Multistage launch vehicle design with thrust profile and trajectory optimization /

Download

index.pdf

Date

2014

Author

Civek Coşkun, Ezgi

Metadata

Show full item record

Item Usage Stats

473
views

280
downloads

In the frame of this thesis, a Matlab® based design tool utilizing a general purpose optimal control solver GPOPS-II® was developed for the optimization of ascent trajectories of multistage launch vehicles. This tool can be utilized both for preliminary mission design of an existing launch vehicle and conceptual design of a new launch vehicle. In the preliminary mission design of an existing launch vehicle, maximizing payload mass is a very common performance measure. Therefore, a trajectory optimization code was developed to determine the optimal trajectory in terms of position and velocity, and the control functions corresponding to that trajectory while maximizing the payload mass. Whereas in the conceptual design of a new launch vehicle, minimization of gross lift-off mass for a specific mission is the primary objective, and staging is an effective way to reduce the vehicle gross lift-off mass. For this purpose, a staging optimization code was developed to determine the staging parameters (mass distribution between stages, propellant and structural mass of each individual stage) which minimize the gross lift-off mass. In this thesis, staging and trajectory optimization codes were integrated by two different manners, namely the decoupled and the coupled approaches, so as to determine the sizing, burn time and thrust time history of each stage together with the optimal trajectory of the launch vehicle. Thus, a quick and effective method to find optimal vehicle configurations in the early design phases was achieved.

Subject Keywords

Trajectory optimization., Launch vehicles (Astronautics).

URI

http://etd.lib.metu.edu.tr/upload/12618011/index.pdf
https://hdl.handle.net/11511/23929

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

Discrete sizing optimization of steel trusses under multiple displacement constraints and load cases using guided stochastic search technique Azad, S. Kazemzadeh; Hasançebi, Oğuzhan (2015-08-01) The guided stochastic search (GSS) is a computationally efficient design optimization technique, which is originally developed for discrete sizing optimization problems of steel trusses with a single displacement constraint under a single load case. The present study aims to investigate the GSS in a more general class of truss sizing optimization problems subject to multiple displacement constraints and load cases. To this end, enhancements of the GSS are proposed in the form of two alternative approaches t...
Multi-objective morphing wing optimization for an Unmanned Air Vehicle Körpe, Durmuş Sinan; Özgen, Serkan (null; 2017-07-03) This work describes the optimization process of a morphing wing for an unmanned air vehicle (UAV) by using multi-objective gradient based optimization algorithmin which maximizationof lift to dragratioand minimization of bending moment at wing rootchord planearedefined asthe objective functions. Six different optimization problems are solved by changing weighted sum coefficients of the objective functions in order to observe the morphing wing planform and the airfoil shape chang...
VERIFICATION OF A FINITE ELEMENT MODEL OF AN UNMANNED AERIAL VEHICLE WING TORQUE BOX VIA EXPERIMENTAL MODAL TESTING Unlusoy, Levent; Şahin, Melin; Yaman, Yavuz (2012-07-04) In this study, the detailed finite element model (FEM) of an unmanned aerial vehicle wing torque box was verified by the experimental modal testing. During the computational studies the free-free boundary conditions were used and the natural frequencies and mode-shapes of the structure were obtained by using the MSC Software. The results were then compared with the experimentally obtained resonance frequencies and mode-shapes. It was observed that the frequencies were in close agreement having an error with...
MULTI MODE PROJECTILE TRACKING WITH MARGINALIZED PARTICLE FILTER Bilgin, Ozan Ozgun; Demirekler, Mübeccel (2015-10-30) In this study, dynamic models for thrusting and ballistic flight modes of multi mode projectile are obtained and Marginalization method is applied by separation of the linear and nonlinear parts of state space model. In Marginalized Particle Filter (MPF), dimension of the nonlinear system is reduced so that the model can be utilized to obtain better estimates of the state using the same number of particles as that of standard particle filter. The Extended Kalman Filter (EKF), the Particle Filter (PF) and th...
Attitude control of multiple rigid body spacecraft with flexible hinge joints Akbulut, Burak; Özgören, Mustafa Kemal; Department of Mechanical Engineering (2009) Control algorithm is developed for a satellite with flexible appendages to achieve a good pointing performance. Detailed modeling activity was carried out that consists of sensor and actuator models, disturbances and system dynamics. Common hardware found in the spacecraft such as reaction wheels, gyroscopes, star trackers etc. were included in the model. Furthermore, the Newton-Euler method is employed for the derivation of multi-body equations of motion. Evaluation of the pointing accuracy with proper poi...

Citation Formats

E. Civek Coşkun, “Multistage launch vehicle design with thrust profile and trajectory optimization /,” Ph.D. - Doctoral Program, Middle East Technical University, 2014.