Modeling and simulation of a canard-based sounding rocket dynamics at climb and descent phases

A proper rocket dynamic model is required in order to obtain the precise prediction from flight test. The objective of this paper is to construct some linear models which are obtained from linearizing nonlinear models on the certain flight conditions i.e. climb phase with supersonic speed and descen...

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Bibliographic Details
Main Authors: Hanif, Azizul, Putro, Idris Eko, Duhri, Rahmat Alfi, Hakiki, Hakim, Arif Nur, Mariani, Lilis, Andiarti, Rika, Artono, Endro
Format: Conference Proceeding
Language:English
Subjects:
Angle of attack
Descent
Dynamic models
Flight conditions
Flight tests
Pitch (inclination)
Sounding rockets
Supersonic speed
Transonic speed
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Summary:A proper rocket dynamic model is required in order to obtain the precise prediction from flight test. The objective of this paper is to construct some linear models which are obtained from linearizing nonlinear models on the certain flight conditions i.e. climb phase with supersonic speed and descent phase with transonic speed. Linearized model is derived by trimming the nonlinear model using small perturbation approach at a certain flight condition. Simulation results reveal that the linear model is accurate enough to represent the rocket dynamic indicated by capability of the linear model to resemble the nonlinear model at both flight conditions with acceptable mean absolute percentage error (MAPE) values. In the climb case for longitudinal mode, the MAPE of pitch angle is 1%, pitch rate is 18%, and angle of attack is 9%. In the descent case for longitudinal mode, the MAPE values are bigger than the climb case, i.e. 9%, 35%, and 25% respectively.
ISSN:0094-243X
1551-7616
DOI:10.1063/5.0181512