Attitude Stability of a Spinning Satellite in an Elliptic Orbit

1966 ◽  
Vol 33 (2) ◽  
pp. 402-405 ◽  
Author(s):  
T. R. Kane ◽  
P. M. Barba
Keyword(s):  
Symmetry Axis ◽  
Elliptic Orbit ◽  
Mass Center ◽  
Orbit Plane ◽  
Attitude Stability ◽  
The Stability

Floque´t theory is used to develop a procedure for testing the stability of a spinning, symmetric satellite whose mass center moves on an elliptic orbit while the symmetry axis remains normal to the orbit plane.

On the Stability of a Tethered System with a Free End in Elliptic Orbit

2001 ◽  
Vol 49 (2) ◽  
pp. 237-253
Author(s):  
M. Ruiz ◽  
J. Peláez ◽  
E. C. Lorenzini
Keyword(s):  
Elliptic Orbit ◽  
The Stability

scholarly journals Road train motion stability in BRT system

2019 ◽  
Vol 254 ◽  
pp. 03007 ◽  
Author(s):  
Vladimir Sakhno ◽  
Juraj Gerlici ◽  
Viktor Poliakov ◽  
Alexandr Kravchenko ◽  
Oleg Omelnitcky ◽  
...  
Keyword(s):  
Critical Speed ◽  
Motor Vehicles ◽  
Mass Center ◽  
Passenger Transportation ◽  
Wheel Drive ◽  
Main Index ◽  
Rapid Transport ◽  
The Stability ◽  
The City ◽  
Potential Stability

The peculiarities of organization and perspectives of mass passenger transportation in the city and beyond are considered with the use of "Bus Rapid Transport" (BRT) or Metrobus. Different aspects of study of motor vehicles (MV) controllability and stability are analyzed. It is substantiated that it is sufficient to consider the potential stability of the MV itself, in order to guarantee the stability of the "driver MV" system with a large reserve. A mathematical model of a three-axle bus train consisting of a bus and two trains (metrobus) is developed and the factors influencing the critical speed as the main index of the stability of its movement are determined. It is established that the increase of the critical speed of the metrobus can be achieved by increasing the base of the bus, the first and the second trailer, as well as the mass of the bus and the coefficients of resistance of the drive wheels of the bus driving axle and the trailers axles. At the same time, increasing the distance from the mass center to the bus rear axle, increasing the distance from the mass center to the point of the coupling of the bus with the first trailer, increasing the mass of trailers and the resistance of the resistance of the wheel drive of the bus axis lead to a decrease in the critical speed of the metrobus. This must be taken into account both when designing metrobuses, and when operating them.

Orbital and Attitude Stability of Space Shuttles in Parking Orbits

1975 ◽  
Vol 26 (1) ◽  
pp. 20-24
Author(s):  
R Arho
Keyword(s):  
Gravitational Field ◽  
Stationary State ◽  
Circular Orbit ◽  
Principal Axis ◽  
Orbital Plane ◽  
Moments Of Inertia ◽  
Attitude Stability ◽  
Principal Moments Of Inertia ◽  
Bounded Perturbation ◽  
The Stability

SummaryA unified treatment is given of the orbital and attitude stability of space shuttles in parking orbits (in vacuo) in the earth’s gravitational field. A shuttle in a circular orbit with a principal axis aligned with the horizontal in the orbital plane is found to be in stationary geostatic equilibrium. The demand for stability leads to a condition which must be satisfied by the principal moments of inertia. The stability which is achieved is not asymptotic without control. The stationary state is a stable centre about which a bounded perturbation oscillation without damping may exist.

scholarly journals Sprawl Angle in Simplified Models of Vertical Climbing: Implications for Robots and Roaches

2011 ◽  
Vol 8 (3-4) ◽  
pp. 441-452 ◽  
Author(s):  
Goran A. Lynch ◽  
Lawrence Rome ◽  
Daniel E. Koditschek
Keyword(s):  
Open Loop ◽  
Physical Models ◽  
Stride Frequency ◽  
Mass Center ◽  
Electromechanical Actuators ◽  
Lateral Forces ◽  
Potential Benefits ◽  
The Stability ◽  
New Hypothesis ◽  
Operating Regimes

Empirical data taken from fast climbing sprawled posture animals reveals the presence of strong lateral forces with significant pendulous swaying of the mass center trajectory in a manner captured by a recently proposed dynamical template [1, 2]. In this simulation study we explore the potential benefits of pendulous dynamical climbing in animals and in robots by examining the stability and power advantages of variously more and less sprawled limb morphologies when driven by conventional motors in contrast with animal-like muscles. For open loop models of gait generation inspired by the neural-deprived regimes of high stride-frequency animal climbing, our results corroborate earlier hypotheses that sprawled posture may be required for stability. For quadratic-in-velocity power output actuation models typical of commercially available electromechanical actuators, our results suggest the new hypothesis that sprawled posture may confer significant energetic advantage. In notable contrast, muscle-powered climbers do not experience an energetic benefit from sprawled posture due to their sufficiently distinct actuator characteristics and operating regimes. These results suggest that the potentially significant benefits of sprawled posture climbing may be distinctly different depending upon the details of the climbers sensorimotor endowment. They offer a cautionary instance against mere copying of biology by engineers or rote study of physical models by biologists through this reminder of how even simple questions addressed by simple models can yield nuanced answers that only begin to hint at the complexity of biological designs and behaviors.

scholarly journals Parametric stability of a double pendulum with variable length and with its center of mass in an elliptic orbit

2022 ◽  
Vol 0 (0) ◽  
pp. 0
Author(s):  
José Laudelino de Menezes Neto ◽  
Gerson Cruz Araujo ◽  
Yocelyn Pérez Rothen ◽  
Claudio Vidal
Keyword(s):  
Stable Equilibrium ◽  
Center Of Mass ◽  
Radius Vector ◽  
Variable Length ◽  
Elliptic Orbit ◽  
Double Pendulum ◽  
Parametric Stability ◽  
Instability Regions ◽  
The Stability ◽  
Boundary Curves

<p style='text-indent:20px;'>We consider the planar double pendulum where its center of mass is attached in an elliptic orbit. We consider the case where the rods of the pendulum have variable length, varying according to the radius vector of the elliptic orbit. We make an Hamiltonian view of the problem, find four linearly stable equilibrium positions and construct the boundary curves of the stability/instability regions in the space of the parameters associated with the pendulum length and the eccentricity of the orbit.</p>

scholarly journals On the stability of a resonant rotation of a satellite in an elliptic orbit

2016 ◽  
pp. 619-632 ◽  
Author(s):  
Б.С. Бардин ◽  
◽  
Е. Чекина ◽  
Keyword(s):  
Elliptic Orbit ◽  
The Stability

Double-boundary interval fault-tolerant control for a multi-vector propulsion ROV with thruster failure

2020 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Liqin Zhou ◽  
Changbin Wang ◽  
Lin Li ◽  
Chengxi Zhang ◽  
Dalei Song ◽  
...  
Keyword(s):  
Fault Tolerant ◽  
Load Capacity ◽  
External Disturbance ◽  
Fault Tolerant Control ◽  
Content Type ◽  
Attitude Stability ◽  
Control Scheme ◽  
Yaw Attitude ◽  
The Stability ◽  
Real Time Information

Purpose A novel fault-tolerant control (FTC) method is proposed to assure the stability of the remote-operated vehicle (ROV) by considering the thruster failure-induced model perturbations. The stability of the ROV with failures is guaranteed and optimized with the determined model perturbation set. The effectiveness of the double-boundary interval fault-tolerant control (DBIFTC) is verified through the experiments and proves that the stability is well maintained, which demonstrates a decent performance. Design/methodology/approach This paper studies a control problem for a multi-vector propulsion ROV by using the DBIFTC method in the presence of thruster failure and external disturbances. The ROV kinematics and dynamical models with multi-vector-arranged thruster failure are investigated and formulated for control system design. Findings In this paper, the authors address the FTC problem of ROV with multi-vector thrusters and propose a DBIFTC scheme. The advantage is that as the kinematic system model of ROV is preanalyzed and identified, the DBIFTC becomes more effective. The mathematical stability of the system under the proposed control scheme can be guaranteed. Research limitations/implications The ROV model used in this paper is based on the system identification of experimental data. Although this model has real experimental value and physical significance, the accuracy can be further improved. Practical implications Cable-controlled underwater ROVs are widely used in military missions and scientific research because of their flexibility, sufficient load capacity and real-time information transmission characteristics. The DBIFTC method proposed in this paper can effectively reduce the problem of underwater vehicle under propeller failure or external disturbance and save unnecessary cost. Social implications The DBIFTC method proposed in this paper can ensure the attitude stability of ROV or other underwater equipment operating in the event of propeller failure or external disturbance. In this way, the robot can better perform undersea work and tasks. Originality/value The kinematics and failure mechanisms of the ROV with multi-vector propulsion system are investigated and established. An optimized DBIFTC scheme is investigated to stabilize ROV yaw attitude under the thruster failure condition. The feasibility and effectiveness of the DBIFTC is experimentally validated.

scholarly journals Attitude Control of a Flexible Spacecraft via Fuzzy Optimal Variance Technique

Mathematics ◽  
2022 ◽  
Vol 10 (2) ◽  
pp. 179
Author(s):  
Chokri Sendi
Keyword(s):  
Attitude Control ◽  
Fuzzy Model ◽  
Control Technique ◽  
Linear Matrix ◽  
Control Input ◽  
Attitude Stability ◽  
Vibration Attenuation ◽  
Compensation Technique ◽  
The Stability ◽  
Takagi Sugeno

This paper investigates the performance of a fuzzy optimal variance control technique for attitude stability and vibration attenuation with regard to a spacecraft made of a rigid platform and multiple flexible appendages that can be retargeted to the line of sight. The proposed technique addresses the problem of actuators’ amplitude and rate constraints. The fuzzy model of the spacecraft is developed based on the Takagi-Sugeno(T-S) fuzzy model with disturbances, and the control input is designed using the Parallel Distributed Compensation technique (PDC). The problem is presented as an optimization problem in the form of Linear Matrix Inequalities (LMIs). The performance and the stability of the proposed controller are investigated through numerical simulation.

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