2 edition of study of attitude stability of a symmetrical satellite in a circular orbit found in the catalog.
study of attitude stability of a symmetrical satellite in a circular orbit
Hsien-tsan Wang
Published
1967
.
Written in
Edition Notes
| Statement | by Hsien-tsan Wang. |
| The Physical Object | |
|---|---|
| Pagination | [9], 87 leaves, bound : |
| Number of Pages | 87 |
| ID Numbers | |
| Open Library | OL14221616M |
In the present thesis, the nonlinear attitude motion of a satellite consisting of a single rigid body, or of two rigid bodies in gyrostat configuration, in a central gravitational field, on a circular or an elliptic orbit, is studied with particular attention given to the understanding of long-time dynamic behavior for a wide range of parameters. 1. An artificial satellite circles Earth in a circular orbit at a location where the acceleration due to gravity is m/s2. a) What is the orbital period of the satellite? First, we compute r from a = GM=r2. We find r = √ GM=a. It is also possible to compute v from v2=r = a, which gives v = √ ar = (GMa)1=4. Now we can compute T from v File Size: 17KB.
satellite as rigid and assumes that there is no interacuion between the orbital motion and the rotational stability of the body. This is implied in the assumption that the center of mass moves in a given orbit; this assumption is referred to as orbital. constraints. Where the body contains moving parts, such as the oscillators, the center of. A spacecraft is in a circular orbit at an attitude of km above the earth's surface. If an onboard rocket provides a delta-v of m/s in the direction of satellite's motion. Calculate the .
feff(r) = l2 μr3 − f(r) = 0, for orbit to be circular. f ′ eff(r) − 3. This is very weak compared to the statement of Bertrand's Theorem. orbit families and the combination of dynamical systems theory with com-puter simulation to study the nature of three body orbits. The study of orbits in the three body problem only makes up half of a spacecraft’s dynamics; the attitude motion is certainly important as well. ISEE-3 was nominally spin-stabilized about its symmetry axis, which.
A model for analytical study of the attitude stability of an orbiting satellite consists of a rigid body whose mass center is constrained to move at constant speed in a circular path about the center of an inverse-square force field.
The body is assumed to have one axis of inertial : Hsien-tsan Wang. A STUDY OF ATTITUDE STABILITY OF A SYMMETRICAL SATELLITE IN A CIRCULAR ORBIT INTRODUCTION The stability of a dynamic system is studied by examining the behavior of solutions to equations of the form x = X(x, x, •••, x), 12 n (where x.
are the generalized coordinates of N-space. in a circular orbit. DeBra and Delp C6l investigated the stability of a satellite of unequal. moments of inertia possessing zero spin relative to an orbiting frame of reference whereas its mass center was moving in a circular orbit.
The attitude stability of a symmetric satellite andFile Size: 7MB. Graduation date: A model for analytical study of the attitude stability of an\ud orbiting satellite consists of a rigid body whose mass center is constrained to move at constant speed in a circular path about the\ud center of an inverse-square force field.
The body is assumed to\ud have one axis of inertial symmetry. This paper treats analytically the problem of the stability of the attitude motions of a gravity-stabilized gyrostat satellite that is in a circular orbit around a spherical planet.
The vehicle considered consists of a body with no special symmetries that has any number of rotors attached to by: system fixed in Earth. However the environmental forces and torques acting on the satellite affect the attitude and the orbit of the satellite.
The rotational motion is described by the Euler’s dynamic equations, which depend on the external torques. Then it is essential to study the influence of the torques in the satellite mission.
A satellite is in a circular orbit around the Earth at an altitude of x 10^6 m. Find (a) the period of the orbit, (b) the speed of the satellite, and (c) the acceleration of the satellite. Back of the book answer just lists m/s but I dont know how to solve it and use exact units, this is what I have what am I doing wrong.
At what altitude will a satellite complete a circular orbit of the Earth in hours. I can't seem to figure this out, I've tried multiple ways. I feel this should be easy. Formula if possible also please. Update: _____ km. Answer Save. 1 Answer.
Relevance. surf_dude. Lv 5. 8 years ago. discuss the statement: "A satellite is continually in free fall". A satellite in a circular orbit around the Earth moves like a projectile.
One component of its motion is parallel to Earth's surface, while the other component is a free-fall acceleration toward Earth. physics chapter Terms in this set (13) impact of gravity on speed of a circling satelite. in circular orbit the speed of a circling satellite is not changed by gravity.
satellite in circular orbit around Earth. always moving perpendicular to gravity and parallel to Earth's surface at constant speed.
period. center of mass of the satellite around the Earth [6]. Thus, assuming that the satellites have well-defined circular orbit, the goal is to study the stability of the rotational motion of the satellite.
In this paper, we consider a gyrostat satellite in circular orbit around a planet, with spherical symmetry in a case, and axial symmetry in another. We establish the equations of the rotational motion of the gyrostat satellite and use the gravitational torque obtained by Maciejeweski [8] when truncating the gravity field in the level of the harmonic by: 3.
The attitude of a spinning symmetrical satellite in an elliptical orbit Is analyzed. The perturbed motion of the satellite is described by linear equations with periodic coefficients.
tability is determined by Floquet theory. Active control is added to the system and results lead to a linear periodic control law. An analytical method is proposed to study the attitude stability of a triaxial spacecraft moving in a circular Keplerian orbit in the geomagnetic field.
The method is developed based on the electrodynamics effect of the influence of the Lorentz force acting on the charged spacecraft’s by: 4. Equation (29) is the linear discrete equation for perturbations of the attitude dynamics of a spacecraft in a circular orbit, expressed in terms of R3 ≃ so(3).
The important feature of (29) is that it is linearized in such a way that it respects the geometry of the special orthogonal group SO(3). mu = ; % Earth’s gravitational parameter [km^3/s^2] R_earth = ; % Earth radius [km] % Plot the speed and period of a satellite in circular LEO as.
Satellite attitude dynamics Introduction Torque-free motion Stability of torque-free motion Dual-spin spacecraft Nutation damper Coning maneuver Attitude control thrusters Yo-yo despin mechanism Gyroscopic attitude control Gravity-gradient stabilization.
We consider the attitude motion of a satellite with a circular orbit in a central Newtonian gravitational field. The satellite is a solid body whose mass geometry is that of a plate.
Stability of circular orbits r0 r0 stable unstable The stability of circular orbits depends on whether the orbit is at the local minimum or maximum of u. When it is at the minimum, small displacements give rise to simple harmonic oscillations around the stable orbit.
This is an extension of the analysis of static stability to a non-inertial : Sourendu Gupta. We study the motion of a symmetrical satellite with a pair of flexible viscoelastic rods in a central Newtonian gravitational field. A restricted problem formulation is considered, when the satellite's center of mass moves along a fixed circular : A.
Shatina. paper, Kovalev-Savchenko theorem (KST) [1] is used for the study of the stability and it ensures that the motion is Liapunov stable. The objective of this paper is to optimize the stability analysis developed in [2,3] for the satellite in a circular orbit by applying the analytical expressions obtained in [4,5] for the coefficients of the normal 4.during attitude manoeuvres.
An analytical orbit control study is also performed to calculate the propellant required to perform station-keeping, for a specific sub-satellite location over a ten year period.
Finally an investigation on the effects caused by thruster misalignment, on satellite attitude .Proteus uses a GPS receiver for orbit determination and control, which provides satellite position information, and a hydrazine monopropellant system for four 1-Newton thrusters that are mounted on the base of the spacecraft.
Nominal attitude control is based on a gyro-stellar concept. The Star Tracker is accommodated on the payload.
