Analytical Mechanics of Space Systems (AIAA Education) by Hanspeter Schaub, John L. Junkins

By Hanspeter Schaub, John L. Junkins

This unmarried resource presents a finished therapy of dynamics of aerospace platforms beginning with the elemental basics. themes variety from easy kinematics and dynamics to extra complex celestial mechanics. It publications you thru a few of the derivations and proofs, yet avoids "cookbook" formulation. as a substitute, the reader is made to appreciate the underlying precept of the concerned equations and proven how you can observe them to numerous dynamical structures. The booklet is split into elements. half I covers analytical remedy of themes resembling simple dynamic ideas as much as complex strength thought. specific consciousness is paid to using rotating reference frames that regularly happen in aerospace structures. half II covers easy celestial mechanics treating the 2-body challenge, limited 3-body challenge, gravity box modelling, perturbation equipment, spacecraft formation flying, and orbit transfers.

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Internal forces cancel in pairs. 43) 40 NEWTONIAN MECHANICS CHAPTER 2 where ri = (Ri − Rc ) is the position vector of mi relative to Rc . Thus Eq. 44) i=1 which is further simplified using the system mass definition in Eq. 46) i=1 After taking two inertial derivatives of Eq. 47) i=1 After substituting Eq. 48) also known as the Super Particle Theorem. The dynamics of the mass center of the system of N particles under the influence of the total external force vector F is the same as the dynamics of the “superparticle” M .

2: Ballistic Trajectories under Constant Gravity Force where g = F/m is the local constant gravitational acceleration. Eq. 16) the velocity vector r(t) ˙ is ˙ = v0 r(t) cos γ0 sin γ0 − Using 0 gt The position vector r(t) is found through Eq. 17). r(t) = x1 (t) x2 (t) = v0 t cos γ0 sin γ0 − 0 gt2 2 By solving the x1 (t) equation for the time t and substituting it into the x2 (t) equation, one obtains the parabola expression relating x2 to x1 (the equation of the path or trajectory): x2 = x1 tan γ0 − g sec2 γ0 2 x1 2v02 An interesting question now arises.

In the first case the force being applied to the mass is assumed to be constant and in the second case it is assumed to be time varying. 14) can be solved for the time varying position vector r(t). Eq. 15) 30 NEWTONIAN MECHANICS CHAPTER 2 After integrating this equation once from an initial time t0 to an arbitrary time t we obtain the following velocity formulation for mass m. 16) After integrating the velocity formulation an expression for the time varying position vector r(t) of mass m is found.

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