scholarly journals Some New Locally Optimal Control Laws for Sailcraft Dynamics in Heliocentric Orbits

2013 ◽  
Vol 2013 ◽  
pp. 1-16 ◽  
Author(s):  
F. A. Abd El-Salam

The concept of solar sailing and its developing spacecraft is presented. The gravitational and solar radiation forces are considered. The effect of source of radiation pressure and the force due to coronal mass ejections and solar wind on the sailcraft configurations is modeled. Some analytical control laws with some mentioned input constraints for optimizing sailcraft dynamics in heliocentric orbit using lagrange’s planetary equations are obtained. Optimum force vector in a required direction is maximized by deriving optimal sail cone angle. Ignoring the absorbed and diffusely reflected parts of the radiation, some special cases are obtained. New control laws that maximize thrust to obtain certain required maximization in some particular orbital element are obtained.

2005 ◽  
Vol 28 (5) ◽  
pp. 1038-1048 ◽  
Author(s):  
Malcolm Macdonald ◽  
Colin R. McInnes

AIChE Journal ◽  
1998 ◽  
Vol 44 (1) ◽  
pp. 116-130 ◽  
Author(s):  
Sairam Valluri ◽  
Masoud Soroush

Author(s):  
A.I. BOKHONSKY ◽  
N.I. VARMINSKAYA ◽  
A.I. RYZHKOV

A reverse optimality principle (ROP) is formulated and an algorithm for its use for constructing optimal portable object movements is presented. Using an example, sufficient conditions for the extremality of the restored criterion functional are verified when constructing an optimal control of the «acceleration–deceleration» type. The following theorems were formulated and proved: on the numerical equality of integrals with different integral functions, on the minimum energy to achieve the goal of optimally controlled motion in the form of «acceleration–deceleration». Basing on the generalization of the results for optimal controls designing of the «acceleration–deceleration» type of motion, whence the known special cases follow, universal analytical control function (translational acceleration) was found. Analytically and numerically was confirmed the existence of the limiting minimum control energy at which the movement of an object from the initial state of rest to a new state of rest is possible at a fixed distance and time of motion.


2006 ◽  
Vol 16 (10) ◽  
pp. 2815-2841 ◽  
Author(s):  
XIAOXIN LIAO ◽  
PEI YU ◽  
SHENGLI XIE ◽  
YULI FU

In this paper, we first give a constructive proof for the existence of globally exponential attractive set of Chua's system with a smooth nonlinear function. Then, we derive a series of simple algebraic sufficient conditions under which two same type of smooth Chua's systems are globally exponentially synchronized using simple linear feedback controls. Also, as the special cases of chaos synchronization, we consider global tracking and global exponentially tracking of periodic motions, as well as global stabilization and globally exponential stabilization of equilibrium points in smooth Chua's systems. We construct a series of simple, easily applicable feedback control laws. Computer simulation results are presented to verify the theoretical predictions.


2020 ◽  
Vol 67 (4) ◽  
pp. 1391-1411
Author(s):  
Pascal Saint-Hilaire ◽  
Jeffrey E. Marchese

AbstractWe present the general concept of a telescope with optics and detectors mounted on two separate spacecrafts, in orbit around the telescope’s target (scopocentric or target-centric orbit), and using propulsion to maintain the Target-Optics-Detector alignment and Optics-Detector distance. Specifically, we study the case of such a telescope with the Sun as the target, orbiting at $\sim $ ∼ 1 AU. We present a simple differential acceleration budget for maintaining Target-Optics-Detector alignment and Optics-Detector distance, backed by simulations of the orbital dynamics, including solar radiation pressure and influence of the planets. Of prime interest are heliocentric orbits (such as Earth-trailing/leading orbits or Distant Retrograde Orbits), where thrust requirement to maintain formation is primarily in a single direction (either sunward or anti-sunward), can be quite minuscule (a few m/s/year), and preferably met by constant-thrust engines such as solar electric propulsion or even by solar sailing via simple extendable and/or orientable flaps or rudders.


2021 ◽  
pp. 107754632199015
Author(s):  
Xingyu Zhou ◽  
Haoping Wang ◽  
Yang Tian

In this article, an adaptive boundary iterative learning vibration control is developed for a class of the rigid–flexible manipulator system under distributed disturbances and input constraints. With the help of the virtual work principle, the dynamics of the rigid–flexible manipulator are modeled and described by coupled ordinary differential equations and partial differential equations. Based on the original infinite dimension system model, three compounded adaptive boundary iterative learning vibration control laws are constructed with disturbance observers and adaptive vibration laws, aiming to track the desired joint angular positions and achieve vibration suppression simultaneously. Three disturbance observers are proposed to determine the upper bounded approximation of the unknown external disturbances. Hyperbolic tangent and saturation functions are incorporated into adaptive vibration laws to handle input constraints. It is proved by Lyapunov–Krasovskii-like composite energy functions that elastic vibrations and tracking errors can asymptotically converge to zero along the iteration axis. Finally, the efficacy of the developed adaptive boundary iterative learning vibration control approach is illustrated by the simulation results under distributed disturbances and input constraints.


Author(s):  
Eloy Peña-Asensio ◽  
Josep Maria Trigo-Rodríguez ◽  
Maria Gritsevich ◽  
Albert Rimola

Abstract The disruption of asteroids and comets produces cm-sized meteoroids that end up impacting the Earth’s atmosphere and producing bright fireballs that might have associated shock waves or, in geometrically-favorable occasions excavate craters that put them into unexpected hazardous scenarios. The astrometric reduction of meteors and fireballs to infer their atmospheric trajectories and heliocentric orbits involves a complex and tedious process that generally requires many manual tasks. To streamline the process, we present a software package called SPMN 3D Fireball Trajectory and Orbit Calculator (3D-FireTOC), an automatic Python code for detection, trajectory reconstruction of meteors, and heliocentric orbit computation from video recordings. The automatic 3D-FireTOC package comprises of a user interface and a graphic engine that generates a realistic 3D representation model, which allows users to easily check the geometric consistency of the results and facilitates scientiï¬c content production for dissemination. The software automatically detects meteors from digital systems, completes the astrometric measurements, performs photometry, computes the meteor atmospheric trajectory, calculates the velocity curve, and obtains the radiant and the heliocentric orbit, all in all quantifying the error measurements in each step. The software applies corrections such as light aberration, refraction, zenith attraction, diurnal aberration and atmospheric extinction. It also characterizes the atmospheric flight and consequently determines fireball fates by using the α − β criterion that analyses the ability of a fireball to penetrate deep into the atmosphere and produce meteorites. We demonstrate the performance of the software by analyzing two bright fireballs recorded by the Spanish Fireball and Meteorite Network (SPMN).


2020 ◽  
pp. 107754632094017
Author(s):  
Ning Ji ◽  
Hongjun Yang ◽  
Jinkun Liu

In this study, we considered the coordination and vibration control for two sets of flexible satellite systems with input constraints and actuator failures. The parameters of both systems were kept uniform, and one was called the master flexible satellite, and the other one was called slave flexible satellite. The two sets of the flexible satellite systems were modelled as partial differential equations. Coordination control laws were designed to turn the master flexible satellite system to the desired angle and then turn the slave system to the angle of the master satellite system. Furthermore, the hyperbolic tangent function was adopted to realize the control input constraint. The adaptive control laws were designed to ensure that the systems work normally even when the actuator fails. Lyapunov’s direct method was adopted and stability analysis was given. Finally, numerical simulations were conducted to validate the results.


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