-
[show abstract]
[hide abstract]
ABSTRACT: Subjects related to a robust multivariable autopilot design are
examined in this paper. First, a canonical robust control design
formulation is introduced and is illustrated by formulating an
integrated autopilot design problem. This formulation addresses the
considerations of missile command following, model parameter variations,
actuator dynamics, flexible dynamics, and parasitic feedback effects.
Then, three robust autopilot designs for the HAVE DASH II missile system
are executed. The controllers are solved using the generalized
Hamiltonian approach which unifies a class of robust control designs in
the same framework in terms of the formulation, data structure, and
solution algorithm. The simulation shows that the designs achieve good
response against significant kinematic and inertia couplings and
aerodynamic parameter variations
American Control Conference, 1995. Proceedings of the; 07/1995
-
[show abstract]
[hide abstract]
ABSTRACT: An approach to integrated guidance/autopilot design is considered
in this study. It consists of two parts: 1) recognizing the importance
of polar coordinates to describe the end game in terms of problem
description and measurement acquisition, the terminal guidance problem
is formulated in terms of polar coordinates; 2a) through the use of the
state transition matrix of the intercept dynamics, a closed form
solution for the transverse command acceleration is obtained; and 2b)
through a commonly used approximation on time-to-go and a coordinate
transformation, a family of proportional navigation optimal guidance
laws is obtained in a closed form. A typical element of such a guidance
law is combined with the autopilot dynamics to result in a feedback
control law in terms of output variables
Control Applications, 1993., Second IEEE Conference on; 10/1993
-
Aerospace Control Systems, 1993. Proceedings. The First IEEE Regional Conference on; 06/1993
-
Aerospace Control Systems, 1993. Proceedings. The First IEEE Regional Conference on; 06/1993
-
[show abstract]
[hide abstract]
ABSTRACT: The feasibility of autopilot design for highly maneuverable
bank-to-turn (BTT) missiles using feedback-linearization-based
approaches is investigated. Two schemes, namely, feedback linearization
and robust feedback linearization, are designed and compared based on a
full-scale six-degree-of-freedom HAVE DASH II terminal homing missile
model. Although the feedback linearization controller is quite
satisfactory in general, a sizable coupling between the longitudinal
motion and lateral motion for large maneuvers is observed. This is
attributed to the uncertainties arising from the approximation of the
aerocoefficients and model simplification. The second scheme, which adds
a robust outer-loop design based on Lyapunov's second method to the
first scheme in order to account for this uncertainty, shows a
significant improvement over the first scheme
Control Applications, 1992., First IEEE Conference on; 10/1992
-
[show abstract]
[hide abstract]
ABSTRACT: The design of a robust full-envelope autopilot for the HAVE DASH
II missile system is delineated. Existing control design methods are
examined and integrated to meet the stringent performance requirements
of the missile autopilot design
Control Applications, 1992., First IEEE Conference on; 10/1992
-
[show abstract]
[hide abstract]
ABSTRACT: An endgame analysis and design framework are described. The
framework can aid in understanding of the endgame dynamics, identifying
critical design parameters, and bringing insights to the
guidance/control design. A worst-case analysis approach is introduced
and applied to the HAVE DASH II system. The analysis approach
generalizes the covariance analysis method and provides a more accurate
prediction of the engagement performance. On the basis of the analysis
framework and performance measure, robust control design methods can be
applied to obtain a robust integrated guidance and control design
Control Applications, 1992., First IEEE Conference on; 10/1992
-
[show abstract]
[hide abstract]
ABSTRACT: A generalized singular robust control approach for missile
autopilot design is described. This approach unifies the generalized
singular linear quadratic linear quadratic Gaussian, and worst-case
H <sup>∞</sup> control design methods using the
generalized Hamiltonian formulation and structure algorithm. Extensions
of this method to multiple-criterion autopilot design problems are also
discussed. The approach considered provides a constructive algorithm to
design a multiple-criterion controller and offers new insights into the
relationship between multiple
H <sub>2</sub>/ H <sup>∞</sup> and multiple H
<sup>∞</sup>/ H <sup>∞</sup> designs
Decision and Control, 1991., Proceedings of the 30th IEEE Conference on; 01/1992
-
[show abstract]
[hide abstract]
ABSTRACT: The adaptive management of a multisensor system is indispensable
for ensuring the synergistic use of multiple sensors to improve system
performance. Two aspects of the multisensor system are addressed. First,
the problem of adaptive management of multiple sensors as a function of
environmental and operational conditions is considered. Second, an
investigation of various fusion schemes at different levels is performed
by considering the use of hybrid measurements which are typically
continuous-valued and discrete-valued. The hybrid-measurement-based
estimation of the jump mode, which suitably describes the environmental
and operational condition changes, is illustrated through simulation. It
is concluded that the improved mode estimation can be used by a
multisensor adaptive management system for environmental
adaptation
Decision and Control, 1991., Proceedings of the 30th IEEE Conference on; 01/1992
-
[show abstract]
[hide abstract]
ABSTRACT: Current air-to-air missile guidance and control technology is assessed. Areas explored include target state estimation, advanced guidance laws, and bank-to-turn autopilots. The assumptions, benefits, and limitations of recent applications of nonlinear filtering, adaptive filtering, modern control, adaptive control, dual control, differential game theory, and modern control design techniques to the air-to-air missile problem are discussed.< >
IEEE Control Systems Magazine 11/1989;
-
[show abstract]
[hide abstract]
ABSTRACT: Some issues associated with the design and implementation of an optimal guidance algorithm in Ada for a tactical missile are presented. Limited microprocessor throughput appears to be the most critical implementation issue. This is associated with the run-time overhead of the Ada language and the efficiency of Ada cross-compilers.
American Control Conference, 1988; 07/1988
