CN104712435B - Engine electronic control - Google Patents
Engine electronic control Download PDFInfo
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- CN104712435B CN104712435B CN201310680782.3A CN201310680782A CN104712435B CN 104712435 B CN104712435 B CN 104712435B CN 201310680782 A CN201310680782 A CN 201310680782A CN 104712435 B CN104712435 B CN 104712435B
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Abstract
The invention provides a kind of engine electronic control, including：Control unit, the controlling position is in aircraft devices cabin for exporting the control signal to engine；And signal processing part, the signal processing part is located in the engine and is communicatively coupled with the control unit, the signal processing part is used to process the sensing signal from the engine to generate the input signal to the control unit, and the wherein control unit generates the control signal according to the input signal from the signal processing part.
Description
Technical field
The present invention relates to aero-engine, more particularly to aero-engine engine electronic control.
Background technology
FADEC（Full Authority Digital Electronic Control）System is the control axis of aviation aircraft.In current main flow aviation
In engine FADEC systems, the digital EEC of core（Engine electronic control）With distribution sensor on the engine and
Actuation mechanism realizes engine control jointly.
EEC contains power module, input/output signal treatment, calculates and the functional module such as control, data communication.Pass
System ground, EEC is generally designed using centralization, and interaction is realized by plate level bus between the internal module of EEC（Fig. 1）.Such as Fig. 1 institutes
Show, EEC is intensively arranged within the engine and communicated with sensor, actuation mechanism and airframe.Such as EEC and sensor,
Pass through cable connection between actuation mechanism, airplane equipment cabin part and system.EEC gathers external input signal and instruction, utilizes
Internal digital computing module realizes control logic, and control signal is nursed one's health, the actuation mechanism or other for arriving outside is exported
Part and system, so as to realize engine control function.
The EEC of above-mentioned centralization is typically installed on the accessory drive gearbox of engine, with integrated level is high, cable distance
It is short, the advantages of signal quality is high, but there is also following shortcoming：
1. engine environmental inclement condition, EEC is arranged on very severe to the design and test requirements document of EEC on engine
Carve, cause the cost of EEC very high；
2., with the continuous improvement that engine control is required, the complexity of engine control algolithm increases, hard to EEC
The requirement of part resource is also more and more, and the volume of EEC will also increase therewith.However, the space on engine is limited, EEC is installed
The EEC larger to volume causes the difficulty installed on engine；
3. as aero-engine control develops towards the direction of flight/propulsion Comprehensive Control, the connection of EEC and flight control system
More and more closely, the distance of the two and the limitation of communication are unfavorable for the design of complex control system and realize for system.
Therefore, traditional centralized EEC designs cannot meet the autgmentability requirement of following complex control system.This area
Need a kind of EEC designs of improvement badly.
The content of the invention
The brief overview of one or more aspects given below is providing to the basic comprehension in terms of these.This general introduction is not
The extensive overview of all aspects for contemplating, and it is also non-to be both not intended to identify the key or decisive key element of all aspects
Attempt to define the scope in terms of any or all.Its unique purpose is to provide the one of one or more aspects in simplified form
A little concepts think the sequence of more detailed description given later.
According to an aspect of the present invention, there is provided a kind of engine electronic control, including：Control unit, the controlling position
For exporting the control signal to engine in aircraft devices cabin；And signal processing part, the signal processing part is located at
It is communicatively coupled in the engine and with the control unit, the signal processing part is used to carry out the sensing signal from the engine
To generate the input signal to the control unit, the wherein control unit is given birth to according to the input signal from the signal processing part for treatment
Into the control signal.
In one example, the engine includes sensor, and the signal processing part receives the sensing signal from the sensor.
In one example, the engine includes actuation mechanism, and the wherein signal processing part includes D/A converter, and the D/A turns
Parallel operation performs digital-to-analogue conversion to the control signal from the control unit, and the control signal of analog form is transferred into the work
Motivation structure.
In one example, the signal processing part include pretreatment module, for the sensing signal is pre-processed with
Generate the input signal to the control unit.
In one example, the pretreatment module includes built-in testing diagnostic module, for being performed according to the sensing signal
Upper electricity or cyclic breakdown diagnosis.
In one example, the pretreatment module includes demarcating modular converter, for according to the curve adjusted of experiment or point
The sensing signal is converted to corresponding engineering value by degree table.
In one example, the pretreatment module includes validity judge module, for performing extreme value to the sensing signal
Diagnosis and slope diagnose to judge whether the sensing signal is credible.
In one example, the pretreatment module includes signal compensation and filtration module, for being carried out to the sensing signal
Lead compensation and digital filter are eliminating high-frequency noise or the disturbance in the sensing signal.
In one example, the signal processing part also includes A/D converter, and the A/D converter performs mould to the sensing signal
Number is changed to generate the sensing signal of digital form, and the wherein pretreatment module carries out pre- to the sensing signal of digital form
Treatment.
In one example, the control unit includes control signal generation module, and the control signal generation module is defeated in response to this
Enter the signal generation control signal.
In one example, the signal processing part includes first communication module, and the control unit includes second communication module, and this
It is defeated that one communication module and the second communication module between the signal processing and the control unit transmit this according to predetermined protocol
Enter signal and the control signal.
In one example, the predetermined protocol includes ARINC664 agreements, the wherein first communication module and second communication
Module is ARINC664 interfaces.
In one example, the predetermined protocol includes TTP/C agreements, the wherein first communication module and the second communication module
It is TTP/C interfaces.
In one example, the control unit is integrated in IMA systems.
In one example, the control unit includes communication module and control signal generation module, the communication module and the control
Signal generation module is integrated in the different subregions of the IMA systems, and is communicated by ARINC653 agreements.
By the solution of the present invention, at least there is many benefits in the following areas：
The holistic cost reduction of 1.EEC, including：The costs such as design, experiment, manufacture, maintenance；
2. eliminate due to EEC volumes and function restriction caused by engine installing space；
3. ensure that engine still with independent maintenance and replacing, and can set without more transfer to flight while more reengining again
Engine controller in standby cabin；
4. the interaction of other mobile systems such as engine control system and flight control system is more facilitated with cooperateing with.
Brief description of the drawings
After the detailed description for reading embodiment of the disclosure in conjunction with the following drawings, better understood when of the invention
Features described above and advantage.In the accompanying drawings, each component is not necessarily drawn to scale, and with similar correlation properties or feature
Component may have same or like reference.
Fig. 1 is the structural representation of traditional centralized EEC；
Fig. 2 is the exemplary functions framework of the EEC of aero-engine；
Fig. 3 shows the high level schematic diagram of the EEC of separate type according to an aspect of the present invention；
Fig. 4 shows the structured flowchart of the separate type EEC of first embodiment of the invention；
Fig. 5 shows the structured flowchart of the preprocessor in the separate type EEC of first embodiment of the invention；With
And
Fig. 6 shows the structured flowchart of separate type EEC according to the second embodiment of the present invention.
Specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.Note, it is below in conjunction with accompanying drawing and specifically real
It is only exemplary to apply the aspects of example description, and is understood not to carry out any limitation to protection scope of the present invention.
At present, the defect of the EEC frameworks of above-mentioned centralization cannot preferably be flown by the way that EEC is transferred directly into environmental condition
Solved among machine equipment cabin, because this will cause sensor/communication distance between actuation mechanism and EEC long, cable weight
Amount is dramatically increased.And, in the case where various types of signal and data are various, communication quality is difficult to ensure that, Project Realization it is feasible
Property is not high.
Therefore, be more reasonably the EEC frameworks of separate type, will the function of EEC be divided into some, by centralization
EEC is decomposed into multiple distributed parts, is respectively deployed in engine and aircraft（For example, aircraft）Among equipment compartment, the two
By cable connection, and the functions such as above-mentioned input/output, calculating and control and data communication are completed jointly.
However, the design of separate type EEC frameworks also faces lot of challenges.In whole aircraft system, engine can be
Independent maintenance, the equipment changed.The EEC frameworks of separate type will cause the maintenance of engine to change more complicated.Because engine
EEC（Especially wherein software）It is closely related with the sensor in control system, the characteristic of actuation mechanism, if separate type
EEC frameworks cannot rational partition functionality, in causing more to reengine and having to change engine body, airplane equipment cabin
The multiple part such as EEC.
Typically EEC includes various functions module, such as input/output signal management and control, test, data pipe
Reason etc., as shown in Figure 2.In one aspect of the invention, the above-mentioned functions feature according to aeroengine control system, there is provided
A kind of EEC schemes, can realize the classifying rationally of EEC functions and separate.According to the program, used according to engine body or control
The relevance of sensor/actuation mechanism, two parts are divided into by EEC functions.Specifically, the work(that only will be associated with engine body
Can, such as control law management moves to working environment more as host computer control function from the engine of work under bad environment
In excellent airplane equipment cabin, while the function of closely being coupled with control sensor/actuation mechanism is protected as control function
Stay within the engine, realize the design of separate type.
Fig. 3 shows the high level schematic diagram of the EEC of separate type according to an aspect of the present invention.As shown in figure 3, traditional
The function of EEC330 be separated into signal processing part 331 and control unit 332.Signal processing part 331 is disposed in engine 310
In, and control unit 332 is disposed in airplane equipment cabin 320, both are communicatively coupled together.
Engine 310 may include sensor 311, such as temperature sensor, pressure sensor etc..Signal processing part 331
Can be to the sensing signal from engine 310, that is, the sensing signal for being received from sensor 311 is processed, and is generated to control
The input signal in portion 332.Control unit 332 may be in response to the input signal life coupled engines 310 from signal processing part 331
Control signal.Signal processing part 331 can carry out necessary treatment to the control signal from control unit 332, and by after treatment
Control signal passes to the actuation mechanism 312 of engine 310.More preferably, the signal transacting of above-mentioned signal processing part 331 and sensing
The physical characteristic correlation of device 311, actuation mechanism 312, and the generation of the control signal of control unit 332 is relevant with the state of engine 310.
Fig. 4 shows the structured flowchart of the separate type EEC of first embodiment of the invention.As shown in figure 4, signal
Processing unit 430 may include A/D converter 432 and pretreatment module 434, to the sensing signal from sensor 411
Reason, to provide input signal to control unit 440, for the control signal of the life coupled engines of control unit 440 provides basis.A/D
Converter 432 can receive sensing signal from sensor 411, and perform analog-to-digital conversion to sensing signal, by sensing signal from simulation
Signal switchs to data signal.
Pretreatment module 434 can perform pretreatment to the sensing signal of the output of A/D converter 432, to generate to control unit
440 input signal.Pre-processed by the A/D to sensing signal, control unit 440 can directly according to the input signal life for receiving
Into control signal.
Fig. 5 shows the structured flowchart of the preprocessor in the separate type EEC of first embodiment of the invention.Such as
Shown in Fig. 5, pretreatment module 434 may include built-in testing（BIT）Diagnostic module 502, for being performed according to sensing signal
Electricity or cyclic breakdown diagnosis.Pretreatment module 434 may also include the song for demarcating modular converter 504 for being adjusted according to experiment
Sensing signal is converted to corresponding engineering value by line or phasing meter.Pretreatment module 434 may also include Effective judgement module
506, for performing extreme value diagnosis and slope diagnosis to sensing signal to judge whether sensing signal is credible.In addition, pretreatment
Module 434 may also include signal compensation and filtration module 508, for sensing signal is carried out lead compensation and digital filter with
Eliminate the high-frequency noise in sensing signal or disturbance.Characteristic of the above-mentioned functions module with sensor is closely related.
Fig. 4 is returned to, signal processing part 430 may also include communication module 436, correspondingly control unit 440 may include the mould that communicates
Block 442, to make it possible to be communicated according to predetermined communication protocol between signal processing part 430 and control unit 440.Communication mould
Input signal from pretreatment module 434 can be packaged and sent to communication module 442 by block 436 according to agreement.Communication
Module 442 can be parsed to obtain the input signal after receiving packet.In order to meet signal processing part 430 and control unit
Real-time Communication for Power between 440, takes around the bandwidth of 10Kbps.In one example, communication module 436 and communication module 442 can
Communicated according to ARINC664 agreements.In this example, communication module 436 and communication module 442 can be that ARICN664 connects
Mouthful.In another example, communication module 436 and communication module 442 can be communicated according to TTP/C agreements.In this example, lead to
Letter module 436 and communication module 442 can be TTP/C interfaces.
Control unit 440 may also include control signal generation module 444, and the latter is received from signal from communication module 442
The input signal in reason portion 438, and the control signal of coupled engines is given birth in response to the input signal.Control unit 440 can control this
Signal processed is sent to signal processing part 430 by communication module 442.
Signal processing part 436 can be received and parsed through by communication module 436 and obtain the control signal.Signal processing part 436
May also include D/A converter 438 and be converted to analog signal to export with by control signal to perform D/A conversions to the control signal
To the actuation mechanism 412 of engine 410, to realize the control to engine 410.
From the foregoing, it will be observed that the functional module of EEC is broadly divided into two parts by this programme, one is input/output signal treatment etc.
The closely related signal processing part of the physical characteristic of sensor, actuation mechanism with engine, two is to calculate control etc. and start
The related control unit of machine bulk state.In practice, once more reengining, it is necessary to match above-mentioned signal processing part again,
And the main functionality of control unit is generally related to engine body state, the actual physics value after signal transacting is concerned only with, the bottom of by
The influence very little of the specific parts of layer.For example, the analogue type electric signal that temperature sensor is sent to signal processing part turns by A/D
Digital quantity is changed to, and is further demarcated as actual temperature value, calibrating parameters therein are closely related with the characteristic of sensor, and control
Only it is concerned about the temperature value of the engine ad-hoc location after demarcating conversion in portion processed.In other words, every calibrating parameters of engine are because passing
Sensor and signal processing circuit characteristic and become, and the control logic for concerning engine body state is stable.
Therefore, in the present invention, protected by by function closely related with the physical characteristic of sensor, actuation mechanism in EEC
Stay on the engine, and the function closely related with engine body is transferred to the more excellent airplane equipment cabin of working environment
In, the defect of traditional centralization EEC was both solved, and area is had no with conventional engines again in the operation more reengined
Not, without changing the control unit in airplane equipment cabin.
Fig. 6 shows the structured flowchart of separate type EEC according to the second embodiment of the present invention.As shown in fig. 6, this point
The difference of the separate type EEC in formula EEC and Fig. 4 is that the control unit 640 in airplane equipment cabin 620 can be integrated in IMA
System（Comprehensively modularized avionics system）In 650.IMA systems 650 provide powerful hardware platform, and utilize software
Partitioning technique and ARINC653 agreements carry a series of airborne set of applications, and mutual feelings are not interfered between ensuring to apply
Under condition, the communications conduit between application can also be provided.
In this embodiment, the control unit 640 of EEC is implemented in the software partition of IMA in the form of software, required
Calculate and storage resource is distributed unitedly by IMA systems 650.IMA only needs to be provided to run above-mentioned corresponding calculating of control software distribution
Source, and increase the communication resource needed for being interacted with the signal processing part 630 on engine on demand.In this embodiment, communicate
Module 642 and control signal generation module 644 can run on same subregion, or run on different subregions.If running on not
Same subregion, then both using IMA systems 650 provide inter-partition communication mechanism interact.IMA systems 650 may also include use
In the control software of airframe, the latter can be operated in different dividing from the control unit 640 of the above-mentioned EEC for engine
Area, and communication and interaction are completed by ARINC653 agreements.
Compared to the scheme of first embodiment, the scheme of the present embodiment is further reduced while communication efficiency is improved
Communications cost and complexity.
By the solution of the present invention, at least there is many benefits in the following areas：
The holistic cost reduction of 1.EEC, including：The costs such as design, experiment, manufacture, maintenance；
2. eliminate due to EEC volumes and function restriction caused by engine installing space；
3. ensure that engine still with independent maintenance and replacing, and can set without more transfer to flight while more reengining again
Engine controller in standby cabin；
4. the interaction of other mobile systems such as engine control system and flight control system is more facilitated with cooperateing with.
It is for so that any person skilled in the art can all make or use this public affairs to provide of this disclosure being previously described
Open.The scope of the present invention is not limited to engine electronic control.For example, some air line optional equipments engine prison
Depending on unit（EMU）, for monitoring, record and feedback engine health status.The function structure of above-mentioned EEC is separated and is also applied for
EMU.For example, the functional unit of the responsible signal input output treatment of EMU is retained on the engine, and charge of overseeing, record
Functional unit with feedback is transferred in the equipment compartment of fuselage.
It will be understood by those skilled in the art that information and signal can be used any technology in various different technologies and skill
Represented with skill.For example, data, instruction, order, information, signal, position that above description is quoted from the whole text（Bit）, code element and
Chip can be represented by voltage, electric current, electromagnetic wave, magnetic field or magnetic particle, light field or optical particle or its any combinations.
Those skilled in the art will further appreciate that, the various illustratives described with reference to the embodiments described herein
Logic plate, module, circuit and algorithm steps can realize being electronic hardware, computer software or combination of the two.For clear
Chu ground explains this interchangeability of hardware and software, various illustrative components, frame, module, circuit and step be above with
Its functional form makees vague generalization description.Such feature be implemented as hardware or software depend on concrete application and
Put on the design constraint of total system.Technical staff can be realized described for every kind of application-specific with different modes
Feature, but such realize that decision-making should not be interpreted to cause departing from the scope of the present invention.
Software should be broadly interpreted to mean instruction, instruction set, code, code segment, program code, program, son
Program, software module, using, software application, software kit, routine, subroutine, object, executable item, perform thread, code,
Function etc., no matter it is all is to address with software, firmware, middleware, microcode, hardware description language or other terms
So.
Various illustrative logic plates, module and the circuit described with reference to presently disclosed embodiment can use general place
Reason device, digital signal processor（DSP）, application specific integrated circuit（ASIC）, field programmable gate array（FPGA）Or other can be compiled
Journey logical device, discrete door or transistor logic, discrete nextport hardware component NextPort or its be designed to carry out function described herein
Any combinations are realized or performed.General processor can be microprocessor, but in alternative, the processor can be appointed
What conventional processor, controller, microcontroller or state machine.Processor is also implemented as the combination of computing device, example
One or more microprocessors that combination, multi-microprocessor such as DSP and microprocessor cooperate with DSP core or it is any its
His such configuration.
The step of method or algorithm for being described with reference to embodiment disclosed herein, can be embodied directly in hardware, in by processor
Embodied in the software module of execution or in combination of the two.Software module can reside in RAM memory, flash memory, ROM and deposit
Reservoir, eprom memory, eeprom memory, register, hard disk, removable disk, CD-ROM or known in the art appoint
In the storage medium of what other forms.Exemplary storage medium is coupled to processor to enable the processor from/to the storage
Medium reads and write-in information.In alternative, storage medium can be integrated into processor.
It is for so that any person skilled in the art can all make or use this public affairs to provide of this disclosure being previously described
Open.Various modifications of this disclosure all will be apparent for a person skilled in the art, and as defined herein general
Suitable principle can be applied to spirit or scope of other variants without departing from the disclosure.Thus, the disclosure is not intended to be limited
Due to example described herein and design, but should be awarded and principle disclosed herein and novel features phase one
The widest scope of cause.
Claims (13)
1. a kind of engine electronic control, including：
Control unit, the controlling position in aircraft devices cabin for exporting the control signal to engine, wherein described
Control unit is integrated in IMA systems, and the control unit includes communication module and control signal generation module, the communication mould
Block and the control signal generation module are integrated in the different subregions of the IMA systems, and by the agreements of ARINC 653
Communicated；And
Signal processing part, the signal processing part is located in the engine and is communicatively coupled with the control unit, the letter
Number processing unit is used to process the sensing signal from the engine to generate the input signal to the control unit, its
Described in control unit the control signal is generated according to the input signal from the signal processing part.
2. engine electronic control as claimed in claim 1, it is characterised in that the engine includes sensor, described
Signal processing part receives the sensing signal from the sensor.
3. engine electronic control as claimed in claim 1, it is characterised in that the engine includes actuation mechanism, its
Described in signal processing part include D/A converter, the D/A converter to from the control unit the control signal perform
Digital-to-analogue conversion, and the control signal of analog form is transferred to the actuation mechanism.
4. engine electronic control as claimed in claim 1, it is characterised in that the signal processing part includes pretreatment mould
Block, for being pre-processed the input signal to generate to the control unit to the sensing signal.
5. engine electronic control as claimed in claim 4, it is characterised in that the pretreatment module includes built-in testing
Diagnostic module, for performing upper electricity or cyclic breakdown diagnosis according to the sensing signal.
6. engine electronic control as claimed in claim 4, it is characterised in that the pretreatment module includes demarcating to be changed
The sensing signal is converted to corresponding engineering value by module, curve or phasing meter for being adjusted according to experiment.
7. engine electronic control as claimed in claim 4, it is characterised in that the pretreatment module is sentenced including validity
Disconnected module, for performing extreme value diagnosis and slope diagnosis to the sensing signal to judge whether the sensing signal is credible.
8. engine electronic control as claimed in claim 4, it is characterised in that the pretreatment module includes signal compensation
And filtration module, for carrying out lead compensation and digital filter to eliminate the height in the sensing signal to the sensing signal
Frequency noise or disturbance.
9. engine electronic control as claimed in claim 4, it is characterised in that the signal processing part also turns including A/D
Parallel operation, the A/D converter performs analog-to-digital conversion to the sensing signal to generate the sensing signal of digital form, wherein
The pretreatment module is pre-processed to the sensing signal of digital form.
10. engine electronic control as claimed in claim 1, it is characterised in that the control signal generation module response
The control signal is generated in the input signal.
11. engine electronic controls as claimed in claim 1, it is characterised in that the signal processing part includes communication mould
The communication module of block, the communication module of the signal processing part and the control unit is according to predetermined protocol in the signal processing part
Divide and the input signal and the control signal are transmitted between the control unit.
12. engine electronic controls as claimed in claim 11, it is characterised in that the predetermined protocol includes ARINC
664 agreements, wherein the communication module of the communication module of the signal processing part and the control unit is the interfaces of ARINC 664.
13. engine electronic controls as claimed in claim 11, it is characterised in that the predetermined protocol is assisted including TTP/C
View, wherein the second communication module of the communication module of the signal processing part and the control unit is TTP/C interfaces.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310680782.3A CN104712435B (en) | 2013-12-12 | 2013-12-12 | Engine electronic control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310680782.3A CN104712435B (en) | 2013-12-12 | 2013-12-12 | Engine electronic control |
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| CN104712435A CN104712435A (en) | 2015-06-17 |
| CN104712435B true CN104712435B (en) | 2017-06-23 |
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| CN201310680782.3A Active CN104712435B (en) | 2013-12-12 | 2013-12-12 | Engine electronic control |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| DE102015217435A1 (en) * | 2015-09-11 | 2017-03-16 | Robert Bosch Gmbh | Integrated circuit |
| CN106873953B (en) * | 2015-12-14 | 2020-06-09 | 中国航空工业第六一八研究所 | Partition framework for data stream of fly-by-wire flight control software and partition building method thereof |
| CN110766930B (en) * | 2019-10-23 | 2021-10-29 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Distributed control system of civil owner flight control system direct mode |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5622045A (en) * | 1995-06-07 | 1997-04-22 | Allison Engine Company, Inc. | System for detecting and accommodating gas turbine engine fan damage |
| CN101694182A (en) * | 2009-09-29 | 2010-04-14 | 上海中科清洁能源技术发展中心 | On-line failure diagnosis, prediction and feedback control method of small/medium size gas turbine and device thereof |
| CN103116320A (en) * | 2011-11-17 | 2013-05-22 | 中航商用航空发动机有限责任公司 | Distributed type aero-engine full authority digital engine control (FADEC) system |
| CN103257599A (en) * | 2012-02-20 | 2013-08-21 | 阿尔斯通技术有限公司 | Control system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4220631B2 (en) * | 1999-09-22 | 2009-02-04 | 三菱重工業株式会社 | Surging detection method and apparatus for gas turbine compressor |
-
2013
- 2013-12-12 CN CN201310680782.3A patent/CN104712435B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5622045A (en) * | 1995-06-07 | 1997-04-22 | Allison Engine Company, Inc. | System for detecting and accommodating gas turbine engine fan damage |
| CN101694182A (en) * | 2009-09-29 | 2010-04-14 | 上海中科清洁能源技术发展中心 | On-line failure diagnosis, prediction and feedback control method of small/medium size gas turbine and device thereof |
| CN103116320A (en) * | 2011-11-17 | 2013-05-22 | 中航商用航空发动机有限责任公司 | Distributed type aero-engine full authority digital engine control (FADEC) system |
| CN103257599A (en) * | 2012-02-20 | 2013-08-21 | 阿尔斯通技术有限公司 | Control system |
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