Optimal terminal guidance with constraints at final time

York, Randy J.; Pastrick, Harold L.

doi:10.2514/6.1976-1916

Cited by 4 publications

(4 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Actually, the design is performed in a given operating point in the flight envelope characterized by constant velocity and altitude, and therefore it can be assumed that τ α is constant. Hence, the following equations hold α = τ αγ (18) θ =γ +α =γ + τ αγ (19) …”

Section: Model Derivationmentioning

confidence: 99%

See 1 more Smart Citation

Missile guidance with constrained intercept body angle

Rusnak

Weiss

Eliav

et al. 2014

IEEE Trans. Aerosp. Electron. Syst.

View full text Add to dashboard Cite

show abstract

Section: Model Derivationmentioning

confidence: 99%

“…In [18,19] it was claimed that the missile attitude is controlled, however the angle of attack was neglected, and thus the derived guidance law actually controls the path angle. The contribution of this paper is in deriving a guidance law that enables enforcing a required terminal body angle.…”

Section: Introductionmentioning

confidence: 99%

Missile guidance with constrained intercept body angle

Rusnak

Weiss

Eliav

et al. 2014

IEEE Trans. Aerosp. Electron. Syst.

View full text Add to dashboard Cite

show abstract

“…Earlier works in this field treated the impact angle as a constraint in the optimal control approach [1,2]. The optimal control approach with angle constraints was also used in recent researches.…”

Section: Introductionmentioning

confidence: 98%

Practical guidance law controlling impact angle

Jung

Kim

2007

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Impact angle is defined as the angle between the velocity vectors of a missile and a target at the instance of interception. The objective of the impact angle control guidance (IACG) law is to guide the missile into a collision course with a specified impact angle. In this paper, a new IACG law considering practical implementation is proposed. By selecting parameters properly, the proposed guidance law can be applied to various engagement situations such as the rear-chase case and the face-to-face case. On the basis of the backstepping control approach, the proposed guidance law only requires information about the impact angle, the line-of-sight rate, and the estimated time-to-go. These features improve the applicability of the proposed guidance law to the real systems. To verify the performance of the proposed guidance law, two-dimensional engagement problem is considered. Numerical simulation results demonstrate that the proposed guidance law is effective for controlling the impact angle.

show abstract

“…Thus, the control problem of terminal flight path angle reduces the standard linear quadratic control problem with a fixed final state. Upon this opportunity, the terminal flight path control problem has been cast into the well-known two-point boundaryvalue (TPBV) problem [3,4]. It is straightforward to extend the concept of optimal guidance to the precise impact angle control problem since the side-effects due to AOA could be successfully eliminated by means of missile acceleration feedback [5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Moon

Jung

2015

Int. J. Control Autom. Syst.

View full text Add to dashboard Cite

A practical homing guidance scheme is newly proposed in order to meet the impact angle and terminal acceleration constraints, simultaneously. Provided that the homing guidance loop is modeled as a linear time-varying differential equation by approximating the missile dynamics as a firstorder system, its closed-form solution is expressed as a linear combination of hypergeometric functions. It implies that the instability of the homing guidance loop is mainly due to the missile dynamic lags and, furthermore, the non-diverging homing trajectory could be obtained by introducing the additional biased acceleration command as a rational function of time-to-go. These inspirational observations motivate us to formulate an impact angle control problem as designing an appropriate biased term which generates a non-diverging time-to-go polynomial homing trajectory for given terminal constraints. The resultant guidance command has a similar form used in conventional guidance laws but its feedback gains vary with time-to-go. This similarity means that, during the flight, the proposed guidance law adaptively embraces existing guidance laws derived by intentionally ignoring the effect of missile dynamic lags. Through the numerical simulations, the performance of the proposed guidance scheme is evaluated.

show abstract

Optimal terminal guidance with constraints at final time

Cited by 4 publications

References 2 publications

Missile guidance with constrained intercept body angle

Missile guidance with constrained intercept body angle

Practical guidance law controlling impact angle

Terminal acceleration stabilizing guidance law for impact angle constrained interception of a non-maneuvering target

Contact Info

Product

Resources

About