Fuel optimal propulsive maneuver of an experimental structure exhibiting spacelike dynamics

Meyer, John L.; Silverberg, Larry

doi:10.2514/3.21591

Cited by 22 publications

(8 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Some of the methods start with an inherently fuel-efficient command profile and solve for the times at which it should switch on and off. 100 Other methods use a weighting function between move speed and fuel usage, [101][102][103][104] or simply allow the command designer to specify the amount of fuel that is to be used for any particular move. 105 All of these methods can be formulated by simply changing the impulses magnitudes in the input shaper.…”

Section: Input Shaping For Time-optimal Controlmentioning

confidence: 99%

Command shaping for flexible systems: A review of the first 50 years

Singhose

2009

Int. J. Precis. Eng. Manuf.

373

183

View full text Add to dashboard Cite

Section: Input Shaping For Time-optimal Controlmentioning

confidence: 99%

Command shaping for flexible systems: A review of the first 50 years

Singhose

2009

Int. J. Precis. Eng. Manuf.

373

183

View full text Add to dashboard Cite

“…Using solution (20), we can easily construct the analytic solution. It is inexpedient to construct a numerical solution subject to constraints (17) and (19) because the conditional extremum cannot give a solution that would be better than that obtained based on the unconditional minimization of function (15) in view of constraint (6). Numerical tests for the segments 0 2 …”

Section: Problem Formulationmentioning

confidence: 99%

“…17),(18) or(19). Preliminarily, it is expedient to test the original parametrized functional (15) for local extremum.…”

mentioning

confidence: 99%

See 1 more Smart Citation

Optimal limited-rate slewing of a flexible spacecraft

Zakrzhevskii

2010

Int Appl Mech

View full text Add to dashboard Cite

The paper presents an efficient method of finding the optimal program control for the reorientation of a spacecraft with flexible appendages at a limited slewing rate. The appendages are incorporated into the mathematical model based on the quasistatic approximation. The problem is solved analytically by parametrizing the functional of a multipoint boundary-value problem. The optimal solution is illustrated graphically for different parts of the attainability domains Introduction. Optimal rest-to-rest maneuvers of spacecraft with flexible appendages have long attracted the attention of researchers and are still of interest because new spacecraft designs, new effectors, new control systems are developed.A common practice is to combine feedforward and feedback controls for such systems. The deformation of flexible appendages can only be measured with distributed sensors. If a spacecraft is not equipped with such sensors, there can be no acceptable quality of feedback. Therefore, whether maneuvers of such spacecraft are successful is strongly dependent on the quality of feedforward control. In this field, a number of fundamental results have been obtained. They allow optimization based on various goal functions. For long-lived spacecraft with a low power-to-weight ratio, it is important to minimize the consumption of energy [17,20,25,26]. For observation satellites that maneuver much, it is important to minimize the maneuver time [5,6,8,9,16,18,19,21,23,24]. The most typical result in this field is bang-bang control, which may appear extremely sensible to simulation errors. Sometimes these goal functions are combined into one with weighted components [11].In some cases, it is important to minimize not the fuel consumption and maneuver time, but rather the moment perturbations of the spacecraft because of the vibrations of flexible appendages. The slewing of such spacecraft should be controlled in such a manner that no vibrations of the flexible appendages occur and affect the operation of the spacecraft equipment. First attempts to solve this problem using goal functions with various combinations of generalized coordinates of elastic displacements and their derivatives were made in the 1970s [2, 3, 10]. Later, it was proposed that feedforward control did not include spectral components of the spacecraft as a whole [7]. Modifications of this approach were applied to elastic nonlinear systems [22], but the residual vibrations were nevertheless significant [11]. The cited studies dealt only with one mode of elastic vibrations. Some relevant issues were analyzed in [12][13][14][15].The papers [4, 27] outline a method of designing an optimal slewing program that minimizes the relative accelerations of the flexible appendages of a spacecraft. The method allows for the infinite number of modes of elastic vibrations, not going beyond the finite-dimensional mathematical model. This is possible if the first several modes are described in the usual formulation and all the higher modes in the quasistatic formulation. Of separat...

show abstract

“…Optimization of a rest-to-rest maneuver of flexible spacecraft can entail various objectives. For SC on long missions with a weak power-to-mass ratio, an important objective is to minimize the energy cost (VanderVelde and He, 1983;Wie et al, 1993;Singh, 1995;Meyer and Silverberg, 1996). For spacecraft dealing with astronomical observations and performing a great number of reorientation maneuvers, it may be important to minimize time.…”

Section: Introductionmentioning

confidence: 99%

Optimal Maneuver of Mechanical System with Internal Degrees of Freedom with State-Variable Constraint

Zakrzhevskii¹

2014

JMSIC

View full text Add to dashboard Cite

An effective procedure is presented for the determination of the optimal control input for maneuvers of a mechanical system with internal degrees of freedom such as a slewing of a spacecraft with flexible appendages or a displacement of a reservoir with a liquid for the case of constraint on velocity of the maneuver. The dynamic equations of motion are formulated, allowing taking into account the flexible elements using the quasistatical approach. The problem of optimal reorientation for rest-to-rest maneuvers is formulated using the objective function, which results in the minimal acceleration of the relative motion of the attached flexible elements during the maneuver. The new features and advantages of the proposed approach are the use of a not widely known objective function for the optimal control problem, which has a clear physical interpretation, and analytical solving the constrained optimization problem by the method based on parameterization of the functional for the multi-point boundary value problem. The solution is illustrated graphically. This analytical solution is applicable also for vibrations rejection at shaping the law of deployment of flexible constructions on spacecraft. It is useful for input shaping motion laws of objects of the ground-based transport in the modes of braking and acceleration for minimization of relative accelerations of passengers and goods.

show abstract

Fuel optimal propulsive maneuver of an experimental structure exhibiting spacelike dynamics

Cited by 22 publications

References 18 publications

Command shaping for flexible systems: A review of the first 50 years

Command shaping for flexible systems: A review of the first 50 years

Optimal limited-rate slewing of a flexible spacecraft

Optimal Maneuver of Mechanical System with Internal Degrees of Freedom with State-Variable Constraint

Contact Info

Product

Resources

About