial to terminal state in a dynamical system. Its four sub-blocks represent partial derivative mappings for position-to-position (A), velocity-to-position (B), position-to-velocity (C), and velocity-to-velocity (D). In differential correction, the B and D sub-blocks provide sensitivities of terminal position and velocity to initial velocity, serving as the core mathematical tool for correction computation. The STM also yields the monodromy matrix for invariant manifold computation.
      • Sun-Earth-Moon System
      • Synodic Frame (Rotating Frame)
      • Synodic Period (and Synodic Frequency)
      • Terminal Performance Index
      • Truncation Strategy
      • Unscented Kalman Filter, UKF
      • Uncertainty Propagation
      • Variational Equation
      • Variable-specific-impulse engine
    • Dynamics & math

      • 3-1-3 Euler Angle Sequence
      • A modified invariant manifold formed by applying a small velocity increment adjustment to the natural invariant manifold. Since the natural manifold's perilune distance usually does not match the target lunar orbit radius, an impulse at the Halo orbit injection point reshapes the manifold to satisfy the selenocentric distance constraint. Perturbed manifolds extend the transfer phase range beyond the two fixed points of natural zero-cost trajectories.
      • Adjoint Control Transformation, ACT
      • Multi-Step Integrator (Adams-Bashforth-Moulton / Cowell / Gauss-Jackson / KSG)
      • Adjoint-Control Transformation
      • Adjoint Method
      • Allowable Control Set
      • Allowed Region
      • Amplitude Condition & Effective Phase (振幅条件与有效相位)
      • An iterative method that maps terminal constraint residuals back to initial velocity corrections via the state transfer matrix. In libration point Halo orbit transfer design, it uses perilune distance and flight path angle as constraints, computing velocity increment corrections through partial derivatives decomposed by the state transfer matrix. The algorithm converges quickly for strongly nonlinear problems but is sensitive to initial guesses, requiring invariant manifolds to provide starting values.
      • Angle-Distance Section Method
      • Adaptive Polynomial Chaos Expansion
      • Arnold Diffusion
      • Arnold Tori
      • Arrival Deflection Angle
      • Artificial Libration Point
      • Asymmetry
      • Asymptotic Tracking
      • Adaptive Trajectory Design Catalog
      • Atmospheric Drag Perturbation
      • Augmented Lagrangian Method
      • Averaging Method
      • Axis Ratio
      • Backward Integration Method
      • 弹道捕获(Ballistic Capture)
      • Bang-bang Control and Lawden's Arc Law (Bang-bang Control & Lawden's Arc Law)
      • Battin-Giorgi Method
      • Ballistic Coefficient
      • Bicircular Restricted Four-Body Problem (BCR4BP)
      • beluga
      • Bilinear Tangent Law
      • Birkhoff Equations
      • Box Covering
      • Conley-McGehee Tube, C-M Tube
      • Cannon Ball Model
      • Canonical Coordinates and Canonical Transformation
      • Cauchy-Green Tensor Method
      • Cell Estimation Technique
      • Center Manifold & NHIM (Center Manifold & Normally Hyperbolic Invariant Manifold)
      • Center Subspace
      • Central Configuration
      • Chaotic Sea
      • Characteristic Curve
      • Characteristic Multiplier
      • Characteristic Parameter
      • 地月转移轨道设计要素(Cislunar Transfer Design Elements)
      • Constrained Markov Decision Process
      • Circular Non-linear Equations of Relative Motion, CNERM
      • Costate Variables and Adjoint Equations
      • Collinear Libration Points
      • Collinear Singularity
      • Collision Belt
      • Collision Curve
      • Collocation with Optimization for Low-Thrust
      • Conic Approximation of Transfer Segment
      • Conley-McGehee Tube
      • Connection
      • Conservative System
      • Constrained Functional
      • Constrained Nonlinear Optimization
      • Constrained X-Axis Crossing Velocity
      • Numerical Continuation
      • Control Curve (U_i)
      • Control Parametrization, B-Spline, Spherical Variables and Throttle
      • Controllability
      • Convex Cone
      • Coriolis Theorem (Transport Theorem)
      • Coupling Maneuver
      • Compound Particle Swarm Optimization
      • Circular Restricted Three-Body Problem (CR3BP)
      • Cross-product Control
      • Cylindrical Isomorphic Mapping
      • Differential Evolution
      • Debris Cloud Evolution
      • Departure Velocity
      • Deviation
      • Differential Correction and Shooting Method
      • Direct Collocation
      • Direct Methods (for Trajectory Optimization)
      • Direction Cosine
      • Discrete Mechanics and Optimal Control (DMOC)
      • Discrete Node
      • Dissipative System
      • Divergent Solution
      • DRO-Lyapunov-DRO Transition Phasing, DLD
      • Discrete Linear Quadratic Regulator
      • Double Pseudo-Range Method
      • Dual-Actor Network
      • Dual-Layer Iterative Algorithm
      • Edelbaum's Equation
      • Eigenmotion Method
      • ELERM
      • Elliptic Region
      • Endpoint Mapping
      • Energy Level
      • Energy Range
      • Ephemeris-Based N-Body Model
      • Equilateral Triangle Libration Point
      • Equivalent Control
      • Equivalent Libration Point
      • Elliptic Restricted Three-Body Problem (ER3BP)
      • Error Dynamics
      • Error Propagation Pattern
      • Euler Quintic Equation
      • Event Map
      • Exosystem
      • Explicit Guidance Law
      • Extreme Terrain Mobility
      • Feedback Linearization
      • Flight-Path Angle
      • Floquet Modal Method and Libration Point Stationkeeping(Floquet模态法与平动点轨道保持)
      • Flow Function Construction Method
      • Flow Tube
      • Focal Distance
      • Forbidden Region
      • Force Function
      • Forward Pass and Backward Sweep
      • Francis-Byrnes-Isidori Equations
      • Fuel-optimal Control
      • Full Force Model
      • Fundamental Solution Set
      • Gauss Planetary Equations
      • Gooding's Method, Lambert Solvers and BVP Iterative Methods
      • Gravitational Asymmetry
      • Halo Orbit Computation
      • Symplectic Structure and Hamiltonian Normal Form
      • Hamiltonian
      • Differential Dynamic Programming, iLQR, HDDP and Sensitivity-Based Methods
      • Direct Collocation for Optimal Control (Hermite-Simpson / Direct Transcription)
      • Heteroclinic Orbit Transfer (Heteroclinic Orbit Transfer / Homoclinic Connections)
      • Heterospace System
      • High-Fidelity Dynamics
      • High-Fidelity Model
      • Hill's Region and the Hill Problem (Hill's Region & Hill Problem)
      • Hill's Problem
      • Hénon f-Family Orbits
      • Halo Orbit Insertion
      • Homotopy Method
      • Horseshoe Map
      • Hyperbolic Character of Collinear Points
      • Hyperelliptic Curve
      • Insertion Maneuver, IM
      • Indirect Gravitational Perturbation
      • Indirect Methods
      • Indirect Phasing
      • Initial Condition Sensitivity
      • Initial guess scheme
      • Initial Guess
      • Inner Frequencies
      • Integral Invariant
      • Interior Interval
      • Intermediate Circular Orbit
      • Intermediate Equations
      • Invariant Manifold (Invariant Manifold / Stable & Unstable Manifolds)
      • Shape-Based Method
      • Jacobi Decomposition
      • Jacobi Integral (Jacobi Constant)
      • KAM Theory and Long-Term Stability(KAM理论与长期稳定性)
      • Kozai Method
      • Kustaanheimo-Stiefel Transformation
      • Triangular Libration Points
      • L4
      • L5
      • Lagrange Coefficients (f and g Functions)
      • Lagrange-d'Alembert Principle
      • Lagrange-Jacobi Identity
      • Lagrange Relaxation
      • Lagrange Stability
      • Lambert Guidance Routine
      • Launch Velocity Error
      • Lawden's Necessary Conditions
      • Levi-Civita Transformation
      • Libration Point (Equilibrium Point)
      • Lie Transformation
      • LQR and the Riccati Equation
      • Lagrangian Relaxation Method
      • Lawden's Necessary Conditions
      • Lobe Dynamics
      • Long-Period, Short-Period, and Dual-Period Motion near Triangular Libration Points
      • Loss Function
      • 低能转移(Low-Energy Transfer)
      • Lunar Synodic Resonance (LSR)
      • Lunar-Flyby-Assisted Plane Change
      • Lunar Flyby and Lunar Gravity Assist
      • Lunar Proximity
      • Lunar Solid Tide
      • Maneuvering flyby
      • Manifold Segment
      • Mass Consumption Rate
      • Mass Leak Technique
      • Mass Leak
      • Massive Exploration
      • Matching Conditions
      • Monte Carlo Trajectory Shooting, MCTS
      • Multiple-Shooting Differential Dynamic Programming, MDDP
      • Measurement Jacobian
      • Microgravity Mobility
      • Minimum Euclidean Norm
      • Multi-Impulsive Staging Guidance, MISG
      • Mixed Method / Hybrid Method
      • Monodromy Matrix and Floquet Stability Theory(单值矩阵与Floquet稳定性分析)
      • Monte Carlo Trajectory Shooting
      • Moving Point Strategy
      • Multi-arc Optimal Control
      • Multi-arc Trajectory Optimization
      • Multicollinearity
      • N-Body Dynamics
      • Natural surrounding fly
      • Near Resonance Theorem
      • Neck Opening Condition
      • Neck Region
      • Nekhorosev Estimates
      • Newton-Raphson Method
      • Node
      • Non-Gaussian Distribution
      • Non-Spherical Gravity Perturbation
      • Non-tangential Injection
      • Nonlinear Tuning
      • Near-Rectilinear Halo Orbit Insertion, NRHOI
      • NSGA II (Non-dominated Sorting Genetic Algorithm II)
      • Null Space Vector
      • Null Vector
      • Numerical integration (orbit propagation)
      • Objective Function
      • Obliquity of Lunar Orbit to Equatorial Plane
      • Optimal Continuation Strategy, OCS
      • Offset
      • Optimal Multi-Impulse, Opt-MI
      • Optimal Maneuver Beyond Perilune
      • Orbital Aerobraking Return
      • Spacecraft Local Orbital Frames (RSW / LVLH / Hill / Euler-Hill Frame)
      • Orbital Element Drift (轨道根数漂移)
      • Orbital Insertion Direction
      • Orbital Resonance (Mean Motion Resonance)
      • Sliding Mode Control and Optimal Sliding Mode Control (OSMC)
      • Parabolic Region
      • Parameter Vector
      • Patch Point
      • Penalty Coefficient
      • Perilune Database
      • Periodic Orbit Family at Triangular Libration Point
      • perturbed gravity assist model
      • Phase Deviation (相位偏差)
      • Phase Flow Structure
      • Phase Space & Phase Space Conduit (相空间与相空间通道)
      • Phasing Flyby
      • Poincaré Map (Poincaré Return Map)
      • Poincaré Section (Surface of Section)
      • Polyhedral Representation
      • Pontryagin's Maximum Principle
      • Position Offset Compensation
      • Potential Function
      • Power-Limited Engine
      • Primaries
      • Primer Vector
      • principal stretching direction
      • Projection Functional
      • PS Plane
      • PS Section
      • Pseudo-inverse Newton Update
      • Pseudospectral Convex Optimization
      • Pseudospectral Method (Spectral Collocation)
      • Qualitative Analysis Method
      • Quasi-random Process for Periodic Orbit Generation
      • θ-r Section Method
      • Real Force Model
      • Region of Prevalence
      • Relative Motion
      • Relaxation Method
      • Reparameterized bounded solution
      • Resonance Transition (Resonance Hopping)
      • Restricted Region
      • Receding Horizon Targeting
      • Richardson Third-Order Analytical Solution
      • Richardson's Method
      • Sampling-Based Reachable Set Approximation Algorithm
      • Sequential Convex Programming (SCP / Successive Convexification)
      • Separatrix
      • Shape-Based Method and Velocity Hodograph
      • Single-Revolution xz-Plane Crossing Control
      • Single-Step Prediction Method
      • Slack Factor
      • Sliding Rule
      • Sphere of Influence, SOI
      • Solar Gravity
      • Solar-Perturbation Lunar Gravity Assist (Forward/Backward LGA)
      • Solar Phase
      • Solar Sail Artificial Libration Point Orbit
      • Solar Sail Propulsion
      • Spacecraft Formation Flying
      • Spatial Distribution Uniqueness
      • Spherical Harmonic Gravity
      • Spherical Harmonic Model
      • Spherical Harmonics
      • Spherical Pendulum
      • Spiral Mode
      • Spiral Region
      • Solar Radiation Pressure Perturbation (SRP)
      • State Jacobian Matrix
      • Station-Keeping / Orbit Maintenance
      • Stationarity Condition
      • Sticky Region
      • Stream Function Method
      • State Transition Tensor
      • Subarc
      • Successive Convex Optimization
      • Surface-to-Mass Ratio
      • Survival Map
      • Symbolic Manipulator
      • System Translation
      • Tangent Circle
      • Tangential Impulsive Maneuver
      • Thrust Direction and Control (Thrust Direction & Control)
      • Target Mode
      • Target Point Strategy
      • Targeting Threshold
      • The angle between the spacecraft velocity vector and the local horizontal plane. A flight path angle of zero indicates the velocity is tangent to the local horizontal, corresponding to the periapsis (or apoapsis) characteristic. The paper uses flight path angle as the differential correction termination condition: integration halts when the angle reaches zero with a negative derivative, identifying the perilune point for constraint evaluation.
      • Theorem of Image Trajectories
      • Theoretical Minimum Velocity Increment, delta-V min
      • Third-Body Perturbation
      • Third-Order Richardson Expansion
      • Three-Body Lambert Problem
      • Tidal Capture
      • Time of Flight (ToF) and Transfer-Time Equations
      • Trajectory Optimization with Sparse Optimal Control Software, TOSOCS
      • Two-Point Boundary Value Problem (TPBVP)
      • Target Phase
      • TPhA
      • Trajectory Constraints
      • Trajectory Splicing Database
      • Transportation Tube Wall
      • Triangular Libration Point
      • Tube Structure
      • Tube Topology
      • Turning Point
      • Impulsive Maneuvers and Rendezvous
      • Two-Layer Guidance and Control
      • Unscented Kalman Filter
      • Universal Variable Algorithm
      • Universal Variable Method
      • Unmodelled Acceleration
      • Unperturbed Problem
      • V-infinity Matching
      • ΔV-TOF Pareto Front
      • Variational Equations
      • Velocity Maximum
      • Velocity Minimum
      • Velocity Wedge
      • Vertical Lyapunov Orbit
      • Variable Specific Impulse Engine, VSI Engine
      • Area-to-Mass Ratio
      • Weierstrass-Erdmann Corner Conditions
      • Weak Stability and Weak Stability Boundary (WSB)(弱稳定性与弱稳定边界)
      • x-z Plane Crossing Target
      • x-Axis Crossing Control, XAC
      • Zero Radial Velocity Condition
      • Zero-Velocity Surface (ZVS)
      • Zonal Harmonic
    • Mission orbits

      • approach phase
      • Axial Resonant Orbit, ARO
      • Radial Amplitude
      • Axial Orbit
      • Out-of-plane Amplitude
      • Ballistic Capture
      • Baseline Trajectory
      • Butterfly Orbit
      • central elliptical arc
      • Circular Orbit Boundary Conditions
      • Cislunar Periodic Orbit
      • Classical Exponential Sinusoid
      • Collision Orbit
      • Connection Arc
      • Control Acceleration
      • Cycler Orbit
      • Departure Time
      • Direct Transfer Trajectory
      • Direct Transfer
      • Distant Retrograde Orbit (DRO)
      • Drift Trajectory
      • Earth-Escape Spiral
      • Earth-Moon Triangular Libration Point Transfer Network
      • Eclipse Avoidance
      • Effective Time of Flight
      • EL1 Orbit
      • Energy-Optimal Spiral
      • Energy-to-Fuel Homotopy Continuation
      • Extended Perilune Rendezvous Method, EPRM
      • Earth-Return Orbit
      • Family Curve of Transfers
      • Far Rendezvous
      • Fast Transfer Trajectory
      • Fixed Point
      • Forward-Moon-Retrograde Flyby in Quadrant II
      • Formation Flight
      • Geocentric Arc
      • Geocentric Segment
      • Gravity Assist / Swingby
      • Grouping of Transfers
      • Halo Orbit
      • Heliocentric Graveyard Orbit
      • Heterogeneous Orbits
      • Heterospace-system Manifold Connection
      • Halo Orbit Insertion
      • Horseshoe Orbit
      • Hybrid Multi-Conic Method
      • Inclination Change
      • Insertion Phase Angle
      • Interior Transfer
      • Initial Periodic Orbit
      • Interplanetary Superhighway, ISP
      • Libration Point / Lagrangian Point
      • Lambert patching method
      • Lambert Problem
      • Three-Impulse Lunar Halo Transfer
      • LGA+WSB Transfer
      • Libration Point Orbit (LPO)
      • Linear Periodic Control
      • Lissajous Orbit
      • LOEWE
      • Long-Path Transfer Orbit
      • Long-Way and Short-Way Solutions
      • Low-Energy Transfer
      • Low-thrust Orbit Transfer
      • Low-Thrust Trajectory
      • Lunar Synodic Resonance, LSR
      • Lyapunov Orbit
      • Maneuver Frequency Optimization
      • Manifold Connection
      • Mildly Unstable
      • Minimum Energy Cislunar Transfer
      • Minimum Energy Trans-lunar Transfer
      • Stable Manifold Insertion
      • Moon-Centered Orbit
      • Minimum Parking Orbit
      • Multi-Body Constellation
      • Nominal Orbit
      • Nominal Transfer
      • Non-Keplerian Orbit
      • Non-Transit Orbit
      • North-South Control
      • Near-Rectilinear Halo Orbit (NRHO)
      • Open-Point Scenario
      • Operational Orbit Library
      • Orbit Chain
      • Orbit Chaining
      • Orbit Maintenance Cost
      • Orbital Stability Index
      • Orthogonal Plane-Crossing Condition
      • P2HO2 Orbit
      • Patched Conic
      • Perigee Geocentric Distance
      • Perigee-Point Scenario
      • Perilune Distance
      • Periodic Orbit Family
      • Periodic Solution
      • Phasing Loop Transfer
      • Pole-Sitter
      • Position-Keeping
      • Prograde in Perigee and Retrograde in Perilune
      • Pseudo-Equinoctial Orbital Elements
      • Quasi-Periodic Orbit, QPO
      • Quasi-Satellite Orbit (QSO)
      • Resonant Orbit, RES
      • Rescue Orbit
      • Resonant Orbit Family
      • Resonant Orbit
      • Perilune Radius
      • Selenocentric Segment
      • Semiminor Axis
      • Super-Geostationary Transfer Orbit
      • Short-Path Transfer Orbit
      • Short-Reach Arrival
      • Special Long-Period Orbit, SLPO
      • SMART-like Transfer
      • Smoothed Trajectory
      • Single-shooting Differential Corrector
      • Storage Orbit
      • Tadpole Orbit
      • Tangential Insertion
      • Tangential Intersection
      • Tangential
      • Orbit Phase
      • Touring Cislunar Periodic Orbit, TCPO
      • The distance from the Moon's center to the closest point of a transfer trajectory or invariant manifold
      • The location on a Halo orbit where the spacecraft transitions from the transfer trajectory onto the periodic orbit. The phase angle of the injection point determines the required velocity increment. For zero-cost transfers, the injection impulse is zero; for perturbed transfers, small impulses are typically needed (0-8 m/s in this paper). The paper divides the Halo orbit into 360 equally-spaced nodes, each a potential injection point.
      • Three-Body Periodic Orbit
      • Thrust-Magnitude Continuation
      • Minimum-Thrust Trajectory
      • Trajectory Section Width
      • Transfer Family
      • Two-maneuver transfer design
      • Two-Phase Transfer
      • Unpowered Lunar Gravity Assist, Unpowered LGA
      • Lunar DRO Insertion Delta-V
      • Vertical Orbit
      • Manifold Insertion
      • Weak Stability Boundary Transfer Trajectory
      • Weak Stability Region Transfer
      • x₀ Value
      • Zero-Cost Transfer Trajectory
      • z-direction Motion Amplitude
    • Navigation & systems

      • Absolute Navigation
      • Autonomous Orbit Determination
      • B-Plane Parameters
      • Barycentric Inertial Frame
      • Barycentric Rotating Frame
      • Batch Least-Squares Differential Correction
      • Bidirectional Inter-Satellite Ranging
      • Combined Autonomous Orbit Determination, CAOD
      • Cislunar Space Satellite Navigation System
      • Close-Range Rendezvous
      • Coverage Blind Spot
      • deep space navigation constellation
      • Deficient Rank
      • Differential Correction
      • DRO GNSS Shadowing by Moon
      • Dual-Layer Inter-Satellite Link
      • Dual Navigation Satellite Scheme
      • Earth-Moon Barycenter Rotating Frame
      • Extended Kalman Filter
      • Engine Limitation
      • Extended Constellation
      • GNSS Sidelobe Signal Navigation
      • Grid Division Method
      • Halo Orbit Rendezvous
      • High-Precision Cislunar Space-Time Benchmark
      • Identifiability Information Matrix
      • Inter-Satellite Ranging
      • Iterative Guidance
      • Linked Autonomous Orbit Determination, LAOD
      • Lunar Global Navigation Satellite System
      • Lunar Global Positioning System, LGPS
      • Liaison Navigation
      • Libration Point Navigation Constellation
      • Libration Point Navigation
      • Linearization Method
      • LNSS-A
      • LPO Constellation
      • Lunar Global Positioning Satellite Constellation
      • Lunar High-Latitude Region
      • Lyapunov Optimal Feedback Guidance
      • Multiple Solutions Phenomenon
      • Navigation Constellation
      • Navigation Update Interval
      • Normal Matrix
      • Northern and Southern NRHO Families
      • NRHO Rendezvous and Docking
      • Optimal Control Based Estimator, OCBE
      • Orbital Amplitude
      • Orbital Rendezvous
      • Phase-Based Deployment Strategy
      • Phasing Maneuver
      • Primary Celestial Body
      • Propulsion Error
      • Rank Deficiency Problem
      • Reference Orbit
      • Relative Trajectory Following
      • Sub-Optimal Feedback Control
      • Starlight Angle
      • Time Synchronization Accuracy
      • Transfer Cost Heat Map
      • Two-Step Optimization Algorithm
      • Unscented OCBE, U-OCBE
      • Unscented Transformation, UT
      • Virtual Trajectory
      • Wait Time
    • Other technologies

      • A search strategy that automatically halves the velocity correction and backtracks when differential correction iteration enters an erroneous region (integration reaches the fixed time limit without satisfying the flight path angle constraint). In the strongly nonlinear phase space around Halo orbits, standard differential correction tends to diverge or converge to large-impulse trajectories. Backstepping search progressively reduces the correction step size until the iteration escapes the erroneous region and finds a solution satisfying the termination condition, improving convergence robustness.
      • Adaptive Trajectory Design
      • Cislunar Space Constellation
      • Floquet Mode Method
      • GEO Deorbiting Strategy
      • GEO Deorbiting
      • General Mission Analysis Tool
      • Low Earth Orbit / LEO
      • Monte Carlo Shooting Simulation
      • Satellite Tool Kit

Gravitational Potential

Author: Tianjiang Shuo

Website: https://cislunarspace.cn

Definition

Gravitational potential is a scalar potential function U(r)U(\mathbf{r})U(r) that describes a celestial body's gravitational field. Its gradient gives the gravitational acceleration vector:

g(r)=∇U(r)\mathbf{g}(\mathbf{r}) = \nabla U(\mathbf{r}) g(r)=∇U(r)

The gravitational potential provides a more compact mathematical description than the vector field — a single scalar function carries the complete information of the gravitational field (Vallado 2022). A spacecraft's potential energy VVV relates to the gravitational potential via U=−V/mU = -V/mU=−V/m, with the potential energy referenced to zero at infinity.

Point-mass potential. When the central body is treated as a point mass or a homogeneous sphere, U=μ/rU = \mu / rU=μ/r, where μ=GM\mu = GMμ=GM is the gravitational parameter and rrr is the distance from the body's center of mass. This is the foundation of the two-body problem — applying ∇U\nabla U∇U yields Newton's gravitational acceleration −μ r^/r2-\mu \,\hat{\mathbf{r}} / r^2−μr^/r2.

Spherical Harmonic Expansion for Non-Spherical Potentials

Real celestial bodies are not homogeneous spheres; their uneven mass distribution and non-spherical shape cause actual gravity to deviate from the point-mass model. For a point P(r,ϕ,λ)P(r, \phi, \lambda)P(r,ϕ,λ) in the exterior space (rrr is distance from the body's center, ϕ\phiϕ is latitude, λ\lambdaλ is longitude), the gravitational potential can be expanded as a spherical harmonic series (Vallado 2022, Ch. 8.6; Yin et al. 2024):

U(r,ϕ,λ)=μr[1+∑ℓ=2∞∑m=0ℓ(Rr) ⁣ℓPˉℓm(sin⁡ϕ)(Cˉℓmcos⁡mλ+Sˉℓmsin⁡mλ)]U(r,\phi,\lambda) = \frac{\mu}{r} \left[ 1 + \sum_{\ell=2}^{\infty} \sum_{m=0}^{\ell} \left(\frac{R}{r}\right)^{\!\ell} \bar{P}_{\ell m}(\sin\phi) \bigl( \bar{C}_{\ell m} \cos m\lambda + \bar{S}_{\ell m} \sin m\lambda \bigr) \right] U(r,ϕ,λ)=rμ​[1+ℓ=2∑∞​m=0∑ℓ​(rR​)ℓPˉℓm​(sinϕ)(Cˉℓm​cosmλ+Sˉℓm​sinmλ)]

where RRR is the reference radius (for Earth, the equatorial radius aea_eae​), Pˉℓm\bar{P}_{\ell m}Pˉℓm​ are normalized associated Legendre functions, and Cˉℓm\bar{C}_{\ell m}Cˉℓm​, Sˉℓm\bar{S}_{\ell m}Sˉℓm​ are normalized spherical harmonic coefficients (Stokes coefficients). The coefficients encode the body's entire mass distribution — low-degree terms describe large-scale shape (oblateness, etc.), while high-degree terms capture local details. The expansion starts from ℓ=2\ell = 2ℓ=2 because ℓ=0\ell = 0ℓ=0 recovers the point-mass potential μ/r\mu/rμ/r, and ℓ=1\ell = 1ℓ=1 terms vanish when the coordinate origin is placed at the body's center of mass.

Three Types of Spherical Harmonic Terms

Based on the relationship between order mmm and degree ℓ\ellℓ, spherical harmonic terms fall into three categories (Vallado 2022; Yin et al. 2024):

TypeConditionGeometric CharacteristicPhysical Meaning
Zonal harmonicsm=0m = 0m=0Vary only with latitude, symmetric about the polar axisEquatorial bulge (J2J_2J2​), pear shape (J3J_3J3​), and other global shapes
Sectoral harmonicsℓ=m\ell = mℓ=mDepend only on longitude, appear as "orange slices"Longitudinal mass concentrations
Tesseral harmonicsℓ≠m≠0\ell \neq m \neq 0ℓ=m=0Vary with both latitude and longitude, "checkerboard" patternRegional mass anomalies

J notation convention. Zonal harmonics commonly use the notation JℓJ_\ellJℓ​ instead of Cℓ,0C_{\ell,0}Cℓ,0​, with the convention Jℓ=−Cℓ,0J_\ell = -C_{\ell,0}Jℓ​=−Cℓ,0​ (Vallado 2022, Eq. 8-20). Earth's J2≈1.0826×10−3J_2 \approx 1.0826 \times 10^{-3}J2​≈1.0826×10−3 is the largest coefficient in absolute value — roughly 1000 times larger than the next largest coefficient J3J_3J3​ — and dominates the non-spherical gravitational perturbation (causing orbital plane precession, perigee rotation, etc.).

Normalization. The raw coefficients CℓmC_{\ell m}Cℓm​ and SℓmS_{\ell m}Sℓm​ become extremely small as ℓ\ellℓ and mmm increase, introducing round-off errors. Therefore, published models use normalized coefficients Cˉℓm\bar{C}_{\ell m}Cˉℓm​, Sˉℓm\bar{S}_{\ell m}Sˉℓm​:

Cˉℓm=(ℓ+m)!(ℓ−m)! k (2ℓ+1)  Cℓm,k={1m=02m≠0\bar{C}_{\ell m} = \sqrt{\frac{(\ell+m)!}{(\ell-m)!\,k\,(2\ell+1)}} \; C_{\ell m}, \qquad k = \begin{cases} 1 & m=0 \\ 2 & m \neq 0 \end{cases} Cˉℓm​=(ℓ−m)!k(2ℓ+1)(ℓ+m)!​​Cℓm​,k={12​m=0m=0​

The corresponding Legendre functions must be inversely normalized to maintain the product CˉℓmPˉℓm=CℓmPℓm\bar{C}_{\ell m} \bar{P}_{\ell m} = C_{\ell m} P_{\ell m}Cˉℓm​Pˉℓm​=Cℓm​Pℓm​ (Vallado 2022, Eq. 8-22).

Normal and Disturbing Potential

In geodesy, the gravitational potential is decomposed into a reference part and a deviation part (Vallado 2022):

U=V+TU = V + T U=V+T

  • Normal potential VVV: Gravitational potential produced by a rotationally symmetric ellipsoid (normal Earth), containing only even-degree zonal harmonics.

  • Disturbing potential TTT: Difference between the true and normal potentials, T=U−VT = U - VT=U−V. The disturbing gravitational acceleration δg=∇T\delta\mathbf{g} = \nabla Tδg=∇T is on the order of 200 mgal200\ \text{mgal}200 mgal (10−5 m/s210^{-5}\ \text{m/s}^210−5 m/s2) and cannot be neglected in precision orbit determination or altimetry.

Earth vs. Moon Comparison

PropertyEarthMoon
J2J_2J2​ magnitude∼1.08×10−3\sim 1.08 \times 10^{-3}∼1.08×10−3∼2.03×10−4\sim 2.03 \times 10^{-4}∼2.03×10−4
High-degree field irregularityRelatively smoothSignificantly more irregular — near-side mascons, slower decay of high-degree coefficients
Impact on low orbitsJ2J_2J2​ dominates perturbationsHigh-degree terms (ℓ\ellℓ up to tens) still significantly affect orbits <100 km<100\ \text{km}<100 km
Representative modelEGM2008 ( degree 2190)GRGM660PRIM ( degree 660)

The irregularity of the lunar gravity field is a critical constraint for cislunar mission design — below approximately 100 km altitude, gravitational irregularities make it difficult to maintain stable orbits with single impulses (Trofimov et al. 2020).

Related Concepts

  • Gravity Field Model

  • Gravity Gradient Matrix

  • J2 Perturbation

  • Third-Body Perturbation

  • CR3BP

  • Libration Point

References

  • Vallado, D. A., 2022, Fundamentals of Astrodynamics and Applications, 5th ed., Microcosm Press. Ch. 8.6.1 — Complete derivation of spherical harmonic expansion, normalization conventions, J notation, and three-way harmonic classification.

  • Yin, Z., Zhang, K., Duan, Y., Liu, J., Mu, Q., 2024, Theoretical research progress of gravitational field modeling in Earth science and deep-space exploration, Reviews of Geophysics and Planetary Physics, 55(5): 501–512. — Systematic review of gravitational field definition, spherical harmonic expansion, and multipole expansion theory.

  • Chao, B. F. & Shih, S. A., 2021, Multimultipole expansion: Unifying formalism for Earth and planetary gravitational dynamics, Surveys in Geophysics, 42: 803–838. — Complex-variable spherical harmonic representation.

  • Trofimov, S. et al., 2020, Transfers from NRHOs to low-perilune orbits, Acta Astronautica, 167: 260–271. — Impact of irregular lunar gravity on low-perilune orbits.

Improve this page
Last Updated: 8/9/26, 10:41 AM
Contributors: Ou Yang Jiahong, ouyangjiahong
Prev
Gravitational Light Deflection
Next
Gravity Field Model
地月空间入门指南
Cislunar Space Beginner's GuideYour guide to cislunar space
View on GitHub

Navigate

  • Home
  • About
  • Space News
  • Glossary

Content

  • Cislunar Orbits
  • Research
  • Resources

English

  • Home
  • About
  • Space News
  • Glossary

Follow Us

© 2026 Cislunar Space Beginner's Guide  |  湘ICP备2026006405号-1
Related:智慧学习助手 UStudy航天任务工具箱 ATK
微信公众号
欢迎关注天疆说扫码关注,手机获取航天资讯