Abstract:This study analyzes the effects of disturbance rejection and radome error on the stability of guidance systems. First, disturbance rejection rate transfer function (DRRTF) models are established. Second, the Lyapunov stability of a proportional navigation guidance system is proposed. The passivity theorems are introduced for the analysis of the Lyapunov stability of the nonlinear time-varying system. Finally, the influence of the different DRRTF models on the stability of the guidance system is analyzed by mat… Show more
“…According to Ref. 3, the refraction by the radome causes a false line-of-sight (LOS) angle called the radome refraction angle. Figure 1 shows the basic geometry for radome analysis considering the stable seeker tracking.Figure 1.Basic geometry for radome analysis.…”
Section: Model Derivationmentioning
confidence: 99%
“…The devastating influence of radome errors on the guidance loop is analyzed in Refs. 3 and 4, with an increase in miss distance as a result of the effect. Hence, the approach of getting true LOS angular rate and obtaining better interception performance under the existence of radome error are very worthy of being studied.…”
This paper presents an integrated guidance and control design for the homing missiles with the radome error compensation to address the guidance problems caused by radome. Firstly, a mathematics model of the integrated guidance and control system with the compensation for the radome error is built by integrating the missile dynamics and the engagement kinematics between the missile and ground target on the longitudinal motion. Secondly, the model is transformed into a normal form by nonlinear coordinate transformation because the system is a time-varying system with mismatched uncertainties. Thirdly, an adaptive control law of the system is designed by adopting the sliding mode control theory, and the stability of the closed-loop system is also conducted. Finally, the simulation proves that the proposed integrated guidance and control scheme can effectively compensate for the radome error and ensure the hit-to-kill attack to the target.
“…According to Ref. 3, the refraction by the radome causes a false line-of-sight (LOS) angle called the radome refraction angle. Figure 1 shows the basic geometry for radome analysis considering the stable seeker tracking.Figure 1.Basic geometry for radome analysis.…”
Section: Model Derivationmentioning
confidence: 99%
“…The devastating influence of radome errors on the guidance loop is analyzed in Refs. 3 and 4, with an increase in miss distance as a result of the effect. Hence, the approach of getting true LOS angular rate and obtaining better interception performance under the existence of radome error are very worthy of being studied.…”
This paper presents an integrated guidance and control design for the homing missiles with the radome error compensation to address the guidance problems caused by radome. Firstly, a mathematics model of the integrated guidance and control system with the compensation for the radome error is built by integrating the missile dynamics and the engagement kinematics between the missile and ground target on the longitudinal motion. Secondly, the model is transformed into a normal form by nonlinear coordinate transformation because the system is a time-varying system with mismatched uncertainties. Thirdly, an adaptive control law of the system is designed by adopting the sliding mode control theory, and the stability of the closed-loop system is also conducted. Finally, the simulation proves that the proposed integrated guidance and control scheme can effectively compensate for the radome error and ensure the hit-to-kill attack to the target.
“…So there exist L 0 > 0, γ 0 ∈ ð0, 05Þ, and a finite adjustment time T reach , and then, the solution of the system (18)…”
Section: International Journal Of Aerospace Engineeringmentioning
confidence: 99%
“…The interference torques of the seeker include spring torques, friction torques, damping torques, etc. The mass imbalance and the coupling between the frames will also cause interference torques [17,18]. The existence of interference torque will make the missile body disturbance to be coupled to the line-of-sight angular velocity information.…”
We propose a new DRR (Disturbance Rejection Rate) compensation method of a roll-pitch seeker based on ESO (extended state observer). The characteristics of a roll-pitch seeker and the DRR definition of two frames of a roll-pitch seeker are analyzed. The influence of different interference torques and different frequency bandwidths on the compensation effect is analyzed. Modeling and simulation of the guidance system of a roll-pitch seeker with the parasitic loop of DRR are carried out. Influence of the new DRR compensation method on dimensionless miss distance is analyzed. Mathematical simulation is established to compare the new ESO-based DRR compensation method with the existing methods such as the feedforward method and Kalman filter method. The analysis and simulation results show that the new ESO-based DRR compensation method has the advantages of high precision, good applicability, and easy adjustment, and the new method can effectively reduce the dimensionless miss distance with different types of input errors. The research of this proposed new method can provide a reference for the latest generation air-to-air missile operations in a high-altitude and high-speed environment and the high-precision research of a roll-pitch seeker.
“…In anti-aircraft missile homing systems equipped with both mechanically and electronically controlled seekers, one observes a phenomenon of the impact of the airframe oscillations on the operation of the tracking systems. Due to the imperfect disturbance rejection performance, missile motion may severely degrade the tracking accuracy [1][2][3][4][5]. This situation is particularly disadvantageous during the terminal guidance phase, as it requires a very rapid reaction on the part of the missile, involving significant rotations of its airframe.…”
A description is given of an application of a linear-quadratic regulator (LQR) for stabilizing the characteristics of an anti-aircraft missile, and an analytical method of selecting the weighting elements of the gain matrix in feedback loop is proposed. A novel method of LQR tuning via a single parameter ς was proposed and tested. The article supplements and develops the topics addressed in the author’s previous work. Its added value includes the observation that the solutions obtained are symmetric pairs, and that the tuning parameter ς proposed for the designed linear-quadratic regulator enables the selection of suitable parameters for the airframe stabilizing loop for the majority of the analytical solutions of the considered Riccati equation.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.
