IEEE - Aerospace and Electronic Systems - April 2023 - 30

Neural Network-Based Controller for Terminal Guidance Applied in Short-Range Rockets
Figure 1.
Rocket configuration.
(NNs). A deep NN is presented in Igreja and Lemos [12]
to be used in launch vehicles. In space rocket low thrust
transfers, an NN is used in Izzo and €Ozt€urk [13].
The purpose of this research is to use an efficient NNbased
approach to improve existing control techniques
with the aid of a versatile mathematical nonlinear flight
dynamics model. The idea is to use solely data from inertial
measurement devices to intelligently decide controller
settings during flight.
CONTRIBUTIONS
ROCKET INPUT PARAMETERS
The primary contribution of this scientific research is the
use ofNNs to create GNC systems for a short-ranged ballistic
rocket when GNSS signals are not an alternative.
The purpose is to use data from an IMU to forecast the
needed deflection of the rocket actuators, enhancing precision
at the time of impact. The key benefit of this development
over old methods is that accuracy may be enhanced
automatically throughout the learning phase of a NN.
The suggested method uses NNs to estimate the
needed movement of the rocket's canard actuators. The
inputs for NNs are the magnitudes detected by the IMU,
and the outputs are the needed deflections of each of the
four canard actuators. The substantial interaction between
lateral and normal rocket nonlinear dynamics may be handled
with this NN-based technique.
A flight dynamics model that simulates the rapid
dynamics of the rocket and takes into consideration nonlinearities
in aerodynamic forces and moments is developed
and used to create a realistic simulation campaign. These
algorithms' precision and usefulness in nondeterministic
contexts, launch circumstances, and projectile conditions
are demonstrated by simulation results.
The rest of this article is organized as follows. The
system modeling is detailed in the " Modeling of System "
section. The " Navigation, Guidance, and Control " section
discusses algorithms for navigation, guidance, and control.
The simulation results are revealed in the " Numerical
30
Figure 2.
Aerodynamic parameters versus Mach numbers.
IEEE A&E SYSTEMS MAGAZINE
APRIL 2023
A 65-mm axis-symmetric rocket [7], [8] is used to test the
suggested GNC technique. The rocket has stabilizing nonmaneuvering
rear wings and extended canard control fins
(see Figure 1). A fuse attached to the rocket's tip serves as
the maneuvering mechanism. It is composed of four
canard surfaces that are separated two by two to provide a
Results " section. Finally, the " Conclusions " ends this
article.
MODELING OF SYSTEM
This section covers the plant's description, the nonlinear
flight mechanics model, and the actuation and sensor models
utilized for navigation.

IEEE - Aerospace and Electronic Systems - April 2023

Table of Contents for the Digital Edition of IEEE - Aerospace and Electronic Systems - April 2023

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