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  • Cislunar glossary (terms & definitions)

    • Cislunar Space Glossary
    • Fundamentals

      • Absolute Range
      • Aerodynamic Coefficient
      • Aerodynamic Moment
      • Aerospace Vehicle
      • Allan Deviation (ADEV)
      • Ballistic Coefficient
      • Bi-Elliptic Transfer
      • Body Frame
      • Celestial Coordinate System
      • Celestial Sphere
      • Characteristic Velocity
      • Coverage Angle
      • Dual One-Way Ranging (DOWR)
      • Earth Ellipsoid
      • Earth Oblateness Perturbation
      • Earth-Centered Earth-Fixed Frame (ECEF)
      • Einstein Equivalence Principle (EEP)
      • Energy Parameter
      • Earth Observation (EO)
      • Finite Thrust Maneuver
      • Free-Flight Phase
      • Free-Flight Trajectory
      • Frozen Orbit
      • Gaussian Perturbation Equations
      • Geocentric Inertial Frame
      • GPS Time
      • Gravitational Potential
      • Gravitational Redshift
      • Gravity Turn
      • Gravity vs Gravitation
      • High Altitude Airship (HAA)
      • Hit Equation
      • Hohmann Transfer
      • Inertial Navigation System
      • Instantaneous Balance Assumption
      • In-Situ Resource Utilization (ISRU)
      • Julian Date
      • Kepler's Equation
      • Korea Multi-Purpose Satellite (KOMPSAT)
      • Lagrangian Perturbation Equations
      • Launch Azimuth
      • Launch Window
      • Lift-to-Drag Ratio
      • Load Factor
      • Longitudinal and Lateral Motion
      • Lunar Lander
      • Minimum Energy Trajectory
      • Near-space
      • Newton's Iteration Method
      • Nuri (KSLV-II)
      • Nutation
      • Optimal Velocity Inclination
      • Orbit Capture
      • Orbit Insertion Conditions
      • Orbital Elements
      • Orbital Equation
      • Orbital Maneuver
      • Orbital Phase
      • Orbital Transfer Vehicle
      • Passive Hydrogen Maser (PHM)
      • Perturbation Motion
      • Phasing Orbit
      • Pitch Program Angle
      • Powered Phase
      • Precession
      • Center of Pressure
      • Range Error Coefficient
      • Reentry Corridor
      • Reentry Phase
      • Repeat Ground Track Orbit
      • Reusable Launch Vehicle
      • Synthetic Aperture Radar (SAR)
      • Satellite Ring
      • Sequential Quadratic Programming
      • Skip Reentry
      • Solar Exposure Factor
      • Specific Angular Momentum
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      • Stagnation Heat Flux
      • Standard Atmosphere
      • Stratospheric Airship
      • Subsatellite Track
      • Sun-Synchronous Orbit
      • Thrust-to-Weight Ratio
      • Thrust
      • Total Angle of Attack
      • Trajectory Equation
      • Trajectory Optimization
      • Trim Angle of Attack
      • True Anomaly
      • Tsiolkovsky Rocket Equation
      • Powered Phase Turning Process
      • Two-Body Problem
      • Coordinated Universal Time
      • Variation of Parameters
      • Velocity Frame
      • Velocity Inclination Angle
      • Vis-Viva Equation
      • Very Low Earth Orbit (VLEO)
      • Walker Constellation
      • Zero-Angle-of-Attack Reentry
    • Dynamics & math

      • A* Search Algorithm (A* Search)
      • A2PPO (Attention-Augmented Proximal Policy Optimization)
      • Action-Angle Variables
      • Backstepping Sliding Mode Control
      • Backward Stability Set
      • Bang-bang Control (Bang-bang Control)
      • Barycentric Synodic Coordinate System
      • Batch Deployment (Batch Deployment)
      • Bicircular Four-Body Problem
      • Birkhoff-Gustavson Normal Form
      • Buoyancy-weight Imbalance
      • Capture Set
      • Central Manifold
      • Chaos Effect
      • Clohessy-Wiltshire (CW) Equation
      • Co-state Normalization (Co-state Normalization)
      • Co-state Variables
      • Coasting Arc (Coasting Arc)
      • Continuation Method (Parameter Continuation)
      • Continuation
      • Cooperative Agent (CA)
      • CR3BP with Low-Thrust (CR3BP-LT)
      • Circular Restricted Three-Body Problem (CR3BP)
      • Curriculum Learning
      • Deep Deterministic Policy Gradient (DDPG)
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      • Detection Graph
      • Differential Correction
      • Differential Evolution (DE) Algorithm
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      • Ephemeris Model
      • Equinoctial Orbital Elements (Equinoctial Orbital Elements)
      • Earth Restricted Three-Body Problem (ERTBP)
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      • Generalized Advantage Estimation (GAE)
      • Gaussian Process Regression
      • Geocentric Rotating Coordinate System (GRC)
      • Hamiltonian
      • Hybrid Cluster Particle Swarm Optimization (HCPSO)
      • Heteroclinic Orbit Transfer (Heteroclinic Orbit Transfer)
      • Hill Three-Body Problem
      • Homotopy Method (Homotopy Method)
      • Improved Baseline Control-Point Method (Improved Baseline Control-Point Method)
      • Impulsive Maneuver
      • Initial Value Optimization
      • Invariant Manifold (Invariant Manifold)
      • J2000 Geocentric Equatorial Coordinate System (J2000 Geocentric Equatorial Coordinate System)
      • Jacobi Constant (Jacobi Integral)
      • K-Means Clustering (K-Means Clustering)
      • K-Medoids Clustering (K-Medoids Clustering)
      • KD-Tree (KD-Tree)
      • Libration Point (Equilibrium Point)
      • Libration Point Spacecraft Body Coordinate System (Libration Point Spacecraft Body Coordinate System)
      • Libration Point Spacecraft Orbital Coordinate System (Libration Point Spacecraft Orbital Coordinate System)
      • Lindstedt-Poincare Method (Lindstedt-Poincare Method)
      • L2-centered Rotating Coordinate System (L2-centered Rotating Coordinate System, LRC)
      • LSTM Neural Network
      • Low-Thrust Transfer MDP Formulation
      • Mass Discontinuity (Mass Discontinuity)
      • Multi-Objective Monte Carlo Tree Search (MO-MCTS)
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      • Monodromy Matrix
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      • Newton-Euler Equations
      • NSGA II (Non-dominated Sorting Genetic Algorithm II)
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      • Poincaré Map
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      • Two-Level Differential Correction Method
      • Two-node Model
      • Variational Mode Decomposition
      • Zero-Effort Miss (ZEM)
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    • Mission orbits

      • Apolune
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    • Navigation & systems

      • Altitude Regulation
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      • Cislunar Spatiotemporal Reference
      • Earth-Moon Hybrid Navigation
      • Extended Kalman Filter (EKF)
      • GPS Aided GEO Augmented Navigation (GAGAN)
      • Earth GNSS Weak Signal Navigation
      • Inter-Satellite Link Navigation
      • Indian Regional Navigation Satellite System (IRNSS)
      • LEO Navigation Augmentation
      • LiAISON Navigation
      • LunaNet (Lunar Network)
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      • Moonlight Initiative
      • Observability
      • Positioning, Navigation, and Timing (PNT)
      • Sun-Earth-Moon Autonomous Navigation
      • Tiandu-1
      • Trajectory Planning
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    • Astronomy & observation

      • Astrometry
      • Background Star Elimination
      • Cislunar Moving Objects
      • Continuous Coverage (CP)
      • Earth Albedo
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      • Hot Pixel
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      • Infrared Radiation
      • Lunar Glare Zone
      • Pointing Constraint
      • Quasi-zero Wind Layer
      • Segmentation Map
      • Shift-and-Add (SAA)
      • Sidereal Tracking
      • Signal-to-Noise Ratio (SNR)
      • Solar Radiation
      • Source Extraction
      • Synthetic Tracking
      • Zonal Wind
    • Military space doctrine

      • Anti-Satellite Test (ASAT)
      • Cislunar Space Situational Awareness
      • Civil-Military Integration
      • Competitive Endurance
      • Component Field Commands
      • Commander, Space Forces (COMSPACEFOR)
      • Counterspace Operations
      • Directed Energy Weapon (DEW)
      • Distributed Architecture
      • DOTMLPF-P Framework
      • Force Design
      • Force Development
      • Force Employment
      • Force Generation
      • Golden Dome
      • Kinetic Weapon
      • Mission Command
      • Mission Delta (MD)
      • Operational Test and Training Infrastructure (OTTI)
      • Persistent Detection Corridor (PDC)
      • Resilience Map
      • Resilient/Disaggregated Architecture
      • Space Domain Awareness (SDA)
      • Space Mission Task Force (SMTF)
      • Space Superiority
      • Space Force Generation Process (SPAFORGEN)
      • System Delta (SYD)
    • Organizations

      • Anduril Industries
      • Booz Allen Hamilton
      • Danuri Lunar Orbiter
      • General Dynamics Mission Systems
      • GITAI USA
      • Indian Space Research Organisation
      • Korea Aerospace Administration
      • Lockheed Martin
      • Northrop Grumman
      • Quindar
      • Raytheon Missiles & Defense
      • Sci-Tec
      • SpaceX
      • Satish Dhawan Space Centre SHAR
      • True Anomaly
      • Turion Space

Einstein Equivalence Principle (EEP)

Author: Tianjiang Says

Reference: Li Y et al. 2026 Chin. Phys. Lett. 43 031101, Will C M 2014 Living Rev. Relativ. 17 4

Website: https://cislunarspace.cn

Definition

The Einstein Equivalence Principle (EEP) is the cornerstone of general relativity and the key framework for testing GR's validity. EEP states: within any freely-falling local reference frame in any gravitational field, the laws of non-gravitational physics have exactly the same form as in the absence of gravity.

EEP contains three sub-principles, each constraining the gravitational invariance of physical laws from different perspectives.

Three Sub-Principles

Weak Equivalence Principle (WEP)

The Weak Equivalence Principle is the most classical statement of equivalence, also known as "inertial mass equals gravitational mass":

All objects accelerate identically in a gravitational field, independent of their composition and structure.

Mathematically: mimg=1\frac{m_i}{m_g} = 1mg​mi​​=1

WEP verification experiments include:

  • Free fall experiments since Newton's era
  • Eötvös torsion balance experiments
  • MICROSCOPE satellite (precision reaching 10−1510^{-15}10−15)

Local Lorentz Invariance (LLI)

Local Lorentz Invariance states:

In the local inertial frame at any spacetime point, the expressions of all non-gravitational physical laws are independent of the reference frame's velocity.

LLI verification typically involves comparing oscillator frequencies of atomic clocks with different spin orientations.

Local Position Invariance (LPI)

Local Position Invariance is the sub-principle most directly related to gravitational redshift:

In a freely-falling local reference frame, the results of any non-gravitational experiment are independent of when and where in spacetime the experiment is performed.

The core meaning of LPI is that fundamental physical constants (such as fine structure constant α\alphaα, electron-proton mass ratio me/mpm_e/m_pme​/mp​, etc.) do not depend on gravitational potential. Gravitational redshift experiments test this assumption by constraining LPI.

Mathematical Formulation of LPI

The relationship between gravitational redshift and LPI is described by introducing a violation parameter α\alphaα:

Δff=(1+α)ΔUc2\frac{\Delta f}{f} = (1 + \alpha) \frac{\Delta U}{c^2} fΔf​=(1+α)c2ΔU​

Where:

  • Δf/f\Delta f/fΔf/f is the relative frequency shift between two clocks
  • ΔU\Delta UΔU is the gravitational potential difference
  • ccc is the speed of light
  • α\alphaα is the LPI violation parameter

If LPI holds, then α=0\alpha = 0α=0; if LPI is violated, α\alphaα deviates from zero.

Testing Status of Sub-Principles

Sub-PrincipleTesting PrecisionRepresentative Experiment
WEP10−1510^{-15}10−15MICROSCOPE satellite
LLI10−2210^{-22}10−22Atomic clock comparison
LPI10−510^{-5}10−5Galileo satellite gravitational redshift

Currently, LPI is the least rigorously tested sub-principle of EEP, which is why gravitational redshift experiments continue to receive attention.

Relation to Gravitational Redshift Measurements

Gravitational redshift experiments are the primary means of testing LPI. By measuring the frequency difference between clocks at different gravitational potentials, one can constrain the LPI violation parameter α\alphaα.

Historically significant gravitational redshift experiments:

  1. Pound-Rebka-Snider (1960s): Ground experiment, precision ~1%
  2. Gravity Probe A (1976): Space maser clock, precision 1.41×10−41.41 \times 10^{-4}1.41×10−4
  3. Galileo Satellites (2018): Elliptical orbit modulation, precision 0.19×10−50.19 \times 10^{-5}0.19×10−5
  4. DRO-A Satellite (2025): First cislunar DRO measurement, precision 8.74×10−38.74 \times 10^{-3}8.74×10−3

Future Prospects for Cislunar Measurements

The unique environment of cislunar space provides new opportunities for LPI testing:

  1. Larger gravitational potential difference: DRO gravitational potential difference (∼6.8×10−10\sim 6.8 \times 10^{-10}∼6.8×10−10) is orders of magnitude larger than ground experiments
  2. Longer observation time: DRO orbits are stable, enabling long-term continuous observation
  3. Higher precision atomic clocks: With clocks achieving 10−1610^{-16}10−16 accuracy, precision could reach 10−610^{-6}10−6

Related Concepts

  • Gravitational Redshift
  • Passive Hydrogen Maser (PHM)
  • Dual One-Way Ranging (DOWR)
  • Allan Deviation (ADEV)
  • Distant Retrograde Orbit (DRO)

References

  • Will C M 2014 Living Rev. Relativ. 17 4
  • Li Y, Liu T et al. 2026 Chin. Phys. Lett. 43 031101
  • Delva P et al. 2018 Phys. Rev. Lett. 121 231101
  • Herrmann S et al. 2018 Phys. Rev. Lett. 121 231102
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Last Updated: 6/5/26, 11:01 AM
Contributors: Cron Job, Ou Yang Jiahong
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