1. A method of controlling a motor vehicle powertrain system, the method comprising:
receiving an input indicative of an operator request for acceleration; and
controlling a plurality of powertrain components as a function of the input so as to maximize powertrain responsiveness using a control strategy that mediates competing torque demands among the plurality of components so that the operator request is prioritized as a core control parameter, wherein mediating the competing torque demands comprises determining other powertain component torque demands and using an optimizer routine having hierarchical weighted control laws to determine an optimized target before issuing a torque command to a torque provider.
2. The method of claim 1, wherein receiving an input comprises receiving an input responsive to throttle position.
3. The method of claim 3, wherein receiving an input comprises measuring a change in throttle position with an electronic throttle controller.
4. The method of claim 3, wherein the electronic throttle controller measures a rate of change of the throttle position.
5. The method of claim 1, wherein controlling the components comprises:
determining vehicle acceleration potential based on known vehicle parameters, wherein determining vehicle acceleration potential comprises:
detecting an applicable vehicle operating regime from a set of operating regimes based on predetermined vehicle operating conditions; and
hierarchically mediating competing torque demands based on the determined vehicle operating regime and the vehicle acceleration potential.
6. The method of claim 5, wherein the vehicle operating regime and the vehicle acceleration potential are uniquely determined at any instant in time by calculation of modeled parameters and the operation of any adjunct powertrain systems are controlled so as to integrate such systems into global powertrain operation in a prioritized manner.
7. The method of claim 5, wherein mediating further comprises using a logical state machine, wherein competing demands are hierarchically adjudicated serially or in parallel according to previously defined state machine logic rules.
8. The method of claim 1, wherein controlling the components comprises referring to a three dimensional calibration surface.
9. The method of claim 8, wherein a dimension of the calibration surface is selected from the group of speed, acceleration rate goal, and required horsepower.
10. A powertrain controller for controlling a vehicle powertrain system, the controller comprising:
a control module arranged to receive an input indicative of an operator request for acceleration; and
a processor arranged to control a plurality of components in the vehicle powertrain system as a function of the request so as to maximize powertrain responsiveness using a control strategy that mediates competing torque demands among the plurality of components so that the operator request is prioritized as a core control parameter, wherein the processor is arranged to mediate between the competing torque demands by determining other powertrain component torque demands and using an optimizer routine having hierarchical weighted control laws to determine an optimized target before issuing a torque command to a torque provider.
11. The powertrain controller of claim 10, wherein the controller is coupled to a torque measuring transducer in operative communication with an engine of the motor vehicle.
12. The powertrain controller of claim 10, wherein the processor further comprises a look-up table of data representative of a three dimensional calibration surface.
13. The powertrain controUer of claim 12, wherein a dimension of the calibration surface is selected from the group of speed, acceleration rate goal, and required horsepower.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. An integrated modular avionics (IMA) system comprising:
one or more network communication busses;
at least one avionics module;
a first line replaceable unit operably coupled to the one or more communication busses, the first line replaceable unit including a first node communication controller having one or more first embedded processors;
an additional line replaceable unit operably coupled to the one or more communication busses, the additional line replaceable unit including an additional node communication controller having one or more additional embedded processors,
wherein the one or more first embedded processors of the first node communication controller and the one or more additional embedded processors of the additional node communication controller redundantly host the at least one avionics module, wherein the avionics function of the at least one avionics module is unrelated to at least one of a function of the first line replaceable unit or a function of the additional line replaceable unit.
2. The integrated modular avionics system of claim 1, wherein the one or more network communication busses comprise:
an Ethernet bus.
3. The integrated modular avionics system of claim 1, wherein the one or more network communication busses comprise:
an Avionics Full-Duplex Switched Ethernet (AFDX) bus.
4. The integrated modular avionics system of claim 1, wherein the one or more network communication busses comprise:
an optical network bus.
5. The integrated modular avionics system of claim 4, wherein the optical network bus comprises:
an Ethernet passive optical network (EPON) bus.
6. The integrated modular avionics system of claim 1, wherein the one or more network communication busses comprises:
at least one of an IEEE 1553 bus, an IEEE 1394a bus, an IEEE 1394b bus, a FlexRay bus, a TPP bus, and a PCI Express bus.
7. The integrated modular avionics system of claim 1, wherein at least one of the first line replaceable unit or the additional line replaceable unit includes a host processor and an IO controller communicatively coupled via a high-speed interconnection.
8. The integrated modular avionics system of claim 7, wherein the high-speed interconnection comprises at least one of a PCI express data link, a 10 Gbps Ethernet data link, and a 1 Gbps Ethernet data link.
9. The integrated modular avionics system of claim 1, wherein at least one of the one or more first embedded processors of the first node communication controller or the one or more additional embedded processors of the additional node communication controller comprises:
a first processor and at least a second processor, wherein the first processor is different than the at least a second processor.
10. The integrated modular avionics system of claim 7, wherein the IO controller comprises:
an optical AFDX off-load engine.
11. The integrated modular avionics system of claim 1, wherein at least one of the first line replaceable unit or the additional line replaceable unit comprise:
at least one of a display unit, a radio, and a cabin audio device, an aircraft braking system, a secondary power system, a flight management system, a flight control system, and a surveillance system.
12. The integrated modular avionics system of claim 1, wherein the at least one avionics module is simultaneously hosted on a first node communication controller of a first line replaceable unit and at least a second node communication controller of at least a second line replaceable unit.
13. The integrated modular avionics system of claim 1, wherein at least one of the first node communication controller or the additional node communication controller are configured as a general IO processing ASIC.
14. The integrated modular avionics system of claim 1, wherein at least one of the first node communication controller or the additional node communication controller are configured as a master network controller ASIC.
15. An integrated modular avionics (IMA) system comprising:
a network communication bus;
at least one avionics module;
a first line replaceable unit operably coupled to the network communication bus, the first line replaceable unit including:
a first node communication controller including: one or more first host processors configured to host one or more native functions of the first line replaceable unit; and one or more first embedded processors;
an additional line replaceable unit operably coupled to the network communication bus, the additional line replaceable unit including:
an additional node communication controller including: one or more additional host processors configured to host one or more native functions of the additional line replaceable unit; and one or more additional embedded processors,
wherein the one or more first embedded processors of the first node communication controller and the one or more additional embedded processors of the additional node communication controller redundantly host the at least one avionics module, wherein the avionics function of the at least one avionics module is unrelated to at least one of a function of the first line replaceable unit or a function of the additional line replaceable unit.
16. The integrated modular avionics system of claim 15, wherein the network communication bus comprises:
at least one of an Ethernet bus, an Avionics Full-Duplex Switched Ethernet (AFDX) bus, and an optical network bus, an IEEE 1553 bus, an IEEE 1394a bus, an IEEE 1394b bus, a FlexRay bus, a TPP bus, and a PCI Express bus.
17. The integrated modular avionics system of claim 15, wherein at least one of the first line replaceable unit or the additional line replaceable unit comprises:
an inputoutput (IO) controller;
one or more IO ports coupled to the network communications bus, wherein the IO controller is configured to route data between at least one of the first embedded processor or the additional embedded processor and the at least one avionics module via the one or more IO ports and the network communication bus, wherein the one or more IO ports include at least one of an optical network port, a AFDX network port, and an Ethernet port, an IEEE 1553 port, an IEEE 1394a port, an IEEE 1394b port, a FlexRay port, a TPP port, and a PCI Express port.
18. The integrated modular avionics system of claim 15, wherein at least one of the one or more first embedded processors of the first node communication controller or the one or more additional embedded processors of the additional node communication controller comprises:
an A9 ARM processor.
19. The integrated modular avionics system of claim 15, wherein at least one of the one or more first embedded processors or the one or more additional embedded processors comprises:
a first processor and at least a second processor, wherein the first processor is different than the at least a second processor.
20. The integrated modular avionics system of claim 15, further comprising:
an IO controller.
21. The integrated modular avionics system of claim 15, further comprising:
one or more memory units.