4 edition of Hypersonic vehicle trajectory optimization and control found in the catalog.
Hypersonic vehicle trajectory optimization and control
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va
Written in English
|Statement||S.N. Balakrishnan, J. Shen, J.R. Grohs.|
|Series||NASA contractor report -- NASA CR-206809.|
|Contributions||Shen, J., Grohs, J. R., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Model predictive control guidance Real-time trajectory optimization for time-optimal way point following subject to exclusion zone, actuator, structural and thermal constraints Constrained flight control Extended Command Governor (ECG) protects nominal closed-loop system against critical constraint violation •x-y trajectory, target sets. This paper focuses on the optimization of a spiral-diving trajectory for a hypersonic vehicle to strike a stationary target. Second-order cone programming (SOCP), a subclass of convex optimization, is applied to achieve this optimization task. The existing optimal control methods for solving the optimization problem are mainly divided into Author: Lei He, Xiaodong Yan, Shuo Tang.
Common Aero Vehicle Autonomous Reentry Trajectory Optimization Satisfying Waypoint and No-Fly Zone Constraints [Jorris, Timothy R.] on *FREE* shipping on qualifying offers. Common Aero Vehicle Autonomous Reentry Trajectory Optimization Cited by: Trajectory optimization is the process of designing a trajectory that minimizes (or maximizes) some measure of performance while satisfying a set of constraints. Generally speaking, trajectory optimization is a technique for computing an open-loop solution to an optimal control problem. It is often used for systems where computing the full closed-loop solution is not required, impractical or.
A method for determing the optimum-trajectory flight path for an air-breathing single-stage-to-orbit vehicle is presented. A calculus-of-variations direct method of steepest descent is used to determine angle of attack, bank angle, and engine power setting time histories. Trajectory profiles resulting from using both nominal and off-nominal vehicle sytem parameters and environmental conditions. limited to small excursions from the target flight condition, so that the vehicle stability and control can be adequately described using linear models. For hypersonic flight tests, the requirement for small excursions also arises from the desire to fly the vehicle on a specific planned trajectory. Even small deviations from a.
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HYPERSONIC VEHICLE TRAJECTORY OPTIMIZATION AND CONTROL EXECUTIVE SUMMARY Two classes of neural networks have been developed for the study of hypersonic vehicle trajectory optimization and control.
The first one is called an 'adaptive critic'. This paper presents a penetration trajectory optimization algorithm for an air-breathing hypersonic vehicle, where the prerequisite penetration condition is analyzed and control costs are chosen as an objective function to minimize the fuel consumption and maneuver : Binbin Yan, Ruifan Liu, Pei Dai, Muzeng Xing, Shuangxi Liu.
Chudej K., Pesch H.J., Wächter M., Sachs G., Le Bras F. () Instationary Heat-Constrained Trajectory Optimization of a Hypersonic Space Vehicle by ODE–PDE-Constrained Optimal Control.
In: Variational Analysis and Aerospace Engineering. Springer Optimization and Its Applications, vol Springer, New York, NY. First Online 15 June Cited by: 9. Journal of Guidance, Control, and Dynamics Vol.
21, No. 1 January Use of Neural Network Approximation in Multiple-Unmanned Aerial Vehicle Trajectory Optimization Joseph Horn. penetration trajectory optimization algorithm for an air-breathing hypersonic vehicle, where the prerequisite penetration condition is analyzed and control costs are chosen as an objective function to minimize the fuel consumption and maneuver : Binbin Yan, Ruifan Liu, Pei Dai, Muzeng Xing, Shuangxi Liu.
First, the system dynamics of hypersonic flight are described, and the trajectory optimization problem is formulated as a highly nonlinear optimal control problem.
Then, the state-action vectors are extracted from the optimal trajectories generated by solving the formulated optimal control problem from random initial states using a homotopy method. Abstract: To support the global reach concept, the hypersonic vehicle is designed to realize the global strike mission.
The paper applies the enhancing parametrization method to the reentry trajectory optimization of the hypersonic vehicle. This problem is considered as an optimal control problem with some path constraints, which must be satisfied along the reentry by: 3.
The trajectory optimization technology is one of the key technologies for hypersonic air-vehicle. There are multiple constraints in the process of hypersonic flight, such as uncertainty of flight environment, thermal current, dynamic pressure and overload.
The trajectory optimization of hypersonic air-vehicle is facing with a great : Changzhu Wei, Rong Huang, Hao Li, Yongzhi Shan. A fast ascent trajectory optimization method for hypersonic air-breathing vehicles by Oscar J Murillo Jr A dissertation submitted to the graduate faculty in partial ful llment of the requirements for the degree of DOCTOR OF PHILOSOPHY Major: Aerospace Engineering Program of Study Committee: Ping Lu, Major Professor Stephen Holland Atul Kelkar Author: Oscar Jaime Murillo.
An Introduction to Trajectory Optimization: How to Do Your Own Direct Collocation Mapped Chebyshev pseudospectral methods for optimal trajectory planning of differentially flat hypersonic vehicle systems.
Aerospace Science and A novel adaptive Gauss pseudospectral method for nonlinear optimal control of constrained hypersonic re-entry Cited by: This paper presents a penetration trajectory optimization algorithm for an air-breathing hypersonic vehicle, where the prerequisite penetration condition is analyzed and control costs are chosen.
Generation of optimal reentry trajectory for a hypersonic vehicle (HV) satisfying both boundary conditions and path constraints is a challenging task. As a relatively new swarm intelligent algorithm, an adaptive fireworks algorithm (AFWA) has exhibited promising performance on some optimization problems.
However, with respect to the optimal reentry trajectory generation under constraints, the Cited by: 2. Abstract: Trajectory optimization problem for hypersonic vehicles has received wide attention as its high speed and large flight range.
The strong nonlinear characteristic of the ascent phase aerodynamics makes the trajectory optimization problem difficult to be solved by the optimal control : Wenzhe Fu, Bo Wang, Xu Li, Lei Liu, Yongji Wang. The trajectory optimization problem is modeled as a nonlinear, multiphase, constraint optimal control problem and is solved using a hp-adaptive pseudospectral method.
hypersonic vehicle trajectory optimization problems, that is, maximum cross-range and maximum plane change. The work was performed by David G. Hull and Jason L. Speyer of the Department of Aerospace Engineering and Engineering Mechanics, University of Texas at Austin, Austin, Texas, File Size: 2MB.
The reentry trajectory optimization for hypersonic vehicle (HV) is a current problem of great interest. Some complex constraints, such as waypoints for reconnaissance and no-fly zones for threat avoidance, are inevitably involved in a global strike by: Similarly, the launch vehicle trajectory optimization including rotational dynamics in the pitch plane using the indirect method is presented in work by Adimurthy.
8 The three dimensional trajectory optimization of the same launch vehicle under the path constraint of minimum aerodynamic loads using the direct method can be found in later work Cited by: 3. Over the past decade, Gauss pseudospectral method (GPM) has been widely used to deal with the reentry trajectory optimization problems for hypersonic vehicle.
However, for the trajectory generated by GPM, all constraints can only be satisfied at each Gauss point. To overcome this problem, in this paper, an improved GPM is proposed. Two kinds of newly defined breaks are applied Cited by: 4.
Get this from a library. Hypersonic vehicle trajectory optimization and control: final report, grant number--NAG 1 [S N Balakrishnan; J Shen; J R Grohs; United States. National Aeronautics and Space Administration.]. The purpose of this task is to assemble a computer code for solving the maximum crossrange and maximum plane change problems for hypersonic vehicles.
These problems are formulated as parameter optimization or nonlinear programming problems by replacing each control function by a number of nodal points and linear interpolation. An existing code for solving the nonlinear programming problem. The results have then been compared with results from optimization using single shooting method.
The results show applicability of these methods in generating hypersonic vehicle trajectory under constraints for ascent, cruise and descend phase in 3 degree of freedom.
KEY WORDS hypersonic vehicle, pseudospectral method, trajectory optimization. 1.This paper presents a trajectory optimization problem of a hypersonic vehicle in 3 degree of freedom under constraints. Here, this problem has been solved using Legendre and Gauss pseudospectral methods.
The vehicle trajectory optimized includes ascent, cruise and descend phase.Navy SBIR BAA Topics Opens June 3, - Closes July 2,