They are equivalent, because it is assumed (in both) that the body does not lose or gain any massive parts.
In case the body is losing massive parts, such as a rocket, both formulations seem inadequate, because it is not clear what the system considered when using words "mass" or "momentum" and "net force" is - whether the force of the expelled gases on the rocket motor nozzles is to be accounted in the net force, and whether $m$ is mass of and inside the rocket, or mass of the whole system, including the expelled gases.
But in fact, the $\mathbf F=m\mathbf a$ formulation is correct and applicable to the rocket, provided $m$ is the mass of and inside the rocket, not including the expelled gases (thus $m$ is changing in time), and $\mathbf F$ includes the force on the nozzles due to expelled gases. This force can be expressed as $\frac{dm}{dt} \mathbf c_0$ where $\mathbf c_0$ is the final velocity of the expelled gases in the frame of the rocket. So the equation of motion for the rocket which experiences external force $\mathbf F_{ext}$ (e.g. due to atmosphere) is
$$
m\mathbf a = \mathbf F_{ext} + \frac{dm}{dt} \mathbf c_0
$$
and this equation holds in all reference frames.
The other formulation $\mathbf F = d\mathbf p/dt$, if $\mathbf p$ means momentum of the rocket $\mathbf p=m\mathbf v$, is incorrect in general, because due to the term $\frac{dm}{dt}\mathbf v$, it depends on the frame of reference. This is not acceptable, because force does not depend on frame of reference - the "$dp/dt$ formulation" would lead to
$$
m\mathbf a + \frac{dm}{dt}\mathbf v = \mathbf F_{ext} + \frac{dm}{dt} \mathbf c_0.
$$
This equation is correct only in the inertial frame where the rocket has zero velocity, where the term $\frac{dm}{dt}\mathbf v$ is zero.