Line-of-Sight Interceptor Guidance for Defending an Aircraft
01 Mar 2011-Journal of Guidance Control and Dynamics (American Institute of Aeronautics and Astronautics (AIAA))-Vol. 34, Iss: 2, pp 522-532
TL;DR: In this paper, the authors defined the following components of an evasive maneuver component normal to the target-missile line of sight: amp, ad, am, target, defender, and missile lateral accelerations, respectively at max, ad max, am max, max, and am max = target, defenders, and missiles maximum lateral acceleration.
Abstract: = missile evasive maneuver normal to defendermissile line of sight amp = missile evasive maneuver component normal to target-missile line of sight at, ad, am = target, defender, and missile lateral accelerations, respectively at max, ad max, am max = target, defender, and missile maximum lateral accelerations, respectively atplos, adplos, amplos = target, defender, and missile accelerations normal to the line of sight, respectively Rd, Rm, Rdm = target-defender, target-missile, and defendermissile closing ranges, respectively tf = defender-missile interception time vt, vd, vm = target, defender, and missile speeds, respectively vtlos, vdlos, vmlos = target, defender, and missile speeds along the line of sight, respectively vtplos, vdplos, vmplos
Citations
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TL;DR: It is shown how the target can lure in the attacker, allowing its defender to intercept the attacking missile even in scenarios in which the defender's maneuverability is at a disadvantage compared with the attacking ballistic missile.
Abstract: Optimal-control-based cooperative evasion and pursuit strategies are derived for an aircraft and its defending missile. The aircraft-defending missile team cooperates in actively protecting the aircraft from a homing missile. The cooperative strategies are derived assuming that the incoming homing missile is using a known linear guidance law. Linearized kinematics, arbitrary-order linear adversaries' dynamics, and perfect information are also assumed. Specific limiting cases are analyzed in which the attacking missile uses proportional navigation, augmented proportional navigation, or optimal guidance. The optimal one-on-one, noncooperative, aircraft evasion strategies from a missile using such guidance laws are also derived. For adversaries with first-order dynamics it is shown that depending on the initial conditions, and in contrast to the optimal one-on-one evasion strategy, the optimal cooperative target maneuver is either constant or arbitrary. These types of maneuvers are also the optimal ones for the defender missile. Simulation results confirm the usefulness and advantages of cooperation. Specifically, it is shown how the target can lure in the attacker, allowing its defender to intercept the attacking missile even in scenarios in which the defender's maneuverability is at a disadvantage compared with the attacking missile.
185 citations
Cites methods from "Line-of-Sight Interceptor Guidance ..."
...In [20] the kinematics of LOS guidance with a moving/maneuvering launch platform was studied and the application of command to LOS guidance as a prospective defender guidance strategy in the target–missile–defender interception scenario was studied....
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TL;DR: In this paper, a linear quadratic differential game formulation for arbitrary-order linear players' dynamics in the continuous and discrete domains is derived for a team composed of two agents, where the target aircraft performs evasive maneuvers and launches a defending missile to intercept the homing missile.
Abstract: Cooperative pursuit―evasion strategies are derived for a team composed of two agents. The specific problem of interest is that of protecting a target aircraft from a homing missile. The target aircraft performs evasive maneuvers and launches a defending missile to intercept the homing missile. The problem is analyzed using a linear quadratic differential game formulation for arbitrary-order linear players' dynamics in the continuous and discrete domains. Perfect information is assumed. The analytic continuous and numeric discrete solutions are presented for zero-lag adversaries' dynamics. The solution of the game provides 1) the optimal cooperative evasion strategy for the target aircraft, 2) the optimal cooperative pursuit strategy for the defending missile, and 3) the optimal strategy of the homing missile for pursuing the target aircraft and for evading the defender missile. The obtained guidance laws are dependent on the zero-effort miss distances of two pursuer―evader pairs: homing missile with target aircraft and defender missile with homing missile. Conditions for the existence of a saddle-point solution are derived and the navigation gains are analyzed for various limiting cases. Nonlinear two-dimensional simulation results are used to validate the theoretical analysis. The advantages of cooperation are shown. Compared with a conventional one-on-one guidance law, cooperation significantly reduces the maneuverability requirements from the defending missile.
180 citations
TL;DR: It is shown that the performance of the target and the defender is highly dependent on the cooperation scheme, as well as the notion of Pareto fronts.
Abstract: Aircraft protection from a missile employing a known linear guidance strategy is considered The aircraft protects itself by using a cooperating defensive missile Depending on the available cooperation scheme, three different cooperative linear quadratic guidance strategies are derived and investigated for arbitrary-order linear-adversaries dynamics: 1) two-way cooperation, where the target–defender team employs its optimal cooperative strategy, 2) one-way cooperation, realized by the defender employing a classical one-on-one guidance law while the target helps by luring in the missile, and 3) one-way cooperation, realized by the target employing an arbitrary evasive strategy while the defender attempts to reach the predicted interception point The performance of the three different cooperative strategies is compared and analyzed via simulation using the notion of Pareto fronts It is shown that the performance of the target and the defender is highly dependent on the cooperation scheme As expected, th
99 citations
Cites methods from "Line-of-Sight Interceptor Guidance ..."
...Another implementation of the cooperation concept between the target and the defender in target–missile–defender engagements was presented in [15] by using the line-of-sight (LOS) guidance scheme....
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94 citations
TL;DR: The three-body engagement scenario is considered where an aerial missile, homing onto a target aircraft, encounters a defender missile launched by the aircraft, and analysis is carried out for proportional navigation and pure pursuit attacking missile strategies.
Abstract: The three-body engagement scenario is considered where an aerial missile, homing onto a target aircraft, encounters a defender missile launched by the aircraft. A given set of defender-missile guidance laws, namely, proportional navigation and line-of-sight guidance, are considered, and analysis is carried out for proportional navigation and pure pursuit attacking missile strategies. Analytic launch envelopes and lateral accelerations ratios for the four resulting scenarios are derived. Closed-form expressions for attackingmissile initial position and launch angles are derived for a successful evasion from the defender. Numerical simulations are carried out which comply with the analytical findings. The resulting launch envelopes are highly sensitive to the adversary’s guidance strategy, and thus, concerning practical implementation, a game theoretic analysis is carried out. Game solutions are obtained in pure and mixed strategies, resulting in the missile’s evasion probability envelope, that is, based on the four individual launch envelopes.
84 citations
Cites background or methods from "Line-of-Sight Interceptor Guidance ..."
...Ratnoo and Shima [13] highlighted LOS guidance (LOSG) law as a prospective defender-missile strategy protecting an aircraft from an incoming missile attack....
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...Case 4: CLOS Defender Against PP missile We use results from the detailed kinematics of the three-body guidance problem with the defender using CLOS guidance [13]....
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...CLOS guided defender exploits the LOS rate based PNG missile homing maneuvers onto the aircraft and guarantees an acceleration demand which is one third [13] of the missile....
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...Case 3: CLOS Defender Against PNG Missile This combination of the three-body guidance strategies is presented in detail in [13]....
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...For the defender we consider the widely used PNG law and also CLOS that was found to have favorable performance in the three-body problem [13]....
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References
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Book•
01 Jan 1990
TL;DR: In this paper, a three-loop Autopilot is used to provide tactical and strategic guidance for a single-antenna MIMO-BMG system using MATLAB units.
Abstract: Numerical Techniques Fundamentals of Tactical Missile Guidance Method of Adjoints and the Homing Loop Noise Analysis Convariance Analysis and the Homing Loop Proportional Navigation and Miss Distance Digital Fading Memory Noise Filters in the Homing Loop Advanced Guidance Laws Kalman Filters and the Homing Loop Other Forms of Tactical Guidance Tactical Zones Strategic Considerations Boosters Lambert Guidance Strategic Intercepts Miscellaneous Topics Ballistic Target Properties Extended Kalman Filtering and Ballistic Coefficient Estimation Ballistic Target Challenges Multiple Targets Weaving Targets Representing Missile Airframe with Transfer Functions Introduction to Flight Control Design Three-Loop Autopilot. Appendices: Tactical and Strategic Missile Guidance Software Converting Programmes to C Converting Programmes to MATLAB Units.
1,536 citations
01 Jan 1998
326 citations
"Line-of-Sight Interceptor Guidance ..." refers background in this paper
...Note that a defender using PNGwith a navigation constant of three would require a terminal acceleration three times that of the missile [20,21]....
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TL;DR: In this article, the trajectories of an ideal missile homing on a target according to the proportional navigation law were analyzed and conditions were determined which enable one to demonstrate that the missile always reaches the target regardless of the initial conditions at launch; the rotational rate of the line of sight is decreasing at the pursuit end.
Abstract: This paper represents a study of the trajectories of an ideal missile homing on a target according to the proportional navigation law. A qualitative study is performed and conditions are determined which enable one to demonstrate that: 1) the missile always reaches the target regardless of the initial conditions at launch; 2) the rotational rate of the line of sight is decreasing at the pursuit end.
240 citations
TL;DR: It is shown how the target can lure in the attacker, allowing its defender to intercept the attacking missile even in scenarios in which the defender's maneuverability is at a disadvantage compared with the attacking ballistic missile.
Abstract: Optimal-control-based cooperative evasion and pursuit strategies are derived for an aircraft and its defending missile. The aircraft-defending missile team cooperates in actively protecting the aircraft from a homing missile. The cooperative strategies are derived assuming that the incoming homing missile is using a known linear guidance law. Linearized kinematics, arbitrary-order linear adversaries' dynamics, and perfect information are also assumed. Specific limiting cases are analyzed in which the attacking missile uses proportional navigation, augmented proportional navigation, or optimal guidance. The optimal one-on-one, noncooperative, aircraft evasion strategies from a missile using such guidance laws are also derived. For adversaries with first-order dynamics it is shown that depending on the initial conditions, and in contrast to the optimal one-on-one evasion strategy, the optimal cooperative target maneuver is either constant or arbitrary. These types of maneuvers are also the optimal ones for the defender missile. Simulation results confirm the usefulness and advantages of cooperation. Specifically, it is shown how the target can lure in the attacker, allowing its defender to intercept the attacking missile even in scenarios in which the defender's maneuverability is at a disadvantage compared with the attacking missile.
185 citations
TL;DR: In this paper, a linear quadratic differential game formulation for arbitrary-order linear players' dynamics in the continuous and discrete domains is derived for a team composed of two agents, where the target aircraft performs evasive maneuvers and launches a defending missile to intercept the homing missile.
Abstract: Cooperative pursuit―evasion strategies are derived for a team composed of two agents. The specific problem of interest is that of protecting a target aircraft from a homing missile. The target aircraft performs evasive maneuvers and launches a defending missile to intercept the homing missile. The problem is analyzed using a linear quadratic differential game formulation for arbitrary-order linear players' dynamics in the continuous and discrete domains. Perfect information is assumed. The analytic continuous and numeric discrete solutions are presented for zero-lag adversaries' dynamics. The solution of the game provides 1) the optimal cooperative evasion strategy for the target aircraft, 2) the optimal cooperative pursuit strategy for the defending missile, and 3) the optimal strategy of the homing missile for pursuing the target aircraft and for evading the defender missile. The obtained guidance laws are dependent on the zero-effort miss distances of two pursuer―evader pairs: homing missile with target aircraft and defender missile with homing missile. Conditions for the existence of a saddle-point solution are derived and the navigation gains are analyzed for various limiting cases. Nonlinear two-dimensional simulation results are used to validate the theoretical analysis. The advantages of cooperation are shown. Compared with a conventional one-on-one guidance law, cooperation significantly reduces the maneuverability requirements from the defending missile.
180 citations
"Line-of-Sight Interceptor Guidance ..." refers methods in this paper
...[11] obtained an analytical solution to the linearquadratic differential game and studied the conditions for the existence of a saddlepoint solution....
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