11-01-2022, 05:54 PM
This HP Program calculates the single impulsive deorbit maneuver required to establish a reentry altitude and flight path angle relative to a non-rotating, spherical Earth. The algorithm uses a tangential delta-v applied opposite to the velocity vector of an initial circular orbit to establish the de-orbit trajectory.
The calculator will request the altitude of the initial circular orbit, the altitude at the entry interface (EI) and the inertial flight path angle at the EI. Altitudes should be input in kilometers and the flight path angle in degrees.
The software will compute and display the orbital elements of the deorbit trajectory and the magnitude of the required deorbit delta-v. It will also provide the Earth-centered-fixed (ECF) flight path angle and speed at entry.
The attached zip archive contains a PDF that explains how the algorithm works.
The calculator will request the altitude of the initial circular orbit, the altitude at the entry interface (EI) and the inertial flight path angle at the EI. Altitudes should be input in kilometers and the flight path angle in degrees.
The software will compute and display the orbital elements of the deorbit trajectory and the magnitude of the required deorbit delta-v. It will also provide the Earth-centered-fixed (ECF) flight path angle and speed at entry.
The attached zip archive contains a PDF that explains how the algorithm works.