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  • 7 commits
  • 80 files changed
  • 1 contributor

Commits on Nov 7, 2021

  1. Convert a benchmark that I had missed.

    @pleroy
    pleroy committed Nov 7, 2021

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    90459b5 View commit details

  2. Remove the old files.

    @pleroy
    pleroy committed Nov 7, 2021
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    8109415 View commit details

  3. The great replacement.

    @pleroy
    pleroy committed Nov 7, 2021
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    af610ad View commit details

  4. Merge remote-tracking branch 'mockingbirdnest/Ondelette' into TheGrea… 

    …tReplacement
    @pleroy
    pleroy committed Nov 7, 2021
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Commits on Nov 9, 2021

  1. Merge.

    @pleroy
    pleroy committed Nov 9, 2021
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    49c1b4c View commit details

  2. More deletions.

    @pleroy
    pleroy committed Nov 9, 2021
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  3. Merge pull request #3200 from pleroy/TheGreatReplacement 

    Rename DiscreteTraject0ry into DiscreteTrajectory
    @pleroy
    pleroy authored Nov 9, 2021
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    6ebbc03 View commit details
Showing with 1,936 additions and 5,797 deletions.
  1. +5 −5 astronomy/geodesy_test.cpp
  2. +10 −10 astronomy/lunar_orbit_test.cpp
  3. +5 −5 astronomy/orbit_analysis_test.cpp
  4. +3 −3 astronomy/orbit_ground_track.hpp
  5. +5 −5 astronomy/orbit_ground_track_body.hpp
  6. +5 −5 astronomy/orbital_elements.hpp
  7. +3 −3 astronomy/orbital_elements_body.hpp
  8. +5 −5 astronomy/orbital_elements_test.cpp
  9. +8 −8 astronomy/standard_product_3.cpp
  10. +5 −5 astronomy/standard_product_3.hpp
  11. +3 −3 astronomy/standard_product_3_test.cpp
  12. +4 −4 astronomy/лидов_古在_test.cpp
  13. +3 −3 astronomy/молния_orbit_test.cpp
  14. +11 −11 benchmarks/apsides.cpp
  15. +4 −4 benchmarks/dynamic_frame.cpp
  16. +10 −10 benchmarks/ephemeris.cpp
  17. +4 −4 benchmarks/planetarium_plot_methods.cpp
  18. +1 −1 ksp_plugin/flight_plan.cpp
  19. +4 −4 ksp_plugin/flight_plan.hpp
  20. +2 −2 ksp_plugin/interface.cpp
  21. +6 −6 ksp_plugin/interface_external.cpp
  22. +13 −13 ksp_plugin/interface_flight_plan.cpp
  23. +8 −8 ksp_plugin/interface_iterator.cpp
  24. +2 −2 ksp_plugin/interface_planetarium.cpp
  25. +12 −12 ksp_plugin/interface_renderer.cpp
  26. +9 −9 ksp_plugin/iterators.hpp
  27. +11 −11 ksp_plugin/iterators_body.hpp
  28. +3 −3 ksp_plugin/manœuvre_body.hpp
  29. +5 −5 ksp_plugin/orbit_analyser.cpp
  30. +7 −7 ksp_plugin/part.cpp
  31. +7 −7 ksp_plugin/part.hpp
  32. +8 −8 ksp_plugin/pile_up.cpp
  33. +5 −5 ksp_plugin/pile_up.hpp
  34. +10 −10 ksp_plugin/planetarium.cpp
  35. +12 −12 ksp_plugin/planetarium.hpp
  36. +17 −17 ksp_plugin/plugin.cpp
  37. +13 −13 ksp_plugin/plugin.hpp
  38. +11 −11 ksp_plugin/renderer.cpp
  39. +11 −11 ksp_plugin/renderer.hpp
  40. +11 −11 ksp_plugin/vessel.cpp
  41. +8 −8 ksp_plugin/vessel.hpp
  42. BIN ksp_plugin_adapter_stub/ksp_plugin_adapter_stub.dll
  43. BIN ksp_plugin_adapter_stub/ksp_plugin_adapter_stub.pdb
  44. +4 −4 ksp_plugin_test/flight_plan_test.cpp
  45. +4 −4 ksp_plugin_test/interface_flight_plan_test.cpp
  46. +3 −3 ksp_plugin_test/manœuvre_test.cpp
  47. +3 −3 ksp_plugin_test/mock_renderer.hpp
  48. +6 −6 ksp_plugin_test/planetarium_test.cpp
  49. +3 −3 ksp_plugin_test/plugin_compatibility_test.cpp
  50. +7 −7 ksp_plugin_test/renderer_test.cpp
  51. +2 −2 ksp_plugin_test/vessel_test.cpp
  52. +4 −4 mathematica/mathematica_test.cpp
  53. +13 −13 physics/apsides.hpp
  54. +8 −8 physics/apsides_body.hpp
  55. +8 −8 physics/apsides_test.cpp
  56. +2 −2 physics/body_centred_body_direction_dynamic_frame_test.cpp
  57. +0 −217 physics/discrete_traject0ry.hpp
  58. +0 −875 physics/discrete_traject0ry_body.hpp
  59. +0 −775 physics/discrete_traject0ry_test.cpp
  60. +162 −237 physics/discrete_trajectory.hpp
  61. +702 −533 physics/discrete_trajectory_body.hpp
  62. +3 −3 physics/discrete_trajectory_segment.hpp
  63. +3 −3 physics/discrete_trajectory_segment_iterator.hpp
  64. +656 −850 physics/discrete_trajectory_test.cpp
  65. +12 −12 physics/ephemeris.hpp
  66. +12 −12 physics/ephemeris_body.hpp
  67. +12 −12 physics/ephemeris_test.cpp
  68. +0 −249 physics/forkable.hpp
  69. +0 −551 physics/forkable_body.hpp
  70. +0 −793 physics/forkable_test.cpp
  71. +3 −3 physics/mock_ephemeris.hpp
  72. +3 −9 physics/physics.vcxproj
  73. +8 −26 physics/physics.vcxproj.filters
  74. +3 −3 testing_utilities/discrete_trajectory_factories.hpp
  75. +1 −1 testing_utilities/discrete_trajectory_factories_body.hpp
  76. +0 −3 testing_utilities/testing_utilities.vcxproj
  77. +0 −9 testing_utilities/testing_utilities.vcxproj.filters
  78. +0 −72 testing_utilities/trajectory_factories.hpp
  79. +0 −95 testing_utilities/trajectory_factories_body.hpp
  80. +0 −98 testing_utilities/trajectory_factories_test.cpp
10 changes: 5 additions & 5 deletions astronomy/geodesy_test.cpp
View file
Original file line number Diff line number Diff line change
@@ -7,7 +7,7 @@
#include "gmock/gmock.h"
#include "gtest/gtest.h"
#include "physics/body_surface_dynamic_frame.hpp"
#include "physics/discrete_traject0ry.hpp"
#include "physics/discrete_trajectory.hpp"
#include "physics/solar_system.hpp"
#include "quantities/si.hpp"
#include "testing_utilities/approximate_quantity.hpp"
@@ -33,7 +33,7 @@ using integrators::methods::QuinlanTremaine1990Order12;
using physics::BodySurfaceDynamicFrame;
using physics::ContinuousTrajectory;
using physics::DegreesOfFreedom;
using physics::DiscreteTraject0ry;
using physics::DiscreteTrajectory;
using physics::Ephemeris;
using physics::KeplerianElements;
using physics::KeplerOrbit;
@@ -126,15 +126,15 @@ TEST_F(GeodesyTest, DISABLED_LAGEOS2) {

ephemeris_->Prolong(final_time);

DiscreteTraject0ry<ICRS> primary_lageos2_trajectory;
DiscreteTrajectory<ICRS> primary_lageos2_trajectory;
primary_lageos2_trajectory.Append(
initial_time, itrs_.FromThisFrameAtTime(initial_time)(initial_dof_ilrsa));
DiscreteTraject0ry<ICRS> secondary_lageos2_trajectory;
DiscreteTrajectory<ICRS> secondary_lageos2_trajectory;
secondary_lageos2_trajectory.Append(
initial_time, itrs_.FromThisFrameAtTime(initial_time)(initial_dof_ilrsb));
auto flow_lageos2 =
[this, final_time](
DiscreteTraject0ry<ICRS>& lageos2_trajectory) -> absl::Status {
DiscreteTrajectory<ICRS>& lageos2_trajectory) -> absl::Status {
return ephemeris_->FlowWithAdaptiveStep(
&lageos2_trajectory,
Ephemeris<ICRS>::NoIntrinsicAcceleration,
20 changes: 10 additions & 10 deletions astronomy/lunar_orbit_test.cpp
View file
Original file line number Diff line number Diff line change
@@ -18,7 +18,7 @@
#include "mathematica/mathematica.hpp"
#include "physics/apsides.hpp"
#include "physics/body_surface_dynamic_frame.hpp"
#include "physics/discrete_traject0ry.hpp"
#include "physics/discrete_trajectory.hpp"
#include "physics/kepler_orbit.hpp"
#include "physics/massless_body.hpp"
#include "physics/oblate_body.hpp"
@@ -57,7 +57,7 @@ using physics::BodySurfaceDynamicFrame;
using physics::ComputeApsides;
using physics::ComputeNodes;
using physics::DegreesOfFreedom;
using physics::DiscreteTraject0ry;
using physics::DiscreteTrajectory;
using physics::Ephemeris;
using physics::KeplerianElements;
using physics::KeplerOrbit;
@@ -363,7 +363,7 @@ TEST_P(LunarOrbitTest, NearCircularRepeatGroundTrackOrbit) {
IsNear(4.7e-13_⑴));
}

DiscreteTraject0ry<ICRS> trajectory;
DiscreteTrajectory<ICRS> trajectory;
trajectory.Append(J2000, initial_state);
auto const instance = ephemeris_->NewInstance(
{&trajectory},
@@ -377,7 +377,7 @@ TEST_P(LunarOrbitTest, NearCircularRepeatGroundTrackOrbit) {

// To find the nodes, we need to convert the trajectory to a reference frame
// whose xy plane is the Moon's equator.
DiscreteTraject0ry<LunarSurface> surface_trajectory;
DiscreteTrajectory<LunarSurface> surface_trajectory;
for (auto const& [time, degrees_of_freedom] : trajectory) {
surface_trajectory.Append(
time, lunar_frame_.ToThisFrameAtTime(time)(degrees_of_freedom));
@@ -413,8 +413,8 @@ TEST_P(LunarOrbitTest, NearCircularRepeatGroundTrackOrbit) {
mathematica::ExpressIn(Metre));
}

DiscreteTraject0ry<LunarSurface> ascending_nodes;
DiscreteTraject0ry<LunarSurface> descending_nodes;
DiscreteTrajectory<LunarSurface> ascending_nodes;
DiscreteTrajectory<LunarSurface> descending_nodes;
ComputeNodes(surface_trajectory,
surface_trajectory.begin(),
surface_trajectory.end(),
@@ -423,8 +423,8 @@ TEST_P(LunarOrbitTest, NearCircularRepeatGroundTrackOrbit) {
ascending_nodes,
descending_nodes);

DiscreteTraject0ry<ICRS> apoapsides;
DiscreteTraject0ry<ICRS> periapsides;
DiscreteTrajectory<ICRS> apoapsides;
DiscreteTrajectory<ICRS> periapsides;
ComputeApsides(*ephemeris_->trajectory(moon_),
trajectory,
trajectory.begin(),
@@ -435,12 +435,12 @@ TEST_P(LunarOrbitTest, NearCircularRepeatGroundTrackOrbit) {

struct Nodes {
std::string_view const name;
DiscreteTraject0ry<LunarSurface> const& trajectory;
DiscreteTrajectory<LunarSurface> const& trajectory;
};

struct Apsides {
std::string_view const name;
DiscreteTraject0ry<ICRS> const& trajectory;
DiscreteTrajectory<ICRS> const& trajectory;
};

std::vector<double> descending_node_eccentricities;
10 changes: 5 additions & 5 deletions astronomy/orbit_analysis_test.cpp
View file
Original file line number Diff line number Diff line change
@@ -14,7 +14,7 @@
#include "mathematica/mathematica.hpp"
#include "numerics/polynomial.hpp"
#include "physics/body_centred_non_rotating_dynamic_frame.hpp"
#include "physics/discrete_traject0ry.hpp"
#include "physics/discrete_trajectory.hpp"
#include "physics/ephemeris.hpp"
#include "physics/solar_system.hpp"
#include "testing_utilities/approximate_quantity.hpp"
@@ -36,7 +36,7 @@ using numerics::EstrinEvaluator;
using numerics::PolynomialInMonomialBasis;
using physics::BodyCentredNonRotatingDynamicFrame;
using physics::BodySurfaceDynamicFrame;
using physics::DiscreteTraject0ry;
using physics::DiscreteTrajectory;
using physics::Ephemeris;
using physics::MasslessBody;
using physics::RotatingBody;
@@ -144,18 +144,18 @@ class OrbitAnalysisTest : public ::testing::Test {

// Returns a GCRS trajectory obtained by stitching together the trajectories
// of |sp3_orbit.satellites| in |sp3_orbit.files|.
not_null<std::unique_ptr<DiscreteTraject0ry<GCRS>>> EarthCentredTrajectory(
not_null<std::unique_ptr<DiscreteTrajectory<GCRS>>> EarthCentredTrajectory(
SP3Orbit const& sp3_orbit) {
BodyCentredNonRotatingDynamicFrame<ICRS, GCRS> gcrs{ephemeris_.get(),
&earth_};
BodySurfaceDynamicFrame<ICRS, ITRS> itrs{ephemeris_.get(), &earth_};

auto result = make_not_null_unique<DiscreteTraject0ry<GCRS>>();
auto result = make_not_null_unique<DiscreteTrajectory<GCRS>>();
for (auto const& file : sp3_orbit.files.names) {
StandardProduct3 sp3(
SOLUTION_DIR / "astronomy" / "standard_product_3" / file,
sp3_orbit.files.dialect);
std::vector<not_null<DiscreteTraject0ry<ITRS> const*>> const& orbit =
std::vector<not_null<DiscreteTrajectory<ITRS> const*>> const& orbit =
sp3.orbit(sp3_orbit.satellite);
CHECK_EQ(orbit.size(), 1);
auto const& arc = *orbit.front();
6 changes: 3 additions & 3 deletions astronomy/orbit_ground_track.hpp
View file
Original file line number Diff line number Diff line change
@@ -7,7 +7,7 @@
#include "astronomy/orbit_recurrence.hpp"
#include "astronomy/orbital_elements.hpp"
#include "geometry/interval.hpp"
#include "physics/discrete_traject0ry.hpp"
#include "physics/discrete_trajectory.hpp"
#include "physics/rotating_body.hpp"

namespace principia {
@@ -16,7 +16,7 @@ namespace internal_orbit_ground_track {

using geometry::Instant;
using geometry::Interval;
using physics::DiscreteTraject0ry;
using physics::DiscreteTrajectory;
using physics::RotatingBody;
using quantities::Angle;
using quantities::AngularFrequency;
@@ -67,7 +67,7 @@ class OrbitGroundTrack {
// sun-synchronicity is analysed.
template<typename PrimaryCentred, typename Inertial>
static absl::StatusOr<OrbitGroundTrack> ForTrajectory(
DiscreteTraject0ry<PrimaryCentred> const& trajectory,
DiscreteTrajectory<PrimaryCentred> const& trajectory,
RotatingBody<Inertial> const& primary,
std::optional<MeanSun> const& mean_sun);

10 changes: 5 additions & 5 deletions astronomy/orbit_ground_track_body.hpp
View file
Original file line number Diff line number Diff line change
@@ -31,7 +31,7 @@ Angle CelestialLongitude(Position<PrimaryCentred> const& q) {
// The resulting angles are neither normalized nor unwound.
template<typename PrimaryCentred, typename Inertial>
std::vector<Angle> PlanetocentricLongitudes(
DiscreteTraject0ry<PrimaryCentred> const& nodes,
DiscreteTrajectory<PrimaryCentred> const& nodes,
RotatingBody<Inertial> const& primary) {
std::vector<Angle> longitudes;
longitudes.reserve(nodes.size());
@@ -55,7 +55,7 @@ Angle MeanSolarTime(Iterator const& it,

template<typename PrimaryCentred>
Interval<Angle> MeanSolarTimesOfNodes(
DiscreteTraject0ry<PrimaryCentred> const& nodes,
DiscreteTrajectory<PrimaryCentred> const& nodes,
OrbitGroundTrack::MeanSun const& mean_sun) {
Interval<Angle> mean_solar_times;
std::optional<Angle> mean_solar_time;
@@ -120,11 +120,11 @@ inline OrbitGroundTrack::EquatorCrossingLongitudes::EquatorCrossingLongitudes(

template<typename PrimaryCentred, typename Inertial>
absl::StatusOr<OrbitGroundTrack> OrbitGroundTrack::ForTrajectory(
DiscreteTraject0ry<PrimaryCentred> const& trajectory,
DiscreteTrajectory<PrimaryCentred> const& trajectory,
RotatingBody<Inertial> const& primary,
std::optional<MeanSun> const& mean_sun) {
DiscreteTraject0ry<PrimaryCentred> ascending_nodes;
DiscreteTraject0ry<PrimaryCentred> descending_nodes;
DiscreteTrajectory<PrimaryCentred> ascending_nodes;
DiscreteTrajectory<PrimaryCentred> descending_nodes;
OrbitGroundTrack ground_track;
RETURN_IF_ERROR(ComputeNodes(trajectory,
trajectory.begin(),
10 changes: 5 additions & 5 deletions astronomy/orbital_elements.hpp
View file
Original file line number Diff line number Diff line change
@@ -6,7 +6,7 @@
#include "geometry/interval.hpp"
#include "geometry/named_quantities.hpp"
#include "physics/body.hpp"
#include "physics/discrete_traject0ry.hpp"
#include "physics/discrete_trajectory.hpp"
#include "physics/massive_body.hpp"
#include "quantities/named_quantities.hpp"
#include "quantities/quantities.hpp"
@@ -18,7 +18,7 @@ namespace internal_orbital_elements {
using geometry::Instant;
using geometry::Interval;
using physics::Body;
using physics::DiscreteTraject0ry;
using physics::DiscreteTrajectory;
using physics::MassiveBody;
using quantities::Angle;
using quantities::AngularFrequency;
@@ -37,7 +37,7 @@ class OrbitalElements {

template<typename PrimaryCentred>
static absl::StatusOr<OrbitalElements> ForTrajectory(
DiscreteTraject0ry<PrimaryCentred> const& trajectory,
DiscreteTrajectory<PrimaryCentred> const& trajectory,
MassiveBody const& primary,
Body const& secondary);

@@ -146,13 +146,13 @@ class OrbitalElements {

template<typename PrimaryCentred>
static std::vector<EquinoctialElements> OsculatingEquinoctialElements(
DiscreteTraject0ry<PrimaryCentred> const& trajectory,
DiscreteTrajectory<PrimaryCentred> const& trajectory,
MassiveBody const& primary,
Body const& secondary);

template<typename PrimaryCentred>
static std::vector<Length> RadialDistances(
DiscreteTraject0ry<PrimaryCentred> const& trajectory);
DiscreteTrajectory<PrimaryCentred> const& trajectory);

// |equinoctial_elements| must contain at least 2 elements.
static absl::StatusOr<Time> SiderealPeriod(
6 changes: 3 additions & 3 deletions astronomy/orbital_elements_body.hpp
View file
Original file line number Diff line number Diff line change
@@ -33,7 +33,7 @@ using quantities::si::Radian;

template<typename PrimaryCentred>
absl::StatusOr<OrbitalElements> OrbitalElements::ForTrajectory(
DiscreteTraject0ry<PrimaryCentred> const& trajectory,
DiscreteTrajectory<PrimaryCentred> const& trajectory,
MassiveBody const& primary,
Body const& secondary) {
OrbitalElements orbital_elements;
@@ -139,7 +139,7 @@ inline Interval<Length> OrbitalElements::radial_distance_interval() const {
template<typename PrimaryCentred>
std::vector<OrbitalElements::EquinoctialElements>
OrbitalElements::OsculatingEquinoctialElements(
DiscreteTraject0ry<PrimaryCentred> const& trajectory,
DiscreteTrajectory<PrimaryCentred> const& trajectory,
MassiveBody const& primary,
Body const& secondary) {
DegreesOfFreedom<PrimaryCentred> const primary_dof{
@@ -176,7 +176,7 @@ OrbitalElements::OsculatingEquinoctialElements(

template<typename PrimaryCentred>
std::vector<Length> OrbitalElements::RadialDistances(
DiscreteTraject0ry<PrimaryCentred> const& trajectory) {
DiscreteTrajectory<PrimaryCentred> const& trajectory) {
std::vector<Length> radial_distances;
radial_distances.reserve(trajectory.size());
DegreesOfFreedom<PrimaryCentred> const primary_dof{PrimaryCentred::origin,
10 changes: 5 additions & 5 deletions astronomy/orbital_elements_test.cpp
View file
Original file line number Diff line number Diff line change
@@ -10,7 +10,7 @@
#include "gtest/gtest.h"
#include "mathematica/mathematica.hpp"
#include "physics/body_centred_non_rotating_dynamic_frame.hpp"
#include "physics/discrete_traject0ry.hpp"
#include "physics/discrete_trajectory.hpp"
#include "physics/ephemeris.hpp"
#include "physics/kepler_orbit.hpp"
#include "physics/solar_system.hpp"
@@ -35,7 +35,7 @@ using integrators::methods::DormandالمكاوىPrince1986RKN434FM;
using integrators::methods::QuinlanTremaine1990Order12;
using physics::BodyCentredNonRotatingDynamicFrame;
using physics::DegreesOfFreedom;
using physics::DiscreteTraject0ry;
using physics::DiscreteTrajectory;
using physics::Ephemeris;
using physics::KeplerianElements;
using physics::KeplerOrbit;
@@ -77,7 +77,7 @@ class OrbitalElementsTest : public ::testing::Test {

// Completes |initial_osculating_elements| and returns a GCRS trajectory
// obtained by flowing the corresponding initial conditions in |ephemeris|.
static not_null<std::unique_ptr<DiscreteTraject0ry<GCRS>>>
static not_null<std::unique_ptr<DiscreteTrajectory<GCRS>>>
EarthCentredTrajectory(
KeplerianElements<GCRS>& initial_osculating_elements,
Instant const& initial_time,
@@ -86,7 +86,7 @@ class OrbitalElementsTest : public ::testing::Test {
MassiveBody const& earth = FindEarthOrDie(ephemeris);
ephemeris.Prolong(final_time);
BodyCentredNonRotatingDynamicFrame<ICRS, GCRS> gcrs{&ephemeris, &earth};
DiscreteTraject0ry<ICRS> icrs_trajectory;
DiscreteTrajectory<ICRS> icrs_trajectory;
KeplerOrbit<GCRS> initial_osculating_orbit{earth,
MasslessBody{},
initial_osculating_elements,
@@ -110,7 +110,7 @@ class OrbitalElementsTest : public ::testing::Test {
/*speed_integration_tolerance=*/1 * Milli(Metre) / Second
},
/*max_ephemeris_steps=*/std::numeric_limits<std::int64_t>::max());
auto result = make_not_null_unique<DiscreteTraject0ry<GCRS>>();
auto result = make_not_null_unique<DiscreteTrajectory<GCRS>>();
for (auto const& [time, degrees_of_freedom] : icrs_trajectory) {
result->Append(time, gcrs.ToThisFrameAtTime(time)(degrees_of_freedom));
}
16 changes: 8 additions & 8 deletions astronomy/standard_product_3.cpp
View file
Original file line number Diff line number Diff line change
@@ -32,9 +32,9 @@ using quantities::si::Second;
// n-point finite difference formulæ on the positions to produce a trajectory
// with consistent velocities.
template<int n>
not_null<std::unique_ptr<DiscreteTraject0ry<ITRS>>> ComputeVelocities(
DiscreteTraject0ry<ITRS> const& arc) {
auto result = make_not_null_unique<DiscreteTraject0ry<ITRS>>();
not_null<std::unique_ptr<DiscreteTrajectory<ITRS>>> ComputeVelocities(
DiscreteTrajectory<ITRS> const& arc) {
auto result = make_not_null_unique<DiscreteTrajectory<ITRS>>();
CHECK_GE(arc.size(), n);
std::array<Instant, n> times;
std::array<Position<ITRS>, n> positions;
@@ -193,7 +193,7 @@ StandardProduct3::StandardProduct3(
std::forward_as_tuple());
CHECK(inserted) << "Duplicate satellite identifier " << id << ": "
<< full_location;
it->second.push_back(make_not_null_unique<DiscreteTraject0ry<ITRS>>());
it->second.push_back(make_not_null_unique<DiscreteTrajectory<ITRS>>());
satellites_.push_back(id);
} else {
CHECK_EQ(columns(c, c + 2), " 0") << full_location;
@@ -330,9 +330,9 @@ StandardProduct3::StandardProduct3(
// from the check.
CHECK_EQ(id, satellites_[i]) << location;

std::vector<not_null<std::unique_ptr<DiscreteTraject0ry<ITRS>>>>& orbit =
std::vector<not_null<std::unique_ptr<DiscreteTrajectory<ITRS>>>>& orbit =
it->second;
DiscreteTraject0ry<ITRS>& arc = *orbit.back();
DiscreteTrajectory<ITRS>& arc = *orbit.back();

Position<ITRS> const position =
Displacement<ITRS>({float_columns(5, 18) * Kilo(Metre),
@@ -376,7 +376,7 @@ StandardProduct3::StandardProduct3(
// Bad or absent positional and velocity values are to be set to 0.000000.
if (position == ITRS::origin || velocity == ITRS::unmoving) {
if (!arc.empty()) {
orbit.push_back(make_not_null_unique<DiscreteTraject0ry<ITRS>>());
orbit.push_back(make_not_null_unique<DiscreteTrajectory<ITRS>>());
}
} else {
arc.Append(epoch, {position, velocity});
@@ -439,7 +439,7 @@ StandardProduct3::satellites() const {
return satellites_;
}

std::vector<not_null<DiscreteTraject0ry<ITRS> const*>> const&
std::vector<not_null<DiscreteTrajectory<ITRS> const*>> const&
StandardProduct3::orbit(SatelliteIdentifier const& id) const {
return FindOrDie(const_orbits_, id);
}
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