A satellite of mass \(m\) orbits a planet of mass \(M\) in an initial circular orbit of radius \(R\) with orbital speed \(v_0\). The satellite transitions to a larger coplanar circular orbit of radius \(4R\) via a Hohmann transfer ellipse. At point \(P\) on the initial orbit, an instantaneous tangential forward thrust injects the satellite into the elliptical transfer orbit, which has periapsis distance \(R\) at point \(P\) and apoapsis distance \(4R\) at point \(A\). In terms of \(m\), \(R\), and \(v_0\), what are the magnitude of the satellite's angular momentum \(L_{\text{trans}}\) about the planet's center during the transfer orbit and the work \(W_1\) done on the satellite by the engine thrust during this initial burn?