Flight Performance Of Constant/ Variable Thrust Programmed Rocket In Vacuum With Constant Thrust Inclination With Respect To Horizon For Given Launching Velocity and Angle
Abstract
 The rocket is launched at an angle of elevation with an initial velocity and thereafter is maneuvered with a constant or variable thrust which is again inclined at a constant angle with respect to the horizon. The overall range consisting of power and coasting phases has been determined. Finally this paper deals with maximization of the range with respect to optimum launching angle and thrust inclination. Two numerical examples are cited.
Downloads
References
Miele,A.(1962),Flight Mechanics, Vol1, PP.335-355, Addison-Wesley, Pub. Company, Inc. ,Reading, Massachussets.
S.N. Maitra, Variable Thrust Programming For Rockets Flown With Constant Thrust Inclination With Respect To Horizon In Vacuum, Journal Of Aero. Soc. Of India, Vol 32,Feb-Nov 1980,PP.85-93.
Copyright (c) 2015 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).