There was an earlier question about suborbital hops. I will reuse some of the diagrams and explanation from that answer.
A minimum energy ellipse between departure and destination corners of a Lambert space triangle is described on page 65 of the 1993 edition of Prussing and Conway's Orbital Mechanics textbook.
In this particular Lambert Space triangle, both r1$r_1$ and r2$r_2$ would be the radius of the moon, 1738 km. The 3 points of the triangle would be moon's center and the departure and destination points on the lunar surface. θ$\theta$ would be the angle between the two points.
The second focus of this minimum energy ellipse would lie on the center of the chord connecting the points on the lunar surface.
Distance between foci, (2e*a)$2e\cdot a$, is r cos(θ/2)$r \cos(\frac\theta2)$. The major axis of this ellipse (2a$2a$) is r(1 + sin(θ/2))$r(1 + \sin(\frac\theta2))$.
Knowing r$r$ (1738 km) and a (r(1 + sin(θ/2))$a = r(1 + \sin(\frac\theta2))$, the vis viva equation can be used to get delta v$\Delta v$ for take off as well as soft landing at other end of suborbital hop.
The vis viva equation is v = sqrt(Gm(2/a - 1/r)$$v = \sqrt{GM\left(\frac2a - \frac1r\right)}$$
Another useful piece of info is what angle you should depart from the moon's surface. If the destination is near, the angle will be close to 45º$45^\circ$. As the angle between departure and destination approaches 180º$180^\circ$, the flight path angle will approach 0º$0^\circ$, that is, horizontal.
I made a spreadsheet for this. User can input data into the colored cells. I set it for Luna, but a user could also input mass and radius of other bodies, Ceres and Mercury for example.
