State Transformations
Classical Orbital Elements (coe)
AstroRepresentations.convert6_cart_to_coe
— Functionconvert6_cart_to_coe(sv::AbstractVector{<:Number}, μ::Number)
Convert cartesian state representation into classical orbital elements.
Inputs
sv
– state vector –L, T
μ
– center gravitational parameter –L³/T²
Output
Classical orbital elements representation of the state as a SVector{6}
.
References
- Vallado, David A. - Fundamentals of astrodynamics and applications. Vol. 12. Springer Science & Business Media, 2001.
AstroRepresentations.convert6_coe_to_cart
— Functionconvert6_coe_to_cart(sv::AbstractVector{<:Number}, μ::Number)
Convert classical orbital elements state vector to cartesian state.
Inputs
sv
– Keplerian elements –L, rad
μ
– Center's gravitational parameter –L³/T²
Output
Cartesian representation of the state as a SVector{6}
.
References
- Vallado, David A. - Fundamentals of astrodynamics and applications. Vol. 12. Springer Science & Business Media, 2001.
Equinoctial Orbital Elements (equi)
AstroRepresentations.convert6_cart_to_equi
— Functionconvert6_cart_to_equi(sv::AbstractVector{<:Number}, μ::Number)
Convert cartesian state vector to Equinoctial keplerian elements.
Inputs
sv
– state vector –L, T
μ
– center gravitational parameter –L³/T²
Output
Equinoctial representation of the state as a SVector{6}
.
References
- Vallado, David A. - Fundamentals of astrodynamics and applications, 2013.
- Cefola - DOI: 10.2514/6.1972-937
AstroRepresentations.convert6_equi_to_cart
— Functionconvert6_equi_to_cart(equi::AbstractVector{<:Number}, μ::Number)
Convert equinoctial state elements to cartesian state.
Inputs
equi
– Equinoctial elements –L, rad
μ
– center gravitational parameter –L³/T²
Output
Cartesian representation of the state as a SVector{6}
.
References
- Vallado, David A. - Fundamentals of astrodynamics and applications, 2013.
- Cefola - DOI: 10.2514/6.1972-937
AstroRepresentations.convert6_coe_to_equi
— Functionconvert6_coe_to_equi(coe::AbstractVector{<:Number})
Convert classical orbital elements state vector to Equinoctial keplerian elements.
Inputs
coe
– Keplerian elements –L, rad
Output
Equinoctial representation of the state as a SVector{6}
.
References
- Vallado, David A. - Fundamentals of astrodynamics and applications, 2013.
AstroRepresentations.convert6_equi_to_coe
— Functionconvert6_equi_to_coe(coe::AbstractVector{<:Number})
Convert Equinoctial keplerian elements to classical orbital elements state vector .
Inputs
equi
– Equinoctial elements –L, rad
Output
Keplerian representation of the state as a SVector{6}
.
References
- Vallado, David A. - Fundamentals of astrodynamics and applications, 2013.
Spherical State Representation (sphe)
AstroRepresentations.convert6_cart_to_sphe
— Functionconvert6_cart_to_sphe(sv::AbstractVector{<:Number})
Convert cartesian state into spherical (ra-dec) representation.
AstroRepresentations.convert6_sphe_to_cart
— Functionconvert6_sphe_to_cart(sv::AbstractVector{<:Number})
Convert spherical (ra-dec) state into cartesian representation.
AstroRepresentations.convert3_cart_to_sphe
— Functionconvert3_cart_to_sphe(sv::AbstractVector{<:Number})
Convert cartesian position into spherical (ra-dec).
AstroRepresentations.convert3_sphe_to_cart
— Functionconvert6_sphe_to_cart(sv::AbstractVector{<:Number})
Convert spherical (ra-dec) position into cartesian.