ECI-ROE Transformations¶

Transformations between Earth-Centered Inertial (ECI) state vectors and Relative Orbital Elements (ROE).

These functions combine the ECI↔KOE and OE↔ROE transformations to provide direct conversion between inertial Cartesian states and quasi-nonsingular Relative Orbital Elements.

Note

For conceptual explanations of ROE, see ROE Transformations.

state_eci_to_roe `builtin` ¶

state_eci_to_roe(x_chief: Union[ndarray, List], x_deputy: Union[ndarray, List], angle_format: AngleFormat) -> ndarray

Converts chief and deputy satellite ECI state vectors to quasi-nonsingular Relative Orbital Elements (ROE).

This function converts both ECI states to Keplerian orbital elements, then computes the quasi-nonsingular Relative Orbital Elements between them.

The ROE formulation provides a mean description of relative motion that is nonsingular for circular and near-circular orbits. The ROE vector contains: - da: Relative semi-major axis (dimensionless) - dλ: Relative mean longitude (degrees or radians) - dex: x-component of relative eccentricity vector (dimensionless) - dey: y-component of relative eccentricity vector (dimensionless) - dix: x-component of relative inclination vector (degrees or radians) - diy: y-component of relative inclination vector (degrees or radians)

Parameters:

Name	Type	Description	Default
`x_chief`	`ndarray or list`	6D ECI state vector of the chief satellite [x, y, z, vx, vy, vz] (m, m/s), shape (6,)	required
`x_deputy`	`ndarray or list`	6D ECI state vector of the deputy satellite [x, y, z, vx, vy, vz] (m, m/s), shape (6,)	required
`angle_format`	`AngleFormat`	Format of angular elements in output (DEGREES or RADIANS)	required

Returns:

Type	Description
`ndarray`	numpy.ndarray: Relative orbital elements [da, dλ, dex, dey, dix, diy] shape (6,)

Example

import brahe as bh
import numpy as np

bh.initialize_eop()

# Define chief and deputy orbital elements (degrees)
oe_chief = np.array([bh.R_EARTH + 700e3, 0.001, 97.8, 15.0, 30.0, 45.0])
oe_deputy = np.array([bh.R_EARTH + 701e3, 0.0015, 97.85, 15.05, 30.05, 45.05])

# Convert to ECI states
x_chief = bh.state_koe_to_eci(oe_chief, bh.AngleFormat.DEGREES)
x_deputy = bh.state_koe_to_eci(oe_deputy, bh.AngleFormat.DEGREES)

# Compute ROE directly from ECI states
roe = bh.state_eci_to_roe(x_chief, x_deputy, bh.AngleFormat.DEGREES)
print(f"Relative orbital elements: {roe}")
# Relative orbital elements: [1.413e-4, 9.321e-2, 4.324e-4, 2.511e-4, 5.0e-2, 4.954e-2]

state_roe_to_eci `builtin` ¶

state_roe_to_eci(x_chief: Union[ndarray, List], roe: Union[ndarray, List], angle_format: AngleFormat) -> ndarray

Converts chief satellite ECI state and quasi-nonsingular Relative Orbital Elements (ROE) to deputy satellite ECI state.

This function converts the chief ECI state to Keplerian orbital elements, applies the ROE to obtain deputy orbital elements, then converts back to ECI state.

Parameters:

Name	Type	Description	Default
`x_chief`	`ndarray or list`	6D ECI state vector of the chief satellite [x, y, z, vx, vy, vz] (m, m/s), shape (6,)	required
`roe`	`ndarray or list`	Relative orbital elements [da, dλ, dex, dey, dix, diy] shape (6,)	required
`angle_format`	`AngleFormat`	Format of angular elements in input ROE (DEGREES or RADIANS)	required

Returns:

Type	Description
`ndarray`	numpy.ndarray: 6D ECI state vector of the deputy satellite [x, y, z, vx, vy, vz] (m, m/s), shape (6,)

Example

import brahe as bh
import numpy as np

bh.initialize_eop()

# Define chief orbital elements and convert to ECI
oe_chief = np.array([bh.R_EARTH + 700e3, 0.001, 97.8, 15.0, 30.0, 45.0])
x_chief = bh.state_koe_to_eci(oe_chief, bh.AngleFormat.DEGREES)

# Define ROE (small relative orbit)
roe = np.array([1.413e-4, 9.321e-2, 4.324e-4, 2.511e-4, 5.0e-2, 4.954e-2])

# Compute deputy ECI state from chief and ROE
x_deputy = bh.state_roe_to_eci(x_chief, roe, bh.AngleFormat.DEGREES)
print(f"Deputy ECI state: {x_deputy}")

ECI-ROE Transformations¶

state_eci_to_roe builtin ¶

state_roe_to_eci builtin ¶

state_eci_to_roe `builtin` ¶

state_roe_to_eci `builtin` ¶