Orbital mechanics and formation flying: A digital control by P A Capó-Lugo, P M Bainum

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By P A Capó-Lugo, P M Bainum

Geared toward scholars, college and execs within the aerospace box, this ebook presents functional details at the improvement, research, and regulate of a unmarried and/or a number of spacecraft in area. This publication is split into significant sections: unmarried and a number of satellite tv for pc movement. the 1st part analyses the orbital mechanics, orbital perturbations, and angle dynamics of a unmarried satellite tv for pc round the Earth. utilizing the information of a unmarried satellite tv for pc movement, the interpretation of a bunch of satellites referred to as formation flying or constellation is defined. Formation flying has been one of many major learn themes over the past few years and this booklet explains diversified regulate methods to regulate the satellite tv for pc perspective movement and/or to keep up the constellation jointly. The keep watch over schemes are defined within the discrete area such that it may be simply carried out at the laptop on board the satellite tv for pc. the main target of this e-book is to teach the reader the sensible and the implementation approach within the discrete area.

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48, Issue no. 1, pp. 69–87, January–March 2000. indb 4 18/02/12 1:15 PM Introduction [4] Carpenter, Russell J. , ‘Navigation Accuracy Guidelines for Orbital Formation Flying’, The Journal of the Astronautical Sciences, Vol. 53, Issue no. 2, pp. 207–219, April–June 2005. [5] Carter, T. , ‘Fuel-Optimal Rendezvous Near a Point in General Keplerian Orbit’, Journal of Guidance, Control and Dynamics, Vol. 10, Issue no. 6, pp. 567–573, November–December 1987. [6] Vadali, S. , Vaddi, S. S. and Alfriend, K.

The orbital period describes the amount of time that the satellite takes to complete one full orbit. 20)) is constant. 51) where a is the semimajor axis, and b is the semiminor axis of the ellipse.

The deployment procedure is shown in Chapter 10. This chapter uses very simple techniques to cause the satellite to depart from a near-Earth orbit to a highly elliptical orbit. Once the satellite reaches the apogee point of the transfer orbit, the station-keeping techniques shown in Chapter 9 are used to correct the orbital motion of the satellite. In Chapter 11, the reconfiguration procedure of the satellite is performed. The reconfiguration procedure changes the orbital dimensions of a satellite from one particular orbit to another.

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