Aero compression combustion drive assembly control system
A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member A control method is further included.
1. A control method for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control method comprising:
sensing a pressure parameter in each of a plurality of compression chambers of the engine member;
providing the sensed pressure parameters to a control system device;
providing a plurality of control programs to the control system device;
the control system device calculating an indicated mean effective pressure based on the sensed pressure parameters; and
the control system device acting on the calculated indicated mean effective pressure parameter to effect a control strategy in the engine member.
2. The control method of claim 1 , including implementing the control strategy in the engine member by affecting the operation of at least one fuel injector.
3. The control method of claim 2 , including affecting a fuel pulse timing of at least one fuel injector.
4. The control method of claim 2 , including affecting a fuel pulse duration of at least one fuel injector.
5. The control method of claim 2 , including affecting the operation of at least one turbocharger.
6. The control method of claim 1 , wherein the control device calculates the indicated mean effective pressure during an engine run-up prior to takeoff to determine engine performance.
7. The control method of claim 6 , wherein the control device measures an available engine power based on weather conditions.
8. A control method for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control method comprising:
sensing a pressure parameter in each of a plurality of compression chambers of the engine member;
providing the sensed pressure parameters to a control system device;
providing a plurality of control programs to the control system device;
the control system device calculating an indicated mean effective pressure based on the sensed pressure parameters;
the control system device acting on the calculated indicated mean effective pressure parameter to effect a control strategy in the engine member; and
providing an alert of at least one of a possible degradation of engine components or weak compression chamber performance.
9. The control method of claim 8 , further comprising implementing the control strategy in the engine member by affecting the operation of at least one fuel injector.
10. The control method of claim 9 , further comprising calculating the indicated mean effective pressure during an engine run-up prior to takeoff to determine engine performance.
11. The control method of claim 8 , further comprising measuring an available engine power based on weather conditions.
12. The control method of claim 8 , further comprising affecting a fuel pulse timing of at least one fuel injector.
13. The control method of claim 8 , further comprising affecting a fuel pulse duration of at least one fuel injector.
14. The control method of claim 8 , further comprising affecting the operation of at least one turbocharger.
15. A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system comprising:
a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member and for providing the sensed pressure parameters to a control system device;
the control system device having a plurality of control programs for effecting selected engine control;
the control system device calculating an indicated mean effective pressure based on the sensed pressure parameters; and
the control system device acting on the calculated indicated mean effective pressure parameter to effect a control strategy in the engine member; and
providing an alert of a possible degradation of engine components.
16. The control system of claim 15 , wherein the control system implements the control strategy in the engine member by affecting the operation of at least one fuel injector.
17. The control system of claim 15 , wherein the control system implements the control strategy in the engine member by affecting a fuel pulse timing of at least one fuel injector.
18. The control system of claim 15 , wherein the control system implements the control strategy in the engine member by affecting a fuel pulse duration of at least one fuel injector.
19. The control system of claim 15 , wherein the control system implements the control strategy in the engine member by affecting the operation of at least one turbocharger.
20. The control system of claim 15 , wherein the control device calculates the indicated mean effective pressure during an engine run-up prior to takeoff to determine engine performance.