The Mach number controller computes the suitable nominal value for gas generator pressure while accounting for the pertinent gas generator dynamics. This procedure requires the knowledge of the pressure sensitive burning rate with adequate narrow tolerance limits. In the case of high-g flight maneuvers, the system can optionally switch over to a simple command for the pressure nominal value. An adaptive controller is nested within the Mach number loop to keep the gas generator pressure in closed loop control. Thus, an open loop control of the mass flow rate is provided. This loop is controlled by the flight Mach number loop, its value being derived from flight data. The installation of prototype engines on test stands in a hardware-in-the-loop configuration and the required additional simulation procedure is described. Test results are given.
Speed Control of a Missile with Throttleable Ducted Rocket Propulsion
1987
15 pages
Report
Keine Angabe
Englisch
Missile Guidance & Control Systems , Missiles , Speed control , Adaptive control , Burning rate , Control systems design , Controllers , Ducted rocket engines , Feedback control , Gas generators , Mass flow , Solid propellant combustion , Solid propellant rocket engines , Engine tests , Flow velocity , Mach number , Mathematical models , Simulation , Foreign technology