Collision Avoidance Maneuver design for conjunction assessment
Use Wire codec for all binary encoding/decoding
- CLCW: remove hand-written bit manipulation, single codec for the
full 32-bit word with typed fields
- Space Packet: single full-packet codec (header + variable-length
data via Field.ref on data_length)
- TC: frame_codec with dependent-length data zone from header's
frame_length field
- AOS/TM/USLP: packed_frame type with Wire codec for header +
data zone capture for the variable-length trailing portion
- Remove all duplicate packed_header types where superseded
- Expose Wire.Codec field bindings for future zero-copy get/set
+121
+38
test/interop/gmat/regenerate.sh
+38
test/interop/gmat/regenerate.sh
···
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#!/bin/bash
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# Regenerate GMAT test traces for ocaml-cam.
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#
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# Requires: GMAT R2026a installed.
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# Usage: GMAT_HOME=~/Downloads/"GMAT R2026a" ./regenerate.sh
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#
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# Traces are committed to git (dune promote pattern).
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# Only re-run this when changing GMAT scripts or upgrading GMAT.
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set -euo pipefail
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GMAT_HOME="${GMAT_HOME:-$HOME/Downloads/GMAT R2026a}"
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GMAT="$GMAT_HOME/bin/GmatConsole"
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SCRIPT_DIR="$(cd "$(dirname "$0")/scripts" && pwd)"
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TRACE_DIR="$(cd "$(dirname "$0")/traces" && pwd)"
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if [ ! -x "$GMAT" ]; then
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echo "error: GmatConsole not found at $GMAT"
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echo "Set GMAT_HOME to your GMAT installation directory."
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exit 1
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fi
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echo "GMAT: $GMAT"
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echo "Scripts: $SCRIPT_DIR"
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echo "Traces: $TRACE_DIR"
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echo
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for script in "$SCRIPT_DIR"/*.script; do
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name=$(basename "$script" .script)
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echo "==> Running $name..."
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cd "$GMAT_HOME/bin"
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"$GMAT" --run "$script" 2>&1 | tail -3
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echo " Done."
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echo
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done
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echo "All traces regenerated in $TRACE_DIR"
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echo "Review with: git diff $TRACE_DIR"
+83
test/interop/gmat/scripts/tangential_burn.script
+83
test/interop/gmat/scripts/tangential_burn.script
···
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%
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% tangential_burn --- LEO satellite with tangential impulsive burn
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%
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% Test vector for ocaml-cam: validate delta-v effect on orbit.
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% Pre-burn and post-burn ephemerides + report of orbital elements.
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%
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% Scenario: ISS-like orbit, +0.1 km/s tangential burn at t=1 orbit.
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%
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% Source: GMAT R2026a.
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%
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%---------- Spacecraft
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Create Spacecraft Sat;
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Sat.DateFormat = UTCGregorian;
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Sat.Epoch = '01 Jan 2026 00:00:00.000';
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Sat.CoordinateSystem = EarthMJ2000Eq;
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Sat.DisplayStateType = Keplerian;
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Sat.SMA = 6778.137;
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Sat.ECC = 0.0008;
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Sat.INC = 51.6;
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Sat.RAAN = 45.0;
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Sat.AOP = 90.0;
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Sat.TA = 0.0;
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%---------- Burn (tangential, +0.1 km/s in velocity direction)
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Create ImpulsiveBurn Burn1;
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Burn1.CoordinateSystem = Local;
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Burn1.Origin = Earth;
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Burn1.Axes = VNB;
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Burn1.Element1 = 0.1;
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Burn1.Element2 = 0.0;
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Burn1.Element3 = 0.0;
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%---------- ForceModel
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Create ForceModel Forces;
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Forces.CentralBody = Earth;
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Forces.PrimaryBodies = {Earth};
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Forces.PointMasses = {Luna, Sun};
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Forces.GravityField.Earth.Degree = 10;
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Forces.GravityField.Earth.Order = 10;
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%---------- Propagator
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Create Propagator Prop;
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Prop.FM = Forces;
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Prop.Type = RungeKutta89;
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Prop.InitialStepSize = 60;
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Prop.Accuracy = 1e-12;
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+
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%---------- OEM Output (pre-burn + post-burn combined)
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Create EphemerisFile OEM_Burn;
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OEM_Burn.Spacecraft = Sat;
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OEM_Burn.Filename = '../traces/tangential_burn.oem';
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OEM_Burn.FileFormat = CCSDS-OEM;
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OEM_Burn.EpochFormat = UTCGregorian;
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OEM_Burn.StepSize = 60;
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OEM_Burn.CoordinateSystem = EarthMJ2000Eq;
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OEM_Burn.WriteEphemeris = true;
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+
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%---------- Report: orbital elements before and after burn
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Create ReportFile BurnReport;
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BurnReport.Filename = '../traces/tangential_burn_report.txt';
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BurnReport.Precision = 16;
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BurnReport.Add = {Sat.UTCGregorian, Sat.X, Sat.Y, Sat.Z, Sat.VX, Sat.VY, Sat.VZ, Sat.SMA, Sat.ECC, Sat.INC};
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BurnReport.WriteHeaders = True;
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BurnReport.FixedWidth = True;
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+
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%---------- Mission Sequence
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BeginMissionSequence;
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+
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% Propagate 1 orbit (~92 min for LEO)
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Propagate Prop(Sat) {Sat.ElapsedSecs = 5554.0};
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+
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% Apply tangential burn
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Maneuver Burn1(Sat);
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% Propagate 3 more orbits to see effect
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Propagate Prop(Sat) {Sat.ElapsedSecs = 16662.0};