Near optimal guidance law for descent to a point using inverse problem approach

Naghash, Abolghasem; Esmaelzadeh, Reza; Mortazavi, Mehdi; Jamilnia, Reza

doi:10.1016/j.ast.2007.06.006

Cited by 18 publications

(13 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In this paper, the author extends the previous works done on maximizing terminal velocity [19][20][21]. An explicit guidance law is developed by flatness approach for guiding a hypersonic unthrusted reentry vehicle (RV) to a fixed point on the ground (Eisler's problem [2]).…”

Section: Introductionmentioning

confidence: 79%

“…In guidance applications, the variable guidance gains are correlated with the shape of the trajectory that will follow and satisfy particular terminal constraints. Although, with an extension of Taranenko [15], Cameron [16], and Page's [17] methods, the use of this approach in guidance algorithm design has been developed by Hough [11] and Yakimenko [5], it still suffers from serious flaws: a relatively large number of optimization parameters (Ops) (Taranenko,20;Mortazavi [18], 12; and Hough, 8) depending on the vehicle's velocity vector, relatively difficult numerical calculations, accuracy dependence on the number of segments used in the approximation, and offline application.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

On-Board Near Optimal Flight Trajectory Generation using Deferential Flatness

Esmaelzadeh¹

2014

IJCA

View full text Add to dashboard Cite

An optimal explicit guidance law that maximizes terminal velocity is developed for a reentry vehicle to a fixed target. The equations of motion are reduced with differential flatness approach and acceleration commands are related to trajectory's parameters. An optimal trajectory is determined by solving a real-coded genetic algorithm. For online trajectory generation, optimal trajectory is approximated. The approximated trajectory is compared with the pure proportional navigation, and genetic algorithm's solutions. The near optimal terminal velocity solution compares very well with these solutions. The approach robustness is examined by Monte Carlo simulation. Other advantages such as trajectory representation with minimum parameters, applicability to any reentry vehicle configuration and any control scheme, and Time-to-Go independency make this guidance approach more favorable.

show abstract

Section: Introductionmentioning

confidence: 79%

Section: Introductionmentioning

confidence: 99%

On-Board Near Optimal Flight Trajectory Generation using Deferential Flatness

Esmaelzadeh¹

2014

IJCA

View full text Add to dashboard Cite

show abstract

“…Bézier functions have been used for explicit solutions to several mathematical and engineering problems. Recent use of this has also been made in reference trajectory generation and near optimal guidance law [6]. However, the guidance design previously presented [6] is unable to meet terminal angle constraints and lacked terminal velocity controlling feature.…”

Section: Introductionmentioning

confidence: 96%

“…Recent use of this has also been made in reference trajectory generation and near optimal guidance law [6]. However, the guidance design previously presented [6] is unable to meet terminal angle constraints and lacked terminal velocity controlling feature. Satisfaction of terminal angular and velocity constraints are especially important for advanced guided weapons and planetary entry missions.…”

Section: Introductionmentioning

confidence: 96%

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

“…Also, Naghash and Esmaelzadeh developed an explicit guidance law that maximized terminal velocity for a reentry vehicle to a fixed target. Acceleration commands were derived by solving an inverse problem related to Bezier parameters and an optimal Bezier curve was determined by solving a genetic algorithm [18] . The presented study concentrates on finding an analytical methodology to compute the open-loop timeoptimal guidance strategy for satellite injection problem.…”

Section: Introductionmentioning

confidence: 99%

Determination of Nonlinear Optimal Feedback Law for Satellite Injection Problem Using Neighboring Optimal Control

Afshari¹,

Novinzadeh²,

Roshanian³

2009

American J. of Applied Sciences

View full text Add to dashboard Cite

An optimal trajectory design of a nonlinear satellite injection problem for transfer to a final target orbit by minimizing the time was investigated. Indeed, this design was an exact solution to the nonlinear two-point boundary value problem which determined optimal control history as well as optimal state trajectories in the open-loop form. Furthermore, the obtained optimal guidance strategy was exerted in the closed-loop form against the environment disturbances using neighboring optimal control method in the exact solution. Neighboring Optimal Control (NOC) law could produce timevariant feedback gains minimizing the performance measure to second order for perturbations from a nominal optimal path. Generally, this law was a function of perturbations appeared in the states and constraints and could be computed utilizing the backward sweep method. The simulation results indicated that the presented methodology was successfully utilized in the real world applications with good robustness to each noise or disturbance produced in each state variable.

show abstract

Near optimal guidance law for descent to a point using inverse problem approach

Cited by 18 publications

References 20 publications

On-Board Near Optimal Flight Trajectory Generation using Deferential Flatness

On-Board Near Optimal Flight Trajectory Generation using Deferential Flatness

Bézier approximation based inverse dynamic guidance for entry glide trajectory

Determination of Nonlinear Optimal Feedback Law for Satellite Injection Problem Using Neighboring Optimal Control

Contact Info

Product

Resources

About

Near optimal guidance law for descent to a point using inverse problem approach

Cited by 18 publications

References 20 publications

On-Board Near Optimal Flight Trajectory Generation using Deferential Flatness

On-Board Near Optimal Flight Trajectory Generation using Deferential Flatness

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

Determination of Nonlinear Optimal Feedback Law for Satellite Injection Problem Using Neighboring Optimal Control

Contact Info

Product

Resources

About

Bézier approximation based inverse dynamic guidance for entry glide trajectory