Rocket performance with constant radial thrust acceleration in vacuum
In this paper is first found out the approximate altitude attained by the spacecraft in vacuum at any time after it is subjected to a constant radial thrust acceleration in vacuum, i.e., a variable thrust designated by constant thrust-to- weight ratio in the radial direction. The mass-variation law due to propellant consumption and the trajectory of the spacecraft in elliptic integral form in the neighborhood of the Earth and thereafter in normal integral form with sufficient accuracy are determined.
Copyright (c) 2018 Journal of Advanced Mathematics
This work is licensed under a Creative Commons Attribution 4.0 International License.
Authors who publish with this journal agree to the following terms:
- Authors retain copyright and grant the journal right of first publication with the work simultaneously licensed under a Creative Commons Attribution License that allows others to share the work with an acknowledgement of the work's authorship and initial publication in this journal.
- Authors are able to enter into separate, additional contractual arrangements for the non-exclusive distribution of the journal's published version of the work (e.g., post it to an institutional repository or publish it in a book), with an acknowledgement of its initial publication in this journal.
- Authors are permitted and encouraged to post their work online (e.g., in institutional repositories or on their website) prior to and during the submission process, as it can lead to productive exchanges, as well as earlier and greater citation of published work (See The Effect of Open Access).