Showing papers on "Missile published in 2019"
TL;DR: By adding a feedback controller to the obtained optimal guidance law, both impact time and angle requirements are achieved and the singularity problem is tackled.
82 citations
TL;DR: The proposed output feedback CTSMGL not only guarantees the rates of the line-of-sight angles converge to zero in finite time but also ensures the continuity of control action.
41 citations
TL;DR: Numerical simulation results show that the proposed impact time and angle constrained guidance law has a good performance even though the missile has a constant acceleration.
40 citations
TL;DR: A robust guidance law considering autopilot dynamics for maneuvering target interception in three-dimensional environment and terminal angle constraints is proposed and an adaptive second-order sliding mode observer is presented whose design parameters can be adjusted autonomously according to the estimation error.
39 citations
TL;DR: A constraint based nonlinear goal programming (multi-objective) model for weapon assignment problem to minimize survival probability was developed and not only gave optimum assignment but also resulted in engagement times and defense success for multi-defense sites.
38 citations
TL;DR: A novel nonlinear mapping based guidance strategy is proposed for attacking stationary and non-maneuvering moving targets with desired impact angle and seeker's field-of-view constraints, and the seeker's FOV constraint is transformed to be the limit of the relative speed perpendicular to the LOS between missile and target.
34 citations
TL;DR: A novel impact angle constrained integrated guidance and control scheme is proposed with non-singular terminal sliding mode control (NTSMC) technique for missile to intercept a maneuverable target and the stability of closed-loop integrated system is rigorously proved by utilizing the Lyapunov theorem.
34 citations
TL;DR: The result demonstrates that the proposed guidance law enables the missile to simultaneously achieve the interception and desired impact time without violating the prespecified FOV limits.
Abstract: This paper proposes a guidance law that achieves the desired terminal impact time without violating a seeker's field-of-view (FOV) limits. In order to derive the guidance law, kinematic conditions for impact time control are defined, and the backstepping control technique is applied for the satisfaction of the conditions. As a virtual control input for the backstepping structure, the missile lead angle, which represents the angle between the line-of-sight (LOS) and missile velocity vector, is used and its magnitude is limited by a prescribed limit. Then, the seeker's look angle can also be confined within a specific range because the seeker look angle is mainly determined by the difference between the LOS and the velocity vector. This capability to confine the seeker's look angle with achieving the desired impact time is the main contribution of the paper. To evaluate the performance of the proposed law, numerical simulation is conducted. The result demonstrates that the proposed guidance law enables the missile to simultaneously achieve the interception and desired impact time without violating the prespecified FOV limits.
33 citations
TL;DR: This study investigates the cooperative time-varying formation guidance (CTFG) problem for leader-following missiles to intercept a maneuvering target with switching communication topologies and gives a four-step approach to determine the parameters in the CTFG law.
Abstract: This study investigates the cooperative time-varying formation guidance (CTFG) problem for leader-following missiles to intercept a maneuvering target with switching communication topologies. Multiple missiles are classified into a leader missile and multiple follower missiles. The leader missile intercepts the maneuvering target under the modified proportional navigation guidance law. The follower missiles are expected to form a predefined time-varying formation and track the trajectory of the leader missile. Multiple missiles intercept the maneuvering target simultaneously and then form a many-to-one engagement. A four-step approach to determine the parameters in the CTFG law is given. The convergence of the approach is discussed. A numerical example for multiple missiles intercepting a maneuvering target subjected to switching communication topologies is presented.
33 citations
TL;DR: A novel continuous adaptive finite time guidance (CAFTG) law is proposed for homing missiles by introducing three-dimensional nonlinear dynamics describing the pursuit situation of the missile and the target to obtain the mathematical model of engagement.
32 citations
TL;DR: In this article, a mathematical model of a moving mass control (MMC) missile is established, and the angular motion equation is finally obtained by some linearized assumptions, and sufficient and necessary conditions of coning motion stability for MMC missiles with angular rate loops under fast and slow spinning rates are analytically derived and further verified by numerical simulations.
Abstract: Moving mass control (MMC) is a new control method in control field. It is a potential way to solve the problem of aerodynamic rudder control insufficiency caused by the low density of upper atmosphere, to reduce the high speed missile aerodynamic thermal load, and to solve the problem of rudder surface ablation. However, the spinning of the airframe and the movement of internal moving mass induce the serious dynamic cross-coupling between pitch and yaw channels, which may lead to system instability in the form of a divergent coning motion. In this paper, the mathematical model of the MMC missile is established, and the angular motion equation is finally obtained by some linearized assumptions. Then, the sufficient and necessary conditions of coning motion stability for MMC missiles with angular rate loops under fast and slow spinning rates are analytically derived and further verified by numerical simulations. It is noticed that the upper bound of the control gain is affected by the location of the moving mass and the spinning rate of the missile.
TL;DR: This paper explores the Hawk missile simulation task using a Systems Theoretic Accident Model and Process (STAMP) and its corresponding hazard analysis Systems-Theoretic Process Analysis (STPA) methodology to map the key stakeholders within this operation.
TL;DR: A recently proposed nonlinear programming sensitivity-based algorithm is used and embedded in the optimization framework for optimization-based predictive control for the problem of missile interception.
Abstract: This paper focuses on the design and implementation of optimization-based predictive control for the problem of missile interception. Due to the inherent nonlinearities of the missile–target dynamics or even constraints, it is usually difficult to design a high-accuracy and high-efficiency control algorithm. A nonlinear receding horizon pseudospectral control (RHPC) scheme is constructed and applied to generate the optimal control command. The problem of state estimation, in the presence of measurement noise, is solved by implementing a moving horizon estimation (MHE) algorithm. Since the RHPC and MHE algorithms solve the online open-loop optimal control problem at each sampling instant, the computational cost associated with them can be high. In order to decrease the computational demand due to the optimization process, a recently proposed nonlinear programming sensitivity-based algorithm is used and embedded in the optimization framework. Numerical simulations and analysis are presented to demonstrate the effectiveness of the proposed control scheme.
TL;DR: The effectiveness and robustness of the proposed integrated guidance and control algorithm are verified through numerical simulations and the finite-time stability of the closed-loop system is proven based on Lyapunov theory.
Abstract: In this paper, considering a class of skid-to-turn (STT) missile with impact angle constraint to intercept the maneuvering target, a three-dimensional integrated guidance and control law based on the fractional integral terminal sliding mode control (FITSMC) scheme is proposed. Firstly, a three-dimensional integrated guidance and control model is established for missile-target relative motion and nonlinear missile dynamics with multiple system uncertainties and unknown disturbances. Secondly, in order to achieve the desired impact angle in finite-time without singularity, a novel nonsingular FITSMC scheme is employed to construct the sliding surface, and a modified filter is applied to dynamic surface control design. Also, an extended state observer is introduced to estimate and compensate the system uncertainties and unknown disturbances. Then, a robust integrated guidance and control scheme with impact angle constraint is developed using aforementioned techniques. Furthermore, the finite-time stability of the closed-loop system is proven based on Lyapunov theory. Finally, the effectiveness and robustness of the proposed integrated guidance and control algorithm are verified through numerical simulations.
TL;DR: Simulation results including Monte Carlo simulations, nonlinear six-Degree-Of-Freedom (6-DOF) simulations and different ranges are presented to demonstrate the efficacy of the proposed control scheme.
TL;DR: A line-of-sight (LOS) angle constraint is derived for the unmanned aerial vehicle to track a virtual target moving along the reference trajectory, by which the trajectory-following problem is transformed into an angle-constrained terminal guidance problem such that well-developed terminal guidance laws can be incorporated into the design of a trajectory- Following guidance scheme.
TL;DR: The dynamic model and aerodynamic model are established on the variable span characteristic and the adaptive dynamic surface control back-stepping method is used to establish the integrated guidance and control with terminal angular constraint in the dive phase of the hypersonic variable span missile.
Abstract: The morphing aircraft can improve the flight performance of hypersonic vehicles by satisfying the flight requirements of large airspace and large velocity field. In this paper, for the hypersonic variable span missile, the dynamic model and aerodynamic model are established on the variable span characteristic. The adaptive dynamic surface control back-stepping method is used to establish the integrated guidance and control (IGC) with terminal angular constraint in the dive phase of the hypersonic variable span missile. The span variety is used to assist the lift control to achieve fast and stable control for the centroid motion. The simulation results demonstrate that the feasibility and robustness of the IGC method of the hypersonic variable span missile is better than the invariable span.
10 Jul 2019
TL;DR: Sliding mode control based guidance strategies for an aircraft and defending missile team against an attacking interceptor are proposed and it is shown that knowledge of the bound on interceptor acceleration suffices to ensure its interception.
Abstract: This paper proposes sliding mode control based guidance strategies for an aircraft and defending missile team against an attacking interceptor. The proposed guidance strategies are generalizations of the line-of-sight guidance concept. By considering a nonlinear framework, problems that arise from linearization of engagement dynamics are circumvented. It is shown that knowledge of the bound on interceptor acceleration suffices to ensure its interception. Further, corresponding to different cost functions, optimal cooperative strategies are derived for the aircraft-defender team. Simulations vindicate the efficacy of the proposed strategies.
01 Aug 2019
TL;DR: Using the Lyapunov-like approach, the performance of DGGL against the high-speed target with an arbitrary but upper-bounded maneuvering acceleration is well studied, and conditions that guarantee the capture of this type of maneuvering target are presented.
Abstract: The interception of high-speed target with an arbitrary maneuvering acceleration causes serious troubles to the guidance and control system design of airborne missile. A novel guidance law based on...
TL;DR: A backstepping-based continuous three-order finite-time guidance law is designed such that the heading angle tracking is guaranteed and the superiority of the guidanceLaw is demonstrated by a series of simulation results.
Abstract: A novel method of exoatmospheric guidance law design is proposed in this paper. By analyzing the nonlinear kinematic equations, a class of nominal motions that requires no maneuver effort can be derived for a nose jet control missile. A unique time to go can be solved online from the equations derived from the property of the nominal motion to guarantee a perfect interception. With the time to go determined, the nominal heading angle and heading angular rate can be obtained to impose an impact angle constraint. A backstepping-based continuous three-order finite-time guidance law is designed such that the heading angle tracking is guaranteed. The superiority of the guidance law is demonstrated by a series of simulation results.
17 Jun 2019
TL;DR: The system components, hardware development campaign, test execution, and test conclusions are described, which were a major milestone in a technology development campaign for Nano-ADEPT: the application of ADEPT for small secondary payloads.
Abstract: On September 12th, 2018, a sounding rocket flight test was conducted on a mechanically-deployed atmospheric entry system known as the Adaptable Deployable Entry and Placement Technology (ADEPT). The purpose of the Sounding Rocket One (SR-1) test was to gather critical flight data for evaluating the vehicle's in-space deployment performance and supersonic stability. This flight test was a major milestone in a technology development campaign for Nano-ADEPT: the application of ADEPT for small secondary payloads. The test was conducted above White Sands Missile Range, New Mexico on a SpaceLoft XL rocket manufactured by UP Aerospace. This paper describes the system components, hardware development campaign, test execution, and test conclusions.
TL;DR: An all-aspect guidance law that allows the missile to achieve the interception of a target at the prescribed impact angle for any initial conditions, despite the absence of the information of the target acceleration.
Abstract: This paper presents an all-aspect guidance law that allows the missile to achieve the interception of a target at the prescribed impact angle for any initial conditions. The proposed guidance law is designed to intercept a maneuvering target without requiring information of the normal acceleration of the target. In order to develop a guidance law that ensures all-aspect capability, the kinematic conditions that always guarantee the interception of the maneuvering target at the desired impact angle are defined. The defined kinematic conditions are expressed as two error variables for simultaneously satisfying the homing and impact angle control, and the guidance law is derived by stabilizing both error variables near zero based on the backstepping control technique. The analysis of the overall closed-loop dynamics verifies that the proposed law achieves the interception of the maneuvering target at the prescribed impact angle from any initial heading and boresight conditions, despite the absence of the information of the target acceleration. Numerical simulations also demonstrate that the proposed law achieves an acceptable miss distance at the desired impact angle for various initial conditions against different types of nonstationary targets: nonmaneuvering targets, constant-maneuvering targets, and weaving targets.
TL;DR: A new nonlinear guidance law for air-to-ground missile cooperation attacks that can make the missiles hit the target accurately at the same time with the ideal impact angles and can realize the control saturation constraints of the missiles is proposed.
Abstract: A new nonlinear guidance law for air-to-ground missile cooperation attacks is proposed in this paper. This guidance law enables missiles with different initial conditions to attack targets simultaneously, and it can also precisely satisfy the terminal impact angle conditions in both flight-path angle and heading angle. The guidance law is devised using the model predictive static programming (MPSP) method, and the control saturation constraint is incorporated in the MPSP algorithm. The first-order-lag acceleration of the missile is taken as the state variable to realize the convergence of the terminal acceleration to zero. Moreover, a collision avoidance strategy for three-dimensional missile cooperative flight is proposed. The simulation results show that the guidance law can make the missiles hit the target accurately at the same time with the ideal impact angles and can realize the control saturation constraints of the missiles. This can increase the attack effects and is significant for collaborative attacks.
TL;DR: A non-‘Stop-Go’ mathematical model is devised and it can avoid the large errors introduced by the acceleration, which is neglected in the traditional model.
Abstract: The spaceborne transmitter/missile-borne receiver (ST/MR) synthetic aperture radar (SAR) could provide several unique advantages, such as wide coverage, unrestricted geography, a small detection probability of the missile, and forward-looking imaging. However, it is also accompanied by problems in imaging, including geometric model establishment and focusing algorithm design. In this paper, an ST/MR SAR model is first presented and then the flight-path constraint, characterized by geometric configurations, is derived. Considering the impacts brought about by the maneuvers of the missile, a non-‘Stop-Go’ mathematical model is devised and it can avoid the large errors introduced by the acceleration, which is neglected in the traditional model. Finally, a two-dimensional (2-D) scaling algorithm is developed to focus the ST/MR data. Without introducing any extra operations, it can greatly remove the spatial variations of the range, azimuth, and cross-coupling phases simultaneously and entirely in the 2-D hybrid domain. Simulation results verify the effectiveness of the proposed model and focusing approach.
TL;DR: To perform an accurate fire-and-forget attack of seeker-less missile with the consideration of the localization error, a new cooperative guidance strategy of multi-missiles is proposed.
TL;DR: A novel cooperative guidance strategy is proposed to implement the fire-and-forget attacks of seekers-less missiles in which the motion information of a maneuvering target and the strict requirement on the convergence time of the position are not required for the seeker-less missile.
TL;DR: A cooperative interception scenario between a target, its defenders, and missiles attacking said target is considered and optimal cooperative guidance laws are developed.
Abstract: A cooperative interception scenario between a target, its defenders, and missiles attacking said target is considered. Optimal cooperative guidance laws are developed for two distinct scenarios: 1)...
TL;DR: This flight marks the first successful operation of a transition-edge sensor array and its time-division multiplexing readout system in space.
Abstract: Micro-X is a sounding rocket-borne instrument that uses a microcalorimeter array to perform high-resolution X-ray spectroscopy. This instrument flew for the first time on July 22nd, 2018 from the White Sands Missile Range, USA. This flight marks the first successful operation of a Transition-Edge Sensor array and its time division multiplexing read-out system in space. This launch was dedicated to the observation of the supernova remnant Cassiopeia A. A failure in the attitude control system prevented the rocket from pointing and led to no time on target. The on-board calibration source provided X-rays in flight, and it is used to compare detector performance during pre-flight integration, flight, and after the successful post-flight recovery. This calibration data demonstrates the capabilities of the detector in a space environment as well as its potential for future flights.
TL;DR: A novel head-pursuit guidance law considering the dynamic characteristics of a missile control system and the target mobility is presented via combining a fast power reaching law with backstepping sliding mode control to meet the needs of high-precision guidance for intercepting hypersonic targets.
Abstract: In order to meet the needs of high-precision guidance for intercepting hypersonic targets, a novel head-pursuit guidance law considering the dynamic characteristics of a missile control system and the target mobility is presented via combining a fast power reaching law with backstepping sliding mode control in this paper. Initially, a three-dimensional head-pursuit system model of the missile and target is established. Subsequently, the system model is decomposed into a pitch plane system and lateral plane system, the control system dynamics are equivalent to second-order systems, and finite-time disturbance observers are introduced to estimate the target accelerations. On the basis of the previous work, the head-pursuit guidance laws of the vertical system and the lateral system which can stabilize the closed-loop system are designed separately and strict proofs of the methods are given. Finally, simulations are carried out to verify the effectiveness of this head-pursuit guidance law.
TL;DR: An observer-based partial integrated guidance and control scheme for missiles to achieve hit-to-kill attack at a given impact angle is presented, which removes the requirement of knowing the bound of disturbances and hence making the scheme more applicable to real missile systems.
Abstract: In this paper, we present an observer-based partial integrated guidance and control (PIGC) scheme for missiles to achieve hit-to-kill attack at a given impact angle. This is particularly useful as the lethality of a missile can be maximized if collision occurs at a certain angle. A novel sliding mode observer is proposed to estimate all states of the system in finite time, from which the PIGC is designed to make all states converge to zero and achieve the objective. The observer parameters are automatically updated by adaptive laws, which removes the requirement of knowing the bound of disturbances and hence making the scheme more applicable to real missile systems.