convert3_cart_to_sphe(sv::AbstractVector{<:Number})

Convert cartesian position into spherical (ra-dec).

convert6_sphe_to_cart(sv::AbstractVector{<:Number})

Convert spherical (ra-dec) position into cartesian.

convert6_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.

convert6_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

convert6_cart_to_sphe(sv::AbstractVector{<:Number})

Convert cartesian state into spherical (ra-dec) representation.

convert6_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.

convert6_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.

convert6_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

convert6_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.

convert6_sphe_to_cart(sv::AbstractVector{<:Number})

Convert spherical (ra-dec) state into cartesian representation.

eca_to_tra(eca::Number, ecc::Number)

Convert eccentric anomaly to true anomaly.

hya_to_tra(hca::Number, ecc::Number)

Convert hyperbolic anomaly to true anomaly.

man_to_tra(man::Number, ecc::Number)

Convert mean anomaly to true anomaly.

par_to_tra(pca::Number)

Convert parabolic anomaly to true anomaly.

tra_to_eca(tra::Number, ecc::Number)

Convert true anomaly to eccentric anomaly.

tra_to_hya(tra::Number, ecc::Number)

Convert true anomaly to hyperbolic anomaly.

tra_to_man(tra::Number, ecc::Number)

Convert true anomaly into mean anomaly

tra_to_par(ta::Number)

Convert true anomaly to parabolic anomaly.