Trait TimeUnits
pub trait TimeUnits: Copy + Mul<Unit, Output = Duration> {
// Provided methods
fn centuries(self) -> Duration { ... }
fn weeks(self) -> Duration { ... }
fn days(self) -> Duration { ... }
fn hours(self) -> Duration { ... }
fn minutes(self) -> Duration { ... }
fn seconds(self) -> Duration { ... }
fn milliseconds(self) -> Duration { ... }
fn microseconds(self) -> Duration { ... }
fn nanoseconds(self) -> Duration { ... }
}
Expand description
A trait to automatically convert some primitives to a duration
#[cfg(feature = "std")]
{
use hifitime::prelude::*;
use std::str::FromStr;
assert_eq!(Duration::from_str("1 d").unwrap(), 1.days());
assert_eq!(Duration::from_str("10.598 days").unwrap(), 10.598.days());
assert_eq!(Duration::from_str("10.598 min").unwrap(), 10.598.minutes());
assert_eq!(Duration::from_str("10.598 us").unwrap(), 10.598.microseconds());
assert_eq!(Duration::from_str("10.598 seconds").unwrap(), 10.598.seconds());
assert_eq!(Duration::from_str("10.598 nanosecond").unwrap(), 10.598.nanoseconds());
}
Provided Methods§
fn centuries(self) -> Duration
fn weeks(self) -> Duration
fn days(self) -> Duration
fn hours(self) -> Duration
fn minutes(self) -> Duration
fn minutes(self) -> Duration
Examples found in repository?
examples/02_jwst_covar_monte_carlo/main.rs (line 122)
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fn main() -> Result<(), Box<dyn Error>> {
pel::init();
// Dynamics models require planetary constants and ephemerides to be defined.
// Let's start by grabbing those by using ANISE's latest MetaAlmanac.
// For details, refer to https://github.com/nyx-space/anise/blob/master/data/latest.dhall.
// Download the regularly update of the James Webb Space Telescope reconstucted (or definitive) ephemeris.
// Refer to https://naif.jpl.nasa.gov/pub/naif/JWST/kernels/spk/aareadme.txt for details.
let mut latest_jwst_ephem = MetaFile {
uri: "https://naif.jpl.nasa.gov/pub/naif/JWST/kernels/spk/jwst_rec.bsp".to_string(),
crc32: None,
};
latest_jwst_ephem.process(true)?;
// Load this ephem in the general Almanac we're using for this analysis.
let almanac = Arc::new(
MetaAlmanac::latest()
.map_err(Box::new)?
.load_from_metafile(latest_jwst_ephem, true)?,
);
// By loading this ephemeris file in the ANISE GUI or ANISE CLI, we can find the NAIF ID of the JWST
// in the BSP. We need this ID in order to query the ephemeris.
const JWST_NAIF_ID: i32 = -170;
// Let's build a frame in the J2000 orientation centered on the JWST.
const JWST_J2000: Frame = Frame::from_ephem_j2000(JWST_NAIF_ID);
// Since the ephemeris file is updated regularly, we'll just grab the latest state in the ephem.
let (earliest_epoch, latest_epoch) = almanac.spk_domain(JWST_NAIF_ID)?;
println!("JWST defined from {earliest_epoch} to {latest_epoch}");
// Fetch the state, printing it in the Earth J2000 frame.
let jwst_orbit = almanac.transform(JWST_J2000, EARTH_J2000, latest_epoch, None)?;
println!("{jwst_orbit:x}");
// Build the spacecraft
// SRP area assumed to be the full sunshield and mass if 6200.0 kg, c.f. https://webb.nasa.gov/content/about/faqs/facts.html
// SRP Coefficient of reflectivity assumed to be that of Kapton, i.e. 2 - 0.44 = 1.56, table 1 from https://amostech.com/TechnicalPapers/2018/Poster/Bengtson.pdf
let jwst = Spacecraft::builder()
.orbit(jwst_orbit)
.srp(SrpConfig {
area_m2: 21.197 * 14.162,
cr: 1.56,
})
.dry_mass_kg(6200.0)
.build();
// Build up the spacecraft uncertainty builder.
// We can use the spacecraft uncertainty structure to build this up.
// We start by specifying the nominal state (as defined above), then the uncertainty in position and velocity
// in the RIC frame. We could also specify the Cr, Cd, and mass uncertainties, but these aren't accounted for until
// Nyx can also estimate the deviation of the spacecraft parameters.
let jwst_uncertainty = SpacecraftUncertainty::builder()
.nominal(jwst)
.frame(LocalFrame::RIC)
.x_km(0.5)
.y_km(0.3)
.z_km(1.5)
.vx_km_s(1e-4)
.vy_km_s(0.6e-3)
.vz_km_s(3e-3)
.build();
println!("{jwst_uncertainty}");
// Build the Kalman filter estimate.
// Note that we could have used the KfEstimate structure directly (as seen throughout the OD integration tests)
// but this approach requires quite a bit more boilerplate code.
let jwst_estimate = jwst_uncertainty.to_estimate()?;
// Set up the spacecraft dynamics.
// We'll use the point masses of the Earth, Sun, Jupiter (barycenter, because it's in the DE440), and the Moon.
// We'll also enable solar radiation pressure since the James Webb has a huge and highly reflective sun shield.
let orbital_dyn = OrbitalDynamics::point_masses(vec![MOON, SUN, JUPITER_BARYCENTER]);
let srp_dyn = SolarPressure::new(vec![EARTH_J2000, MOON_J2000], almanac.clone())?;
// Finalize setting up the dynamics.
let dynamics = SpacecraftDynamics::from_model(orbital_dyn, srp_dyn);
// Build the propagator set up to use for the whole analysis.
let setup = Propagator::default(dynamics);
// All of the analysis will use this duration.
let prediction_duration = 6.5 * Unit::Day;
// === Covariance mapping ===
// For the covariance mapping / prediction, we'll use the common orbit determination approach.
// This is done by setting up a spacecraft OD process, and predicting for the analysis duration.
let ckf = KF::no_snc(jwst_estimate);
// Build the propagation instance for the OD process.
let prop = setup.with(jwst.with_stm(), almanac.clone());
let mut odp = SpacecraftODProcess::ckf(prop, ckf, None, almanac.clone());
// Define the prediction step, i.e. how often we want to know the covariance.
let step = 1_i64.minutes();
// Finally, predict, and export the trajectory with covariance to a parquet file.
odp.predict_for(step, prediction_duration)?;
odp.to_parquet("./02_jwst_covar_map.parquet", ExportCfg::default())?;
// === Monte Carlo framework ===
// Nyx comes with a complete multi-threaded Monte Carlo frame. It's blazing fast.
let my_mc = MonteCarlo::new(
jwst, // Nominal state
jwst_estimate.to_random_variable()?,
"02_jwst".to_string(), // Scenario name
None, // No specific seed specified, so one will be drawn from the computer's entropy.
);
let num_runs = 5_000;
let rslts = my_mc.run_until_epoch(
setup,
almanac.clone(),
jwst.epoch() + prediction_duration,
num_runs,
);
assert_eq!(rslts.runs.len(), num_runs);
// Finally, export these results, computing the eclipse percentage for all of these results.
// For all of the resulting trajectories, we'll want to compute the percentage of penumbra and umbra.
let eclipse_loc = EclipseLocator::cislunar(almanac.clone());
let umbra_event = eclipse_loc.to_umbra_event();
let penumbra_event = eclipse_loc.to_penumbra_event();
rslts.to_parquet(
"02_jwst_monte_carlo.parquet",
Some(vec![&umbra_event, &penumbra_event]),
ExportCfg::default(),
almanac,
)?;
Ok(())
}
fn seconds(self) -> Duration
fn seconds(self) -> Duration
Examples found in repository?
examples/03_geo_analysis/stationkeeping.rs (line 107)
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fn main() -> Result<(), Box<dyn Error>> {
pel::init();
// Set up the dynamics like in the orbit raise.
let almanac = Arc::new(MetaAlmanac::latest().map_err(Box::new)?);
let epoch = Epoch::from_gregorian_utc_hms(2024, 2, 29, 12, 13, 14);
// Define the GEO orbit, and we're just going to maintain it very tightly.
let earth_j2000 = almanac.frame_from_uid(EARTH_J2000)?;
let orbit = Orbit::try_keplerian(42164.0, 1e-5, 0., 163.0, 75.0, 0.0, epoch, earth_j2000)?;
println!("{orbit:x}");
let sc = Spacecraft::builder()
.orbit(orbit)
.dry_mass_kg(1000.0) // 1000 kg of dry mass
.fuel_mass_kg(1000.0) // 1000 kg of fuel, totalling 2.0 tons
.srp(SrpConfig::from_area(3.0 * 6.0)) // Assuming 1 kW/m^2 or 18 kW, giving a margin of 4.35 kW for on-propulsion consumption
.thruster(Thruster {
// "NEXT-STEP" row in Table 2
isp_s: 4435.0,
thrust_N: 0.472,
})
.mode(GuidanceMode::Thrust) // Start thrusting immediately.
.build();
// Set up the spacecraft dynamics like in the orbit raise example.
let prop_time = 30.0 * Unit::Day;
// Define the guidance law -- we're just using a Ruggiero controller as demonstrated in AAS-2004-5089.
let objectives = &[
Objective::within_tolerance(StateParameter::SMA, 42_164.0, 5.0), // 5 km
Objective::within_tolerance(StateParameter::Eccentricity, 0.001, 5e-5),
Objective::within_tolerance(StateParameter::Inclination, 0.05, 1e-2),
];
let ruggiero_ctrl = Ruggiero::from_max_eclipse(objectives, sc, 0.2)?;
println!("{ruggiero_ctrl}");
let mut orbital_dyn = OrbitalDynamics::point_masses(vec![MOON, SUN]);
let mut jgm3_meta = MetaFile {
uri: "http://public-data.nyxspace.com/nyx/models/JGM3.cof.gz".to_string(),
crc32: Some(0xF446F027), // Specifying the CRC32 avoids redownloading it if it's cached.
};
jgm3_meta.process(true)?;
let harmonics = Harmonics::from_stor(
almanac.frame_from_uid(IAU_EARTH_FRAME)?,
HarmonicsMem::from_cof(&jgm3_meta.uri, 8, 8, true)?,
);
orbital_dyn.accel_models.push(harmonics);
let srp_dyn = SolarPressure::default(EARTH_J2000, almanac.clone())?;
let sc_dynamics = SpacecraftDynamics::from_model(orbital_dyn, srp_dyn)
.with_guidance_law(ruggiero_ctrl.clone());
println!("{sc_dynamics}");
// Finally, let's use the Monte Carlo framework built into Nyx to propagate spacecraft.
// Let's start by defining the dispersion.
// The MultivariateNormal structure allows us to define the dispersions in any of the orbital parameters, but these are applied directly in the Cartesian state space.
// Note that additional validation on the MVN is in progress -- https://github.com/nyx-space/nyx/issues/339.
let mc_rv = MultivariateNormal::new(
sc,
vec![StateDispersion::zero_mean(StateParameter::SMA, 3.0)],
)?;
let my_mc = MonteCarlo::new(
sc, // Nominal state
mc_rv,
"03_geo_sk".to_string(), // Scenario name
None, // No specific seed specified, so one will be drawn from the computer's entropy.
);
// Build the propagator setup.
let setup = Propagator::rk89(
sc_dynamics.clone(),
IntegratorOptions::builder()
.min_step(10.0_f64.seconds())
.error_ctrl(ErrorControl::RSSCartesianStep)
.build(),
);
let num_runs = 25;
let rslts = my_mc.run_until_epoch(setup, almanac.clone(), sc.epoch() + prop_time, num_runs);
assert_eq!(rslts.runs.len(), num_runs);
// For all of the resulting trajectories, we'll want to compute the percentage of penumbra and umbra.
rslts.to_parquet(
"03_geo_sk.parquet",
Some(vec![
&EclipseLocator::cislunar(almanac.clone()).to_penumbra_event()
]),
ExportCfg::default(),
almanac,
)?;
Ok(())
}
More examples
examples/03_geo_analysis/raise.rs (line 121)
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fn main() -> Result<(), Box<dyn Error>> {
pel::init();
// Dynamics models require planetary constants and ephemerides to be defined.
// Let's start by grabbing those by using ANISE's latest MetaAlmanac.
// This will automatically download the DE440s planetary ephemeris,
// the daily-updated Earth Orientation Parameters, the high fidelity Moon orientation
// parameters (for the Moon Mean Earth and Moon Principal Axes frames), and the PCK11
// planetary constants kernels.
// For details, refer to https://github.com/nyx-space/anise/blob/master/data/latest.dhall.
// Note that we place the Almanac into an Arc so we can clone it cheaply and provide read-only
// references to many functions.
let almanac = Arc::new(MetaAlmanac::latest().map_err(Box::new)?);
// Fetch the EME2000 frame from the Almabac
let eme2k = almanac.frame_from_uid(EARTH_J2000).unwrap();
// Define the orbit epoch
let epoch = Epoch::from_gregorian_utc_hms(2024, 2, 29, 12, 13, 14);
// Build the spacecraft itself.
// Using slide 6 of https://aerospace.org/sites/default/files/2018-11/Davis-Mayberry_HPSEP_11212018.pdf
// for the "next gen" SEP characteristics.
// GTO start
let orbit = Orbit::keplerian(24505.9, 0.725, 7.05, 0.0, 0.0, 0.0, epoch, eme2k);
let sc = Spacecraft::builder()
.orbit(orbit)
.dry_mass_kg(1000.0) // 1000 kg of dry mass
.fuel_mass_kg(1000.0) // 1000 kg of fuel, totalling 2.0 tons
.srp(SrpConfig::from_area(3.0 * 6.0)) // Assuming 1 kW/m^2 or 18 kW, giving a margin of 4.35 kW for on-propulsion consumption
.thruster(Thruster {
// "NEXT-STEP" row in Table 2
isp_s: 4435.0,
thrust_N: 0.472,
})
.mode(GuidanceMode::Thrust) // Start thrusting immediately.
.build();
let prop_time = 180.0 * Unit::Day;
// Define the guidance law -- we're just using a Ruggiero controller as demonstrated in AAS-2004-5089.
let objectives = &[
Objective::within_tolerance(StateParameter::SMA, 42_165.0, 20.0),
Objective::within_tolerance(StateParameter::Eccentricity, 0.001, 5e-5),
Objective::within_tolerance(StateParameter::Inclination, 0.05, 1e-2),
];
// Ensure that we only thrust if we have more than 20% illumination.
let ruggiero_ctrl = Ruggiero::from_max_eclipse(objectives, sc, 0.2).unwrap();
println!("{ruggiero_ctrl}");
// Define the high fidelity dynamics
// Set up the spacecraft dynamics.
// Specify that the orbital dynamics must account for the graviational pull of the Moon and the Sun.
// The gravity of the Earth will also be accounted for since the spaceraft in an Earth orbit.
let mut orbital_dyn = OrbitalDynamics::point_masses(vec![MOON, SUN]);
// We want to include the spherical harmonics, so let's download the gravitational data from the Nyx Cloud.
// We're using the JGM3 model here, which is the default in GMAT.
let mut jgm3_meta = MetaFile {
uri: "http://public-data.nyxspace.com/nyx/models/JGM3.cof.gz".to_string(),
crc32: Some(0xF446F027), // Specifying the CRC32 avoids redownloading it if it's cached.
};
// And let's download it if we don't have it yet.
jgm3_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 Earth centered Earth fixed frame, IAU Earth.
let harmonics = Harmonics::from_stor(
almanac.frame_from_uid(IAU_EARTH_FRAME)?,
HarmonicsMem::from_cof(&jgm3_meta.uri, 8, 8, true).unwrap(),
);
// Include the spherical harmonics into the orbital dynamics.
orbital_dyn.accel_models.push(harmonics);
// We define the solar radiation pressure, using the default solar flux and accounting only
// for the eclipsing caused by the Earth.
let srp_dyn = SolarPressure::default(EARTH_J2000, almanac.clone())?;
// 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 sc_dynamics = SpacecraftDynamics::from_model(orbital_dyn, srp_dyn)
.with_guidance_law(ruggiero_ctrl.clone());
println!("{:x}", orbit);
// We specify a minimum step in the propagator because the Ruggiero control would otherwise drive this step very low.
let (final_state, traj) = Propagator::rk89(
sc_dynamics.clone(),
IntegratorOptions::builder()
.min_step(10.0_f64.seconds())
.error_ctrl(ErrorControl::RSSCartesianStep)
.build(),
)
.with(sc, almanac.clone())
.for_duration_with_traj(prop_time)?;
let fuel_usage = sc.fuel_mass_kg - final_state.fuel_mass_kg;
println!("{:x}", final_state.orbit);
println!("fuel usage: {:.3} kg", fuel_usage);
// Finally, export the results for analysis, including the penumbra percentage throughout the orbit raise.
traj.to_parquet(
"./03_geo_raise.parquet",
Some(vec![
&EclipseLocator::cislunar(almanac.clone()).to_penumbra_event()
]),
ExportCfg::default(),
almanac,
)?;
for status_line in ruggiero_ctrl.status(&final_state) {
println!("{status_line}");
}
ruggiero_ctrl
.achieved(&final_state)
.expect("objective not achieved");
Ok(())
}
examples/04_lro_od/main.rs (line 97)
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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", "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 mut almanac = MetaAlmanac::new(meta.to_string_lossy().to_string())
.map_err(Box::new)?
.process(true)
.map_err(Box::new)?;
let mut moon_pc = almanac.planetary_data.get_by_id(MOON)?;
moon_pc.mu_km3_s2 = 4902.74987;
almanac.planetary_data.set_by_id(MOON, moon_pc)?;
let mut earth_pc = almanac.planetary_data.get_by_id(EARTH)?;
earth_pc.mu_km3_s2 = 398600.436;
almanac.planetary_data.set_by_id(EARTH, earth_pc)?;
// Save this new kernel for reuse.
// In an operational context, this would be part of the "Lock" process, and should not change throughout the mission.
almanac
.planetary_data
.save_as(&data_folder.join("lro-specific.pca"), true)?;
// Lock the almanac (an Arc is a read only structure).
let almanac = Arc::new(almanac);
// 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()
.dry_mass_kg(1018.0) // Launch masses
.fuel_mass_kg(900.0)
.srp(SrpConfig {
// SRP configuration is arbitrary, but we will be estimating it anyway.
area_m2: 3.9 * 2.7,
cr: 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 48 hours with a one minute time step.
let traj_as_flown = Traj::from_bsp(
lro_frame,
MOON_J2000,
almanac.clone(),
sc_template,
5.seconds(),
Some(Epoch::from_str("2024-01-01 00:00:00 UTC")?),
Some(Epoch::from_str("2024-01-02 00:00:00 UTC")?),
Aberration::LT,
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 moon_pa_frame = IAU_MOON_FRAME;
let sph_harmonics = Harmonics::from_stor(
almanac.frame_from_uid(moon_pa_frame)?,
HarmonicsMem::from_shadr(&jggrx_meta.uri, 80, 80, true)?,
);
// 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.clone())?;
// 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,
"./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_many(ground_station_file)?;
// 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, RangeDoppler, _>::new(
devices,
traj_as_flown.clone(),
configs,
)?;
trk.build_schedule(almanac.clone())?;
let arc = trk.generate_measurements(almanac.clone())?;
// Save the simulated tracking data
arc.to_parquet_simple("./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 initial_estimate = sc.to_estimate()?;
println!("== FILTER STATE ==\n{sc_seed:x}\n{initial_estimate}");
let kf = KF::new(
// Increase the initial covariance to account for larger deviation.
initial_estimate,
// Until https://github.com/nyx-space/nyx/issues/351, we need to specify the SNC in the acceleration of the Moon J2000 frame.
SNC3::from_diagonal(10 * Unit::Minute, &[1e-11, 1e-11, 1e-11]),
);
// We'll set up the OD process to reject measurements whose residuals are mover than 4 sigmas away from what we expect.
let mut odp = ODProcess::ckf(
setup.with(initial_estimate.state().with_stm(), almanac.clone()),
kf,
Some(ResidRejectCrit::default()),
almanac.clone(),
);
odp.process_arc::<GroundStation>(&arc)?;
let ric_err = traj_as_flown
.at(odp.estimates.last().unwrap().epoch())?
.orbit
.ric_difference(&odp.estimates.last().unwrap().orbital_state())?;
println!("== RIC at end ==");
println!("RIC Position (m): {}", ric_err.radius_km * 1e3);
println!("RIC Velocity (m/s): {}", ric_err.velocity_km_s * 1e3);
odp.to_parquet("./04_lro_od_results.parquet", ExportCfg::default())?;
// 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 = odp.to_traj()?;
// Build the RIC difference.
od_trajectory.ric_diff_to_parquet(
&traj_as_flown,
"./04_lro_od_truth_error.parquet",
ExportCfg::default(),
)?;
Ok(())
}
fn milliseconds(self) -> Duration
fn microseconds(self) -> Duration
fn nanoseconds(self) -> Duration
Object Safety§
This trait is not object safe.