PID guidance law design using short time stability approach

Golestani, Mehdi; Mohammadzaman, Iman

doi:10.1016/j.ast.2015.02.016

Cited by 18 publications

(13 citation statements)

References 13 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the field of control technology, it is well-understood that the concept of PI control, apart from the adaptive control technique, is a simple and an effective way to attenuate the effect of external disturbances. Based on this aspect, guidance laws based on PI-control were proposed recently in [18], [19]. The rationale behind this approach is that if the unknown target acceleration is considered as an external disturbance of the guidance system from the control perspective, then the integral term in the guidance command can help reduce the sensitivity to the unknown target acceleration.…”

Section: Introductionmentioning

confidence: 99%

“…The rationale behind this approach is that if the unknown target acceleration is considered as an external disturbance of the guidance system from the control perspective, then the integral term in the guidance command can help reduce the sensitivity to the unknown target acceleration. Recent works regarding PI guidance in [18], [19] revealed that it can significantly improve the guidance performance for a maneuvering target in terms of miss distance compared to the conventional PNG.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Optimal Proportional-Integral Guidance With Reduced Sensitivity to Target Maneuvers

Lee

2018

IEEE Trans. Aerosp. Electron. Syst.

View full text Add to dashboard Cite

This paper proposes a new optimal guidance law based on proportional-integral (PI) concept to reduce the sensitivity to unknown target maneuvers. Compared to existing PI guidance laws, the proposed guidance command is derived in the optimal control framework while guaranteeing finite time convergence. The kinematics equation with respect to the zero-effort-miss (ZEM) is utilized and the integral ZEM is augmented as a new system state. The proposed guidance law is derived through the Schwarz's inequality method. The closed-form solution of proposed guidance law is presented to provide better insight of its properties. Additionally, the working principle of the integral command is investigated to show why the proposed guidance law is robust against unknown target accelerations. The analytical results reveal that the proposed optimal guidance law is exactly the same as an instantaneous direct model reference adaptive guidance law with a pre-specified reference model. The potential significance of the obtained results is that it can provide a point of connection between PI guidance laws and adaptive guidance laws. Therefore, it allows us to have better understanding of the physical meaning of both guidance laws and provides the possibility in designing a new guidance law that takes advantages of both approaches. Finally, the performance of the guidance law developed is demonstrated by nonlinear numerical simulations with extensive comparisons.

show abstract

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Optimal Proportional-Integral Guidance With Reduced Sensitivity to Target Maneuvers

Lee

2018

IEEE Trans. Aerosp. Electron. Syst.

View full text Add to dashboard Cite

show abstract

“…For a physical process finished in a finite-time interval, finite-time control theory may be more effective, since it only focuses on the concerned time interval and the performance indices are always defined in the concerned finite-time interval [23]. Furthermore, there have been some researches applying finite-time control theory for the terminal guidance problems in recent years [24][25][26][27][28][29][30]. Hence, the finite-time control methods will be used to solve the triangle interception problems, as dealt with in this paper.…”

Section: Introductionmentioning

confidence: 99%

Triangle Interception Scenario: A Finite-Time Guidance Approach

Guo

et al. 2016

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

Considering an aircraft threatened by an interceptor, one of the effective penetration strategies is to release a Defender from the aircraft to confront the interceptor. In this case, the aircraft, the Defender, and the interceptor constitute the three-body guidance relationship, and the cooperation of the aircraft and its Defender to achieve the best tactical effects turns into a concerned problem. This paper studies the triangle interception guidance problem via the finite-time theory. The paper presents linear system Input-Output Finite-Time Stabilization (IO-FTS) method. The sufficient conditions of the linear system, being IO-FTS, under Finite-Time Boundedness (FTB) constraint are proposed, by which the state feedback controllers design method is obtained, via Linear Matrix Inequalities (LMIs). The triangle interception guidance problems are studied in three different cases, where the proposed methods are applied to the guidance design. The simulation results illustrate the effectiveness of the proposed methods.

show abstract

“…Then the system given by (26) and (27) is described by IO-FTS with respect to T, S w , S y t in the finite time interval 0, T . The state feedback controller u t = K t x t , and…”

Section: S T = C T T S Y T C T 35mentioning

confidence: 99%

“…The guidance command is also meaningful in a finite time interval [21][22][23]. Recently, many scholars have conducted related research to obtain a finite time convergent guidance law based on finite time theory in the terminal guidance phase [24][25][26]. The concept of a finite time theory was first proposed by Dorato in 1961 [27].…”

Section: Introductionmentioning

confidence: 99%

Cooperative Intercept Guidance of Multiple Aircraft with a Lure Role Included

Zhang

Guo

Wang

2018

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

When threatened by a pursuer, an evading aircraft launches two defenders to accomplish a cooperative evasion, constituting a fouraircraft interception engagement. Under the assumption that the pursuing aircraft adopts the augmented proportional guidance law and first-order dynamics, a cooperative intercept mathematical model with an intercept angle constraint is established, allowing for the cooperative maneuvering of the evader. Based on the differential linear matrix inequality (DLMI), a controller design method of input and output finite time stability (IO-FTS) is proposed and applied to the aircraft's cooperative intercept scenario. A cooperation performance analysis is carried out for two cases: (1) two defenders intercept the pursuer with various intercept angle constraints, and (2) the evader acts in a lure role to cooperate with two defenders. The simulation results indicate that the proposed method of controller design has the ability to guarantee that the two defenders intercept the pursuer at the preassigned intercept angles. The cooperative intercept scenario with a lure role is shown to be a very effective method for reducing the maximum required acceleration for defenders, which confirms the availability and advantage of cooperation. The strong adaptability and robustness of the cooperative guidance law with respect to various initial launch conditions is also verified.

show abstract

PID guidance law design using short time stability approach

Cited by 18 publications

References 13 publications

Optimal Proportional-Integral Guidance With Reduced Sensitivity to Target Maneuvers

Optimal Proportional-Integral Guidance With Reduced Sensitivity to Target Maneuvers

Triangle Interception Scenario: A Finite-Time Guidance Approach

Cooperative Intercept Guidance of Multiple Aircraft with a Lure Role Included

Contact Info

Product

Resources

About