Homing Missiles Research Articles

Stability of Single-Channel Homing Rolling Aerospace Vehicle

This paper aims to analyze the stability of a special class of single-channel slow-rotating homing missiles using the Frank–Wall stability criterion. To achieve this, starting from the model of a slow-rolling missile with six degrees of freedom (6 DOFs) in the body frame, a 6-DOFs model in the Resal frame is obtained, which is used to linearize the coupled commanded motion. Based on the linearized model, we obtain the structural scheme of the commanded object and define the flight quality parameters. The obtained linear model has a complex representation (with real and imaginary parts) due to the coupling between longitudinal channels for the rolling missile. Then, the kinematic guidance equations, the seeker equations and the actuator relations using a switching function, specific to the slow-rolling single-channel missile, are defined. The guidance kinematic equations, the seeker equations and the actuator model are linearized in the Resal frame, and the structural diagram of the homing missile is constructed. Starting from this, the characteristic polynomial having complex coefficients is determined and then analyzed with the Frank–Wall stability criterion. Based on the analysis, a stability range is determined for the navigation constant (k), and a minimum and possibly a maximum limit for the time to hit the target tgo is obtained. The stability range defined for the navigation constant in the linear model is finally validated in the nonlinear model in the body frame.

Adaptive control law based integrated guidance and control design for missile with the radome error compensation

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.

Target identification and control model of autopilot for passive homing missiles

Target identification and control model of autopilot for passive homing missiles

Three-dimensional impact-time-constrained proportional navigation guidance using range-varying gain

This paper presents a novel feedback guidance law to address the impact time control problem of homing missiles in three-dimensional (3D) space. First, a range-varying gain is incorporated into the conventional proportional navigation guidance (PNG) law, which leads to globally precise time-to-go solution and achievable impact time region. Next, an impact time control guidance (ITCG) law is developed by augmenting the proposed varying-gain PNG law with a feedback biased term. Unlike most existing studies, the proposed ITCG law does not involve any linearized approximations or numerical iterative schemes. Furthermore, it can achieve the desired impact time and high-precision interception for a wide launch envelop with arbitrary initial leading angles. Finally, extensive numerical simulations, including comparison studies and Monte Carlo assessments, are carried out to validate the theoretical findings.

A Homing Missile-Like Nanotherapeutic with Single-Atom Catalytic Sites for In Situ Elimination of Intracellular Bacterial Pathogens.

Intracellular bacterial pathogens hiding in host cells tolerate the innate immune system and high-dose antibiotics, resulting in recurrent infections that are difficult to treat. Herein, a homing missile-like nanotherapeutic (FeSAs@Sa.M) composed of a single-atom iron nanozyme (FeSAs) core coated with infected macrophage membrane (Sa.M) is developed for in situ elimination of intracellular methicillin-resistant S. aureus (MRSA). Mechanically, the FeSAs@Sa.M initially binds to the extracellular MRSA via the bacterial recognition ability of the Sa.M component. Subsequently, the FeSAs@Sa.M can be transported to the intracellular MRSA-located regions in the host cell like a homing missile under the guidance of the extracellular MRSA to which it is attached, generating highly toxic reactive oxygen species (ROS) for intracellular MRSA killing via the enzymatic activities of the FeSAs core. The FeSAs@Sa.M is far superior to FeSAs in killing intracellular MRSA, proposing a feasible strategy for treating intracellular infections by in situ generating ROS in bacterial residing regions.

Optimal predictive guidance law based on guidance law identification using variable structure interactive multiple guidance law model

For a defender protecting a target from an incoming high-maneuvering homing missile, an Optimal Predictive Guidance Law (OPGL) is proposed based on a guidance law identification algorithm. First, a guidance law identification algorithm based on the Interactive Multiple Guidance law Model (IMGM) is designed. IMGM uses multiple sub-filters for parallel processing, and there is interaction between the inputs and outputs of the sub-filters. Second, the VSIMGM algorithm is further designed based on the IMGM algorithm. In this algorithm, a new guidance law model subset is constructed based on the original guidance law model set. By reducing the number of models, the model error is reduced, and the identification probability of the guidance law model is improved. Then, based on the identification result of the identification algorithm, the OPGL is given by using the variational method through the steps of linearizing the kinematic model and reducing the order of state equation. The OPGL reduces the overload requirement of the defender and improves interception accuracy without assuming the maneuver mode of a homing missile. Finally, the effectiveness of the proposed OPGL and guidance law identification algorithm based on VSIMGM is demonstrated using numerical simulation. Compared with the guidance law identification algorithm based on MMAE and IMGM, the guidance law identification algorithm based on VSIMGM can quickly, stably, and accurately identify the guidance law. In addition, based on the guidance law identification results of the homing missile, compared with proportional navigation, augmented proportional navigation, differential game guidance (DGG), and sliding mode guidance (SMG), OPGL can reduce the required overload of the missile and achieve accurate interception.

Time and FOV constraint guidance applicable to maneuvering target via sliding mode control

This paper focuses on designing a novel homing missile guidance law applicable to intercepting maneuvering target while considering time and field-of-view (FOV) constraints. To realize accurate zero miss-distance and time control, a sliding mode manifold consisting of the range-to-go, expected impact time and two newly-defined weighting functions is constructed based on a nonlinear model, which can guarantee the interception at a prescribed impact time once the sliding mode has reached. Then, an overall guidance command is derived by taking both finite time convergence of sliding mode manifold and non-singularity into consideration. A new guidance strategy with boundary conditions is proposed to satisfy FOV requirement. Furthermore, the feasibility for intercepting maneuvering target is demonstrated via a Lyapunov-like approach. Numerical simulations validate the performance of the proposed guidance law, and a comparative study indicates that the proposed method is superior to relative guidance laws in terms of maneuvering target interception.

Field-to-View Constrained Integrated Guidance and Control for Hypersonic Homing Missiles Intercepting Supersonic Maneuvering Targets

An integrated guidance and control (IGC) scheme considering the field-of-view (FOV) constraint is proposed in this paper for hypersonic skid-to-turn (STT) missiles with a strapdown seeker intercepting a high-speed maneuvering target, which is based on the backstepping control (BC), barrier Lyapunov function (BLF), sliding mode control (SMC), dynamic surface control (DSC), and reduced-order extended state observer (ESO). First, a fifth-order strict feedback IGC model considering the rudder delay dynamics is derived, which also considers the drag effect on the axial velocity. Second, the missile guidance control system based on the BC consists of seeker, guidance, angle-of-attack, attitude, and rudder subsystems. The seeker subsystem was designed based on the BLF, and the other four subsystems were designed based on the SMC. The system-lumped disturbances, including unknown target maneuvers, unmodeled parts, perturbations caused by aerodynamic parameter variations, and external disturbances, were estimated and compensated for using the reduced-order ESO. The DSC prevented the “differential explosion” caused by virtual control commands introduced by the BC. Subsequently, the stability of the closed-loop system was strictly proven using the Lyapunov theory, and the boundedness of the FOV angle was strictly derived. Finally, the simulation results demonstrated the effectiveness and robustness of the proposed IGC scheme.

In-Flight Radome Slope Estimation for Homing Guidance Using Bearing-Only Measurement via Gaussian Process Regression

The radome refraction problem gives rise to guidance performance deterioration for homing missiles. Aiming to eliminate the effect of radome refraction on the radar seeker, a novel method is proposed for correcting the radome-induced measurement error by using the estimated guidance information. A dynamic model for the estimation system is formulated and the guidance information is estimated online via a multiple-model filtering framework. A Gaussian process regression scheme is introduced to reconstruct the mapping model with respect to the radome error and look angle. Furthermore, an analytical expression for radome slope estimation is derived by calculating the derivative of the surrogate function, represented with Gaussian process models. The contaminated measurement is corrected based on the estimated guidance information and radome slope. Extensive simulation results illustrate that the proposed method is able to estimate the radome slope accurately and improve the guidance accuracy effectively.

Angular acceleration compensation guidance law for passive homing missiles

Abstract Proportional navigation guidance law (PNG) is widely used for passive homing missiles. But PNG often suffers from inaccurate tracking of target or even failure when the target is maneuvering quickly or releasing artificial decoys. In order to solve this problem, the angular acceleration compensation guidance law (AACG) is constructed by using line of sight (LOS) angular velocity and LOS angular acceleration. The stability analysis with Lyapunov stability theory shows that AACG system is asymptotically stable on a large scale under certain stability constraint conditions. AACG command is designed to be perpendicular to the LOS and optimized by gravity compensation. AACG is neither dependent on target acceleration nor the distance between the missile and the target. The numerical simulation results indicate that AACG has good guidance performance on air-to-air missiles when the target maneuvers violently or releases artificial decoys in the endgame term.

A Convex Programming-Based Approach to Trajectory Optimization for Survivability Enhancement of Homing Missiles

A Convex Programming-Based Approach to Trajectory Optimization for Survivability Enhancement of Homing Missiles

An approach for object tracking, categorization, and autopilot guidance for passive homing missiles

An approach for object tracking, categorization, and autopilot guidance for passive homing missiles

Synthesis of the Anti-Ship Missile Homing System while Ensuring an Acceptable Oscillation Index of the Stabilization System

Synthesis of the Anti-Ship Missile Homing System while Ensuring an Acceptable Oscillation Index of the Stabilization System

Model predictive guidance for active aircraft protection from a homing missile

This paper proposes a novel guidance law based on model predictive control for protecting an aircraft from a homing missile. Considering that in the target-missile-defender engagement the attacking missile is pursuing the target aircraft by employing a known linear guidance law, a non-linear predictive model for the engagement is established. This predictive model allows converting the three-body engagement to a one-on-one engagement. The time-to-go for the defender towards the future position of the incoming missile is analytically derived, indicating that the optimal time for the defender to intercept the incoming missile is a fixed-point of a real-valued function. As a result, the optimal interception duration can be obtained by a standard fixed-point iteration method, and thus the interception point can be readily predicted via integrating the predictive model. The guidance command is generated by directly leading the defender to the predicted intercept point. Numerical simulations in different scenarios validate the algorithm to be computationally efficient, and demonstrate that the proposed strategy outperforms previous techniques in terms of miss distance, engagement duration, and the control effort.

Generalized Guidance Formulation for Impact Angle Interception with Physical Constraints

This paper proposes an optimal impact angle control guidance law for homing missiles with a narrow field-of-view of the seekers. As groundwork for designing a guidance law, we first present a general guidance structure that can achieve any terminal constraint of the line-of-sight rate based on the optimal control theory. We configure the desired profile of the line-of-sight rate using a saturation function whose exact form is determined to satisfy the required boundary conditions. By combining the line-of-sight rate profile with the optimal guidance structure, we develop a guidance law that achieves an impact angle interception with the field-of-view constraint. Herein, as the entire guidance structure is derived based on exact kinematics without any approximation, the proposed law ensures the accurate impact angle interception for various engagement scenarios. This precise consideration of the engagement kinematics also accurately ensures the energy optimality of preventing the excessive use of control inputs when homing. To evaluate the performance of the proposed method, numerical simulations with various engagement scenarios are conducted, and the results demonstrate that the proposed law allows missiles to accurately intercept their targets with the desired impact angles and without violating the prescribed field-of-view constraint.

New Look-Angle Tracking Guidance Strategy for Impact Time and Angle Control

This paper presents a new guidance strategy for a certain class of homing missiles subject to various terminal constraints and lateral acceleration limit. To achieve zero miss distance in the presence of various terminal impact constraints, a planar engagement scenario of missiles is considered to develop a feedback guidance law of tracking a time-varying look angle that is modeled as an inverse tangent function. The proposed strategy can be applied to both the impact time control and the impact time and angle control guidance problems. Furthermore, it does not require any forms of time-to-go estimation, numerical iterations, and linearization procedures. Numerical simulations are conducted to validate the effectiveness, robustness, and energy efficiency of the proposed guidance strategy in comparison with other existing guidance strategies.

Synthesis of a High-Precision Missile Homing System with an Permissible Stability Margin of the Normal Acceleration Stabilization System

The proportional guidance method-based missile homing systems (MHS) have been widely used the real-world environments. In these systems, in order to destroy the targets at different altitudes, a normal acceleration stabilization system (NASS) is often utilized. Therefore, the MHS are complex and the synthesis of these systems are a complex task. However, it is necessary to synthesize NASS during the synthesis of the MHS. To simplify the synthesis process, a linear model of the NASS is used. In addition, we make use of the available commands in Control System Toolbox in MATLAB. Because the Toolbox has the commands to describe the transfer function, determine the stability gain margin, and the values of the transient respond of the linear automatic systems. Thus, this article presents two methods for synthesizing the missile homing systems, including (i) a method for synthesizing the MHS while ensuring the permissible stability gain margin of the NASS, and (ii) a method for synthesizing the MHS while ensuring the permissible stability margin of the NASS by overshoot. These techniques are very easy to implement using MATLAB commands. The synthesis of the proposed MHS is carried out by the parametric optimization method. To validate the performance of the proposed techniques, we compare them withthe MHS synthesized by ensuring the stability margin of the NASS bythe oscillation index. The results show that, two our proposed methods and the existing method provide the same results in terms of high-precision. Nevertheless, the proposed methods are simple and faster than the conventional method. The article also investigates the effect of gravity, longitudinal acceleration of the rocket, andblinding of the homing head on the accuracy of the synthesized MHS. The results illustrate that they have a little effect on its accuracy.

Modified three‐dimensional true proportional navigation and its inverse optimal form

AbstractA novel three‐dimensional modified true proportional navigation (MTPN) guidance and its inverse optimal form are proposed for the interception of the nonmaneuvering and maneuvering targets, and the nonlinear dynamic characteristics of pursuit situations and target maneuvers are taken into full account. The proposed approach is feasible without knowing any prior information or estimate of the target maneuvers, which are regarded as the unknown disturbance input. Therefore, the TPN‐type guidance is extended to intercept the maneuvering targets with bounded unknown accelerations. Moreover, the explicit physical significance is given for each component of the navigation gain expression of MTPN. The inverse optimal control approach and the input‐to‐state stability are introduced to the MTPN design. Using the MTPN, the homing missile can conduct the terminal homing guidance phase in any particular direction with respect to their nonmaneuvering or maneuvering targets through choosing an appropriate inertial reference coordinate system in practice. Using the proposed schemes, the line‐of‐sight (LOS) rate is globally exponentially stable for nonmaneuvering targets, and is input‐to‐state stability (ISS) for maneuvering targets with bounded unknown accelerations. Performed simulation results have confirmed the effectiveness of the proposed scheme.

Multi-agent cooperative multi-model adaptive guidance law

ABSTRACTA multi-agent engagement scenario is considered in which a high-value aircraft launches two defenders to intercept two homing missiles aimed at the aircraft. Under the assumption that all aircrafts have first-order linear dynamic characteristics, a combined multiple-mode adaptive estimation (MMAE) and a two-way cooperative optimal guidance law are proposed for the target–defenders team. Considering the full cooperation of the target and both the two defenders, the two-way cooperative strategies provide the analytical expressions for their optimal control input, enabling the target–defenders team to intercept the missiles with minimal control effort. To successfully intercept the missiles, MMAE is used to identify the guidance laws adopted by the missiles and estimate their states. The simulation results show that the target cooperating with the defenders to perform lure manoeuvres for the missiles can improve the guidance performance of the defenders as well as reduce the control effort of the defenders for intercepting the missiles.

О моделировании методов наведения самонаводящихся ракет в системе Wolfram Mathematica

Modern air defense systems are very complex and high-tech products. To design them and analyze their capabilities, you need to use very complex mathematical models. At the same time, the development of both air attack and air defense systems is taking place at a rapid pace, so the emerging modeling problems need effective and visual solutions. One of these tasks is to simulate the guidance of an anti-aircraft guided missile on an air target. It is also important to develop an effective methodology for teaching cadets of military universities methods of computer modeling of problems arising in their practice. Moreover, this problem should be solved both when they study the course of higher mathematics and special disciplines. When mathematically modeling the guidance of anti-aircraft guided missiles, in particular, homing missiles, it is necessary to solve systems of differential equations of a rather complex structure. The study of such systems in the course of scientific research or during the training of cadets of higher military educational institutions requires a lot of time and effort. Modern scientific software, in particular, the Wolfram Mathematica system, makes this work much easier, which makes it possible to widely use this system. The paper presents models of homing missiles using the chase method and the method of a constant lead angle for various purposes, and shows the convenience of using the Mathematica system to estimate the required acceleration of the rocket. This allows you to evaluate the effectiveness of shooting at various targets and the zone of destruction of an anti-aircraft missile system. In the course of the study, the expediency of using this technique in conducting scientific research and training cadets of military universities is justified.