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  2. Two-body problem - Wikipedia

    en.wikipedia.org/wiki/Two-body_problem

    [2] Let x 1 and x 2 be the vector positions of the two bodies, and m 1 and m 2 be their masses. The goal is to determine the trajectories x 1 (t) and x 2 (t) for all times t, given the initial positions x 1 (t = 0) and x 2 (t = 0) and the initial velocities v 1 (t = 0) and v 2 (t = 0). When applied to the two masses, Newton's second law states that

  3. Two-body problem in general relativity - Wikipedia

    en.wikipedia.org/wiki/Two-body_problem_in...

    Since the closed classical orbit is an ellipse in general, the quantity A(1 − e 2) is the semi-latus rectum l of the ellipse. Hence, the final formula of angular apsidal precession for a unit complete revolution is δ φ ≈ 6 π G ( M + m ) c 2 l {\displaystyle \delta \varphi \approx {\frac {6\pi G(M+m)}{c^{2}l}}}

  4. Orbit modeling - Wikipedia

    en.wikipedia.org/wiki/Orbit_modeling

    Orbit modeling is the process of creating mathematical models to simulate motion of a massive body as it moves in orbit around another massive body due to gravity.Other forces such as gravitational attraction from tertiary bodies, air resistance, solar pressure, or thrust from a propulsion system are typically modeled as secondary effects.

  5. n-body problem - Wikipedia

    en.wikipedia.org/wiki/N-body_problem

    The n-body problem considers n point masses m i, i = 1, 2, …, n in an inertial reference frame in three dimensional space ℝ 3 moving under the influence of mutual gravitational attraction. Each mass m i has a position vector q i. Newton's second law says that mass times acceleration m i ⁠ d 2 q i / dt 2 ⁠ is equal to the sum of the ...

  6. Barycenter (astronomy) - Wikipedia

    en.wikipedia.org/wiki/Barycenter_(astronomy)

    If Jupiter had Mercury's orbit (57,900,000 km, 0.387 AU), the Sun–Jupiter barycenter would be approximately 55,000 km from the center of the Sun (⁠ r 1 / R 1 ⁠ ≈ 0.08). But even if the Earth had Eris's orbit (1.02 × 10 10 km, 68 AU), the Sun–Earth barycenter would still be within the Sun (just over 30,000 km from the center).

  7. Spacecraft flight dynamics - Wikipedia

    en.wikipedia.org/wiki/Spacecraft_flight_dynamics

    Hohmann transfer orbit, 2, from an orbit (1) to a higher orbit (3) A Hohmann transfer orbit is the simplest maneuver which can be used to move a spacecraft from one altitude to another. Two burns are required: the first to send the craft into the elliptical transfer orbit, and a second to circularize the target orbit.

  8. Universe Sandbox - Wikipedia

    en.wikipedia.org/wiki/Universe_Sandbox

    Universe Sandbox is a series of interactive space sandbox gravity simulator educational software video games.Using Universe Sandbox, users can see the effects of gravity on objects in the universe and run scale simulations of the Solar System, various galaxies or other simulations, while at the same time interacting and maintaining control over gravity, time, and other objects in the universe ...

  9. List of space flight simulation games - Wikipedia

    en.wikipedia.org/wiki/List_of_space_flight...

    PlayStation 2 Released for PlayStation 2 only; a Windows game with the same name was published by Grabituk.com, but it is not a space flight simulator Starglider: 1986 Argonaut Games: Rainbird Software: Amiga, Amstrad CPC, Apple II, Atari ST, Commodore 64, ZX Spectrum Starship 1: 1977 Atari Atari Arcade Starship Command: 1983 Peter Irvin Acornsoft