CN109426675A - Aircraft onboard machine-electronic equipment control and management integrated system redundancy management method based on Stateflow - Google Patents
Aircraft onboard machine-electronic equipment control and management integrated system redundancy management method based on Stateflow Download PDFInfo
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Abstract
For the defect of traditional electrical and mechanical comprehensive management system redundancy management functional development, using the Stateflow tool of Simulink, propose the Aircraft onboard machine-electronic equipment control and management integrated system redundancy management method based on Stateflow, establish Aircraft onboard machine-electronic equipment control and management integrated system architectural model, the state machine model of design electrical and mechanical comprehensive management computer；Design the redundancy management logic based on truth table.This method can be in electrical and mechanical comprehensive management system development early stage, design Aircraft onboard machine-electronic equipment control and management integrated system redundancy management method, the system failure can be found in advance, improve development efficiency, save development cost, the complexity of Aircraft onboard machine-electronic equipment control and management integrated system design can be reduced, the readily understood degree of model is significantly larger than document and code, mitigates demand, design, realizes that the communication of correlation engineering teacher is difficult.
Description
Technical field
It is more particularly the airborne electrical and mechanical comprehensive pipe based on Stateflow the present invention relates to a kind of redundancy management method
Manage system margin management method.
Background technique
Airborne Electromechanical Systems refer to and ensure that flying the system worked wells such as control, aviation electronics and persons on board pacifies on aircraft
Full equipment.Airborne Electromechanical Systems include power supply system, fuel system, hydraulic system, environmental control system, brake system, undercarriage
More than ten of system such as system, engine system, accessory power system.Domestic and international aircraft industry department introduces electrical and mechanical comprehensive management
System changes Mechatronic Systems from traditional association type framework to synthesization or even depth synthesization framework.
The redundancy management function of current Aircraft onboard machine-electronic equipment control and management integrated system relies primarily on C language code realization, with electromechanics
Total management system synthesization degree is higher and higher, and system developer links up difficult, the complexity of design by code and document
Degree is increasing, code it is portable also worse and worse.It is extremely urgent to change above situation.
Stateflow is a kind of patterned design development tool in Matlab/Simulink series of products, is limited shape
The image hotpoint tool of state machine.It is mainly used for that the expression of logical relation is controlled and detected in Simulink.User can carry out
When Simulink is emulated, the conversion between each state is realized using this patterned tool, solves complicated monitoring logic
Problem.It may be implemented to be patterned modeling and simulation to the complication system based on Finite State Machine, design and develop determination
, detection control system, it is easier to design different phase modification design, assessment result and verify system performance.It is existing
There is technical situation.
Summary of the invention
The purpose of the present invention:
Aircraft onboard machine-electronic equipment control and management integrated system also brings a series of problems, including system while obtaining huge income
Scale increase " domino effect " caused by the exploitation introduced, design and comprehensive difficult, reliability failures, from loose coupling to
Close coupling bring safety reappraises.
Aircraft industry department is badly in need of establishing Aircraft onboard machine-electronic equipment control and management integrated system using a kind of advanced, scientific method.Its
Middle modeling and simulation technology is a kind of effective means, and first can reduce airborne electrical and mechanical comprehensive management system by modeling/emulation
The complexity for design of uniting, the readily understood degree of model are significantly larger than document and code, mitigate demand, design, realize related work
The communication of Cheng Shi is difficult；Second can be reduced high by modeling/emulation in the design defect of product development early detection system
Reprocess cost, accelerate product delivery cycle；Third is set by modeling/emulation, formation for Aircraft onboard machine-electronic equipment control and management integrated system
The standards system of meter, Specification Design process instruct Mechatronic Systems designer.
Technical solution of the present invention:
In order to achieve the above-mentioned object of the invention, the technical solution adopted by the present invention are as follows: the airborne electromechanics based on Stateflow is comprehensive
Close management system redundancy management method.
Aircraft onboard machine-electronic equipment control and management integrated system redundancy management method based on Stateflow is divided into three steps: establishing airborne electromechanics
Total management system architectural model；Design the state machine model of electrical and mechanical comprehensive management computer；Design is based on truth table
Redundancy management logic.
Step 1. establishes Aircraft onboard machine-electronic equipment control and management integrated system architectural model
According to Mechatronic Systems actual conditions, using the Chart of Stateflow, establish Airborne Electromechanical Systems fault detection and
The architectural model of processing.Each state indicates that an electrical and mechanical comprehensive manages computer, and all electrical and mechanical comprehensive management calculate
The priority relationship of machine be on > under, it is left > right.
Step 2. designs the state machine model of electrical and mechanical comprehensive management computer
On the basis of step 1, the state machine model of design electrical and mechanical comprehensive management computer.It is each in Stateflow
State indicates that an electrical and mechanical comprehensive manages computer, each electrical and mechanical comprehensive management computer is made of 5 sub- states,
Passive, Active, Standby, Off, Isolated, this 5 sub- states respectively indicate locating for electrical and mechanical comprehensive management computer
In different modalities.
A.Passive: the init state for entering periodic duty after electrical and mechanical comprehensive management computer powers on is indicated；
B.Active: indicate that electrical and mechanical comprehensive management computer is active, i.e. this IEMC is in main control；
C.Standby: indicate that electrical and mechanical comprehensive management computer is in Status of Backups, electrical and mechanical comprehensive management computer, which is not done, to be referred to
Enable output；
D.Off: indicating that electrical and mechanical comprehensive manages computer glitch state, arrives once there is electrical and mechanical comprehensive management COMPUTER DETECTION
Transient fault enters survey state；
E.Isolated indicates isolation, according to the specific logic of system, when transient fault reaches certain threshold values, entrance
Isolation, system take safety measures.
Step 3. designs the redundancy management logic based on truth table
On the basis of step 2, the transition relationship of the sub- state in each parent status is initially set up, including from original state
To Passive state, Passive state to Active Standby state, Standby state to Active state.Off
State is to Isolated state.The condition of Passive/Standby state to the Active state of IEMSC is that IEMSC currently locates
In Passive state.The condition of Passive/Active/Standby state to the Off state of IEMSC is go_off (i.e. system
Detect failure).The condition of Off state to the Isolated state of IEMSC is [fails >=n], i.e., failure has reached n
It is secondary.The condition of Off to the Off state of IEMSC is go_off [fails < n], i.e., when continuous fault number is less than n, IEMSC1 is still
So it is in Off state.
It is realized according to the monitored results of Aircraft onboard machine-electronic equipment control and management integrated system as inputting using the truth table of Stateflow
The redundancy management logic of airborne Electromechanical Management computer.Truth table includes condition table and action schedule.In condition table, Condition
Each condition in (condition) column will first judge that supervising signal is effective (T) or failure (F).Each Decision (decision) column are implicit
The with operation of each condition.The last one decision in table is known as default decision, it includes determining in addition to aforementioned list
Every other decision outside plan.Acting (Action) indicates the result of decision.Action schedule is the specific of the movement of condition table, movement
It needs specifically to indicate that monitoring signal virtual value obtains number.Such as table 1,2.
1 Aircraft onboard machine-electronic equipment control and management integrated system troubleshooting condition table of table
| Description | Condition | D1 (decision 1) | D2 | D3 | …… | DM (default decision) | |
| 1 | Validity[1] | T | T | F | …… | - | |
| 2 | Validity[2] | F | T | F | …… | - | |
| 3 | Validity[3] | F | T | F | …… | - | |
| …… | …… | …… | …… | …… | …… | …… | …… |
| N | Validity[N] | …… | - | ||||
| Movement | 1 | 2 | 3 | …… | X |
2 Aircraft onboard machine-electronic equipment control and management integrated system action schedule of table
| Description | Movement | |
| 1 | Num=1 | |
| 2 | ||
| …… | …… | …… |
| X | Num=x |
Detailed description of the invention
The architectural model of the fault detection of Fig. 1 Airborne Electromechanical Systems and processing
The airborne electrical and mechanical comprehensive of Fig. 2 manages computer mode machine model
Specific embodiment
Using undercarriage control control system as case, the operation that RIU (remote interface units) receives pilot refers to this patent
It enables (receiving/releasing/emergency is put), RIU controls different types of valve in Landing Gear System, while IEMSC (the electrical and mechanical comprehensive pipe of double redundancy
Reason computer) receive the landing gear switch signal that RIU is acquired, IEMSC puts to the vote to the switching signal of redundance, and monitors and open
The validity of OFF signal, and vote value and monitored results are issued RIU, continue to control undercarriage mechanical device.Below in conjunction with
The present invention is described in further detail for drawings and examples.
1. establishing Aircraft onboard machine-electronic equipment control and management integrated system architectural model
Since the electrical and mechanical comprehensive management system in case is double redundancy, using the Chart of Stateflow, airborne machine is established
The architectural model of electric system fault detection and processing, there are two state I EMSC1 and IEMSC2 altogether.Each state indicates
One electrical and mechanical comprehensive manages computer, as shown in Figure 1, IEMSC1 is on the upper left side of IEMSC2, that is to say, that IEMSC1 is as master
Node, IEMSC2 are used as from node.
2. designing the state machine model of electrical and mechanical comprehensive management computer
Design the state machine model of electrical and mechanical comprehensive management computer.Each state in Stateflow indicates an electromechanics
Integrated management computer, each electrical and mechanical comprehensive management computer are made of 5 sub- states, Passive Active Standby
Off Isolated, this 5 sub- states respectively indicate different conditions at electrical and mechanical comprehensive management computer.
3. designing the redundancy management logic based on truth table
The transition relationship of the sub- state in each parent status IEMSC is established, including from original state to Passive state,
Passive state is to Active Standby state, Standby state to Active state.Off state is to Isolated
State.Shown in specific transition relationship table 1.
The transition relationship of different conditions in present case is described in detail in table 3.The Passive/Standby state of IEMSC1 arrives
The condition of Active state is that IEMSC2 is currently at Passive state.The Passive/Active/Standby shape of IEMSC1
The condition of state to Off state is go_off (i.e. system detection to failure).Item of the Off state of IEMSC1 to Isolated state
Part is [fails >=3], i.e., failure has reached 3 times.The condition of Off to the Off state of IEMSC1 be go_off [fails <
3], i.e., when continuous fault number is less than 3, IEMSC1 is still within Off state.
The remaining of airborne Electromechanical Management computer is realized with the input of the RIU of double redundancy using the truth table of Stateflow
Degree management logic.Truth table includes condition table and action schedule.In condition table table 4, preceding hatch door puts down limit switches 1 in place
(Front_Door_Deploy_State1) He Qianqi hatch door puts down 2 (Front_Door_Deploy_ of limit switches in place
State2) as input.When Front_Door_Deploy_State1 is true and Front_Door_Deploy_State2 is
When true, trigger action 1.It is true when Front_Door_Deploy_State1 is false and Front_Door_Deploy_State2
When, trigger action 2.When Front_Door_Deploy_State1 is true and Front_Door_Deploy_State2 is false
When, trigger action 3.It is false when Front_Door_Deploy_State1 is false and Front_Door_Deploy_State2
When, trigger action 4.In 5 action schedule of table, movement 1 is default-action, for sky.Movement 2 indicates that airborne electrical and mechanical comprehensive management calculates
There is transient fault, send (go_off, IEMSC.IEMSC1) in machine 1；Movement 3 indicates that airborne electrical and mechanical comprehensive management computer 2 goes out
Existing transient fault, send (go_off, IEMSC.IEMSC2)；Movement 4 indicates that airborne electrical and mechanical comprehensive management computer 1,2 all occurs
Transient fault, send (go_off, IEMSC.IEMSC1), send (go_off, IEMSC.IEMSC2).
3 electrical and mechanical comprehensive of table manages computer mode relationship
| Original state | Passive | Active | Standby | Off | Isolated | |
| Original state | \ | Automatically | \ | \ | go_off[！in(off)] | \ |
| Passive | \ | \ | ！IEMSC2_act() | IEMSC2_act() | go_off[！in(off)] | 、 |
| Active | \ | \ | \ | IEMSC2_act() | go_off[！in(off)] | \ |
| Standby | \ | \ | ！IEMSC2_act() | \ | go_off[！in(off)] | \ |
| Off | [validity1] | \ | \ | \ | go_off[fails<3] | [fails >=3] |
| Isolated | \ | \ | \ | \ | \ | \ |
Aircraft onboard machine-electronic equipment control and management integrated system troubleshooting condition table of the table 4 towards undercarriage control
| Description | Condition | D1 | D2 | D3 | D4 | |
| 1 | Preceding hatch door puts down limit switches 1 in place | Front_Door_Deploy_State1 | T | F | T | F |
| F | Preceding hatch door puts down limit switches 2 in place | Front_Door_Deploy_State2 | T | T | F | F |
| Movement | 1 | 2 | 3 | 4 |
Aircraft onboard machine-electronic equipment control and management integrated system troubleshooting action schedule of the table 5 towards undercarriage control
Claims (2)
1. a kind of Aircraft onboard machine-electronic equipment control and management integrated system redundancy management method based on Stateflow, it is characterized in that: being divided into three steps:
Establish Aircraft onboard machine-electronic equipment control and management integrated system architectural model；Design the state machine model of electrical and mechanical comprehensive management computer；Design
Redundancy management logic based on truth table；Specific step is as follows:
Step 1: establishing Aircraft onboard machine-electronic equipment control and management integrated system architectural model
The inspection of Aircraft onboard machine-electronic equipment control and management integrated system failure is established using the Chart of Stateflow according to Mechatronic Systems actual conditions
The architectural model surveyed and handled；Each state indicates that an electrical and mechanical comprehensive manages computer, all electrical and mechanical comprehensive management
The priority relationship of computer be on > under, it is left > right；
Step 2: the state machine model of design electrical and mechanical comprehensive management computer
On the basis of step 1, the state machine model of design electrical and mechanical comprehensive management computer；Each state in Stateflow
Indicate that an electrical and mechanical comprehensive management computer, each electrical and mechanical comprehensive management computer are made of 5 sub- states, Passive
Active Standby Off Isolated, this 5 sub- states respectively indicate difference at electrical and mechanical comprehensive management computer
Mode；
The Passive: the init state for entering periodic duty after electrical and mechanical comprehensive management computer powers on is indicated；
The Active: indicate that electrical and mechanical comprehensive management computer is active, i.e. this IEMC is in main control；
The Standby: indicate that electrical and mechanical comprehensive management computer is in Status of Backups, electrical and mechanical comprehensive management computer does not instruct
Output；
The Off: indicating that electrical and mechanical comprehensive manages computer glitch state, once electrical and mechanical comprehensive occur manages COMPUTER DETECTION to wink
When failure enter survey state；
The Isolated indicates isolation, according to the specific logic of system, when transient fault reaches certain threshold values, into every
From state, system takes safety measures；
Step 3: redundancy management logic of the design based on truth table
On the basis of step 2, initially set up the transition relationship of the sub- state in each parent status, including from original state to
Passive state, Passive state to Active Standby state, Standby state to Active state；Off shape
State is to Isolated state；The condition of Passive/Standby state to the Active state of IEMSC is that IEMSC is currently at
Passive state；The condition of Passive/Active/Standby state to the Off state of IEMSC is go_off, i.e., system is examined
Measure failure；The condition of Off state to the Isolated state of IEMSC is [fails >=n], i.e., failure has reached n times；
The condition of Off to the Off state of IEMSC is go_off [fails < n], i.e., when continuous fault number is less than n, IEMSC1 still locates
In Off state；
It is realized airborne according to the monitored results of Aircraft onboard machine-electronic equipment control and management integrated system as inputting using the truth table of Stateflow
The redundancy management logic of Electromechanical Management computer.
2. a kind of Aircraft onboard machine-electronic equipment control and management integrated system redundancy management method based on Stateflow according to claim 1,
It is characterized in that: the truth table includes condition table and action schedule；Each condition in condition table, in Condition (condition) column
First to judge that supervising signal is effective (T) or failure (F)；Each Decision (decision) column imply the "AND" behaviour of each condition
Make；The last one decision in table is known as default decision, it includes the every other decision other than the decision of aforementioned list；
Acting (Action) indicates the result of decision；Action schedule is the specific of the movement of condition table, and movement needs specific expression monitoring letter
Number virtual value obtains number.
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