Struct Frame 

pub struct Frame {
    pub ephemeris_id: i32,
    pub orientation_id: i32,
    pub force_inertial: bool,
    pub mu_km3_s2: Option<f64>,
    pub shape: Option<Ellipsoid>,
    pub frozen_epoch: Option<Epoch>,
}

A Frame uniquely defined by its ephemeris center and orientation. Refer to FrameDetail for frames combined with parameters.

:type ephemeris_id: int :type orientation_id: int :type force_inertial: bool :type mu_km3_s2: float, optional :type shape: Ellipsoid, optional :type frozen_epoch: Epoch, optional :rtype: Frame

Fields

ephemeris_id: i32

orientation_id: i32

force_inertial: bool

If true, the DCM of this frame will always force its time derivative to zero, inertially fixing the frame.

mu_km3_s2: Option<f64>

Gravity parameter of this frame, only defined on celestial frames

shape: Option<Ellipsoid>

Shape of the geoid of this frame, only defined on geodetic frames

frozen_epoch: Option<Epoch>

If set, the DCM will always be evaluated at the provided epoch, freezing it in time.

Implementations

impl Frame

pub const fn new(ephemeris_id: i32, orientation_id: i32) -> Frame

Constructs a new frame given its ephemeris and orientations IDs, without defining anything else (so this is not a valid celestial frame, although the data could be populated later).

pub const fn from_ephem_j2000(ephemeris_id: i32) -> Frame

Examples found in repository

nyx-core/examples/02_jwst_covar_monte_carlo/main.rs (line 51)

    const JWST_J2000: Frame = Frame::from_ephem_j2000(JWST_NAIF_ID);

nyx-core/examples/04_lro_od/main.rs (line 66)

fn main() -> Result<(), Box<dyn Error>> {
    pel::init();

    // ====================== //
    // === ALMANAC SET UP === //
    // ====================== //

    // Dynamics models require planetary constants and ephemerides to be defined.
    // Let's start by grabbing those by using ANISE's MetaAlmanac.

    let output_folder: PathBuf = [env!("CARGO_MANIFEST_DIR"), "../data", "04_output"]
        .iter()
        .collect();

    let data_folder: PathBuf = [env!("CARGO_MANIFEST_DIR"), "examples", "04_lro_od"]
        .iter()
        .collect();

    let meta = data_folder.join("lro-dynamics.dhall");

    // Load this ephem in the general Almanac we're using for this analysis.
    let almanac = Arc::new(
        MetaAlmanac::new(meta.to_string_lossy().as_ref())
            .map_err(Box::new)?
            .process(true)
            .map_err(Box::new)?,
    );

    // Orbit determination requires a Trajectory structure, which can be saved as parquet file.
    // In our case, the trajectory comes from the BSP file, so we need to build a Trajectory from the almanac directly.
    // To query the Almanac, we need to build the LRO frame in the J2000 orientation in our case.
    // Inspecting the LRO BSP in the ANISE GUI shows us that NASA has assigned ID -85 to LRO.
    let lro_frame = Frame::from_ephem_j2000(-85);

    // To build the trajectory we need to provide a spacecraft template.
    let sc_template = Spacecraft::builder()
        .mass(Mass::from_dry_and_prop_masses(1018.0, 900.0)) // Launch masses
        .srp(SRPData {
            // SRP configuration is arbitrary, but we will be estimating it anyway.
            area_m2: 3.9 * 2.7,
            coeff_reflectivity: 0.96,
        })
        .orbit(Orbit::zero(MOON_J2000)) // Setting a zero orbit here because it's just a template
        .build();
    // Now we can build the trajectory from the BSP file.
    // We'll arbitrarily set the tracking arc to 24 hours with a five second time step.
    let traj_as_flown = Traj::from_bsp(
        lro_frame,
        MOON_J2000,
        &almanac,
        sc_template,
        5.seconds(),
        Some(Epoch::from_str("2024-01-01 01:00:00 UTC")?),
        Some(Epoch::from_str("2024-01-02 01:00:00 UTC")?),
        None,
        Some("LRO".to_string()),
    )?;

    println!("{traj_as_flown}");

    // ====================== //
    // === MODEL MATCHING === //
    // ====================== //

    // Set up the spacecraft dynamics.

    // Specify that the orbital dynamics must account for the graviational pull of the Earth and the Sun.
    // The gravity of the Moon will also be accounted for since the spaceraft in a lunar orbit.
    let mut orbital_dyn = OrbitalDynamics::point_masses(vec![EARTH, SUN, JUPITER_BARYCENTER]);

    // We want to include the spherical harmonics, so let's download the gravitational data from the Nyx Cloud.
    // We're using the GRAIL JGGRX model.
    let mut jggrx_meta = MetaFile {
        uri: "http://public-data.nyxspace.com/nyx/models/Luna_jggrx_1500e_sha.tab.gz".to_string(),
        crc32: Some(0x6bcacda8), // Specifying the CRC32 avoids redownloading it if it's cached.
    };
    // And let's download it if we don't have it yet.
    jggrx_meta.process(true)?;

    // Build the spherical harmonics.
    // The harmonics must be computed in the body fixed frame.
    // We're using the long term prediction of the Moon principal axes frame.
    let moon_pa_frame = MOON_PA_FRAME.with_orient(31008);
    let sph_harmonics = GravityField::new(GravityFieldData::from_shadr(
        &jggrx_meta.uri,
        81,
        81,
        almanac.frame_info(moon_pa_frame)?,
    )?);

    // Include the spherical harmonics into the orbital dynamics.
    orbital_dyn.accel_models.push(sph_harmonics);

    // We define the solar radiation pressure, using the default solar flux and accounting only
    // for the eclipsing caused by the Earth and Moon.
    // Note that by default, enabling the SolarPressure model will also enable the estimation of the coefficient of reflectivity.
    let srp_dyn = SolarPressure::new(vec![EARTH_J2000, MOON_J2000], &almanac)?;

    // Finalize setting up the dynamics, specifying the force models (orbital_dyn) separately from the
    // acceleration models (SRP in this case). Use `from_models` to specify multiple accel models.
    let dynamics = SpacecraftDynamics::from_model(orbital_dyn, srp_dyn);

    println!("{dynamics}");

    // Now we can build the propagator.
    let setup = Propagator::default_dp78(dynamics.clone());

    // For reference, let's build the trajectory with Nyx's models from that LRO state.
    let (sim_final, traj_as_sim) = setup
        .with(*traj_as_flown.first(), almanac.clone())
        .until_epoch_with_traj(traj_as_flown.last().epoch())?;

    println!("SIM INIT:  {:x}", traj_as_flown.first());
    println!("SIM FINAL: {sim_final:x}");
    // Compute RIC difference between SIM and LRO ephem
    let sim_lro_delta = sim_final
        .orbit
        .ric_difference(&traj_as_flown.last().orbit)?;
    println!("{traj_as_sim}");
    println!(
        "SIM v LRO - RIC Position (m): {:.3}",
        sim_lro_delta.radius_km * 1e3
    );
    println!(
        "SIM v LRO - RIC Velocity (m/s): {:.3}",
        sim_lro_delta.velocity_km_s * 1e3
    );

    traj_as_sim.ric_diff_to_parquet(
        &traj_as_flown,
        output_folder.join("./04_lro_sim_truth_error.parquet"),
        ExportCfg::default(),
    )?;

    // ==================== //
    // === OD SIMULATOR === //
    // ==================== //

    // After quite some time trying to exactly match the model, we still end up with an oscillatory difference on the order of 150 meters between the propagated state
    // and the truth LRO state.

    // Therefore, we will actually run an estimation from a dispersed LRO state.
    // The sc_seed is the true LRO state from the BSP.
    let sc_seed = *traj_as_flown.first();

    // Load the Deep Space Network ground stations.
    // Nyx allows you to build these at runtime but it's pretty static so we can just load them from YAML.
    let ground_station_file: PathBuf = [
        env!("CARGO_MANIFEST_DIR"),
        "examples",
        "04_lro_od",
        "dsn-network.yaml",
    ]
    .iter()
    .collect();

    let devices = GroundStation::load_named(ground_station_file)?;

    let proc_devices = devices.clone();

    // Typical OD software requires that you specify your own tracking schedule or you'll have overlapping measurements.
    // Nyx can build a tracking schedule for you based on the first station with access.
    let trkconfg_yaml: PathBuf = [
        env!("CARGO_MANIFEST_DIR"),
        "examples",
        "04_lro_od",
        "tracking-cfg.yaml",
    ]
    .iter()
    .collect();

    let configs: BTreeMap<String, TrkConfig> = TrkConfig::load_named(trkconfg_yaml)?;

    // Build the tracking arc simulation to generate a "standard measurement".
    let mut trk = TrackingArcSim::<Spacecraft, GroundStation>::with_seed(
        devices.clone(),
        traj_as_flown.clone(),
        configs,
        123, // Set a seed for reproducibility
    )?;

    trk.build_schedule(&almanac)?;
    let arc = trk.generate_measurements(&almanac)?;
    // Save the simulated tracking data
    arc.to_parquet_simple(output_folder.join("04_lro_simulated_tracking.parquet"))?;

    // We'll note that in our case, we have continuous coverage of LRO when the vehicle is not behind the Moon.
    println!("{arc}");

    // Now that we have simulated measurements, we'll run the orbit determination.

    // ===================== //
    // === OD ESTIMATION === //
    // ===================== //

    let sc = SpacecraftUncertainty::builder()
        .nominal(sc_seed)
        .frame(LocalFrame::RIC)
        .x_km(0.5)
        .y_km(0.5)
        .z_km(0.5)
        .vx_km_s(5e-3)
        .vy_km_s(5e-3)
        .vz_km_s(5e-3)
        .build();

    // Build the filter initial estimate, which we will reuse in the filter.
    let mut initial_estimate = sc.to_estimate()?;
    initial_estimate.covar *= 1.5;

    println!("== FILTER STATE ==\n{sc_seed:x}\n{initial_estimate}");

    // Build the SNC in the Moon J2000 frame, specified as a velocity noise over time.
    let process_noise = ProcessNoise3D::from_velocity_km_s(
        &[5e-13, 5e-13, 5e-13],
        1 * Unit::Hour,
        10 * Unit::Minute,
        None,
    );

    println!("{process_noise}");

    // We'll set up the OD process to reject measurements whose residuals are move than 3 sigmas away from what we expect.
    let odp = SpacecraftKalmanOD::new(
        setup,
        KalmanVariant::ReferenceUpdate,
        Some(SigmaRejection::default()),
        proc_devices,
        almanac.clone(),
    )
    .with_process_noise(process_noise);

    let od_sol = odp.process_arc(initial_estimate, &arc)?;

    let final_est = od_sol.estimates.last().unwrap();

    println!("{final_est}");

    let ric_err = traj_as_flown
        .at(final_est.epoch())?
        .orbit
        .ric_difference(&final_est.orbital_state())?;
    println!("== RIC at end ==");
    println!("RIC Position (m): {:.3}", ric_err.radius_km * 1e3);
    println!("RIC Velocity (m/s): {:.3}", ric_err.velocity_km_s * 1e3);

    println!(
        "Num residuals rejected: #{}",
        od_sol.rejected_residuals().len()
    );
    println!(
        "Percentage within +/-3: {}",
        od_sol.residual_ratio_within_threshold(3.0).unwrap()
    );
    println!("Ratios normal? {}", od_sol.is_normal(None).unwrap());
    od_sol.nis_consistency(None)?.log();

    od_sol.to_parquet(
        output_folder.join("04_lro_od_results.parquet"),
        ExportCfg::default(),
    )?;

    // Create the ephemeris
    let ephem = od_sol.to_ephemeris("LRO rebuilt".to_string());
    let ephem_start = ephem.start_epoch().unwrap();
    let ephem_end = ephem.end_epoch().unwrap();
    // Check that the covariance is PSD throughout the ephemeris by interpolating it.
    for epoch in TimeSeries::inclusive(ephem_start, ephem_end, Unit::Minute * 5) {
        ephem
            .covar_at(
                epoch,
                anise::ephemerides::ephemeris::LocalFrame::RIC,
                &almanac,
            )
            .unwrap_or_else(|e| panic!("covar not PSD at {epoch}: {e}"));
    }
    // Export as BSP!
    ephem
        .write_spice_bsp(
            -85,
            output_folder.join("04_lro_rebuilt.bsp").to_str().unwrap(),
            None,
        )
        .expect("could not built BSP");
    let new_almanac = Almanac::default()
        .load(output_folder.join("04_lro_rebuilt.bsp").to_str().unwrap())
        .unwrap();
    new_almanac.describe(None, None, None, None, None, None, None, None);
    let (spk_start, spk_end) = new_almanac.spk_domain(-85).unwrap();

    assert!((ephem_start - spk_start).abs() < Unit::Microsecond * 1);
    assert!((ephem_end - spk_end).abs() < Unit::Microsecond * 1);

    // In our case, we have the truth trajectory from NASA.
    // So we can compute the RIC state difference between the real LRO ephem and what we've just estimated.
    // Export the OD trajectory first.
    let od_trajectory = od_sol.to_traj()?;
    // Build the RIC difference.
    od_trajectory.ric_diff_to_parquet(
        &traj_as_flown,
        output_folder.join("04_lro_od_truth_error.parquet"),
        ExportCfg::default(),
    )?;

    Ok(())
}

pub const fn from_orient_ssb(orientation_id: i32) -> Frame

pub const fn new_inertial(ephemeris_id: i32, orientation_id: i32) -> Frame

pub fn from_name(center: &str, ref_frame: &str) -> Result<Frame, AlmanacError>

Attempts to create a new frame from its center and reference frame name. This function is compatible with the CCSDS OEM names.

pub fn with_ellipsoid(self, shape: Ellipsoid) -> Frame

Define Ellipsoid shape and return a new Frame

pub fn stripped(self) -> Frame

Returns a copy of this frame with the graviational parameter and the shape information from this frame. Use this to prevent astrodynamical computations.

:rtype: None

impl Frame

pub fn py_new( ephemeris_id: i32, orientation_id: i32, mu_km3_s2: Option<f64>, shape: Option<Ellipsoid>, ) -> Frame

Initializes a new Frame provided its ephemeris and orientation identifiers, and optionally its gravitational parameter (in km^3/s^2) and optionally its shape (cf. [Ellipsoid]).

pub fn from_asn1(_cls: &Bound<'_, PyType>, data: &[u8]) -> Result<Frame, PyErr>

Decodes an ASN.1 DER encoded byte array into a Frame.

:type data: bytes :rtype: Frame

pub fn to_asn1<'py>( &self, py: Python<'py>, ) -> Result<Bound<'py, PyBytes>, PyErr>

Encodes this Frame into an ASN.1 DER encoded byte array.

:rtype: bytes

impl Frame

pub const fn with_ephem(&self, new_ephem_id: i32) -> Frame

Returns a copy of this Frame whose ephemeris ID is set to the provided ID

:type new_ephem_id: int :rtype: Frame

pub const fn with_orient(&self, new_orient_id: i32) -> Frame

Returns a copy of this Frame whose orientation ID is set to the provided ID

:type new_orient_id: int :rtype: Frame

Examples found in repository

nyx-core/examples/06_lunar_orbit_determination/main.rs (line 104)

fn main() -> Result<(), Box<dyn Error>> {
    pel::init();

    // ====================== //
    // === ALMANAC SET UP === //
    // ====================== //

    // Dynamics models require planetary constants and ephemerides to be defined.
    // Let's start by grabbing those by using ANISE's MetaAlmanac.

    let data_folder: PathBuf = [
        env!("CARGO_MANIFEST_DIR"),
        "examples",
        "06_lunar_orbit_determination",
    ]
    .iter()
    .collect();

    let meta = data_folder.join("metaalmanac.dhall");

    // Load this ephem in the general Almanac we're using for this analysis.
    let almanac = MetaAlmanac::new(meta.to_string_lossy().as_ref())
        .map_err(Box::new)?
        .process(true)
        .map_err(Box::new)?;

    // Lock the almanac (an Arc is a read only structure).
    let almanac = Arc::new(almanac);

    // Build a nominal trajectory
    // TODO: Switch this to a sequence once the OD over a spacecraft sequence is implemented.

    let epoch = Epoch::from_gregorian_utc_at_noon(2024, 2, 29);
    let moon_j2000 = almanac.frame_info(MOON_J2000)?;

    // To build the trajectory we need to provide a spacecraft template.
    let orbiter = Spacecraft::builder()
        .mass(Mass::from_dry_and_prop_masses(1018.0, 900.0))
        .srp(SRPData {
            area_m2: 3.9 * 2.7,
            coeff_reflectivity: 0.96,
        })
        .orbit(Orbit::try_keplerian_altitude(
            150.0, 0.00212, 33.6, 45.0, 45.0, 0.0, epoch, moon_j2000,
        )?) // Setting a zero orbit here because it's just a template
        .build();

    // ========================== //
    // === BUILD NOMINAL TRAJ === //
    // ========================== //

    // Set up the spacecraft dynamics.

    // Specify that the orbital dynamics must account for the graviational pull of the Earth and the Sun.
    // The gravity of the Moon will also be accounted for since the spaceraft in a lunar orbit.
    let mut orbital_dyn = OrbitalDynamics::point_masses(vec![EARTH, SUN, JUPITER_BARYCENTER]);

    // We want to include the spherical harmonics, so let's download the gravitational data from the Nyx Cloud.
    // We're using the GRAIL JGGRX model.
    let mut jggrx_meta = MetaFile {
        uri: "http://public-data.nyxspace.com/nyx/models/Luna_jggrx_1500e_sha.tab.gz".to_string(),
        crc32: Some(0x6bcacda8), // Specifying the CRC32 avoids redownloading it if it's cached.
    };
    // And let's download it if we don't have it yet.
    jggrx_meta.process(true)?;

    // Build the spherical harmonics.
    // The harmonics must be computed in the body fixed frame.
    // We're using the long term prediction of the Moon principal axes frame.
    let moon_pa_frame = MOON_PA_FRAME.with_orient(31008);
    let sph_harmonics = GravityField::new(GravityFieldData::from_shadr(
        &jggrx_meta.uri,
        80,
        80,
        almanac.frame_info(moon_pa_frame)?,
    )?);

    // Include the spherical harmonics into the orbital dynamics.
    orbital_dyn.accel_models.push(sph_harmonics);

    // We define the solar radiation pressure, using the default solar flux and accounting only
    // for the eclipsing caused by the Earth and Moon.
    // Note that by default, enabling the SolarPressure model will also enable the estimation of the coefficient of reflectivity.
    let srp_dyn = SolarPressure::new(vec![MOON_J2000], &almanac)?;

    // Finalize setting up the dynamics, specifying the force models (orbital_dyn) separately from the
    // acceleration models (SRP in this case). Use `from_models` to specify multiple accel models.
    let dynamics = SpacecraftDynamics::from_model(orbital_dyn, srp_dyn);

    println!("{dynamics}");

    let setup = Propagator::rk89(dynamics.clone(), IntegratorOptions::default());

    let truth_traj = setup
        .with(orbiter, almanac.clone())
        .for_duration_with_traj(Unit::Day * 2)?
        .1;

    // ==================== //
    // === OD SIMULATOR === //
    // ==================== //

    // Load the Deep Space Network ground stations.
    // Nyx allows you to build these at runtime but it's pretty static so we can just load them from YAML.
    let ground_station_file = data_folder.join("dsn-network.yaml");
    let devices = GroundStation::load_named(ground_station_file)?;

    let proc_devices = devices.clone();

    // Typical OD software requires that you specify your own tracking schedule or you'll have overlapping measurements.
    // Nyx can build a tracking schedule for you based on the first station with access.
    let configs: BTreeMap<String, TrkConfig> =
        TrkConfig::load_named(data_folder.join("tracking-cfg.yaml"))?;

    // Build the tracking arc simulation to generate a "standard measurement".
    let mut trk = TrackingArcSim::<Spacecraft, GroundStation>::with_seed(
        devices.clone(),
        truth_traj.clone(),
        configs,
        123, // Set a seed for reproducibility
    )?;

    trk.build_schedule(&almanac)?;
    let arc = trk.generate_measurements(&almanac)?;
    // Save the simulated tracking data
    arc.to_parquet_simple("./data/04_output/06_lunar_simulated_tracking.parquet")?;

    // We'll note that in our case, we have continuous coverage of LRO when the vehicle is not behind the Moon.
    println!("{arc}");

    // Now that we have simulated measurements, we'll run the orbit determination.

    // ===================== //
    // === OD ESTIMATION === //
    // ===================== //

    let sc = SpacecraftUncertainty::builder()
        .nominal(orbiter)
        .frame(LocalFrame::RIC)
        .x_km(0.5)
        .y_km(0.5)
        .z_km(0.5)
        .vx_km_s(5e-3)
        .vy_km_s(5e-3)
        .vz_km_s(5e-3)
        .build();

    // Build the filter initial estimate, which we will reuse in the filter.
    let initial_estimate = sc.to_estimate()?;

    println!("== FILTER STATE ==\n{orbiter:x}\n{initial_estimate}");

    // Build the SNC in the Moon J2000 frame, specified as a velocity noise over time.
    let process_noise = ProcessNoise3D::from_velocity_km_s(
        &[1e-14, 1e-14, 1e-14],
        1 * Unit::Hour,
        10 * Unit::Minute,
        None,
    );

    println!("{process_noise}");

    // We'll set up the OD process to reject measurements whose residuals are move than 3 sigmas away from what we expect.
    let odp = SpacecraftKalmanScalarOD::new(
        setup,
        KalmanVariant::ReferenceUpdate,
        Some(SigmaRejection::default()),
        proc_devices,
        almanac.clone(),
    )
    .with_process_noise(process_noise);

    let od_sol = odp.process_arc(initial_estimate, &arc)?;

    let final_est = od_sol.estimates.last().unwrap();

    println!("{final_est}");

    let ric_err = truth_traj
        .at(final_est.epoch())?
        .orbit
        .ric_difference(&final_est.orbital_state())?;
    println!("== RIC at end ==");
    println!("RIC Position (m): {:.3}", ric_err.radius_km * 1e3);
    println!("RIC Velocity (m/s): {:.3}", ric_err.velocity_km_s * 1e3);

    println!(
        "Num residuals rejected: #{}",
        od_sol.rejected_residuals().len()
    );
    println!(
        "Percentage within +/-3: {}",
        od_sol.residual_ratio_within_threshold(3.0).unwrap()
    );
    println!("Whitened residuals normal? {}", od_sol.is_normal(None)?);
    println!("NIS consistency: {}", od_sol.nis_consistency(None)?);

    od_sol.to_parquet(
        "./data/04_output/06_lunar_od_results.parquet",
        ExportCfg::default(),
    )?;

    let od_trajectory = od_sol.to_traj()?;
    // Build the RIC difference.
    od_trajectory.ric_diff_to_parquet(
        &truth_traj,
        "./data/04_output/06_lunar_od_truth_error.parquet",
        ExportCfg::default(),
    )?;

    Ok(())
}

nyx-core/examples/04_lro_od/main.rs (line 116)

fn main() -> Result<(), Box<dyn Error>> {
    pel::init();

    // ====================== //
    // === ALMANAC SET UP === //
    // ====================== //

    // Dynamics models require planetary constants and ephemerides to be defined.
    // Let's start by grabbing those by using ANISE's MetaAlmanac.

    let output_folder: PathBuf = [env!("CARGO_MANIFEST_DIR"), "../data", "04_output"]
        .iter()
        .collect();

    let data_folder: PathBuf = [env!("CARGO_MANIFEST_DIR"), "examples", "04_lro_od"]
        .iter()
        .collect();

    let meta = data_folder.join("lro-dynamics.dhall");

    // Load this ephem in the general Almanac we're using for this analysis.
    let almanac = Arc::new(
        MetaAlmanac::new(meta.to_string_lossy().as_ref())
            .map_err(Box::new)?
            .process(true)
            .map_err(Box::new)?,
    );

    // Orbit determination requires a Trajectory structure, which can be saved as parquet file.
    // In our case, the trajectory comes from the BSP file, so we need to build a Trajectory from the almanac directly.
    // To query the Almanac, we need to build the LRO frame in the J2000 orientation in our case.
    // Inspecting the LRO BSP in the ANISE GUI shows us that NASA has assigned ID -85 to LRO.
    let lro_frame = Frame::from_ephem_j2000(-85);

    // To build the trajectory we need to provide a spacecraft template.
    let sc_template = Spacecraft::builder()
        .mass(Mass::from_dry_and_prop_masses(1018.0, 900.0)) // Launch masses
        .srp(SRPData {
            // SRP configuration is arbitrary, but we will be estimating it anyway.
            area_m2: 3.9 * 2.7,
            coeff_reflectivity: 0.96,
        })
        .orbit(Orbit::zero(MOON_J2000)) // Setting a zero orbit here because it's just a template
        .build();
    // Now we can build the trajectory from the BSP file.
    // We'll arbitrarily set the tracking arc to 24 hours with a five second time step.
    let traj_as_flown = Traj::from_bsp(
        lro_frame,
        MOON_J2000,
        &almanac,
        sc_template,
        5.seconds(),
        Some(Epoch::from_str("2024-01-01 01:00:00 UTC")?),
        Some(Epoch::from_str("2024-01-02 01:00:00 UTC")?),
        None,
        Some("LRO".to_string()),
    )?;

    println!("{traj_as_flown}");

    // ====================== //
    // === MODEL MATCHING === //
    // ====================== //

    // Set up the spacecraft dynamics.

    // Specify that the orbital dynamics must account for the graviational pull of the Earth and the Sun.
    // The gravity of the Moon will also be accounted for since the spaceraft in a lunar orbit.
    let mut orbital_dyn = OrbitalDynamics::point_masses(vec![EARTH, SUN, JUPITER_BARYCENTER]);

    // We want to include the spherical harmonics, so let's download the gravitational data from the Nyx Cloud.
    // We're using the GRAIL JGGRX model.
    let mut jggrx_meta = MetaFile {
        uri: "http://public-data.nyxspace.com/nyx/models/Luna_jggrx_1500e_sha.tab.gz".to_string(),
        crc32: Some(0x6bcacda8), // Specifying the CRC32 avoids redownloading it if it's cached.
    };
    // And let's download it if we don't have it yet.
    jggrx_meta.process(true)?;

    // Build the spherical harmonics.
    // The harmonics must be computed in the body fixed frame.
    // We're using the long term prediction of the Moon principal axes frame.
    let moon_pa_frame = MOON_PA_FRAME.with_orient(31008);
    let sph_harmonics = GravityField::new(GravityFieldData::from_shadr(
        &jggrx_meta.uri,
        81,
        81,
        almanac.frame_info(moon_pa_frame)?,
    )?);

    // Include the spherical harmonics into the orbital dynamics.
    orbital_dyn.accel_models.push(sph_harmonics);

    // We define the solar radiation pressure, using the default solar flux and accounting only
    // for the eclipsing caused by the Earth and Moon.
    // Note that by default, enabling the SolarPressure model will also enable the estimation of the coefficient of reflectivity.
    let srp_dyn = SolarPressure::new(vec![EARTH_J2000, MOON_J2000], &almanac)?;

    // Finalize setting up the dynamics, specifying the force models (orbital_dyn) separately from the
    // acceleration models (SRP in this case). Use `from_models` to specify multiple accel models.
    let dynamics = SpacecraftDynamics::from_model(orbital_dyn, srp_dyn);

    println!("{dynamics}");

    // Now we can build the propagator.
    let setup = Propagator::default_dp78(dynamics.clone());

    // For reference, let's build the trajectory with Nyx's models from that LRO state.
    let (sim_final, traj_as_sim) = setup
        .with(*traj_as_flown.first(), almanac.clone())
        .until_epoch_with_traj(traj_as_flown.last().epoch())?;

    println!("SIM INIT:  {:x}", traj_as_flown.first());
    println!("SIM FINAL: {sim_final:x}");
    // Compute RIC difference between SIM and LRO ephem
    let sim_lro_delta = sim_final
        .orbit
        .ric_difference(&traj_as_flown.last().orbit)?;
    println!("{traj_as_sim}");
    println!(
        "SIM v LRO - RIC Position (m): {:.3}",
        sim_lro_delta.radius_km * 1e3
    );
    println!(
        "SIM v LRO - RIC Velocity (m/s): {:.3}",
        sim_lro_delta.velocity_km_s * 1e3
    );

    traj_as_sim.ric_diff_to_parquet(
        &traj_as_flown,
        output_folder.join("./04_lro_sim_truth_error.parquet"),
        ExportCfg::default(),
    )?;

    // ==================== //
    // === OD SIMULATOR === //
    // ==================== //

    // After quite some time trying to exactly match the model, we still end up with an oscillatory difference on the order of 150 meters between the propagated state
    // and the truth LRO state.

    // Therefore, we will actually run an estimation from a dispersed LRO state.
    // The sc_seed is the true LRO state from the BSP.
    let sc_seed = *traj_as_flown.first();

    // Load the Deep Space Network ground stations.
    // Nyx allows you to build these at runtime but it's pretty static so we can just load them from YAML.
    let ground_station_file: PathBuf = [
        env!("CARGO_MANIFEST_DIR"),
        "examples",
        "04_lro_od",
        "dsn-network.yaml",
    ]
    .iter()
    .collect();

    let devices = GroundStation::load_named(ground_station_file)?;

    let proc_devices = devices.clone();

    // Typical OD software requires that you specify your own tracking schedule or you'll have overlapping measurements.
    // Nyx can build a tracking schedule for you based on the first station with access.
    let trkconfg_yaml: PathBuf = [
        env!("CARGO_MANIFEST_DIR"),
        "examples",
        "04_lro_od",
        "tracking-cfg.yaml",
    ]
    .iter()
    .collect();

    let configs: BTreeMap<String, TrkConfig> = TrkConfig::load_named(trkconfg_yaml)?;

    // Build the tracking arc simulation to generate a "standard measurement".
    let mut trk = TrackingArcSim::<Spacecraft, GroundStation>::with_seed(
        devices.clone(),
        traj_as_flown.clone(),
        configs,
        123, // Set a seed for reproducibility
    )?;

    trk.build_schedule(&almanac)?;
    let arc = trk.generate_measurements(&almanac)?;
    // Save the simulated tracking data
    arc.to_parquet_simple(output_folder.join("04_lro_simulated_tracking.parquet"))?;

    // We'll note that in our case, we have continuous coverage of LRO when the vehicle is not behind the Moon.
    println!("{arc}");

    // Now that we have simulated measurements, we'll run the orbit determination.

    // ===================== //
    // === OD ESTIMATION === //
    // ===================== //

    let sc = SpacecraftUncertainty::builder()
        .nominal(sc_seed)
        .frame(LocalFrame::RIC)
        .x_km(0.5)
        .y_km(0.5)
        .z_km(0.5)
        .vx_km_s(5e-3)
        .vy_km_s(5e-3)
        .vz_km_s(5e-3)
        .build();

    // Build the filter initial estimate, which we will reuse in the filter.
    let mut initial_estimate = sc.to_estimate()?;
    initial_estimate.covar *= 1.5;

    println!("== FILTER STATE ==\n{sc_seed:x}\n{initial_estimate}");

    // Build the SNC in the Moon J2000 frame, specified as a velocity noise over time.
    let process_noise = ProcessNoise3D::from_velocity_km_s(
        &[5e-13, 5e-13, 5e-13],
        1 * Unit::Hour,
        10 * Unit::Minute,
        None,
    );

    println!("{process_noise}");

    // We'll set up the OD process to reject measurements whose residuals are move than 3 sigmas away from what we expect.
    let odp = SpacecraftKalmanOD::new(
        setup,
        KalmanVariant::ReferenceUpdate,
        Some(SigmaRejection::default()),
        proc_devices,
        almanac.clone(),
    )
    .with_process_noise(process_noise);

    let od_sol = odp.process_arc(initial_estimate, &arc)?;

    let final_est = od_sol.estimates.last().unwrap();

    println!("{final_est}");

    let ric_err = traj_as_flown
        .at(final_est.epoch())?
        .orbit
        .ric_difference(&final_est.orbital_state())?;
    println!("== RIC at end ==");
    println!("RIC Position (m): {:.3}", ric_err.radius_km * 1e3);
    println!("RIC Velocity (m/s): {:.3}", ric_err.velocity_km_s * 1e3);

    println!(
        "Num residuals rejected: #{}",
        od_sol.rejected_residuals().len()
    );
    println!(
        "Percentage within +/-3: {}",
        od_sol.residual_ratio_within_threshold(3.0).unwrap()
    );
    println!("Ratios normal? {}", od_sol.is_normal(None).unwrap());
    od_sol.nis_consistency(None)?.log();

    od_sol.to_parquet(
        output_folder.join("04_lro_od_results.parquet"),
        ExportCfg::default(),
    )?;

    // Create the ephemeris
    let ephem = od_sol.to_ephemeris("LRO rebuilt".to_string());
    let ephem_start = ephem.start_epoch().unwrap();
    let ephem_end = ephem.end_epoch().unwrap();
    // Check that the covariance is PSD throughout the ephemeris by interpolating it.
    for epoch in TimeSeries::inclusive(ephem_start, ephem_end, Unit::Minute * 5) {
        ephem
            .covar_at(
                epoch,
                anise::ephemerides::ephemeris::LocalFrame::RIC,
                &almanac,
            )
            .unwrap_or_else(|e| panic!("covar not PSD at {epoch}: {e}"));
    }
    // Export as BSP!
    ephem
        .write_spice_bsp(
            -85,
            output_folder.join("04_lro_rebuilt.bsp").to_str().unwrap(),
            None,
        )
        .expect("could not built BSP");
    let new_almanac = Almanac::default()
        .load(output_folder.join("04_lro_rebuilt.bsp").to_str().unwrap())
        .unwrap();
    new_almanac.describe(None, None, None, None, None, None, None, None);
    let (spk_start, spk_end) = new_almanac.spk_domain(-85).unwrap();

    assert!((ephem_start - spk_start).abs() < Unit::Microsecond * 1);
    assert!((ephem_end - spk_end).abs() < Unit::Microsecond * 1);

    // In our case, we have the truth trajectory from NASA.
    // So we can compute the RIC state difference between the real LRO ephem and what we've just estimated.
    // Export the OD trajectory first.
    let od_trajectory = od_sol.to_traj()?;
    // Build the RIC difference.
    od_trajectory.ric_diff_to_parquet(
        &traj_as_flown,
        output_folder.join("04_lro_od_truth_error.parquet"),
        ExportCfg::default(),
    )?;

    Ok(())
}

pub const fn is_celestial(&self) -> bool

Returns whether this is a celestial frame

:rtype: bool

pub const fn is_geodetic(&self) -> bool

Returns whether this is a geodetic frame

:rtype: bool

pub const fn ephem_origin_id_match(&self, other_id: i32) -> bool

Returns true if the ephemeris origin is equal to the provided ID

:type other_id: int :rtype: bool

pub const fn orient_origin_id_match(&self, other_id: i32) -> bool

Returns true if the orientation origin is equal to the provided ID

:type other_id: int :rtype: bool

pub const fn ephem_origin_match(&self, other: Frame) -> bool

Returns true if the ephemeris origin is equal to the provided frame

:type other: Frame :rtype: bool

pub const fn orient_origin_match(&self, other: Frame) -> bool

Returns true if the orientation origin is equal to the provided frame

:type other: Frame :rtype: bool

pub fn strip(&mut self)

Removes the graviational parameter and the shape information from this frame. Use this to prevent astrodynamical computations.

:rtype: None

pub fn mu_km3_s2(&self) -> Result<f64, PhysicsError>

Returns the gravitational parameters of this frame, if defined

:rtype: float

pub fn with_mu_km3_s2(&self, mu_km3_s2: f64) -> Frame

Returns a copy of this frame with the graviational parameter set to the new value.

:type mu_km3_s2: float :rtype: Frame

pub fn mean_equatorial_radius_km(&self) -> Result<f64, PhysicsError>

Returns the mean equatorial radius in km, if defined

:rtype: float

pub fn semi_major_radius_km(&self) -> Result<f64, PhysicsError>

Returns the semi major radius of the tri-axial ellipoid shape of this frame, if defined

:rtype: float

pub fn flattening(&self) -> Result<f64, PhysicsError>

Returns the flattening ratio (unitless)

:rtype: float

pub fn polar_radius_km(&self) -> Result<f64, PhysicsError>

Returns the polar radius in km, if defined

:rtype: float

pub fn is_dynamic(&self) -> bool

Returns true if this is a dynamic frame, e.g. Mean/True of Date/Epoch

:rtype: bool

Trait Implementations

impl Clone for Frame

fn clone(&self) -> Frame

Returns a duplicate of the value.

fn clone_from(&mut self, source: &Self)

Performs copy-assignment from source.

impl Copy for Frame

impl Debug for Frame

fn fmt(&self, f: &mut Formatter<'_>) -> Result<(), Error>

Formats the value using the given formatter.

impl<'a> Decode<'a> for Frame

fn decode<R>(decoder: &mut R) -> Result<Frame, Error>

where R: Reader<'a>,

Attempt to decode this message using the provided decoder.

fn from_der(bytes: &'a [u8]) -> Result<Self, Error>

Parse Self from the provided DER-encoded byte slice.

impl DerefToPyAny for Frame

impl<'de> Deserialize<'de> for Frame

fn deserialize<__D>( __deserializer: __D, ) -> Result<Frame, <__D as Deserializer<'de>>::Error>

where __D: Deserializer<'de>,

Deserialize this value from the given Serde deserializer.

impl Display for Frame

fn fmt(&self, f: &mut Formatter<'_>) -> Result<(), Error>

Formats the value using the given formatter.

impl Encode for Frame

fn encoded_len(&self) -> Result<Length, Error>

Compute the length of this value in bytes when encoded as ASN.1 DER.

fn encode(&self, encoder: &mut impl Writer) -> Result<(), Error>

Encode this value as ASN.1 DER using the provided [Writer].

fn encode_to_slice<'a>(&self, buf: &'a mut [u8]) -> Result<&'a [u8], Error>

Encode this value to the provided byte slice, returning a sub-slice containing the encoded message.

fn encode_to_vec(&self, buf: &mut Vec<u8>) -> Result<Length, Error>

Encode this message as ASN.1 DER, appending it to the provided byte vector.

fn to_der(&self) -> Result<Vec<u8>, Error>

Encode this type as DER, returning a byte vector.

impl From<&Frame> for FrameUid

fn from(frame: &Frame) -> FrameUid

Converts to this type from the input type.

impl From<&FrameUid> for Frame

fn from(uid: &FrameUid) -> Frame

Converts to this type from the input type.

impl From<Frame> for FrameUid

fn from(frame: Frame) -> FrameUid

Converts to this type from the input type.

impl From<FrameUid> for Frame

fn from(uid: FrameUid) -> Frame

Converts to this type from the input type.

impl<'a, 'py> FromPyObject<'a, 'py> for Frame

where Frame: Clone,

type Error = PyClassGuardError<'a, 'py>

The type returned in the event of a conversion error.

fn extract( obj: Borrowed<'a, 'py, PyAny>, ) -> Result<Frame, <Frame as FromPyObject<'a, 'py>>::Error>

Extracts Self from the bound smart pointer obj.

impl<'py> IntoPyObject<'py> for Frame

type Target = Frame

The Python output type

type Output = Bound<'py, <Frame as IntoPyObject<'py>>::Target>

The smart pointer type to use.

type Error = PyErr

The type returned in the event of a conversion error.

fn into_pyobject( self, py: Python<'py>, ) -> Result<<Frame as IntoPyObject<'py>>::Output, <Frame as IntoPyObject<'py>>::Error>

Performs the conversion.

impl LowerExp for Frame

fn fmt(&self, f: &mut Formatter<'_>) -> Result<(), Error>

Only prints the ephemeris name

impl LowerHex for Frame

fn fmt(&self, f: &mut Formatter<'_>) -> Result<(), Error>

Only prints the UID

impl Octal for Frame

fn fmt(&self, f: &mut Formatter<'_>) -> Result<(), Error>

Only prints the orientation name

impl PartialEq for Frame

fn eq(&self, other: &Frame) -> bool

Equality operator ==.

fn ne(&self, other: &Rhs) -> bool

Inequality operator !=.

impl PyClass for Frame

const NAME: &'static str = "Frame"

Name of the class.

type Frozen = False

Whether the pyclass is frozen.

impl PyTypeInfo for Frame

const NAME: &'static str = <Self as ::pyo3::PyClass>::NAME

👎Deprecated since 0.28.0:

prefer using ::type_object(py).name() to get the correct runtime value

Class name.

const MODULE: Option<&'static str> = <Self as ::pyo3::impl_::pyclass::PyClassImpl>::MODULE

👎Deprecated since 0.28.0:

prefer using ::type_object(py).module() to get the correct runtime value

Module name, if any.

fn type_object_raw(py: Python<'_>) -> *mut PyTypeObject

Returns the PyTypeObject instance for this type.

fn type_object(py: Python<'_>) -> Bound<'_, PyType>

Returns the safe abstraction over the type object.

fn is_type_of(object: &Bound<'_, PyAny>) -> bool

Checks if object is an instance of this type or a subclass of this type.

fn is_exact_type_of(object: &Bound<'_, PyAny>) -> bool

Checks if object is an instance of this type.

impl Serialize for Frame

fn serialize<__S>( &self, __serializer: __S, ) -> Result<<__S as Serializer>::Ok, <__S as Serializer>::Error>

where __S: Serializer,

Serialize this value into the given Serde serializer.

impl StaticType for Frame

Available on crate feature metaload only.

fn static_type() -> SimpleType

Return the Dhall type that represents this type.

impl StructuralPartialEq for Frame