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  2. Orbit Irrigation Products - Wikipedia

    en.wikipedia.org/wiki/Orbit_Irrigation_Products

    Orbit logo. Orbit Irrigation Products, Inc, located in Salt Lake City, UT, United States, is a manufacturer and supplier of irrigation products for residential and commercial markets and has been in business since 1986. It distributes over 2,000 products to 40 countries on five continents. Orbit was acquired by Husqvarna Group in December 2021 ...

  3. Orbital maneuver - Wikipedia

    en.wikipedia.org/wiki/Orbital_maneuver

    The Oberth effect is used in a powered flyby or Oberth maneuver where the application of an impulse, typically from the use of a rocket engine, close to a gravitational body (where the gravity potential is low, and the speed is high) can give much more change in kinetic energy and final speed (i.e. higher specific energy) than the same impulse ...

  4. Comparison of orbital rocket engines - Wikipedia

    en.wikipedia.org/wiki/Comparison_of_orbital...

    Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio

  5. Spike (missile) - Wikipedia

    en.wikipedia.org/wiki/Spike_(missile)

    Spike (Hebrew: ספייק) is an Israeli fire-and-forget anti-tank guided missile and anti-personnel missile with a tandem-charge high-explosive anti-tank (HEAT ...

  6. Dirac delta function - Wikipedia

    en.wikipedia.org/wiki/Dirac_delta_function

    The impulse response can be computed to any desired degree of accuracy by choosing a suitable approximation for δ, and once it is known, it characterizes the system completely. See LTI system theory § Impulse response and convolution. The inverse Fourier transform of the tempered distribution f(ξ) = 1 is the delta function.

  7. Orbital mechanics - Wikipedia

    en.wikipedia.org/wiki/Orbital_mechanics

    From a circular orbit, thrust applied in a direction opposite to the satellite's motion changes the orbit to an elliptical one; the satellite will descend and reach the lowest orbital point (the periapse) at 180 degrees away from the firing point; then it will ascend back. The period of the resultant orbit will be less than that of the original ...