This chapter is about the use control forces and the impulses to manoeuvre the spacecraft into specific and desired orbits. Following the introduction of the principles of space vehicle manoeuvring and conservation of momentum, the equivalence of applying an impulse to the velocity increment it generates is discussed. The components of the velocities of a spacecraft in an orbit in a planeto-centric frame of reference are derived. This is followed by a detailed presentation of the velocity increments required to make specific changes to the orbit, including the trigonometric laws that govern the vector changes to the space vehicle’s velocity, changes to the inclination and other orbital elements, rotating the lines of apsides and nodes and making changes to the orbital geometry and orbital transfers from circular and elliptic orbits to elliptic, circular, parabolic and hyperbolic Keplerian orbits and vice versa. This is followed by a study of the primary methods of two and multi-impulse transfers, leading to coplanar and noncoplanar Hohmann orbital transfers and Oberth’s and Edelbaum’s multi-impulse manoeuvres. Finally, the application of the solution to Lambert’s problem to space vehicle manoeuvring is briefly discussed.


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