ABSTRAK Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
BAB 1 Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
BAB 2 Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
BAB 3 Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
BAB 4 Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
BAB 5 Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
BAB 6 Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
COVER Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
DAFTAR PUSTAKA Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
LAMPIRAN Joshua Levin Kurniawan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
Terbatas  Irwan Sofiyan
» Gedung UPT Perpustakaan
The advancement of aerospace technology, particularly in the realm of space
exploration, has reached remarkable heights. A significant stride in this domain is
the development of Vertical Takeoff Vertical Landing (VTVL) launch vehicles,
wherein a major portion of the vehicle is reusable, making it more sustainable and
cost-effective. This feat has been successfully demonstrated by Falcon 9. The
Falcon 9 utilizes thrust vectoring control (TVC) to achieve vertical landing, a
method that involves manipulating the direction of the thrust vector. However,
implementing TVC for autonomous landing poses several challenges, particularly
in designing a control system for the vehicle during the landing phase. Based on
these challenges, this research thesis aims to contribute to the advancement of
VTVL launch vehicles by proposing a novel approach to modeling the vehicle’s
dynamics and designing controllers, thereby fostering the development of more
sustainable and cost-effective launch vehicles.
This research thesis will introduce a framework to construct a dynamic
simulation of the Falcon 9 First Stage Booster with Interstage using a multibody
approach. This involves creating a 3-D representation model and employing
numerical methods to solve the dynamic system’s state at each simulation time
step. Leveraging the linearized equation of motion, an optimal controller will be
designed using the Linear Quadratic Regulator (LQR) approach. The designed
controller will then undergo testing in the nonlinear multibody dynamic simulation
under various case conditions, including all engine operatives, one engine
operative, positive and negative initial angle of attack condition, and simulation
with noise and disturbance. In this scenario, the controller is designed to track the
target positions of 680 m for downrange distance and 20 m for altitude. From the
test result, it achieved a steady state final landing position of 680.0 m for
downrange distance and 19.3 m for altitude in the all-engine operative condition,
and 679.9 m and 20.5 m, respectively, in the one-engine operative condition.
Moreover, the controller successfully executed the landing maneuver within the
range of -11° to 4° of the initial angle of attack. For the condition where sensor
noise and disturbance in the form of severe turbulence is present, it achieved a
mean downrange distance of 680.5 m with a standard deviation of 5.482 m and a
mean altitude of 20.64 m with a standard deviation of 0.7969 m.