High-Precision Orbit Propagator¶

API reference for the numerical (force-model) propagator. For background, see:

Force Model — modeled forces and physical motivation
Empirical SRP: ECOM — the experimental ECOM solar-radiation-pressure model behind satproperties.ecom
ODE Integrators — solver families, step-size selection, tolerances
State Vectors, STM & Covariance — state representation, STM, covariance propagation, maneuvers
Tutorial: GPS Example
References — primary sources for each force model and integrator
Tutorial: ECOM Solar Radiation Pressure

`propagate(state, begin, end=None, *, duration=None, duration_secs=None, duration_days=None, output_phi=False, propsettings=None, satproperties=None)` ¶

High-precision orbit propagator

Propagate orbits with high-precision force modeling via adaptive Runge-Kutta methods (default is order 9/8).

Parameters:

Name	Type	Description	Default
`state`	`NDArray[float64]`	6-element numpy array representing satellite GCRF position and velocity in meters and meters/second	required
`begin`	`time`	Time at which satellite is at input state	required

Other Parameters:

Name	Type	Description
`end`	`time \| None`	Time at which new position and velocity will be computed
`duration`	`duration \| None`	Duration from `begin` at which new position & velocity will be computed
`duration_secs`	`float \| None`	Duration in seconds from `begin` at which new position and velocity will be computed
`duration_days`	`float \| None`	Duration in days from `begin` at which new position and velocity will be computed
`output_phi`	`bool`	Output 6x6 state transition matrix between begin and end times. Default is False
`propsettings`	`propsettings \| None`	Settings for the propagation; if omitted, defaults are used
`satproperties`	`satproperties \| None`	Drag and radiation pressure susceptibility of satellite

Returns:

Name	Type	Description
`propresult`	`propresult`	Propagation result object holding state outputs, statistics, and dense output if requested

Notes

Propagates satellite ephemeris (position, velocity in GCRF & time) to new time and outputs new position and velocity via Runge-Kutta integration. Inputs and outputs are all in the Geocentric Celestial Reference Frame (GCRF).

Included forces:

Earth gravity with higher-order zonal terms
Sun, Moon gravity
Radiation pressure
Atmospheric drag: NRL-MSISE 2000 density model, with option to include space weather effects

End time must be set by keyword argument, either explicitly or by duration. Solid Earth tides are not (yet) included in the model.

For future propagation (beyond available data files):

Earth orientation parameters use the last available values (constant extrapolation)
Space weather uses the NOAA/SWPC solar cycle forecast for predicted F10.7 values; Ap defaults to 4. If no forecast is available, F10.7 defaults to 150.

Example

import numpy as np

# Define initial state in GCRF (position in meters, velocity in m/s)
state = np.array([6.781e6, 0, 0, 0, 7.5e3, 0])
t0 = satkit.time(2024, 1, 1)

# Propagate forward by 1 day
result = satkit.propagate(state, t0, duration_days=1.0)
print(f"End position: {result.pos} m")
print(f"End velocity: {result.vel} m/s")

# Interpolate at intermediate time
t_mid = t0 + satkit.duration(hours=12)
mid_state = result.interp(t_mid)

`propresult` ¶

Results of a satellite propagation

This class lets the user access results of the satellite propagation

Notes

If enable_interp is set to True in the propagation settings, the propresult object can be used to interpolate solutions at any time between the begin and end times of the propagation via the interp method.

`pos` `property` ¶

GCRF position of satellite, meters

Returns:

Type	Description
`NDArray[float64]`	3-element numpy array representing GCRF position (meters) at end of propagation

`vel` `property` ¶

GCRF velocity of satellite, meters/second

Returns:

Type	Description
`NDArray[float64]`	3-element numpy array representing GCRF velocity in meters/second at end of propagation

`state` `property` ¶

6-element end state (pos + vel) of satellite in meters & meters/second

Returns:

Type	Description
`NDArray[float64]`	6-element numpy array representing state of satellite in meters & meters/second

`state_end` `property` ¶

6-element state (pos + vel) of satellite in meters & meters/second at end of propagation

Notes: - This is the same as the "state" property

Returns:

Type	Description
`NDArray[float64]`	6-element numpy array representing state of satellite in meters & meters/second

`state_begin` `property` ¶

6-element state (pos + vel) of satellite in meters & meters/second at begin of propagation Returns: 6-element numpy array representing state of satellite in meters & meters/second at begin of propagation

`time` `property` ¶

Time at which state is valid

Returns:

Type	Description
`_Time`	Time at which state is valid

`time_end` `property` ¶

Time at which state is valid

Notes: - This is identical to "time" property

Returns:

Type	Description
`_Time`	Time at which state is valid

`time_begin` `property` ¶

Time at which state_begin is valid

Returns:

Type	Description
`_Time`	Time at which state_begin is valid

`stats` `property` ¶

Statistics of propagation

Returns:

Name	Type	Description
`propstats`	`propstats`	Object containing statistics of propagation

`can_interp` `property` ¶

Whether this result supports interpolation

Returns:

Type	Description
`bool`	True if dense output is available for interpolation

`phi` `property` ¶

State transition matrix

Returns:

Type	Description
`NDArray[float64] \| None`	6x6 numpy array representing state transition matrix or None if not computed

`propsettings` ¶

This class contains settings used in the high-precision orbit propagator part of the "satkit" python toolbox

Notes

Default settings:
- abs_error: 1e-8
- rel_error: 1e-8
- gravity_degree: 4
- gravity_order: 4
- gravity_model: gravmodel.egm96
- use_spaceweather: True
- use_sun_gravity: True
- use_moon_gravity: True
- tide_model: tidemodel.solid_step1
- use_relativistic_correction: True
- enable_interp: True
- integrator: integrator.rkv98
- gj_step_seconds: 60.0
- max_steps: 1_000_000
enable_interp enables high-precision interpolation of state between begin and end times via the returned function, it is enabled by default. There is a small increase in computational efficiency if set to false

`abs_error` `property` `writable` ¶

Maximum absolute value of error for any element in propagated state following ODE integration

Returns:

Type	Description
`float`	Maximum absolute value of error for any element in propagated state following ODE integration, default is 1e-8

`rel_error` `property` `writable` ¶

Maximum relative error of any element in propagated state following ODE integration

Returns:

Type	Description
`float`	Maximum relative error of any element in propagated state following ODE integration, default is 1e-8

`gravity_degree` `property` `writable` ¶

Maximum degree of spherical harmonic gravity model

Returns:

Type	Description
`int`	Maximum degree of spherical harmonic gravity model, default is 4

`gravity_order` `property` `writable` ¶

Maximum order of spherical harmonic gravity model

Returns:

Type	Description
`int`	Maximum order of spherical harmonic gravity model, default is same as gravity_degree

`use_sun_gravity` `property` `writable` ¶

Include sun third-body gravitational perturbation

Returns:

Type	Description
`bool`	Whether sun gravity is enabled, default is True

`use_moon_gravity` `property` `writable` ¶

Include moon third-body gravitational perturbation

Returns:

Type	Description
`bool`	Whether moon gravity is enabled, default is True

`use_spaceweather` `property` `writable` ¶

Use space weather data when computing atmospheric density for drag forces

Notes:

Space weather data can have a large effect on the density of the atmosphere
This can be important for accurate drag force calculations
Space weather data is updated every 3 hours. Most-recent data can be downloaded with satkit.utils.update_datafiles()
Default value is True

Returns:

Type	Description
`bool`	Indicate whether or not space weather data should be used when computing atmospheric density for drag forces

`tide_model` `property` `writable` ¶

Solid Earth tide model fidelity.

Default is tidemodel.solid_step1 (IERS 2010 §6.2.1 frequency-independent Love-number response). Set to tidemodel.none to disable.

`use_relativistic_correction` `property` `writable` ¶

Include the general-relativistic acceleration of IERS 2010 §10.3 Eq. 10.12 (PPN β = γ = 1): the Schwarzschild term, geodesic (de Sitter) precession 2 (Ω × v) from the Earth's heliocentric motion, and Lense–Thirring frame dragging from the Earth's spin. Default is True.

The Schwarzschild term dominates below GEO (omitting it costs ~1 m/day at GPS altitude); the geodesic term dominates beyond ~100,000 km (~1 m over 7 days at 200,000 km). Computational cost is negligible. Matches GMAT's RelativisticCorrection.

`require_eop_coverage` `property` `writable` ¶

Raise RuntimeError from propagate if the span extends past the end of the loaded Earth-orientation-parameter (EOP) table, instead of holding the last EOP row constant with a one-time warning. Default False.

Polar motion and UT1−UTC drift by ~0.1 arcsec / ~10 ms over a few months — metres at LEO — so set this for precision work and refresh the data files with satkit.utils.update_datafiles() when it trips. See satkit.frametransform.eop_coverage and eop_status.

`enable_interp` `property` `writable` ¶

Store intermediate data that allows for fast high-precision interpolation of state between begin and end times If not needed, there is a small computational advantage if set to False

`gravity_model` `property` `writable` ¶

Gravity model used for Earth gravity computation

Returns:

Name	Type	Description
`gravmodel`	`gravmodel`	The gravity model, default is gravmodel.egm96

`integrator` `property` `writable` ¶

ODE integrator used for orbit propagation

Returns:

Name	Type	Description
`integrator`	`integrator`	The integrator, default is integrator.rkv98

`gj_step_seconds` `property` `writable` ¶

Fixed step size (seconds) used by integrator.gauss_jackson8.

Ignored by adaptive integrators. Typical values: 30-120 s for LEO, 60-300 s for MEO, 300-600 s for GEO.

Returns:

Type	Description
`float`	Fixed step size in seconds, default is 60.0

`max_steps` `property` `writable` ¶

Maximum number of integrator steps before the propagator aborts.

Applies to all integrators (adaptive Runge-Kutta, Rosenbrock, and Gauss-Jackson 8). Increase for very long propagation arcs or tight tolerances.

Returns:

Type	Description
`int`	Maximum steps, default is 1_000_000

`init(*, abs_error=1e-08, rel_error=1e-08, gravity_degree=4, gravity_order=4, gravity_model=..., use_spaceweather=True, use_sun_gravity=True, use_moon_gravity=True, tide_model=..., use_relativistic_correction=True, enable_interp=True, integrator=..., gj_step_seconds=60.0, max_steps=1000000, require_eop_coverage=False)` ¶

Create propagation settings object used to configure high-precision orbit propagator

Parameters:

Name	Type	Description	Default
`abs_error`	`float`	Maximum absolute value of error for any element in propagated state following ODE integration. Default is 1e-8	`1e-08`
`rel_error`	`float`	Maximum relative error of any element in propagated state following ODE integration. Default is 1e-8	`1e-08`
`gravity_degree`	`int`	Maximum degree of spherical harmonic gravity model, at most 40 (`ValueError` above that). Default is 4	`4`
`gravity_order`	`int`	Maximum order of spherical harmonic gravity model. Must be <= gravity_degree (and so at most 40). Default is same as gravity_degree	`4`
`gravity_model`	`gravmodel`	Gravity model to use. Default is gravmodel.egm96	`...`
`use_spaceweather`	`bool`	Use space weather data when computing atmospheric density for drag forces. Default is True	`True`
`use_sun_gravity`	`bool`	Include sun third-body gravitational perturbation. Default is True	`True`
`use_moon_gravity`	`bool`	Include moon third-body gravitational perturbation. Default is True	`True`
`tide_model`	`tidemodel`	Solid Earth tide model. Default is `tidemodel.solid_step1` (IERS 2010 §6.2.1 frequency-independent Love-number response). Use `tidemodel.none` to disable (e.g., for reproducibility with pre-tide releases).	`...`
`use_relativistic_correction`	`bool`	Include the general-relativistic acceleration of IERS 2010 §10.3 Eq. 10.12 (β=γ=1): Schwarzschild + geodesic (de Sitter) precession + Lense-Thirring. Default is True. Its position effect depends on the orbit, propagation arc, and fitted parameters (~1 m/day at GPS altitude if omitted; the geodesic term dominates beyond ~100,000 km); cost is negligible.	`True`
`enable_interp`	`bool`	Store intermediate data that allows for fast high-precision interpolation of state between begin and end times. Default is True	`True`
`integrator`	`integrator`	ODE integrator to use. Default is integrator.rkv98	`...`
`gj_step_seconds`	`float`	Fixed step size (seconds) used by `integrator.gauss_jackson8`. Ignored by adaptive integrators. Typical values: 30-120 s for LEO, 60-300 s for MEO, 300-600 s for GEO. Default is 60.0.	`60.0`
`max_steps`	`int`	Maximum number of integrator steps before the propagator aborts with a max-steps error. Applies to all integrators (adaptive Runge-Kutta, Rosenbrock, and Gauss-Jackson 8). Default is 1_000_000, which covers very long propagation arcs with plenty of headroom. Lower for a tighter runaway-propagation safeguard.	`1000000`
`require_eop_coverage`	`bool`	Raise `RuntimeError` if the propagation span extends past the end of the loaded Earth-orientation-parameter (EOP) table, instead of holding the last EOP row constant with a one-time warning. Default is False. See `satkit.frametransform.eop_coverage` / `eop_status`.	`False`

Returns:

Name	Type	Description
`propsettings`	`None`	New propsettings object with default settings

Example

settings = satkit.propsettings(
    gravity_degree=16,
    abs_error=1e-10,
    rel_error=1e-10,
    gravity_model=satkit.gravmodel.egm96,
    integrator=satkit.integrator.rkts54,
)

`precompute_terms(begin, end, step=None)` ¶

Precompute terms for fast interpolation of state between begin and end times

This can be used, for example, to compute sun and moon positions only once if propagating many satellites over the same time period

Parameters:

Name	Type	Description	Default
`begin`	`time`	Begin time of propagation	required
`end`	`time`	End time of propagation	required
`step`	`duration \| float \| timedelta`	Step size for interpolation. Default = 60 seconds. float is interpreted as seconds.	`None`

`integrator` ¶

Choice of ODE integrator for orbit propagation

Available integrators, from highest to lowest order:

rkv98 - Verner 9(8) with 8th-degree dense output, 21 stages (default)
rkv98_nointerp - Verner 9(8) without interpolation, 16 stages
rkv87 - Verner 8(7) with 7th-degree dense output, 17 stages
rkv65 - Verner 6(5) with 6th-degree dense output, 10 stages
rkts54 - Tsitouras 5(4) with FSAL, 7 stages
rodas4 - RODAS4 L-stable Rosenbrock 4(3), 6 stages. For stiff problems.
gauss_jackson8 - Gauss-Jackson 8, fixed-step multistep predictor-corrector. For high-precision long-duration orbit propagation (days to months).

Higher-order integrators can take larger time steps for the same accuracy, so despite having more stages per step, they often require fewer total function evaluations. For typical orbit propagation, rkv98 (the default) is recommended. For faster but lower-accuracy propagation, rkts54 or rkv65 can be used. For stiff problems (re-entry, very low perigee), rodas4 is recommended. For long-duration high-precision propagation of smooth orbits, gauss_jackson8 typically uses 3-10× fewer force evaluations than rkv98 at comparable accuracy — but it requires a user-chosen fixed step size (gj_step_seconds), does not handle discontinuities such as impulsive maneuvers, and needs ≥9 steps of startup, so it's unsuitable for very short propagations.

`rkv98` `class-attribute` ¶

Verner 9(8) with 8th-degree dense output, 21 stages (default)

Highest accuracy integrator. Recommended for precision orbit propagation.

`rkv98_nointerp` `class-attribute` ¶

Verner 9(8) without interpolation, 16 stages

Same stepping accuracy as rkv98 but skips interpolation stages. Slightly faster when dense output is not needed (enable_interp=False).

`rkv87` `class-attribute` ¶

Verner 8(7) with 7th-degree dense output, 17 stages

`rkv65` `class-attribute` ¶

Verner 6(5) with 6th-degree dense output, 10 stages

`rkts54` `class-attribute` ¶

Tsitouras 5(4) with FSAL, 7 stages

Fastest integrator. Good for quick propagations where high accuracy is not critical.

`rodas4` `class-attribute` ¶

RODAS4 — L-stable Rosenbrock 4(3), 6 stages

Implicit solver for stiff problems such as re-entry or very low perigee orbits. Uses analytical Jacobian. Does not support dense output interpolation or state transition matrix (output_phi) propagation.

`gauss_jackson8` `class-attribute` ¶

Gauss-Jackson 8 — 8th-order fixed-step multistep predictor-corrector

Specialised for 2nd-order ODEs (r'' = f(t, r, v)). The dominant integrator in high-precision astrodynamics codes (GMAT, STK, ODTK). Typically uses 3-10× fewer force evaluations than rkv98 at comparable accuracy on smooth long-duration orbit propagation.

Uses a fixed step size set via propsettings.gj_step_seconds. Supports dense output interpolation (quintic Hermite, 5th-order). Does not support state transition matrix (output_phi) propagation. Not recommended for highly eccentric orbits or integration across discontinuities (eclipse boundaries, impulsive maneuvers).

`tidemodel` ¶

Solid Earth tide model fidelity for high-precision orbit propagation.

Solid Earth tides deform the Earth under lunar and solar gravitational attraction, perturbing the gravity field. The effect is small (~0.3 m position drift over half a day at GEO; ~1 m/day at GPS altitude) but matters for sub-meter-class propagation accuracy.

Implements IERS Conventions 2010, Chapter 6.

Available models:

none — no solid Earth tide correction
solid_step1 — IERS §6.2.1 Step 1, frequency-independent Love-number response (default). ≈99% of the total signal.
solid_full — Step 1 + §6.2.2 Step 2 frequency-dependent corrections. Step 2 is not yet implemented; currently behaves as solid_step1.

`none` `class-attribute` ¶

No solid Earth tide correction.

`solid_step1` `class-attribute` ¶

IERS 2010 §6.2.1 Step 1 — frequency-independent Love-number response. Accounts for ≈99% of the solid-tide signal at ~5% per-ydot overhead. Default.

`solid_full` `class-attribute` ¶

IERS 2010 Step 1 + Step 2 (frequency-dependent corrections). Step 2 is not yet implemented; currently behaves as solid_step1.

`propstats` ¶

Statistics of a satellite propagation

`num_eval` `property` ¶

Number of function evaluations

`num_accept` `property` ¶

Number of accepted steps in adaptive RK integrator

`num_reject` `property` ¶

Number of rejected steps in adaptive RK integrator

`satproperties` ¶

Satellite properties relevant for drag, radiation pressure, and thrust

This class lets the satellite radiation pressure, drag, and thrust parameters be set for duration of propagation.

Attributes:

Name	Type	Description
`cdaoverm`	`float`	Coefficient of drag times area over mass in m^2/kg
`craoverm`	`float`	Coefficient of radiation pressure times area over mass in m^2/kg
`thrusts`	`list[thrust]`	List of continuous thrust arcs
`ecom`	`ecomparams \| None`	ECOM empirical solar-radiation-pressure coefficients, added to the cannonball term (use `craoverm=0` for a pure ECOM model). See :class:`ecomparams` for the conventions and the "ECOM Solar Radiation Pressure" tutorial for a fit against IGS GPS orbits.

`cdaoverm` `property` `writable` ¶

Coefficient of drag times area over mass. Units are m^2/kg

`craoverm` `property` `writable` ¶

Coefficient of radiation pressure times area over mass. Units are m^2/kg

`thrusts` `property` `writable` ¶

List of continuous thrust arcs

`ecom` `property` `writable` ¶

ECOM solar-radiation-pressure coefficients, or None

When set, the ECOM acceleration (see :class:ecomparams for the DYB frame, sign and eclipse conventions) is added to the cannonball term craoverm; use craoverm=0 for a pure ECOM model. The "ECOM Solar Radiation Pressure" tutorial shows how to fit the coefficients to IGS GPS orbits.

`init(cdaoverm=0, craoverm=0, *, thrusts=None, ecom=None)` ¶

Create a satproperties object

Parameters:

Name	Type	Description	Default
`cdaoverm`	`float`	Coefficient of drag times area over mass in m^2/kg	`0`
`craoverm`	`float`	Coefficient of radiation pressure times area over mass in m^2/kg	`0`
`thrusts`	`list[thrust]`	List of continuous thrust arcs	`None`
`ecom`	`ecomparams`	ECOM solar-radiation-pressure coefficients	`None`

Example:

import satkit as sk

t0 = sk.time(2024, 1, 1)
t1 = t0 + sk.duration.from_hours(2)

props = sk.satproperties(
    cdaoverm=0.01,
    thrusts=[sk.thrust.constant([0, 1e-4, 0], t0, t1, frame=sk.frame.RTN)]
)

# GNSS-style empirical SRP instead of the cannonball
props = sk.satproperties(craoverm=0.0, ecom=sk.ecomparams.reduced(-1e-7, 0, 0, 0, 0))

`ecomparams` ¶

Empirical CODE Orbit Model (ECOM) solar-radiation-pressure coefficients

ECOM expresses the non-gravitational acceleration of a (nominally yaw-steering) satellite in a Sun-oriented frame with constant and harmonic terms. The coefficients are normally estimated in orbit determination; satkit propagates with the values you supply.

Coefficients (all accelerations in m/s²; typical GPS sizes in nm/s²):

d0        e_D (toward Sun), constant, all models      -80 to -110 (negative)
y0        e_Y (solar-panel axis), constant, all       ~1  (attitude/thermal Y-bias)
b0        e_B, constant, all                          ~1-5, varies with beta
dc, ds    e_D, cos/sin phi, ECOM1 (phi = u)           <~1
yc, ys    e_Y, cos/sin phi, ECOM1                     <~1
bc, bs    e_B, cos/sin phi; reduced/ECOM1 (phi = u), ECOM2's B1c/B1s (phi = du)  <~2
d2c, d2s  e_D, cos/sin 2*du, ECOM2                    few (eclipse seasons)
d4c, d4s  e_D, cos/sin 4*du, ECOM2                    few (eclipse seasons)

Experimental: this interface is new and may be reshaped in a minor release; the physics and conventions are stable.

Frame (GCRF), with r the satellite position and s the Sun position:

e_D = unit(s - r) — satellite → Sun
e_Y = unit(e_D × r̂) — solar-panel rotation axis
e_B = e_D × e_Y

Model::

a = ν · [ D(φ)·e_D + Y(φ)·e_Y + B(φ)·e_B ]
D(φ) = d0 + dc cos φ + ds sin φ + d2c cos 2φ + d2s sin 2φ + d4c cos 4φ + d4s sin 4φ
Y(φ) = y0 + yc cos φ + ys sin φ
B(φ) = b0 + bc cos φ + bs sin φ

where ν is the Earth-shadow factor applied to all three axes (the CODE/Bernese convention: the whole ECOM acceleration is switched off in umbra) and φ is the argument of latitude u when sun_relative is False (ECOM1) or Δu, measured from orbit noon, when True (ECOM2).

Because e_D points at the Sun, the physical d0 is negative: about -1e-7 m/s² for a GPS satellite; y0 and the B terms are ~1e-9. All coefficients are in m/s².

Attach to a propagation via satproperties(ecom=...). The ECOM acceleration is added to the cannonball term, so use craoverm=0 for a pure ECOM model.

Example:

import satkit as sk

ecom = sk.ecomparams.reduced(d0=-1.0e-7, y0=1e-9, b0=0, bc=2e-9, bs=-1e-9)
props = sk.satproperties(craoverm=0.0, ecom=ecom)
res = sk.propagate(state, t0, t1, propsettings=settings, satproperties=props)

`d0` `instance-attribute` ¶

Constant D (Sun-direction) term, m/s². Physically negative.

`y0` `instance-attribute` ¶

Constant Y term, m/s² (along the solar-panel axis).

`b0` `instance-attribute` ¶

Constant B term, m/s².

`dc` `instance-attribute` ¶

D cos φ coefficient, m/s².

`ds` `instance-attribute` ¶

D sin φ coefficient, m/s².

`yc` `instance-attribute` ¶

Y cos φ coefficient, m/s².

`ys` `instance-attribute` ¶

Y sin φ coefficient, m/s².

`bc` `instance-attribute` ¶

B cos φ coefficient, m/s² (B1c in ECOM2).

`bs` `instance-attribute` ¶

B sin φ coefficient, m/s² (B1s in ECOM2).

`d2c` `instance-attribute` ¶

D cos 2φ coefficient, m/s² (ECOM2).

`d2s` `instance-attribute` ¶

D sin 2φ coefficient, m/s² (ECOM2).

`d4c` `instance-attribute` ¶

D cos 4φ coefficient, m/s² (ECOM2).

`d4s` `instance-attribute` ¶

D sin 4φ coefficient, m/s² (ECOM2).

`sun_relative` `instance-attribute` ¶

True: harmonics in Δu from orbit noon (ECOM2); False: in the argument of latitude u (ECOM1).

`init(*, d0=0.0, y0=0.0, b0=0.0, dc=0.0, ds=0.0, yc=0.0, ys=0.0, bc=0.0, bs=0.0, d2c=0.0, d2s=0.0, d4c=0.0, d4s=0.0, sun_relative=False)` ¶

Create ECOM coefficients (m/s²); all default to zero.

Parameters:

Name	Type	Description	Default
`d0, y0, b0`	`float`	constant D, Y, B terms	required
`dc, ds`	`float`	D cos φ, D sin φ	required
`yc, ys`	`float`	Y cos φ, Y sin φ	required
`bc, bs`	`float`	B cos φ, B sin φ	required
`d2c, d2s, d4c, d4s`	`float`	even D harmonics (ECOM2)	required
`sun_relative`	`bool`	False → φ = argument of latitude (ECOM1); True → φ = Δu from orbit noon (ECOM2)	`False`

`reduced(d0, y0, b0, bc, bs)` `staticmethod` ¶

Reduced ECOM1: D0, Y0, B0, Bc, Bs in argument of latitude (CODE's classic GPS set)

`ecom1(d0, y0, b0, dc, ds, yc, ys, bc, bs)` `staticmethod` ¶

Full 9-parameter ECOM1 (once-per-revolution terms on D, Y, B in argument of latitude)

`ecom2(d0, y0, b0, b1c, b1s, d2c, d2s, d4c, d4s)` `staticmethod` ¶

ECOM2 (Arnold et al. 2015): D0, Y0, B0, B1c, B1s, D2c, D2s, D4c, D4s in Δu from orbit noon

`to_dict()` ¶

Coefficients as a dict (13 floats plus sun_relative)

`from_dict(d)` `staticmethod` ¶

Build from a dict as produced by :meth:to_dict; missing keys default to zero / False

`thrust` ¶

Continuous thrust acceleration for orbit maneuvers

Represents a constant thrust acceleration over a time window, specified in GCRF (inertial), RTN (CCSDS-standard orbital frame, also known as RSW or RIC), NTW (velocity-aligned), or LVLH.

RTN components are [R, T, N] where R = radial (outward from Earth centre), T = tangential / in-track, N = normal / cross-track (along angular momentum, h = r × v).

Example:

import satkit as sk

t0 = sk.time(2024, 1, 1)
t1 = t0 + sk.duration.from_hours(2)

# In-track thrust in the RTN (a.k.a. RSW, RIC) frame
t = sk.thrust.constant([0, 1e-4, 0], t0, t1, frame=sk.frame.RTN)

# Fixed direction thrust in GCRF frame
t = sk.thrust.constant([0, 0, 1e-3], t0, t1, frame=sk.frame.GCRF)

`accel` `property` ¶

Acceleration vector [m/s^2]

`frame` `property` ¶

Coordinate frame

`start` `property` ¶

Start time of thrust arc

`end` `property` ¶

End time of thrust arc

`constant(accel, start, end, frame)` `staticmethod` ¶

Create a constant thrust acceleration

Parameters:

Name	Type	Description	Default
`accel`	`array - like`	3-element acceleration vector [m/s^2]	required
`start`	`time`	Start time of thrust arc	required
`end`	`time`	End time of thrust arc	required
`frame`	`frame`	Coordinate frame — required, no default (matching the Rust API). Supported values: `frame.GCRF` — inertial Cartesian `frame.RTN` — radial / in-track / cross-track `frame.NTW` — normal-to-velocity / tangent / cross-track (use this for thrust along the velocity vector) `frame.LVLH` — Local Vertical / Local Horizontal	required

Returns:

Name	Type	Description
`thrust`	`thrust`	Thrust object

High-Precision Orbit Propagator¶

propagate(state, begin, end=None, *, duration=None, duration_secs=None, duration_days=None, output_phi=False, propsettings=None, satproperties=None) ¶

propresult ¶

pos property ¶

vel property ¶

state property ¶

state_end property ¶

state_begin property ¶

time property ¶

time_end property ¶

time_begin property ¶

stats property ¶

can_interp property ¶

phi property ¶

propsettings ¶

abs_error property writable ¶

rel_error property writable ¶

gravity_degree property writable ¶

gravity_order property writable ¶

use_sun_gravity property writable ¶

use_moon_gravity property writable ¶

use_spaceweather property writable ¶

tide_model property writable ¶

use_relativistic_correction property writable ¶

require_eop_coverage property writable ¶

enable_interp property writable ¶

gravity_model property writable ¶

integrator property writable ¶

gj_step_seconds property writable ¶

max_steps property writable ¶

precompute_terms(begin, end, step=None) ¶

integrator ¶

rkv98 class-attribute ¶

rkv98_nointerp class-attribute ¶

rkv87 class-attribute ¶

rkv65 class-attribute ¶

rkts54 class-attribute ¶

rodas4 class-attribute ¶

gauss_jackson8 class-attribute ¶

tidemodel ¶

none class-attribute ¶

solid_step1 class-attribute ¶

solid_full class-attribute ¶

propstats ¶

num_eval property ¶

num_accept property ¶

num_reject property ¶

satproperties ¶

cdaoverm property writable ¶

craoverm property writable ¶

thrusts property writable ¶

ecom property writable ¶

__init__(cdaoverm=0, craoverm=0, *, thrusts=None, ecom=None) ¶

ecomparams ¶

d0 instance-attribute ¶

y0 instance-attribute ¶

b0 instance-attribute ¶

dc instance-attribute ¶

ds instance-attribute ¶

yc instance-attribute ¶

ys instance-attribute ¶

bc instance-attribute ¶

bs instance-attribute ¶

d2c instance-attribute ¶

d2s instance-attribute ¶

d4c instance-attribute ¶

d4s instance-attribute ¶

sun_relative instance-attribute ¶

__init__(*, d0=0.0, y0=0.0, b0=0.0, dc=0.0, ds=0.0, yc=0.0, ys=0.0, bc=0.0, bs=0.0, d2c=0.0, d2s=0.0, d4c=0.0, d4s=0.0, sun_relative=False) ¶

reduced(d0, y0, b0, bc, bs) staticmethod ¶

ecom1(d0, y0, b0, dc, ds, yc, ys, bc, bs) staticmethod ¶

ecom2(d0, y0, b0, b1c, b1s, d2c, d2s, d4c, d4s) staticmethod ¶

to_dict() ¶

from_dict(d) staticmethod ¶

thrust ¶

accel property ¶

frame property ¶

start property ¶

end property ¶

constant(accel, start, end, frame) staticmethod ¶

`propagate(state, begin, end=None, *, duration=None, duration_secs=None, duration_days=None, output_phi=False, propsettings=None, satproperties=None)` ¶

`propresult` ¶

`pos` `property` ¶

`vel` `property` ¶

`state` `property` ¶

`state_end` `property` ¶

`state_begin` `property` ¶

`time` `property` ¶

`time_end` `property` ¶

`time_begin` `property` ¶

`stats` `property` ¶

`can_interp` `property` ¶

`phi` `property` ¶

`propsettings` ¶

`abs_error` `property` `writable` ¶

`rel_error` `property` `writable` ¶

`gravity_degree` `property` `writable` ¶

`gravity_order` `property` `writable` ¶

`use_sun_gravity` `property` `writable` ¶

`use_moon_gravity` `property` `writable` ¶

`use_spaceweather` `property` `writable` ¶

`tide_model` `property` `writable` ¶

`use_relativistic_correction` `property` `writable` ¶

`require_eop_coverage` `property` `writable` ¶

`enable_interp` `property` `writable` ¶

`gravity_model` `property` `writable` ¶

`integrator` `property` `writable` ¶

`gj_step_seconds` `property` `writable` ¶

`max_steps` `property` `writable` ¶

`precompute_terms(begin, end, step=None)` ¶

`integrator` ¶

`rkv98` `class-attribute` ¶

`rkv98_nointerp` `class-attribute` ¶

`rkv87` `class-attribute` ¶

`rkv65` `class-attribute` ¶

`rkts54` `class-attribute` ¶

`rodas4` `class-attribute` ¶

`gauss_jackson8` `class-attribute` ¶

`tidemodel` ¶

`none` `class-attribute` ¶

`solid_step1` `class-attribute` ¶

`solid_full` `class-attribute` ¶

`propstats` ¶

`num_eval` `property` ¶

`num_accept` `property` ¶

`num_reject` `property` ¶

`satproperties` ¶

`cdaoverm` `property` `writable` ¶

`craoverm` `property` `writable` ¶

`thrusts` `property` `writable` ¶

`ecom` `property` `writable` ¶

`init(cdaoverm=0, craoverm=0, *, thrusts=None, ecom=None)` ¶

`ecomparams` ¶

`d0` `instance-attribute` ¶

`y0` `instance-attribute` ¶

`b0` `instance-attribute` ¶

`dc` `instance-attribute` ¶

`ds` `instance-attribute` ¶

`yc` `instance-attribute` ¶

`ys` `instance-attribute` ¶

`bc` `instance-attribute` ¶

`bs` `instance-attribute` ¶

`d2c` `instance-attribute` ¶

`d2s` `instance-attribute` ¶

`d4c` `instance-attribute` ¶

`d4s` `instance-attribute` ¶

`sun_relative` `instance-attribute` ¶

`init(*, d0=0.0, y0=0.0, b0=0.0, dc=0.0, ds=0.0, yc=0.0, ys=0.0, bc=0.0, bs=0.0, d2c=0.0, d2s=0.0, d4c=0.0, d4s=0.0, sun_relative=False)` ¶

`reduced(d0, y0, b0, bc, bs)` `staticmethod` ¶

`ecom1(d0, y0, b0, dc, ds, yc, ys, bc, bs)` `staticmethod` ¶

`ecom2(d0, y0, b0, b1c, b1s, d2c, d2s, d4c, d4s)` `staticmethod` ¶

`to_dict()` ¶

`from_dict(d)` `staticmethod` ¶

`thrust` ¶

`accel` `property` ¶

`frame` `property` ¶

`start` `property` ¶

`end` `property` ¶

`constant(accel, start, end, frame)` `staticmethod` ¶