CN204965053U - Telex flight control system - Google Patents
Telex flight control system Download PDFInfo
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- CN204965053U CN204965053U CN201520601551.3U CN201520601551U CN204965053U CN 204965053 U CN204965053 U CN 204965053U CN 201520601551 U CN201520601551 U CN 201520601551U CN 204965053 U CN204965053 U CN 204965053U
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Abstract
The utility model provides a telex flight control system uses on the aircraft, include: a flight controller, an above -mentioned flight controller include first fly to control computer and first actuator controller, above -mentionedly first fly to control computer and the integration of above -mentioned first actuator controller in an above -mentioned flight controller, the 2nd flight controller, above -mentioned the 2nd flight controller include that the second flies to control computer and second actuator controller, and above -mentioned second flies to control computer and the integration of above -mentioned second actuator controller in the 2nd flight controller of the aforesaid, wherein, above -mentioned first actuator controller is the same with the configuration of above -mentioned second actuator controller, above -mentioned firstly fly to control computer and above -mentioned second to fly to control the configuration of computer the same. Through the utility model discloses, solve development cost of system and the high problem of maintenance cost in the correlation technique, and then reached reduce cost's effect.
Description
Technical field
The utility model relates to the communications field, in particular to a kind of fly-by-wire flight control system.
Background technology
At present, fly-by-wire flight control system has become the mainstream development trend of international civil aviation technology.Be no matter trunk line machine or branch line machine also or business airplane, flight control system adopts fax mode (fly-by-wire) to instead of traditional mechanical handling gradually.And adopt fly-by-wire flight control system just to have to consider the layout strategy such as system redundancy, system backup, just have to use complicated electronic hardware and software for realizing corresponding system protection function simultaneously.
In correlation technique, a kind of flight control system adopts the control framework of 2 control enclosure (FCC)+6 main actuator controllers (P-ACE)+1 horizontal stabilizer actuator controllers (HS-ACE) of flying, and another also have 2 pieces of spoiler actuator controllers (S-ACE) to be integrated in flight control enclosure.Control, monitoring, the envelope protection of its flight control enclosure primary responsibility whole system and be cross-linked communication etc. with other system.Actuator controller mainly adopts the control of mimic channel realization to main control surface, spoiler and horizontal stabilizer.
Can find out that system equipment is more from the configuration of above-mentioned flight control system framework, be cross-linked and control more complicated, actuator controller adopts analog form to add weight of equipment, this must cause, and system development cost increases, system weight also increases thereupon, too increases system spare part quantity and system maintenance cost simultaneously.Therefore, optimize fly-by-wire flight control system design proposal, reduce flight control system LRU (LRU) composition to reduce system weight and spare part quantity, reduction system development cost and maintenance cost are the urgent hope of current each main engine plants and airline.
In correlation technique, another kind of aircraft fly-by-wire flight control system adopts redundance control channel, to meet the security of system design object of 1E-9/FH.It is mainly configured with hyperchannel location of instruction sensor, 2 flight controllers (FCU), 2 actuator controllers (ACE) and multiple stage actuator (PCU).Bright spot of the present invention a flight control computer (FCC) and an actuator controller (ACE) is integrated in same cabinet to form a flight controller (FCU), FCC and ACE in FCU all keeps respective function and interface independence.The object of this design proposal is under the prerequisite meeting security of system, reduces system LRU composition, reduces system development cost, reduce spare part quantity and reduce maintenance cost.
Summary of the invention
The utility model provides a kind of fly-by-wire flight control system, at least to solve prior art systems development cost and the high problem of maintenance cost.
According to an aspect of the present utility model, provide a kind of fly-by-wire flight control system, comprise the first flight controller, described first flight controller comprises the first flight control computer and the first actuator controller, and described first flight control computer and described first actuator controller are integrated in described first flight controller; Second flight controller, described second flight controller comprises the second flight control computer and the second actuator controller, and described second flight control computer and described second actuator controller are integrated in described second flight controller; Wherein, described first actuator controller is identical with the configuration of described second actuator controller, and described first flight control computer is identical with the configuration of described second flight control computer.
Preferably, described fly-by-wire flight control system also comprises the 3rd actuator controller and the 4th actuator controller, wherein, described 3rd actuator controller and described 4th actuator controller are the actuator controllers of only two platform independent in described fly-by-wire flight control system except described first actuator controller and described second actuator controller, further, described 3rd actuator controller is identical with the configuration of described 4th actuator controller.
Preferably, described system also comprises only four single remaining rudder face position transducers, described four single remaining rudder face position transducers are port aileron position transducer, starboard aileron position transducer, left elevator position transducer and right elevator position transducer respectively, and described four single remaining rudder face position transducers are connected with described first actuator controller, described second actuator controller, described 3rd actuator controller and described 4th actuator controller respectively.
Preferably, described port aileron position transducer is connected with described 3rd actuator controller; Described starboard aileron position transducer is connected with described first actuator controller; Described left elevator position transducer is connected with described second actuator controller; Described right elevator position transducer is connected with described 4th actuator controller.
Preferably, described 3rd actuator controller is connected with actuator outside actuator outside the port aileron of described aircraft and left elevator respectively, and described first actuator controller is connected with actuator inside actuator inside the port aileron of described aircraft and left elevator respectively.
Preferably, described 4th actuator controller is connected with actuator outside actuator outside the starboard aileron of described aircraft and right elevator respectively, and described second actuator controller is connected with actuator inside actuator inside the starboard aileron of described aircraft and right elevator respectively.
Preferably, described system also comprises left inside side spoiler actuator and Right Inboard spoiler actuator, described left inside side spoiler actuator is connected with described 3rd actuator controller with described Right Inboard spoiler actuator, further, described left inside side spoiler actuator and described Right Inboard spoiler actuator are only controlled by described 3rd actuator controller.
Preferably, described system also comprises left-external side spoiler actuator and right outside side spoiler actuator, described left-external side spoiler actuator is connected with described 4th actuator controller with described right outside side spoiler actuator, further, described left-external side spoiler actuator and described right outside side spoiler actuator are only controlled by described 4th actuator controller.
By the utility model, adopt the first flight controller, described first flight controller comprises the first flight control computer and the first actuator controller, and described first flight control computer and described first actuator controller are integrated in described first flight controller; Second flight controller, described second flight controller comprises the second flight control computer and the second actuator controller, and described second flight control computer and described second actuator controller are integrated in described second flight controller; Wherein, described first actuator controller is identical with the configuration of described second actuator controller, and described first flight control computer is identical with the configuration of described second flight control computer.Solve the problem that system development cost and maintenance cost in correlation technique are high, and then reach the effect reduced costs.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, and form a application's part, schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the structural representation of the fly-by-wire flight control system according to the utility model embodiment;
Fig. 2 is the structural representation of the fly-by-wire flight control system according to the utility model preferred embodiment;
Embodiment
Hereinafter also describe the utility model in detail with reference to accompanying drawing in conjunction with the embodiments.It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.
The utility model provides a kind of fly-by-wire flight control system, and Fig. 1 is the structural representation Fig. 1 according to fly-by-wire flight control system of the present utility model, and as shown in Figure 1, this system comprises:
First flight controller 1, described first flight controller 1 comprises the first flight control computer 11 and the first actuator controller 12, and described first flight control computer 11 and described first actuator controller 12 are integrated in described first flight controller 1; Second flight controller 2, described second flight controller 2 comprises the second flight control computer 21 and the second actuator controller 22, and described second flight control computer 21 and described second actuator controller 22 are integrated in described second flight controller 2; Wherein, described first actuator controller 12 is identical with the configuration of described second actuator controller 22, and described first flight control computer 11 is identical with the configuration of described second flight control computer 11.
In one embodiment, described fly-by-wire flight control system can also comprise the 3rd actuator controller and the 4th actuator controller, wherein, described 3rd actuator controller and described 4th actuator controller are the actuator controllers of only two platform independent in described fly-by-wire flight control system except described first actuator controller and described second actuator controller, further, described 3rd actuator controller is identical with the configuration of described 4th actuator controller.
In another embodiment, described system also comprises only four single remaining rudder face position transducers, described four single remaining rudder face position transducers are port aileron position transducer, starboard aileron position transducer, left elevator position transducer and right elevator position transducer respectively, and described four single remaining rudder face position transducers are connected with described first actuator controller, described second actuator controller, described 3rd actuator controller and described 4th actuator controller respectively.
Wherein, described port aileron position transducer is connected with described 3rd actuator controller; Described starboard aileron position transducer is connected with described first actuator controller; Described left elevator position transducer is connected with described second actuator controller; Described right elevator position transducer is connected with described 4th actuator controller.
Wherein, described 3rd actuator controller is connected with actuator outside actuator outside the port aileron of described aircraft and left elevator respectively, and described first actuator controller is connected with actuator inside actuator inside the port aileron of described aircraft and left elevator respectively.
Wherein, described 4th actuator controller is connected with actuator outside actuator outside the starboard aileron of described aircraft and right elevator respectively, and described second actuator controller is connected with actuator inside actuator inside the starboard aileron of described aircraft and right elevator respectively.
Wherein, described system also comprises left inside side spoiler actuator and Right Inboard spoiler actuator, described left inside side spoiler actuator is connected with described 3rd actuator controller with described Right Inboard spoiler actuator, further, described left inside side spoiler actuator and described Right Inboard spoiler actuator are only controlled by described 3rd actuator controller.
Wherein, described system also comprises left-external side spoiler actuator and right outside side spoiler actuator, described left-external side spoiler actuator is connected with described 4th actuator controller with described right outside side spoiler actuator, further, described left-external side spoiler actuator and described right outside side spoiler actuator are only controlled by described 4th actuator controller.
The utility model additionally provides a kind of preferred fly-by-wire flight control system, and Fig. 2 is the fly-by-wire flight control system according to the utility model preferred embodiment, and as shown in Figure 2, the structure of this system is as follows:
In the design process, require that flight control system can complete the control of 2 pieces of elevating rudders, 2 pieces of ailerons, 4 pieces of spoilers and 1 Block direction rudders, the probability that security of system index request completely loses flight control ability should be less than 1E-9/FH, and the probability that system enters Direct Model should be less than 1E-7/FH.
Fly-by-wire flight control system adopts traditional jociey stick/dish maneuverability pattern, and left and right operating control adopts override lever type of attachment.Main function of system has been the control of 2 pieces of elevating rudders, 2 pieces of ailerons, 4 pieces of spoilers and 1 Block direction rudders, and main composition has instruction sensor, flight controller, actuator controller, actuator, rudder face position transducer and cable.
Each axle location of instruction sensor configures 8, one-sidedly arranges 4, is mainly used in measuring the displacement of driving cabin operating control and provides operation input information for flight control system.Under normal conditions, override lever can guarantee left and right interlock, and when one-sided jam, left and right exports inconsistent, and this computer-chronograph carrys out decision instruction validity according to the variable gradient of instruction.Deceleration handle instruction sensor is 4 remainings, is mainly Air slowdown and ground and slows down and provide operation input.
Flight controller configures 2, each one of left and right electronic equipment case.During normal mode, flight control computer in flight controller uses normal mode control law to complete the control of whole system, monitoring and defencive function, and crosslinked with other system.Every platform flight control computer is provided with controlling brancher and monitoring branch road, and 2 branch roads adopt non-similar electronic hardware and software to avoid common mode failure, simultaneously also in order to ensure the validity of output order to meet security of system requirement.When losing atmosphere data, flight control system can enter degraded mode automatically.
Actuator controller configures 2, each one of left and right electronic equipment case, and every platform actuator controller is provided with and controls and monitoring branch road.Be responsible for the acquisition and processing of all simulations of flight control system, discrete signal, and result is reported flight control computer in digital form.By with corresponding main rudder face actuator form close loop control circuit, thus realize servocontrol to each control surface.In addition, the actuator in flight controller also has these functions, but it adopts dissimilar complicated circuit to avoid common mode failure.Under normal mode, all actuator controllers receive and perform the instruction that FCC sends.Under Direct Model, actuator controller can provide emergency flight control ability.Handle control command according to driving cabin, and realize the control to each control surface by Direct Model control law.
Actuator allocation 15, is respectively 4 elevating rudder actuator, 4 aileron actuator, and 4 spoiler actuator and 3 yaw rudder actuator, accept the steering order that actuator controller sends, realize the deflection control to rudder face.
Rudder face position transducer 4, is provided in left and right aileron and left and right elevating rudder rudder face respectively, and each sensor adopts electric single remaining form, is mainly used in driving cabin each control surface position instruction.
The utility model additionally provides a kind of fly-by-wire flight control system, this fly-by-wire flight control system adopts traditional jociey stick/dish manipulation form, major function has been the control of 2 pieces of elevating rudders, 2 pieces of ailerons, 4 pieces of spoilers and 1 Block direction rudders, it mainly forms has: driving cabin control command sensor, flight controller, actuator controller, actuator, and airborne cable etc.About jociey stick position transducer each 4, be integrated in respectively in pitch control module.About control wheel position transducer each 4, be integrated in respectively in roll manipulation module.About pedal position transducer each 4 (wherein a road is used for Nose Wheel Steering), be integrated in respectively in driftage module and pedal damping module.Decelerating manoeuvre handle configurations 4 position transducers.Flight controller configures 2, is arranged in the electronic equipment case of left and right.Actuator controller configures 2, is arranged in the electronic equipment case of left and right.Actuator allocation 15, is respectively 4 elevating rudder actuator, 4 aileron actuator, 4 spoiler actuator and 3 yaw rudder actuator.Rudder face position transducer 4, is arranged on left and right aileron and left and right elevating rudder respectively.Cable is mainly divided into communication bus type and signal conductor.
The utility model embodiment has following beneficial effect: decrease system LRU composition, the system of reducing is cross-linked complexity, and system adopts modular design to reduce system maintenance cost, improve the reliability of flight control system and send rate, significantly reducing flight control system development cost and operation maintenance cost.Specifically, the utility model has the following advantages:
1. system architecture is more reasonable, and configuration is more optimized, and the basic reliability index MTBF value of system itself is apparently higher than system design goal;
2. system is cross-linked complexity and obviously reduces, and improves security of system;
3. based on the optimization of system architecture, decrease system LRU composition, thus reduce system weight, reduce system unit cost, decrease system spare part quantity and airline maintenance cost simultaneously;
4. system margin configuration is rationally easy, can effectively reduce cable arrangements length;
5. system adopts modular design, more reasonable and convenient in accessibility, effectively improves the maintainability of system.
Obviously, those skilled in the art should be understood that, above-mentioned of the present utility model each module or each step can realize with general calculation element, they can concentrate on single calculation element, or be distributed on network that multiple calculation element forms, alternatively, they can realize with the executable program code of calculation element, thus, they can be stored and be performed by calculation element in the storage device, and in some cases, step shown or described by can performing with the order be different from herein, or they are made into each integrated circuit modules respectively, or the multiple module in them or step are made into single integrated circuit module to realize.Like this, the utility model is not restricted to any specific hardware and software combination.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (8)
1. a fly-by-wire flight control system, application on board the aircraft, is characterized in that, comprising:
First flight controller, described first flight controller comprises the first flight control computer and the first actuator controller, and described first flight control computer and described first actuator controller are integrated in described first flight controller;
Second flight controller, described second flight controller comprises the second flight control computer and the second actuator controller, and described second flight control computer and described second actuator controller are integrated in described second flight controller;
Wherein, described first actuator controller is identical with the configuration of described second actuator controller, and described first flight control computer is identical with the configuration of described second flight control computer.
2. system according to claim 1, it is characterized in that, described fly-by-wire flight control system also comprises the 3rd actuator controller and the 4th actuator controller, wherein, described 3rd actuator controller and described 4th actuator controller are the actuator controllers of only two platform independent in described fly-by-wire flight control system except described first actuator controller and described second actuator controller, further, described 3rd actuator controller is identical with the configuration of described 4th actuator controller.
3. system according to claim 2, it is characterized in that, described system also comprises only four single remaining rudder face position transducers, described four single remaining rudder face position transducers are port aileron position transducer, starboard aileron position transducer, left elevator position transducer and right elevator position transducer respectively, and described four single remaining rudder face position transducers are connected with described first actuator controller, described second actuator controller, described 3rd actuator controller and described 4th actuator controller respectively.
4. system according to claim 3, is characterized in that, described port aileron position transducer is connected with described 3rd actuator controller; Described starboard aileron position transducer is connected with described first actuator controller; Described left elevator position transducer is connected with described second actuator controller; Described right elevator position transducer is connected with described 4th actuator controller.
5. the system according to any one of claim 2 to 4, it is characterized in that, described 3rd actuator controller is connected with actuator outside actuator outside the port aileron of described aircraft and left elevator respectively, and described first actuator controller is connected with actuator inside actuator inside the port aileron of described aircraft and left elevator respectively.
6. the system according to any one of claim 2 to 4, it is characterized in that, described 4th actuator controller is connected with actuator outside actuator outside the starboard aileron of described aircraft and right elevator respectively, and described second actuator controller is connected with actuator inside actuator inside the starboard aileron of described aircraft and right elevator respectively.
7. system according to claim 2, it is characterized in that, described system also comprises left inside side spoiler actuator and Right Inboard spoiler actuator, described left inside side spoiler actuator is connected with described 3rd actuator controller with described Right Inboard spoiler actuator, further, described left inside side spoiler actuator and described Right Inboard spoiler actuator are only controlled by described 3rd actuator controller.
8. system according to claim 2, it is characterized in that, described system also comprises left-external side spoiler actuator and right outside side spoiler actuator, described left-external side spoiler actuator is connected with described 4th actuator controller with described right outside side spoiler actuator, further, described left-external side spoiler actuator and described right outside side spoiler actuator are only controlled by described 4th actuator controller.
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| CN201520601551.3U CN204965053U (en) | 2015-08-11 | 2015-08-11 | Telex flight control system |
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| CN201520601551.3U CN204965053U (en) | 2015-08-11 | 2015-08-11 | Telex flight control system |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107608381A (en) * | 2017-09-30 | 2018-01-19 | 江西洪都航空工业集团有限责任公司 | A kind of fly-by-wire flight control system control framework for mixing redundant configurations |
| CN108363644A (en) * | 2017-12-20 | 2018-08-03 | 中国航空工业集团公司西安飞行自动控制研究所 | The distributed active and standby selection method of fax asynchronous working flight control computer |
| CN110766930A (en) * | 2019-10-23 | 2020-02-07 | 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 |
| CN111045451A (en) * | 2019-12-16 | 2020-04-21 | 西安航空学院 | Control system of aircraft and aircraft |
| CN111142369A (en) * | 2019-12-27 | 2020-05-12 | 中国航空工业集团公司西安飞机设计研究所 | Fly-by-wire flight control system capable of meeting airworthiness requirement |
| WO2022062233A1 (en) * | 2020-09-28 | 2022-03-31 | 中国商用飞机有限责任公司 | Fly-by-wire flight control system, and control method |
| WO2023035497A1 (en) * | 2021-09-07 | 2023-03-16 | 中国商用飞机有限责任公司 | Fly-by-wire flight backup control system and method |
-
2015
- 2015-08-11 CN CN201520601551.3U patent/CN204965053U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107608381A (en) * | 2017-09-30 | 2018-01-19 | 江西洪都航空工业集团有限责任公司 | A kind of fly-by-wire flight control system control framework for mixing redundant configurations |
| CN108363644A (en) * | 2017-12-20 | 2018-08-03 | 中国航空工业集团公司西安飞行自动控制研究所 | The distributed active and standby selection method of fax asynchronous working flight control computer |
| CN108363644B (en) * | 2017-12-20 | 2021-08-03 | 中国航空工业集团公司西安飞行自动控制研究所 | Main and standby selection method for distributed telex asynchronous working flight control computer |
| CN110766930A (en) * | 2019-10-23 | 2020-02-07 | 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 |
| CN111045451A (en) * | 2019-12-16 | 2020-04-21 | 西安航空学院 | Control system of aircraft and aircraft |
| CN111142369A (en) * | 2019-12-27 | 2020-05-12 | 中国航空工业集团公司西安飞机设计研究所 | Fly-by-wire flight control system capable of meeting airworthiness requirement |
| WO2022062233A1 (en) * | 2020-09-28 | 2022-03-31 | 中国商用飞机有限责任公司 | Fly-by-wire flight control system, and control method |
| WO2023035497A1 (en) * | 2021-09-07 | 2023-03-16 | 中国商用飞机有限责任公司 | Fly-by-wire flight backup control system and method |
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