Most rocket launches culminate with liquid-fueled upper stage engines turning off at exactly the precise millisecond a host of parameters — such as flight path angle, orbital inclination, apogee, and perigee — are all met simultaneously.
So then how do solid propellant upper stages like those used on the Antares, Pegasus, and Minotaur fleets from Northrop Grumman perform those same types of mission-precise orbital insertions when solid propellant stages cannot be turned off once ignited?
In short, there are three issues that must be addressed.