Feature/test drag#296
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…ove force handling
…tPropagator SpacecraftPropagator now owns all force building for custom integrators, mirroring the existing VV convenience constructor pattern. RK78Integrator constructors no longer require forces or initial state; forces are added via AddForce() and Initialize() is called by the propagator. Co-Authored-By: Claude Opus 4.6 <noreply@anthropic.com>
Implement dual-mode propagator: SSB-centered (existing, for interplanetary) and central-body-centered (new, for planetary satellite missions). The central-body mode avoids catastrophic cancellation in double precision that occurs when computing satellite-to-body vectors from SSB-centered positions (~5 significant digits lost for LEO). - Add ThirdBodyPerturbation force using Battin's numerically stable formulation: a = -mu / |r-d|^3 * (r + f(q)*d), where f(q) stably computes (1+q)^(3/2)-1 and |r-d|^3 = |d|^3*(1+q)^(3/2) - Add centralBody constructor overloads to SpacecraftPropagator - Replace old propagation tests with conformance-based tests from GMAT R2025a reference data (cases 001, 002, 003) - Both modes tested against same GMAT reference within tolerances Co-Authored-By: Claude Opus 4.6 <noreply@anthropic.com>
…tests; remove .NET 8.0 support - Introduce PropagatorBase, SsbPropagator, and CentralBodyPropagator for modular propagation modes - Implement conformance and infrastructure tests for new propagators - Update Spacecraft propagation logic to select appropriate propagator based on observer type - Remove .NET 8.0 target from project files and NuSpec; standardize on net10.0 - Refactor usages and comments for new propagator classes - Adjust test tolerances and assertions for improved accuracy and consistency
…nd test project references for consistent community linkage; add CLAUDE.md with repository guidance
…formance; refactor GetEphemeris methods and introduce PropagationEphemerisCache
…tate vector handling; convert CB-relative states to SSB-relative on demand and optimize ephemeris retrieval
…ctors for force evaluation; implement UpdateState method for improved state management
…ect corrected ephemeris values
…n-SPICE observers; enhance GetGeometricStateRelativeTo methods across celestial objects
…mputation for non-SPICE observers; reduce SSB round-trips and improve memory allocation efficiency
…amics propagation - Added performance benchmark results for RK78 integration methods in Markdown, CSV, and HTML formats. - Implemented BisectionEventFinder for root-finding within integration steps using cubic Hermite interpolation. - Created AcceptedStep struct to represent integration steps with start and end states. - Introduced CrossingDirection enum to specify event triggering directions. - Developed IEventDetector interface for industry-standard event detection based on continuous g-functions. - Implemented ManeuverEventDetector class to handle impulse maneuvers and event-driven triggering. - Added IntegrationResult struct to encapsulate results of integration segments, including detected events. - Created PropagationSegment class to manage continuous propagation arcs and provide cubic Hermite interpolation. - Developed PropagationSolution class to manage multiple segments and interpolate states at given epochs.
…ralBodyPropagator, implement segment-based event-driven maneuver execution, and enhance event detection system with g-function approach.
…espectively; add IO.Astrodynamics.CLI project to solution
…isTests for accuracy
…propagator-rework # Conflicts: # src/community/IO.Astrodynamics.Net/IO.Astrodynamics.Tests/Propagators/PropagatorTests.cs
… StateVectors access modifier
…prove internal access modifiers
…hemeris computation strategy
…te state vector retrieval
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This pull request updates the propagation and ephemeris API to simplify usage, improve clarity, and make SSB-relative state handling an internal detail. The most significant changes are that all
Propagate()methods now return aPropagationSolutionfor dense output, SSB-specific methods have been removed from the public API, and SPK files are now written with central-body-relative states. Documentation and tests have been updated accordingly.API and Behavior Changes:
Propagate()methods (PropagatorBase,CentralBodyPropagator,TLEPropagator,Spacecraft.Propagate()/PropagateAsync()) now return aPropagationSolutionobject, enabling dense output viaInterpolateAt(epoch). Previously, callers accessed propagated states directly fromStateVectorsRelativeToICRF. [1] [2] [3] [4] [5] [6] [7]GetGeometricStateFromICRF,GetEphemerisFromICRF) have been removed from public interfaces and are now internal. Equivalent functionality is available usingGetEphemeris(epoch, target, observer, frame, aberration)with SSB as the observer. SSB-relative states are now used internally only for aberration correction and star positions. [1] [2]Spacecraft.WriteEphemeris()now contain states relative to the central body, not SSB; SPICE will chain ephemerides automatically using the center body ID.Documentation Updates:
DEVELOPER_GUIDE.mdto reflect the new propagation API, clarify thatStateVectorsRelativeToICRFare CB-relative, and document the internal use of SSB-relative states. [1] [2] [3] [4] [5] [6] [7] [8] [9]Test Suite Updates:
ConfigurationTest.csto use the newGetEphemerismethod (with explicit observer argument) instead of the removedGetEphemerisFromICRF. Test names and assertions were updated to match the new API. [1] [2] [3]