Add TLE proxy (#120)

IO-Aerospace-software-engineering · Jul 4, 2023 · 976f84f · 976f84f
1 parent 0626908
commit 976f84f
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Showing 5 changed files with 82 additions and 5 deletions.
diff --git a/.gitignore b/.gitignore
@@ -11,6 +11,7 @@ CTestTestfile.cmake
 _deps
 out/
 cmake-build-release/
+cmake-build-release-coverage/
 cmake-build-debug/
 .vscode/
 build/lib/

diff --git a/IO.Astrodynamics.Tests/APITests.cpp b/IO.Astrodynamics.Tests/APITests.cpp
@@ -443,7 +443,7 @@ TEST(API, TransformFrame)
 TEST(API, ConvertTLEToStateVectorProxy)
 {
     IO::Astrodynamics::Time::TDB epoch("2021-01-20T18:50:13.663106");
-    auto stateVector = ConvertTLEToStateVectorProxy(
+    auto stateVector = ConvertTLEToStateVectorProxy("ISS",
             "1 25544U 98067A   21020.53488036  .00016717  00000-0  10270-3 0  9054",
             "2 25544  51.6423 353.0312 0000493 320.8755  39.2360 15.49309423 25703",
             epoch.GetSecondsFromJ2000().count());
@@ -456,6 +456,23 @@ TEST(API, ConvertTLEToStateVectorProxy)
     ASSERT_DOUBLE_EQ(664440682.84760022, stateVector.epoch);
 }
 
+TEST(API, GetTLEElementsProxy)
+{
+    auto res = GetTLEElementsProxy("ISS",
+                                                    "1 25544U 98067A   21020.53488036  .00016717  00000-0  10270-3 0  9054",
+                                                    "2 25544  51.6423 353.0312 0000493 320.8755  39.2360 15.49309423 25703");
+    ASSERT_DOUBLE_EQ(6803376.2171725659, res.A);
+    ASSERT_DOUBLE_EQ(4.9299999999999999e-05, res.E);
+    ASSERT_DOUBLE_EQ(0.9013281683026676, res.I);
+    ASSERT_DOUBLE_EQ(6.1615568022666061, res.O);
+    ASSERT_DOUBLE_EQ(5.6003339639830649, res.W);
+    ASSERT_DOUBLE_EQ(0.68479738531249512, res.M);
+    ASSERT_DOUBLE_EQ(664419082.8475914, res.Epoch);
+    ASSERT_DOUBLE_EQ(5.06539394194257e-10, res.BalisticCoefficient);
+    ASSERT_DOUBLE_EQ(0.0001027, res.DragTerm);
+    ASSERT_DOUBLE_EQ(0.0, res.SecondDerivativeOfMeanMotion);
+}
+
 TEST(API, ConvertConicOrbitalElementsToStateVector)
 {
     double perifocalDist = std::sqrt(std::pow(-6.116559469556896E+06, 2) + std::pow(-1.546174698676721E+06, 2) +

diff --git a/IO.Astrodynamics/API/DTO/TLEElementsDTO.h b/IO.Astrodynamics/API/DTO/TLEElementsDTO.h
@@ -0,0 +1,28 @@
+/*
+ Copyright (c) 2023. Sylvain Guillet ([email protected])
+ */
+
+//
+// Created by spacer on 7/4/23.
+//
+
+#ifndef IO_TLEELEMENTSDTO_H
+#define IO_TLEELEMENTSDTO_H
+namespace IO::Astrodynamics::API::DTO
+{
+    struct TLEElementsDTO
+    {
+        double BalisticCoefficient{};
+        double SecondDerivativeOfMeanMotion{};
+        double DragTerm{};
+        double Epoch{};
+        double A{};
+        double E{};
+        double I{};
+        double W{};
+        double O{};
+        double M{};
+        const char *Error{};
+    };
+}
+#endif //IO_TLEELEMENTSDTO_H
diff --git a/IO.Astrodynamics/API/Proxy.cpp b/IO.Astrodynamics/API/Proxy.cpp
@@ -628,11 +628,11 @@ TransformFrameProxy(const char *fromFrame, const char *toFrame, double epoch)
     return frameTransformationDto;
 }
 
-IO::Astrodynamics::API::DTO::StateVectorDTO ConvertTLEToStateVectorProxy(const char *L1, const char *L2, double epoch)
+IO::Astrodynamics::API::DTO::StateVectorDTO ConvertTLEToStateVectorProxy(const char *L1, const char *L2, const char *L3, double epoch)
 {
     ActivateErrorManagement();
     auto earth = std::make_shared<IO::Astrodynamics::Body::CelestialBody>(399);
-    std::string strings[3] = {"ISS", L1, L2};
+    std::string strings[3] = {L1, L2, L3};
     IO::Astrodynamics::OrbitalParameters::TLE tle(earth, strings);
     auto sv = tle.ToStateVector(IO::Astrodynamics::Time::TDB(std::chrono::duration<double>(epoch)));
     auto svDTO = ToStateVectorDTO(sv);
@@ -743,6 +743,34 @@ IO::Astrodynamics::API::DTO::StateVectorDTO ReadEphemerisAtGivenEpochProxy(doubl
     return stateVectorDto;
 }
 
+IO::Astrodynamics::API::DTO::TLEElementsDTO GetTLEElementsProxy(const char *L1, const char *L2, const char *L3)
+{
+    ActivateErrorManagement();
+    std::string lines[3]{L1, L2, L3};
+    auto earth = std::make_shared<IO::Astrodynamics::Body::CelestialBody>(399);
+    IO::Astrodynamics::OrbitalParameters::TLE tle(earth, lines);
+
+    IO::Astrodynamics::API::DTO::TLEElementsDTO tleElementsDto;
+
+    tleElementsDto.A = tle.GetSemiMajorAxis();
+    tleElementsDto.E = tle.GetEccentricity();
+    tleElementsDto.I = tle.GetInclination();
+    tleElementsDto.O = tle.GetRightAscendingNodeLongitude();
+    tleElementsDto.W = tle.GetPeriapsisArgument();
+    tleElementsDto.M = tle.GetMeanAnomaly();
+
+    tleElementsDto.Epoch = tle.GetEpoch().GetSecondsFromJ2000().count();
+
+    tleElementsDto.BalisticCoefficient = tle.GetBalisticCoefficient();
+    tleElementsDto.DragTerm = tle.GetDragTerm();
+    tleElementsDto.SecondDerivativeOfMeanMotion = tle.GetSecondDerivativeOfMeanMotion();
+    if (failed_c())
+    {
+        tleElementsDto.Error = strdup(HandleError());
+    }
+    return tleElementsDto;
+}
+
 #pragma endregion
 
 #pragma region ReadResults

diff --git a/IO.Astrodynamics/API/Proxy.h b/IO.Astrodynamics/API/Proxy.h
@@ -11,6 +11,7 @@
 #include <EquinoctialElementsDTO.h>
 #include <RaDecDTO.h>
 #include <HorizontalDTO.h>
+#include <TLEElementsDTO.h>
 
 #pragma region Proxy
 #ifdef __cplusplus
@@ -252,7 +253,7 @@ MODULE_API IO::Astrodynamics::API::DTO::FrameTransformationDTO TransformFramePro
  * @param epoch
  * @return
  */
-MODULE_API IO::Astrodynamics::API::DTO::StateVectorDTO ConvertTLEToStateVectorProxy(const char *L1, const char *L2, double epoch);
+MODULE_API IO::Astrodynamics::API::DTO::StateVectorDTO ConvertTLEToStateVectorProxy(const char *L1, const char *L2, const char *L3, double epoch);
 
 /**
  * Convert conic orbital elements to state vector
@@ -275,6 +276,7 @@ MODULE_API IO::Astrodynamics::API::DTO::StateVectorDTO ConvertEquinoctialElement
  */
 MODULE_API IO::Astrodynamics::API::DTO::RaDecDTO ConvertStateVectorToEquatorialCoordinatesProxy(IO::Astrodynamics::API::DTO::StateVectorDTO stateVectorDto);
 MODULE_API IO::Astrodynamics::API::DTO::HorizontalDTO GetHorizontalCoordinates(IO::Astrodynamics::API::DTO::StateVectorDTO stateVectorDto);
+MODULE_API IO::Astrodynamics::API::DTO::TLEElementsDTO GetTLEElementsProxy(const char *L1, const char *L2, const char *L3);
 #ifdef __cplusplus
 }
 #endif
@@ -286,7 +288,8 @@ MODULE_API IO::Astrodynamics::API::DTO::HorizontalDTO GetHorizontalCoordinates(I
 
 static constexpr const int lenout = 33;
 
-char * HandleError();
+char *HandleError();
+
 void ActivateErrorManagement();
 
 std::map<int, std::shared_ptr<IO::Astrodynamics::Body::CelestialBody>>