the required launch tube length for acceleration and guidance without presenting an inordinate surface area or wind drag for the entire flight of the aircraft 12 in the drawing the rocket 22 is shown having a muzzle velocity vm with respect to the aircraft the aircraft 12 is assumed to be flying straight and level at a velocity va the horizontal component vh of the rocket is calculated as vm sin u03b8 knowing the rocket velocity vm and the angle of deployment u03b8 the aircraft speed may be adjusted so that va equals vh thus the rocket 22 has only a vertical component vv in the direction of the target t it should be understood that the inner launch tube 20 is expended each time a rockeet 22 is launched that is it simply leaves the outer launch tube 18 by its own momentum referring now to fig2 a 2b and 2c the mechanism by which the components attain full extension is illustrated in fig2 a the rocket 22 and the inner launch tube 20 are shown installed within the outer launch tube 18 in an initial position the rocket 22 is held within the inner launch tube 20 by means of a rocket latch 26 comprising a leaf spring 34 secured to the outside of the inner tube 20 at a mount 35 and extending rearwardly thereof towards a free end having.