Misplaced Pages

#431568

61-589: The satellite, which was insured, was destroyed when the rocket that was launching it exploded. The rocket was a Zenit 3SL being launched by Sea Launch from its Ocean Odyssey launch pad. The launch attempt occurred at 23:22 GMT on 30 January 2007. "There was an explosion as we were lifting off," said Paula Korn, a spokeswoman for Sea Launch. NSS-8 was designed to support a wide range of functions, including broadcast applications, government and military operations, corporate communications and Broadband Internet services. When placed in its final orbital position (57° E),

122-404: A body is proportional to the product of the masses of the two attracting bodies and decreases inversely with the square of the distance between them. To this Newtonian approximation, for a system of two-point masses or spherical bodies, only influenced by their mutual gravitation (called a two-body problem ), their trajectories can be exactly calculated. If the heavier body is much more massive than

183-427: A certain time called the period. This motion is described by the empirical laws of Kepler, which can be mathematically derived from Newton's laws. These can be formulated as follows: Note that while bound orbits of a point mass or a spherical body with a Newtonian gravitational field are closed ellipses , which repeat the same path exactly and indefinitely, any non-spherical or non-Newtonian effects (such as caused by

244-492: A planet, or of an artificial satellite around an object or position in space such as a planet, moon, asteroid, or Lagrange point . Normally, orbit refers to a regularly repeating trajectory, although it may also refer to a non-repeating trajectory. To a close approximation, planets and satellites follow elliptic orbits , with the center of mass being orbited at a focal point of the ellipse, as described by Kepler's laws of planetary motion . For most situations, orbital motion

305-420: A practical sense, both of these trajectory types mean the object is "breaking free" of the planet's gravity, and "going off into space" never to return. In most situations, relativistic effects can be neglected, and Newton's laws give a sufficiently accurate description of motion. The acceleration of a body is equal to the sum of the forces acting on it, divided by its mass, and the gravitational force acting on

366-466: A premature engine shutdown, as the rocket strayed from its lift-off trajectory, plunging into the Pacific Ocean shortly after launch. Orbit This is an accepted version of this page In celestial mechanics , an orbit (also known as orbital revolution ) is the curved trajectory of an object such as the trajectory of a planet around a star, or of a natural satellite around

427-410: A single point called the barycenter. The paths of all the star's satellites are elliptical orbits about that barycenter. Each satellite in that system will have its own elliptical orbit with the barycenter at one focal point of that ellipse. At any point along its orbit, any satellite will have a certain value of kinetic and potential energy with respect to the barycenter, and the sum of those two energies

488-506: A software error resulted in the premature cutoff of the second stage, leaving the ICO F-1 satellite unable to reach orbit. On 29 June 2004, during the launch of Apstar 5 , the upper stage shut down 54 seconds early due to a wiring fault, leaving the satellite in a lower than planned orbit. The spacecraft raised itself to the correct orbit by means of its onboard manoeuvring engines, at the expense of fuel intended for stationkeeping once in

549-491: A technical sense—they are describing a portion of an elliptical path around the center of gravity—but the orbits are interrupted by striking the Earth. If the cannonball is fired with sufficient speed, the ground curves away from the ball at least as much as the ball falls—so the ball never strikes the ground. It is now in what could be called a non-interrupted or circumnavigating, orbit. For any specific combination of height above

610-505: Is a constant value at every point along its orbit. As a result, as a planet approaches periapsis , the planet will increase in speed as its potential energy decreases; as a planet approaches apoapsis , its velocity will decrease as its potential energy increases. There are a few common ways of understanding orbits: The velocity relationship of two moving objects with mass can thus be considered in four practical classes, with subtypes: Orbital rockets are launched vertically at first to lift

671-528: Is a convenient approximation to take the center of mass as coinciding with the center of the more massive body. Advances in Newtonian mechanics were then used to explore variations from the simple assumptions behind Kepler orbits, such as the perturbations due to other bodies, or the impact of spheroidal rather than spherical bodies. Joseph-Louis Lagrange developed a new approach to Newtonian mechanics emphasizing energy more than force, and made progress on

SECTION 10

#1732782440432

732-418: Is adequately approximated by Newtonian mechanics , which explains gravity as a force obeying an inverse-square law . However, Albert Einstein 's general theory of relativity , which accounts for gravity as due to curvature of spacetime , with orbits following geodesics , provides a more accurate calculation and understanding of the exact mechanics of orbital motion. Historically, the apparent motions of

793-407: Is adopted of taking the potential energy as zero at infinite separation, the bound orbits will have negative total energy, the parabolic trajectories zero total energy, and hyperbolic orbits positive total energy. An open orbit will have a parabolic shape if it has the velocity of exactly the escape velocity at that point in its trajectory, and it will have the shape of a hyperbola when its velocity

854-464: Is also a vector. Because our basis vector r ^ {\displaystyle {\hat {\mathbf {r} }}} moves as the object orbits, we start by differentiating it. From time t {\displaystyle t} to t + δ t {\displaystyle t+\delta t} , the vector r ^ {\displaystyle {\hat {\mathbf {r} }}} keeps its beginning at

915-404: Is greater than the escape velocity. When bodies with escape velocity or greater approach each other, they will briefly curve around each other at the time of their closest approach, and then separate, forever. All closed orbits have the shape of an ellipse . A circular orbit is a special case, wherein the foci of the ellipse coincide. The point where the orbiting body is closest to Earth is called

976-581: Is located in the plane using vector calculus in polar coordinates both with the standard Euclidean basis and with the polar basis with the origin coinciding with the center of force. Let r {\displaystyle r} be the distance between the object and the center and θ {\displaystyle \theta } be the angle it has rotated. Let x ^ {\displaystyle {\hat {\mathbf {x} }}} and y ^ {\displaystyle {\hat {\mathbf {y} }}} be

1037-402: Is that it was able to account for the remaining unexplained amount in precession of Mercury's perihelion first noted by Le Verrier. However, Newton's solution is still used for most short term purposes since it is significantly easier to use and sufficiently accurate. Within a planetary system , planets, dwarf planets , asteroids and other minor planets , comets , and space debris orbit

1098-464: The apoapsis is that point at which they are the farthest. (More specific terms are used for specific bodies. For example, perigee and apogee are the lowest and highest parts of an orbit around Earth, while perihelion and aphelion are the closest and farthest points of an orbit around the Sun.) In the case of planets orbiting a star, the mass of the star and all its satellites are calculated to be at

1159-467: The eccentricities of the planetary orbits vary over time. Mercury , the smallest planet in the Solar System, has the most eccentric orbit. At the present epoch , Mars has the next largest eccentricity while the smallest orbital eccentricities are seen with Venus and Neptune . As two objects orbit each other, the periapsis is that point at which the two objects are closest to each other and

1220-646: The equator in the Pacific Ocean , at a point with 154°W longitude , about 370 kilometres east of Kiritimati . The Zenit-3SL design began in the late 1980s as the Zenit-3, a proposed replacement for the Proton-K , which would have used a Zenit-2 rocket with a Block D upper stage. This proposal was shelved after the dissolution of the Soviet Union , as Russia inherited the space programme, however

1281-453: The perigee , and when orbiting a body other than earth it is called the periapsis (less properly, "perifocus" or "pericentron"). The point where the satellite is farthest from Earth is called the apogee , apoapsis, or sometimes apifocus or apocentron. A line drawn from periapsis to apoapsis is the line-of-apsides . This is the major axis of the ellipse, the line through its longest part. Bodies following closed orbits repeat their paths with

SECTION 20

#1732782440432

1342-737: The three-body problem , discovering the Lagrangian points . In a dramatic vindication of classical mechanics, in 1846 Urbain Le Verrier was able to predict the position of Neptune based on unexplained perturbations in the orbit of Uranus . Albert Einstein in his 1916 paper The Foundation of the General Theory of Relativity explained that gravity was due to curvature of space-time and removed Newton's assumption that changes in gravity propagate instantaneously. This led astronomers to recognize that Newtonian mechanics did not provide

1403-446: The three-body problem ; however, it converges too slowly to be of much use. Except for special cases like the Lagrangian points , no method is known to solve the equations of motion for a system with four or more bodies. Rather than an exact closed form solution, orbits with many bodies can be approximated with arbitrarily high accuracy. These approximations take two forms: Differential simulations with large numbers of objects perform

1464-410: The Earth at the point half an orbit beyond, and directly opposite the firing point, below the circular orbit. At a specific horizontal firing speed called escape velocity , dependent on the mass of the planet and the distance of the object from the barycenter, an open orbit (E) is achieved that has a parabolic path . At even greater speeds the object will follow a range of hyperbolic trajectories . In

1525-427: The Sun, their orbital periods respectively about 11.86 and 0.615 years. The proportionality is seen by the fact that the ratio for Jupiter, 5.2 /11.86 , is practically equal to that for Venus, 0.723 /0.615 , in accord with the relationship. Idealised orbits meeting these rules are known as Kepler orbits . Isaac Newton demonstrated that Kepler's laws were derivable from his theory of gravitation and that, in general,

1586-755: The Zenit was manufactured in Ukrainian SSR . Boeing became involved in the programme in 1994. The design was subsequently modified, with a modified version of the Block DM replacing the Block D. Sea Launch integrated the rockets in California , and transfers them to Odyssey via the Sea Launch Commander for transportation to the launch site. Once at the launch site, the rocket was erected on

1647-403: The accelerations in the radial and transverse directions. As said, Newton gives this first due to gravity is − μ / r 2 {\displaystyle -\mu /r^{2}} and the second is zero. Equation (2) can be rearranged using integration by parts. We can multiply through by r {\displaystyle r} because it is not zero unless

1708-462: The atmosphere, in an act commonly referred to as an aerobraking maneuver. As an illustration of an orbit around a planet, the Newton's cannonball model may prove useful (see image below). This is a ' thought experiment ', in which a cannon on top of a tall mountain is able to fire a cannonball horizontally at any chosen muzzle speed. The effects of air friction on the cannonball are ignored (or perhaps

1769-466: The calculations in a hierarchical pairwise fashion between centers of mass. Using this scheme, galaxies, star clusters and other large assemblages of objects have been simulated. The following derivation applies to such an elliptical orbit. We start only with the Newtonian law of gravitation stating that the gravitational acceleration towards the central body is related to the inverse of the square of

1830-517: The center of gravity and mass of the planet, there is one specific firing speed (unaffected by the mass of the ball, which is assumed to be very small relative to the Earth's mass) that produces a circular orbit , as shown in (C). As the firing speed is increased beyond this, non-interrupted elliptic orbits are produced; one is shown in (D). If the initial firing is above the surface of the Earth as shown, there will also be non-interrupted elliptical orbits at slower firing speed; these will come closest to

1891-459: The coordinate system at the center of the mass of the system. Energy is associated with gravitational fields . A stationary body far from another can do external work if it is pulled towards it, and therefore has gravitational potential energy . Since work is required to separate two bodies against the pull of gravity, their gravitational potential energy increases as they are separated, and decreases as they approach one another. For point masses,

NSS-8 - Misplaced Pages Continue

1952-474: The correct orbit . On 30 January 2007, a Zenit-3SL exploded on the launch pad after an engine failure caused by debris in the turbopump . The payload on that flight was the NSS-8 communications satellite for SES New Skies . This caused a considerable amount of downtime whilst damage to the launch platform was repaired. On 1 February 2013, during the launch of Intelsat-27, a Zenit-3SL launch vehicle suffered

2013-683: The distance r {\displaystyle r} of the orbiting object from the center as a function of its angle θ {\displaystyle \theta } . However, it is easier to introduce the auxiliary variable u = 1 / r {\displaystyle u=1/r} and to express u {\displaystyle u} as a function of θ {\displaystyle \theta } . Derivatives of r {\displaystyle r} with respect to time may be rewritten as derivatives of u {\displaystyle u} with respect to angle. Plugging these into (1) gives So for

2074-434: The distance between them, namely where F 2 is the force acting on the mass m 2 caused by the gravitational attraction mass m 1 has for m 2 , G is the universal gravitational constant, and r is the distance between the two masses centers. From Newton's Second Law, the summation of the forces acting on m 2 related to that body's acceleration: where A 2 is the acceleration of m 2 caused by

2135-428: The entire analysis can be done separately in these dimensions. This results in the harmonic parabolic equations x = A cos ⁡ ( t ) {\displaystyle x=A\cos(t)} and y = B sin ⁡ ( t ) {\displaystyle y=B\sin(t)} of the ellipse. The location of the orbiting object at the current time t {\displaystyle t}

2196-408: The force of gravitational attraction F 2 of m 1 acting on m 2 . Combining Eq. 1 and 2: Solving for the acceleration, A 2 : where μ {\displaystyle \mu \,} is the standard gravitational parameter , in this case G m 1 {\displaystyle Gm_{1}} . It is understood that the system being described is m 2 , hence

2257-417: The gravitational energy decreases to zero as they approach zero separation. It is convenient and conventional to assign the potential energy as having zero value when they are an infinite distance apart, and hence it has a negative value (since it decreases from zero) for smaller finite distances. When only two gravitational bodies interact, their orbits follow a conic section . The orbit can be open (implying

2318-490: The highest accuracy in understanding orbits. In relativity theory , orbits follow geodesic trajectories which are usually approximated very well by the Newtonian predictions (except where there are very strong gravity fields and very high speeds) but the differences are measurable. Essentially all the experimental evidence that can distinguish between the theories agrees with relativity theory to within experimental measurement accuracy. The original vindication of general relativity

2379-400: The maiden flight. The only launch to be conducted to an orbit other than GTO was that of ICO F-1 , which was intended to be placed into medium Earth orbit , however the rocket failed to reach orbit. Of thirty-six rockets launched, three failed, with a fourth placing its payload into an incorrect, but recoverable orbit. The first failure occurred during the third flight, on 12 March 2000, when

2440-427: The model was capable of reasonably accurately predicting the planets' positions in the sky, more and more epicycles were required as the measurements became more accurate, hence the model became increasingly unwieldy. Originally geocentric , it was modified by Copernicus to place the Sun at the centre to help simplify the model. The model was further challenged during the 16th century, as comets were observed traversing

2501-504: The mountain is high enough that the cannon is above the Earth's atmosphere, which is the same thing). If the cannon fires its ball with a low initial speed, the trajectory of the ball curves downward and hits the ground (A). As the firing speed is increased, the cannonball hits the ground farther (B) away from the cannon, because while the ball is still falling towards the ground, the ground is increasingly curving away from it (see first point, above). All these motions are actually "orbits" in

NSS-8 - Misplaced Pages Continue

2562-410: The object never returns) or closed (returning). Which it is depends on the total energy ( kinetic + potential energy ) of the system. In the case of an open orbit, the speed at any position of the orbit is at least the escape velocity for that position, in the case of a closed orbit, the speed is always less than the escape velocity. Since the kinetic energy is never negative if the common convention

2623-471: The orbital speed of each planet is not constant, as had previously been thought, but rather that the speed depends on the planet's distance from the Sun. Third, Kepler found a universal relationship between the orbital properties of all the planets orbiting the Sun. For the planets, the cubes of their distances from the Sun are proportional to the squares of their orbital periods. Jupiter and Venus, for example, are respectively about 5.2 and 0.723 AU distant from

2684-498: The orbiting object crashes. Then having the derivative be zero gives that the function is a constant. which is actually the theoretical proof of Kepler's second law (A line joining a planet and the Sun sweeps out equal areas during equal intervals of time). The constant of integration, h , is the angular momentum per unit mass . In order to get an equation for the orbit from equation (1), we need to eliminate time. (See also Binet equation .) In polar coordinates, this would express

2745-411: The orbits of bodies subject to gravity were conic sections (this assumes that the force of gravity propagates instantaneously). Newton showed that, for a pair of bodies, the orbits' sizes are in inverse proportion to their masses , and that those bodies orbit their common center of mass . Where one body is much more massive than the other (as is the case of an artificial satellite orbiting a planet), it

2806-421: The origin and rotates from angle θ {\displaystyle \theta } to θ + θ ˙   δ t {\displaystyle \theta +{\dot {\theta }}\ \delta t} which moves its head a distance θ ˙   δ t {\displaystyle {\dot {\theta }}\ \delta t} in

2867-627: The perpendicular direction θ ^ {\displaystyle {\hat {\boldsymbol {\theta }}}} giving a derivative of θ ˙ θ ^ {\displaystyle {\dot {\theta }}{\hat {\boldsymbol {\theta }}}} . We can now find the velocity and acceleration of our orbiting object. The coefficients of r ^ {\displaystyle {\hat {\mathbf {r} }}} and θ ^ {\displaystyle {\hat {\boldsymbol {\theta }}}} give

2928-477: The planets were described by European and Arabic philosophers using the idea of celestial spheres . This model posited the existence of perfect moving spheres or rings to which the stars and planets were attached. It assumed the heavens were fixed apart from the motion of the spheres and was developed without any understanding of gravity. After the planets' motions were more accurately measured, theoretical mechanisms such as deferent and epicycles were added. Although

2989-405: The platform, and a three-day countdown was initiated. The countdown was fully automated, and personnel were evacuated from the launch platform to Commander prior to launch. Zenit-3SL launches predominantly carried communications satellites into geosynchronous transfer orbits . As of 2009, the only payload to be launched by a Zenit-3SL that was not a communications satellite was a DemoSat , on

3050-548: The radial and transverse polar basis with the first being the unit vector pointing from the central body to the current location of the orbiting object and the second being the orthogonal unit vector pointing in the direction that the orbiting object would travel if orbiting in a counter clockwise circle. Then the vector to the orbiting object is We use r ˙ {\displaystyle {\dot {r}}} and θ ˙ {\displaystyle {\dot {\theta }}} to denote

3111-408: The rocket above the atmosphere (which causes frictional drag), and then slowly pitch over and finish firing the rocket engine parallel to the atmosphere to achieve orbit speed. Once in orbit, their speed keeps them in orbit above the atmosphere. If e.g., an elliptical orbit dips into dense air, the object will lose speed and re-enter (i.e. fall). Occasionally a space craft will intentionally intercept

SECTION 50

#1732782440432

3172-668: The satellite would have provided coverage to two-thirds of the planet, serving countries in Europe, Africa, the Middle East, the Indian subcontinent and Asia. This article about one or more spacecraft of the Netherlands is a stub . You can help Misplaced Pages by expanding it . This article about one or more communications satellites is a stub . You can help Misplaced Pages by expanding it . Zenit 3SL The Zenit-3SL

3233-509: The slight oblateness of the Earth , or by relativistic effects , thereby changing the gravitational field's behavior with distance) will cause the orbit's shape to depart from the closed ellipses characteristic of Newtonian two-body motion . The two-body solutions were published by Newton in Principia in 1687. In 1912, Karl Fritiof Sundman developed a converging infinite series that solves

3294-440: The smaller, as in the case of a satellite or small moon orbiting a planet or for the Earth orbiting the Sun, it is accurate enough and convenient to describe the motion in terms of a coordinate system that is centered on the heavier body, and we say that the lighter body is in orbit around the heavier. For the case where the masses of two bodies are comparable, an exact Newtonian solution is still sufficient and can be had by placing

3355-437: The spheres. The basis for the modern understanding of orbits was first formulated by Johannes Kepler whose results are summarised in his three laws of planetary motion. First, he found that the orbits of the planets in our Solar System are elliptical, not circular (or epicyclic ), as had previously been believed, and that the Sun is not located at the center of the orbits, but rather at one focus . Second, he found that

3416-730: The standard Euclidean bases and let r ^ = cos ⁡ ( θ ) x ^ + sin ⁡ ( θ ) y ^ {\displaystyle {\hat {\mathbf {r} }}=\cos(\theta ){\hat {\mathbf {x} }}+\sin(\theta ){\hat {\mathbf {y} }}} and θ ^ = − sin ⁡ ( θ ) x ^ + cos ⁡ ( θ ) y ^ {\displaystyle {\hat {\boldsymbol {\theta }}}=-\sin(\theta ){\hat {\mathbf {x} }}+\cos(\theta ){\hat {\mathbf {y} }}} be

3477-412: The standard derivatives of how this distance and angle change over time. We take the derivative of a vector to see how it changes over time by subtracting its location at time t {\displaystyle t} from that at time t + δ t {\displaystyle t+\delta t} and dividing by δ t {\displaystyle \delta t} . The result

3538-443: The subscripts can be dropped. We assume that the central body is massive enough that it can be considered to be stationary and we ignore the more subtle effects of general relativity . When a pendulum or an object attached to a spring swings in an ellipse, the inward acceleration/force is proportional to the distance A = F / m = − k r . {\displaystyle A=F/m=-kr.} Due to

3599-463: The system's barycenter in elliptical orbits . A comet in a parabolic or hyperbolic orbit about a barycenter is not gravitationally bound to the star and therefore is not considered part of the star's planetary system. Bodies that are gravitationally bound to one of the planets in a planetary system, either natural or artificial satellites , follow orbits about a barycenter near or within that planet. Owing to mutual gravitational perturbations ,

3660-498: The way vectors add, the component of the force in the x ^ {\displaystyle {\hat {\mathbf {x} }}} or in the y ^ {\displaystyle {\hat {\mathbf {y} }}} directions are also proportionate to the respective components of the distances, r x ″ = A x = − k r x {\displaystyle r''_{x}=A_{x}=-kr_{x}} . Hence,

3721-679: Was an expendable carrier rocket operated by Sea Launch . First flown in 1999, it was launched 36 times, with three failures and one partial failure. It was a member of the Zenit family of rockets, and is built by the Yuzhnoye Design Bureau . RKK Energia produced the Block DM-SL upper stage , whilst the payload fairing was produced by Boeing . Launches were conducted from the Ocean Odyssey platform anchored on

SECTION 60

#1732782440432
#431568