Notes

• NOTE Figure 3-1 illustrates an arbitrary thrust or pressure history of a rocket propulsion system. An igniter peak can, but need not, be observed.Depending on the application, a time, t0, is defined at which the propulsion system is assumed to deliver a thrust, and a time, te, at which the propulsion system is assumed not to deliver an thrust any more. The burning time is the time interval defined as the difference between the two times: tb=te - t0.