Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Chawla, Charu; Sarmah, Pranjit; Padhi, Radhakant

doi:10.1016/j.ast.2010.04.001

Cited by 47 publications

(28 citation statements)

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The dynamics of missile can smooth the missile acceleration to some extent. 1 It is an interesting open issue to design a cooperative guidance law with smoother missile acceleration under switching sensing/communication topology considering the dynamics of missile. Second, the convergence rate of δ max (t) is determined by both the adjustable gain K ci (or equivalently, k i ) and the connectivity of the sensing/communication network.…”

Section: Case 3 Fixed Sensing/communication Topology Of Leader-follomentioning

confidence: 99%

“…The issue of impact angle control guidance (IACG) has been addressed in an amount of works, from the biased proportional navigation guidance based IACG laws [8,9,13,21,31] to the optimal control theory based IACG laws [12,22,23], from the model predictive static programming technique based IACG laws [1,16] to the sliding mode control theory based IACG laws [4,10,11,14,20,28,32], too numerous to mention one by one.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Wang

Zhang

2015

Aerospace Science and Technology

View full text Add to dashboard Cite

Section: Case 3 Fixed Sensing/communication Topology Of Leader-follomentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Wang

Zhang

2015

Aerospace Science and Technology

View full text Add to dashboard Cite

“…Their scheme however lacked in constraining terminal velocity. Very recently an entry guidance scheme based on Model Predictive Static Programming (MPSP) has been presented by C. Chawla, et al [5]. This method reduces the complexity of optimal control by converting dynamic programming problem to a static programming problem.…”

Section: Introductionmentioning

confidence: 98%

Bézier approximation based inverse dynamic guidance for entry glide trajectory

Rahman

Zhang

Chen

2013

2013 9th Asian Control Conference (ASCC)

View full text Add to dashboard Cite

An explicit entry guidance law has been developed using inverse dynamics approach. The inverse dynamics problem is solved through Bézier curve approximation of the vehicle trajectory. Most important and novel feature of the developed guidance law is its ability to satisfy the terminal angular and velocity constraints besides position constraints. Through shape preserving 'Bézier parameters' the guidance law has the ability to control terminal velocity. For entry glide flight the guidance law incorporates limits on acceleration and attack angle which are converted from path constraints. The results demonstrate remarkably good efficiency in meeting terminal constraints.

show abstract

“…MPSP is suitable for two-point boundary value problems with terminal constraints. Applications of the technology on different issues can be seen in recent articles [22][23][24]. The following are the main contributions of this paper:…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

Zhang

Chen

2019

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

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.

show abstract

Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Cited by 47 publications

References 21 publications

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Bézier approximation based inverse dynamic guidance for entry glide trajectory

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

Contact Info

Product

Resources

About

Suboptimal reentry guidance of a reusable launch vehicle using pitch plane maneuver

Cited by 47 publications

References 21 publications

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

Distributed cooperative guidance of multiple anti-ship missiles with arbitrary impact angle constraint

B&#x00E9;zier approximation based inverse dynamic guidance for entry glide trajectory

Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

Contact Info

Product

Resources

About

Bézier approximation based inverse dynamic guidance for entry glide trajectory