CN111003155A - Method for flap control system with high reliability and low cost - Google Patents
Method for flap control system with high reliability and low cost Download PDFInfo
- Publication number
- CN111003155A CN111003155A CN201911376698.6A CN201911376698A CN111003155A CN 111003155 A CN111003155 A CN 111003155A CN 201911376698 A CN201911376698 A CN 201911376698A CN 111003155 A CN111003155 A CN 111003155A
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- Prior art keywords
- flap
- control
- control system
- standby
- realized
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/042—Initiating means actuated personally operated by hand
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
Abstract
The invention belongs to the field of flight control systems of military and civil aircraft, and provides a method for a flap control system with high reliability and low cost, which comprises the following steps: flap control systems can be divided into three major parts: the flap control part, the flap control part and the flap drive transmission execution part are connected with each other by cables; for the flap control part, a flap control handle and a flap standby control panel are adopted; for the flap control part, two sets of flap control computers and two sets of flap motor control modules are arranged; for the flap drive transmission execution part, a flap motor drive unit, a flap drive line train, a flap ball screw actuator, a wing tip brake device (WTB), and a Flap Position Sensor (FPSU) are designed. The invention reduces the development complexity of the flap control system; the flap control system has high reliability; the flap control system is low in overall development cost.
Description
Technical Field
The invention belongs to the field of flight control systems of military and civil aircrafts.
Background
The flap control system is a main means for realizing the function, and the goals of improving the reliability of the flap control system and reducing the cost of the flap control system are always pursued by the system design. The technical scheme provides a reasonable solution by combining practical engineering technical application experience and domestic and foreign technical development levels, meets the requirement on the reliability of the front flaps of the airplane, and achieves the purpose of reducing the cost.
Flap control systems can be divided mainly into three major parts: the flap control part, the flap control part and the flap drive execution part.
In a civil aircraft, a flap control part adopts a flap control handle and a standby override switch, a flap control part adopts an integrated flap control computer form, a return-free flap ball screw actuator is adopted in a flap transmission execution part, the stepping control of flaps is realized, the system integration level is high, and the system weight is light. However, in a standby state, only specific gear control can be realized, the system cannot realize command control of all gears, and the airplane has a form with special requirements; the high system integration and the specific flap ball screw actuator application result in high overall development costs.
In a certain airplane, a flap control part adopts a flap control handle and an override control plate, a flap control part adopts a flap control computer, a power supply processing module and a motor driving module, and a flap transmission execution part adopts a flap ball screw actuator and a hydraulic wing tip brake device, so that the stepping control of flaps is realized. However, the override control panel commands issue an override flap control computer to execute another set of control strategy, so that special requirements are provided for drivers, and certain use risks exist; the flap control part has more divided modules and heavier weight; the flap drive execution part adopts the forms of power drive and hydraulic brake, the complexity of the system is increased, and the overall reliability is not high.
Disclosure of Invention
The purpose of the invention is as follows: the method for the flap control system with high reliability and low cost is provided, the complexity of system development is reasonably reduced, and the cost of system development is effectively reduced.
The technical scheme is as follows:
a method of a highly reliable, low cost flap control system, comprising:
flap control systems can be divided into three major parts: the flap control part, the flap control part and the flap drive transmission execution part are connected with each other by cables;
for the flap control part, a flap control handle and a flap standby control panel are adopted;
for the flap control part, two sets of flap control computers and two sets of flap motor control modules are arranged;
for the flap drive transmission execution part, a flap motor drive unit, a flap drive line train, a flap ball screw actuator, a wing tip brake device (WTB), and a Flap Position Sensor (FPSU) are designed.
The flap control part adopts a flap control handle to realize multi-gear control command output in a normal control state; and in the standby operation state, a flap standby control panel is adopted to operate and command the output.
The flap standby control panel is provided with a flap standby switch and a flap standby control knob or switch, the flap standby switch realizes control instruction switching between the flap control handle and the flap standby control knob or switch, and the flap standby control knob or switch realizes issuing of standby control instructions.
The flap control computer is internally provided with a control channel and a monitoring channel, so that the acquisition, the processing and the selection of flap control instructions are realized, the interaction of external system cross-linking information is realized, the monitoring of the state of a flap system is realized, and the output and position closed-loop functions of complex control resolving instructions are realized.
The flap motor control module realizes instruction response and monitoring state report of a flap control computer through hardware and monitoring circuit design, realizes modulation and boosting of input high-voltage alternating current into direct current, and realizes control monitoring and speed closed-loop control functions of a flap motor driving unit.
The flap motor driving unit adopts two electric motor components and a speed comprehensive mechanism, realizes control and braking of a response flap motor control module, realizes torque limitation of output torque, and provides motor monitoring related signals and mechanical instruction output of speed superposition.
The flap transmission line system is composed of a torsion bar assembly, a supporting bearing and an angle changing device, so that the transmission of output torque of a flap motor driving unit is realized, the support and the angle changing transmission of the transmission line system on a wing back beam are realized, and the output of a flap wing ball screw actuator and a wing tip brake device is realized.
Two devices are arranged on each flap of the flap ball screw actuator, so that the input torque transmission and the limitation of a flap transmission line system are realized, the change of the torque transmission direction and the change of the transmission ratio are realized, and the connection and the driving of a flap control surface are realized.
The wing tip brake device adopts an electromagnetic power-off brake mode to realize torque braking and holding on the transmission line system and realize torque transmission and support of the normal transmission line system.
The flap position sensor is connected to the outermost flap ball screw actuator through a gear box, so that the flap position is measured and reported.
Has the advantages that:
1, reducing the development complexity of a flap control system;
2 the flap control system has high reliability;
3 the flap control system has lower overall development cost.
Drawings
FIG. 1 is a schematic diagram of the system of the present invention.
Detailed Description
The main technical scheme of the invention is as follows:
as shown in fig. 1, for an aircraft employing multiple flaps at the trailing edge of the wing, the flap control system can be divided into three major parts: the flap control system comprises a flap control part 1, a flap control part 2 and a flap drive transmission execution part 3, which are connected with each other by cables.
For the flap control part 1, a flap control handle and a flap standby control board are adopted according to the flap control characteristics and functional requirements. And under a normal operation state, a flap operation handle is adopted to realize the multi-gear operation control instruction output. And in the standby operation state, a flap standby control panel is adopted to operate and command the output. The flap standby control panel is provided with a flap standby switch and a flap standby control knob (or switch), the flap standby switch realizes control instruction switching between the flap control handle and the flap standby control knob (or switch), and the flap standby control knob (or switch) realizes issuing of standby control instructions.
For the 2 flap control part, two sets of flap control computers and two sets of flap motor control modules are arranged according to the regional electrical characteristics and the safety analysis result, so that the electrical control reliability is higher. The flap control computer is internally provided with a control channel and a monitoring channel, and can realize the acquisition, processing and selection of flap control instructions, the interaction of external system cross-linking information, the monitoring of flap system states and the output and position closed-loop functions of complex control resolving instructions through the matching design of software and hardware. The flap motor control module can realize instruction response and monitoring state report of a flap control computer, can realize modulation and boosting of input high-voltage alternating current into direct current, and can realize control monitoring and speed closed-loop control functions of a flap motor driving unit through hardware and monitoring circuit design.
For the 3-flap drive transmission executing part, a flap motor drive unit, a flap drive line system, a flap ball screw actuator, a wing tip brake device (WTB) and a Flap Position Sensor (FPSU) are designed according to the drive form, the structural characteristics of a flap control surface and the complexity of an executing mechanism. The flap motor driving unit adopts two electric motor components and a speed comprehensive mechanism, can realize control and braking in response to a flap motor control module, can realize torque limitation of output torque, and can provide motor monitoring related signals and speed superposed mechanical instruction output. The flap transmission line system is composed of the torsion bar assembly, the supporting bearing and the angle changing device, can realize the transmission of the output torque of the flap motor driving unit, can realize the supporting and angle changing transmission of the transmission line system on the wing back beam, and can realize the output of the flap ball screw actuator and the wing tip brake device. Two devices are arranged on each flap ball screw actuator, so that the input torque transmission and the limitation of a flap transmission line system can be realized, the change of the torque transmission direction and the change of the transmission ratio can be realized, and the connection and the driving of a flap control surface can be realized. The wing tip brake device adopts an electromagnetic power-off brake mode, can realize torque brake and holding on the transmission line system, and can realize torque transmission and support of the normal transmission line system. The flap position sensor is connected to the outermost flap ball screw actuator through a gear box, and measurement and reporting of the flap position can be achieved.
The best embodiment is as follows:
on a certain type of airplane, the control of the left outer flap, the left inner flap, the right inner flap and the right outer flap of the trailing edge is required to be completed according to the gears 0, 1, 2 and 3. The technical scheme is implemented as follows:
the flap control system is divided into three major parts: the flap control system comprises a flap control part 1, a flap control part 2 and a flap drive transmission execution part 3, which are connected with each other by cables.
For the flap 1 manipulating part, a flap manipulating handle and a flap standby control board are used. And under a normal operation state, the flap operation handle is adopted to realize the operation control instruction output of the 0, 1, 2 and 3 gears. And in a standby operation state, a flap standby control board is adopted to realize the output of a retraction operation instruction. The flap standby switch on the flap standby control panel realizes the switching of control instructions between the flap control handle and the flap standby control knob, and the flap standby control knob on the flap standby control panel realizes the output of retraction control instructions.
For the 2 flap control part, two sets of flap control computers and two sets of flap motor control modules are arranged, and the flap control computers and the flap motor control modules are in communication connection through hard wires and bus cables. The flap control computer is internally provided with a control channel and a monitoring channel, so that the acquisition, the processing and the selection of flap control instructions are realized, the folding and unfolding control instructions of the flap standby control knob are converted into 0, 1, 2 and 3 gear instructions, the interaction of external system crosslinking information is realized, the monitoring of the state of a flap system is realized, and the output and position closed-loop functions of complex control resolving instructions are realized. The flap motor control module realizes instruction response and monitoring state report of a flap control computer through hardware and monitoring circuit design, realizes modulation and boosting of input high-voltage alternating current into direct current, and realizes control monitoring and speed closed-loop control functions of a flap motor driving unit.
For the 3-flap drive transmission execution part, a flap motor drive unit, a flap drive line system, a flap ball screw actuator, a wing tip brake device (WTB), and a Flap Position Sensor (FPSU) are designed. The flap motor driving unit adopts two electric motor components and a speed comprehensive mechanism, realizes control and braking of a response flap motor control module, realizes torque limitation of output torque, and realizes mechanical instruction output of motor monitoring related signals and speed superposition. The flap transmission line system realizes the transmission of the output torque of the flap motor driving unit through the torsion bar component and the supporting bearing, realizes the support and the transmission of the transmission line system on the wing back beam, and realizes the output of the contra-flap ball screw actuator and the wing tip brake device. Two devices are arranged on each flap of the flap ball screw actuator, so that the input torque transmission and the limitation of a flap transmission line system are realized, the change of the torque transmission direction and the change of the transmission ratio are realized, and the connection and the driving of a flap control surface are realized. The wing tip brake device adopts an electromagnetic power-off brake mode, realizes torque brake and holding on the transmission line system, and realizes torque transmission and support of the normal transmission line system. The flap position sensor is connected to the outermost flap ball screw actuator through the gear box, and measurement and reporting of the flap position are achieved.
Claims (10)
1. A method of a highly reliable, low cost flap control system, comprising:
flap control systems can be divided into three major parts: the flap control part, the flap control part and the flap drive transmission execution part are connected with each other by cables;
for the flap control part, a flap control handle and a flap standby control panel are adopted;
for the flap control part, two sets of flap control computers and two sets of flap motor control modules are arranged;
for the flap drive transmission execution part, a flap motor drive unit, a flap drive line train, a flap ball screw actuator, a wing tip brake device (WTB), and a Flap Position Sensor (FPSU) are designed.
2. The method of claim 1, wherein the flap control system is a high-reliability low-cost flap control system,
the flap control part adopts a flap control handle to realize multi-gear control command output in a normal control state; and in the standby operation state, a flap standby control panel is adopted to operate and command the output.
3. A method of a highly reliable, low cost flap control system according to claim 2,
the flap standby control panel is provided with a flap standby switch and a flap standby control knob or switch, the flap standby switch realizes control instruction switching between the flap control handle and the flap standby control knob or switch, and the flap standby control knob or switch realizes issuing of standby control instructions.
4. The method of claim 1, wherein the flap control system is a high-reliability low-cost flap control system,
the flap control computer is internally provided with a control channel and a monitoring channel, so that the acquisition, the processing and the selection of flap control instructions are realized, the interaction of external system cross-linking information is realized, the monitoring of the state of a flap system is realized, and the output and position closed-loop functions of complex control resolving instructions are realized.
5. The method of claim 1, wherein the flap control system is a high-reliability low-cost flap control system,
the flap motor control module realizes instruction response and monitoring state report of a flap control computer through hardware and monitoring circuit design, realizes modulation and boosting of input high-voltage alternating current into direct current, and realizes control monitoring and speed closed-loop control functions of a flap motor driving unit.
6. The method of claim 1, wherein the flap control system is a high-reliability low-cost flap control system,
the flap motor driving unit adopts two electric motor components and a speed comprehensive mechanism, realizes control and braking of a response flap motor control module, realizes torque limitation of output torque, and provides motor monitoring related signals and mechanical instruction output of speed superposition.
7. The method of claim 1, wherein the flap control system is a high-reliability low-cost flap control system,
the flap transmission line system is composed of a torsion bar assembly, a supporting bearing and an angle changing device, so that the transmission of output torque of a flap motor driving unit is realized, the support and the angle changing transmission of the transmission line system on a wing back beam are realized, and the output of a flap wing ball screw actuator and a wing tip brake device is realized.
8. The method of claim 1, wherein the flap control system is a high-reliability low-cost flap control system,
two devices are arranged on each flap of the flap ball screw actuator, so that the input torque transmission and the limitation of a flap transmission line system are realized, the change of the torque transmission direction and the change of the transmission ratio are realized, and the connection and the driving of a flap control surface are realized.
9. The method of claim 1, wherein the flap control system is a high-reliability low-cost flap control system,
the wing tip brake device adopts an electromagnetic power-off brake mode to realize torque braking and holding on the transmission line system and realize torque transmission and support of the normal transmission line system.
10. The method of claim 1, wherein the flap control system is a high-reliability low-cost flap control system,
the flap position sensor is connected to the outermost flap ball screw actuator through a gear box, so that the flap position is measured and reported.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911376698.6A CN111003155A (en) | 2019-12-27 | 2019-12-27 | Method for flap control system with high reliability and low cost |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911376698.6A CN111003155A (en) | 2019-12-27 | 2019-12-27 | Method for flap control system with high reliability and low cost |
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| CN111003155A true CN111003155A (en) | 2020-04-14 |
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| CN201911376698.6A Pending CN111003155A (en) | 2019-12-27 | 2019-12-27 | Method for flap control system with high reliability and low cost |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112124568A (en) * | 2020-09-28 | 2020-12-25 | 中国商用飞机有限责任公司 | Fly-by-wire flight control system and control method |
| CN112407249A (en) * | 2020-11-05 | 2021-02-26 | 中国航空工业集团公司西安航空计算技术研究所 | Voting monitoring method for gears of double-redundancy flap control handle |
| CN114194381A (en) * | 2021-12-30 | 2022-03-18 | 中国航空工业集团公司西安飞机设计研究所 | Three-level torque protection device of flap actuating system of large aircraft |
| CN114261509A (en) * | 2021-12-30 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Flap limit position protection system and method |
| CN114261510A (en) * | 2021-12-30 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Power drive device monitoring system that skids |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112124568A (en) * | 2020-09-28 | 2020-12-25 | 中国商用飞机有限责任公司 | Fly-by-wire flight control system and control method |
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| CN112407249A (en) * | 2020-11-05 | 2021-02-26 | 中国航空工业集团公司西安航空计算技术研究所 | Voting monitoring method for gears of double-redundancy flap control handle |
| CN114194381A (en) * | 2021-12-30 | 2022-03-18 | 中国航空工业集团公司西安飞机设计研究所 | Three-level torque protection device of flap actuating system of large aircraft |
| CN114261509A (en) * | 2021-12-30 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Flap limit position protection system and method |
| CN114261510A (en) * | 2021-12-30 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Power drive device monitoring system that skids |
| CN114194381B (en) * | 2021-12-30 | 2023-06-23 | 中国航空工业集团公司西安飞机设计研究所 | Three-level torque protection device of large-scale aircraft flap actuating system |
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Application publication date: 20200414 |
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