CN111516857A - Flap distributed driving system - Google Patents
Flap distributed driving system Download PDFInfo
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- CN111516857A CN111516857A CN202010362850.1A CN202010362850A CN111516857A CN 111516857 A CN111516857 A CN 111516857A CN 202010362850 A CN202010362850 A CN 202010362850A CN 111516857 A CN111516857 A CN 111516857A
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- 230000007246 mechanism Effects 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 abstract description 12
- 230000033001 locomotion Effects 0.000 abstract description 5
- 230000007547 defect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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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
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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
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps
Abstract
The invention belongs to the field of aviation flap drive control, and particularly relates to a flap distributed drive system. The system is a distributed driving configuration in which a power driving device is respectively arranged on a transmission line system between a left inner flap and a right outer flap, and the configuration omits the transmission line system for connecting the left driving system and the right driving system and reduces the number of the driving devices, so that the number of components of the high-lift system is reduced, and the configuration of the high-lift system is simplified. Meanwhile, the distributed driving configuration enlarges the range of deflection angles between the inner flap and the outer flap; the power driving device of each side wing surface is reduced to one, and simultaneously, the transmission line system of the inner flap and the outer flap is not disconnected, so that the movement consistency of the inner flap and the outer flap of the single side wing surface is ensured.
Description
Technical Field
The invention belongs to the field of aviation flap drive control, and particularly relates to a flap distributed drive system.
Background
The large modern aircraft achieves the purpose of increasing the wing area by extending the trailing edge flaps 9, 10, 20, 21 on the wings 11, 19 during takeoff, and the increased area of the wings 11, 19 increases the lift of the aircraft in order to take off and land the aircraft at a lower speed. During flight of the aircraft, the pilot operates the yaw angle of the left and right ailerons 18, 22 to effect roll maneuver of the aircraft. The driving of the trailing edge flaps 9, 10, 20 and 21 of the left and right wing surfaces of the airplane generally adopts a central centralized driving mode (fig. 1), and a power driving device 1 positioned in the center of the airplane is controlled by a slat control computer 23 to drive the left and right outer flaps 9 and 21 and the inner flaps 10 and 20 to simultaneously bias upwards or downwards so as to ensure the synchronism of the movement of the left and right trailing edge flaps; the ailerons 18, 22 are individual airfoils located at the ends of the wings 11, 19.
The traditional central centralized driving mode connects the left and right driving lines together, so that the consistency of the motion of the left and right airfoils is ensured, but the transmission line of the centralized driving configuration is long, so that the high-lift driving system has more components and heavy weight.
The distributed drive mode of reference patent 1 (EP 2851284a1) is based on the traditional central centralized drive mode, and a drive device is respectively added between the transmission line systems of the left inner flap and the right inner flap, so that the function of mutually independent motion between the outer flap and the inner flap is realized. However, because the configuration adds the independent driving function on the basis of the central centralized driving mode, the complexity of the high lift system is not reduced, and the high lift system still has the defects of more components and heavy weight.
The distributed drive mode of reference 2 (patent number: US20040200928a1) eliminates the structure of connecting the transmission line systems of the left and right flaps, and realizes completely independent drive of the inner and outer flaps, but the distributed drive mode reduces the number and weight of the high-lift system components because the distributed drive mode not only integrates a motor for each actuator, but also disconnects the transmission line systems of the inner and outer flaps, but the distributed drive mode of reference 2 has the defects of more drive and poor synchronism of the inner and outer flaps.
Disclosure of Invention
The purpose of the invention is as follows: provided is a flap distributed drive system that is light in weight and highly safe.
The technical scheme is as follows:
in a first aspect, there is provided a flap distributed drive system comprising: a left drive system 113, a right drive system 116, and a slat control computer 123, wherein the left drive system 113 and the right drive system 116 are respectively controlled by the slat control computer 123.
Further, the left driving system and the right driving system each include an inner side position sensor 101, a first actuator 102, an inner side wing tip braking device 103, a second actuator 104, a third actuator 105, an outer side wing tip braking device 106, a fourth actuator 107, an outer side position sensor 108, and a power driving device 109, wherein a left end output shaft of the power driving device 109 is fixedly connected with a right end input shaft of the third actuator 105 through a spline, a right end output shaft of the power driving device 109 is fixedly connected with a left end input shaft of the second actuator 104 through a spline, and the power driving device 109 is controlled by a slat control computer 123; the left input shaft of the third actuator 105 is fixedly connected with the right input shaft of the outer wing tip braking device 106 through a spline, and the output shaft of the third actuator 105 is connected with the outer flap 111 through a track; the left input shaft of the outboard wingtip braking device 106 is fixedly connected with the right input shaft of the fourth actuator 107 through a spline; the output shaft of the fourth actuator 107 is connected with the outer flap 111 through a track; the outer side position sensor 108 is fixedly connected to the fourth actuator 107 through a flange plate and a spline, and a position signal of the outer side position sensor 108 is fed back to the slat control computer 123; the right input shaft of the second actuator is fixedly connected with the left input shaft of the inner wingtip braking device through a spline, and the output shaft of the second actuator is connected with the inner flap through a track; the right input shaft of the inboard wingtip braking device is fixedly connected with the left input shaft of the first actuator through a spline; the output shaft of the first actuator is connected with the inner flap through a track; the inner side position sensor is fixedly connected with the first actuator through a flange plate and a spline, and a position signal of the inner side position sensor is fed back to the slat control computer.
Further, N actuators are further included between the third actuator and the outboard wing tip braking device, wherein N is a positive integer, the N actuators are connected in series, and the output shaft and the outboard wing are connected through a rail.
Further, N actuators are further included between the third actuator and the outboard wing tip braking device, wherein N is a positive integer, the N actuators are connected in series, and the output shaft and the inner flap are connected through a rail.
Further, the left driving system and the right driving system respectively comprise an inner side position sensor 101, a first actuator 102, a second actuator 104, a third actuator 105, a fourth actuator 107, an outer side position sensor 108 and a power driving device 109, wherein the first actuator 102, the second actuator 104, the third actuator 105 and the fourth actuator 107 are respectively provided with a non-return mechanism, a left end output shaft of the power driving device 109 is fixedly connected with a right end input shaft of the third actuator 105 through a spline, a right end output shaft of the power driving device 109 is fixedly connected with a left end input shaft of the second actuator 104 through a spline, and the power driving device 109 is controlled by a slat control computer 123; a left input shaft of the third actuator 105 and a right input shaft of the fourth actuator 107 are fixedly connected through splines, and an output shaft of the third actuator 105 is connected with the outer flap 111 through a track; the output shaft of the fourth actuator 107 is connected with the outer flap 111 through a track; the outer side position sensor 108 is fixedly connected to the fourth actuator 107 through a flange plate, and a position signal of the outer side position sensor 108 is fed back to the slat control computer 123; the right input shaft of the second actuator is fixedly connected with the left input shaft of the first actuator through a spline, and the output shaft of the second actuator is connected with the inner flap through a track; the output shaft of the first actuator is connected with the inner flap through a track; the inner side position sensor is fixedly connected with the first actuator through a flange plate, and a position signal of the inner side position sensor is fed back to the slat control computer.
Further, under the condition that the flap comprises the middle flap, the left driving system and the right driving system respectively comprise a fifth actuator and a sixth actuator, the fifth actuator and the sixth actuator are connected in series between an output shaft of the power driving device and the second actuator or between an output shaft of the power driving device and the third actuator, and output shafts of the fifth actuator and the sixth actuator are respectively connected with the middle flap through tracks.
Further, in the case where the flap comprises a middle flap, the left and right drive systems further comprise N actuators, where N is a positive integer, the N actuators being connected in series and the output shaft being connected with the middle flap by a track.
Further, the power driving apparatus 109 includes a first motor 114, a second motor 115, a gear box 118, an outside brake module 112 and an inside brake module 117, wherein the first motor 114 is connected with the gear box 118, and the second motor 115 is connected with the gear box 118; the left end of the gear box 118 is connected to the outboard brake module 112 and the right end of the gear box 118 is connected to the inboard brake module 117.
The invention has the beneficial effects that: the invention relates to a distributed drive configuration in which a power drive device is arranged on each of transmission lines between left and right inner and outer flaps, and the configuration eliminates the transmission line system for connecting the left and right drive systems and reduces the number of the drive devices from 3 to 2, thereby reducing the number of parts of a high lift system and simplifying the configuration of the high lift system. Meanwhile, the distributed driving configuration enlarges the range of deflection angles between the inner flap and the outer flap; the number of the power driving devices of each side wing surface is reduced to 1, and meanwhile, the transmission line system of the inner flap and the outer flap is not disconnected, so that the movement consistency of the inner flap and the outer flap of the single side wing surface is ensured.
After the drive lines of the left wing surface and the right wing surface are disconnected, the deflection angle of the outer flap of the invention is larger than that of the reference patent 1. By the differential function of the power driving device, the left and right outer side flaps can be controlled to deflect a larger angle up and down, and the airplane roll maneuvering function can be completely realized by replacing ailerons.
Drawings
FIG. 1 is a schematic diagram of a central centralized drive architecture according to the prior art;
the wing control system comprises a power driving device 1, a power driving device 2, a first actuator 3, a second actuator 4, a third actuator 5, a fourth actuator 6, a wing tip braking device 7, a track 8, a wing tip position sensor 9, an outer flap 10, an inner flap 11, a wing 12, a motor 13, a gear box 14, a power-down braking device 15, a motor 16, a power-down braking device 17, a torsion bar 18, an aileron 19, a wing 20, an inner flap 21, an outer flap 22, an aileron 23 and a slat control computer
FIG. 2 is a schematic illustration of a flap distributed drive system according to an embodiment of the invention;
101, an inner side position sensor 102, a first actuator 103, an inner side wing tip braking device 104, a second actuator 105, a third actuator 106, an outer side wing tip braking device 107, a fourth actuator 108, an outer side position sensor 109, a power driving device 110, a left inner flap 111, a left outer flap 112, an outer side braking module 113, a left driving system 114, a first motor 115, a second motor 116, a right driving system 117, an inner side braking module 118, a gear box 119, a left wing 120, a right wing 121, a right inner flap 122, a right outer flap 123, a slat control computer
Detailed Description
The invention provides a flap distributed driving system, namely a driving device is respectively arranged between transmission line systems between inner flaps and outer flaps of left and right wing surfaces, and a traditional centralized power driving device 1 and a transmission line system 17 connected with left and right driving mechanisms are eliminated.
The invention provides a flap distributed drive system, as shown in FIG. 2, comprising: a left drive system 113, a right drive system 116, and a slat control computer 123, wherein the left drive system 113 and the right drive system 116 are respectively controlled by the slat control computer 123.
Further, the left driving system and the right driving system each include an inner side position sensor 101, a first actuator 102, an inner side wing tip braking device 103, a second actuator 104, a third actuator 105, an outer side wing tip braking device 106, a fourth actuator 107, an outer side position sensor 108, and a power driving device 109, wherein a left end output shaft of the power driving device 109 is fixedly connected with a right end input shaft of the third actuator 105 through a spline, a right end output shaft of the power driving device 109 is fixedly connected with a left end input shaft of the second actuator 104 through a spline, and the power driving device 109 is controlled by a slat control computer 123; the left input shaft of the third actuator 105 is fixedly connected with the right input shaft of the outer wing tip braking device 106 through a spline, and the output shaft of the third actuator 105 is connected with the outer flap 111 through a track; the left input shaft of the outboard wingtip braking device 106 is fixedly connected with the right input shaft of the fourth actuator 107 through a spline; the output shaft of the fourth actuator 107 is connected with the outer flap 111 through a track; the outer side position sensor 108 is fixedly connected to the fourth actuator 107 through a flange plate and a spline, and a position signal of the outer side position sensor 108 is fed back to the slat control computer 123; the right input shaft of the second actuator is fixedly connected with the left input shaft of the inner wingtip braking device through a spline, and the output shaft of the second actuator is connected with the inner flap through a track; the right input shaft of the inboard wingtip braking device is fixedly connected with the left input shaft of the first actuator through a spline; the output shaft of the first actuator is connected with the inner flap through a track; the inner side position sensor is fixedly connected with the first actuator through a flange plate and a spline, and a position signal of the inner side position sensor is fed back to the slat control computer.
Further, N actuators are further included between the third actuator and the outboard wing tip braking device, wherein N is a positive integer, the N actuators are connected in series, and the output shaft and the outboard wing are connected through a rail.
Further, N actuators are further included between the third actuator and the outboard wing tip braking device, wherein N is a positive integer, the N actuators are connected in series, and the output shaft and the inner flap are connected through a rail.
Further, the left driving system and the right driving system respectively comprise an inner side position sensor 101, a first actuator 102, a second actuator 104, a third actuator 105, a fourth actuator 107, an outer side position sensor 108 and a power driving device 109, wherein the first actuator 102, the second actuator 104, the third actuator 105 and the fourth actuator 107 are respectively provided with a non-return mechanism, a left end output shaft of the power driving device 109 is fixedly connected with a right end input shaft of the third actuator 105 through a spline, a right end output shaft of the power driving device 109 is fixedly connected with a left end input shaft of the second actuator 104 through a spline, and the power driving device 109 is controlled by a slat control computer 123; a left input shaft of the third actuator 105 and a right input shaft of the fourth actuator 107 are fixedly connected through splines, and an output shaft of the third actuator 105 is connected with the outer flap 111 through a track; the output shaft of the fourth actuator 107 is connected with the outer flap 111 through a track; the outer side position sensor 108 is fixedly connected to the fourth actuator 107 through a flange plate, and a position signal of the outer side position sensor 108 is fed back to the slat control computer 123; the right input shaft of the second actuator is fixedly connected with the left input shaft of the first actuator through a spline, and the output shaft of the second actuator is connected with the inner flap through a track; the output shaft of the first actuator is connected with the inner flap through a track; the inner side position sensor is fixedly connected with the first actuator through a flange plate, and a position signal of the inner side position sensor is fed back to the slat control computer.
Further, under the condition that the flap comprises the middle flap, the left driving system and the right driving system respectively comprise a fifth actuator and a sixth actuator, the fifth actuator and the sixth actuator are connected in series between an output shaft of the power driving device and the second actuator or between an output shaft of the power driving device and the third actuator, and output shafts of the fifth actuator and the sixth actuator are respectively connected with the middle flap through tracks.
Further, in the case where the flap comprises a middle flap, the left and right drive systems further comprise N actuators, where N is a positive integer, the N actuators being connected in series and the output shaft being connected with the middle flap by a track.
Further, the power driving apparatus 109 includes a first motor 114, a second motor 115, a gear box 118, an outside brake module 112 and an inside brake module 117, wherein the first motor 114 is connected with the gear box 118, and the second motor 115 is connected with the gear box 118; the left end of the gear box 118 is connected to the outboard brake module 112 and the right end of the gear box 118 is connected to the inboard brake module 117.
Example (b):
a flap distributed drive system. The system includes a left drive system 113, a right drive system 116, a slat control computer 123, a left wing 119, a right wing 120, a left inner flap 110 and a left outer flap 111, a right inner flap 121 and a right outer flap 122.
The left drive system 113 includes: a third actuator 105, an outboard tip brake device 106, a fourth actuator 107, an outboard position sensor 108, a power drive device 109, a second actuator 104, an inboard tip brake device 103, a first actuator 102, and an inboard position sensor 101.
The power drive 109 includes a first motor 114, a second motor 115, a gear box 118, an outboard brake module 112, and an inboard brake module 117.
The first motor 114 and the gear box 118 are fixedly connected through a spline shaft, and the second motor 115 and the gear box 118 are fixedly connected through a spline shaft; the left end of the gear box 118 is fixedly connected with the outer brake module 112 through a spline shaft, and the right end of the gear box is fixedly connected with the inner brake module 117 through a spline shaft.
A left end output shaft of the power driving device 109 is fixedly connected with a right end input shaft of the third actuator 105 through a spline, a right end output shaft is fixedly connected with a left end input shaft of the second actuator 104 through a spline, and a first motor and a second motor of the power driving device 109 are respectively controlled by a slat control computer 123; the left input shaft of the third actuator 105 is fixedly connected with the right input shaft of the outer wing tip braking device 106 through a spline, and the output shaft is connected with the outer flap 111 through a track; the left input shaft of the outboard wingtip braking device 106 is fixedly connected with the right input shaft of the fourth actuator 107 through a spline; the output shaft of the fourth actuator 107 is connected with the outer flap 111 through a track; the outboard position sensor 108 is fixedly connected to the fourth actuator 107 via a flange, and a position signal of the outboard position sensor 108 is fed back to the slat control computer 123.
The right input shaft of the second actuator 104 is fixedly connected with the left input shaft of the inboard wingtip braking device 103 through a spline, and the output shaft of the second actuator 104 is connected with the left inboard flap 110 through a track; the right input shaft of the inboard wingtip braking device 103 is fixedly connected with the left input shaft of the first actuator 102 through a spline; the output shaft of the first actuator 102 is connected with the left inner flap 110 through a track; the inner side position sensor 101 is fixedly connected to the first actuator 102 through a flange, and a position signal of the inner side position sensor 101 is fed back to the slat control computer 123.
The right drive system 116 is identical in configuration to the left drive system 113.
When the flaps perform a synchronous extension or retraction function: the outboard wing tip brake device 106 and the inboard wing tip brake device 103 are both in a brake release state, the inboard brake module 117 and the outboard brake module 112 are both in a brake state, the slat control computer 123 is used for controlling the first motor 114 and the second motor 115, the output torque and the rotational speed of the first motor 114 are transmitted to the gear box 118, the output torque and the rotational speed of the second motor 115 are transmitted to the gear box 118, the gear box 118 transmits the integrated torque and the rotational speed to the third actuator 105 and the fourth actuator 107 through a left-end output shaft, meanwhile, the integrated torque and the rotation speed are transmitted to the first actuator 102 and the second actuator 104 through a right output shaft, the third actuator 105 and the fourth actuator 107 drive the left outer flap 111 through a track, and the first actuator 102 and the second actuator 104 drive the left inner flap 110 through a track, so that the extending or retracting functions of the left outer flap 111 and the left inner flap 110 are realized. The outboard position sensor 108 monitors the yaw angle of the left outboard flap 111 and feeds back the monitored angle to the slat control computer 123, and the inboard position sensor 101 monitors the yaw angle of the left inboard flap 110 and feeds back the monitored angle to the slat control computer 123.
The right side flaps 121, 122 are extended or retracted on the same principle as the left side flaps 110, 111.
When the left inner flap 110 performs a differential function with respect to the left outer flap 111: both the inboard tip brake 103 and the outboard brake module 112 are in a released state, and the outboard tip brake 106 and the inboard brake module 117 are in a braked state. The slat control computer 123 is used for controlling the first motor 114 and the second motor 115, the output torque and the rotational speed of the first motor 114 are transmitted to the gear box 118, the output torque and the rotational speed of the second motor 115 are transmitted to the gear box 118, the gear box 118 transmits the integrated torque and rotational speed to the first actuator 102 and the second actuator 104 through a right output shaft, the first actuator 102 and the second actuator 104 drive the left inner flap 110, and the differential function of the left inner flap 110 relative to the left outer flap 111 is realized. The outboard position sensor 108 monitors the yaw angle of the left outboard flap 111 and feeds back the monitored angle to the slat control computer 123, and the inboard position sensor 101 monitors the yaw angle of the left inboard flap 110 and feeds back the monitored angle to the slat control computer 123.
When the left outer flap 111 performs a differential function with respect to the left inner flap 110: both the outboard wing tip brake 106 and the inboard brake module 117 are in a released state and the inboard wing tip brake 103 and the outboard brake module 112 are in a braked state. The slat control computer 123 is used for controlling the first motor 114 and the second motor 115, the output torque and the rotational speed of the first motor 114 are transmitted to the gear box 118, the output torque and the rotational speed of the second motor 115 are transmitted to the gear box 118, the gear box 118 transmits the integrated torque and rotational speed to the third actuator 105 and the fourth actuator 107 through a left output shaft, and the third actuator 105 and the fourth actuator 107 drive the left outer flap 111 to realize the differential function of the left outer flap 111 relative to the left inner flap 110. The outboard position sensor 108 monitors the yaw angle of the left outboard flap 111 and feeds back the monitored angle to the slat control computer 123, and the inboard position sensor 101 monitors the yaw angle of the inner flap 110 and feeds back the monitored angle to the slat control computer 123.
The left outer flap (111) and the right outer flap (122) are simultaneously differential to realize the function of the roll control of the aileron.
Claims (8)
1. A flap distributed drive system, comprising: the driving system comprises a left driving system (113), a right driving system (116) and a slat control computer (123), wherein the left driving system (113) and the right driving system (116) are respectively controlled by the slat control computer (123).
2. The system according to claim 1, wherein each of the left and right drive systems comprises an inboard position sensor (101), a first actuator (102), an inboard wing tip brake device (103), a second actuator (104), a third actuator (105), an outboard wing tip brake device (106), a fourth actuator (107), an outboard position sensor (108), and a power drive device (109), wherein a left end output shaft of the power drive device (109) is fixedly coupled with a right end input shaft of the third actuator (105) by a spline, a right end output shaft of the power drive device (109) is fixedly coupled with a left end input shaft of the second actuator (104) by a spline, and the power drive device (109) is controlled by a slat control computer (123); a left input shaft of the third actuator (105) is fixedly connected with a right input shaft of the outboard wingtip braking device (106) through a spline, and an output shaft of the third actuator (105) is connected with the outboard flap (111) through a track; the left input shaft of the outboard wingtip braking device (106) is fixedly connected with the right input shaft of the fourth actuator (107) through a spline; the output shaft of the fourth actuator (107) is connected with the outer flap (111) through a track; the outer side position sensor (108) is fixedly connected to the fourth actuator (107) through a flange plate and a spline, and a position signal of the outer side position sensor (108) is fed back to the slat control computer (123); the right input shaft of the second actuator (104) is fixedly connected with the left input shaft of the inner wingtip braking device (103) through a spline, and the output shaft of the second actuator (104) is connected with the inner flap through a track; the right input shaft of the inboard wingtip braking device (103) is fixedly connected with the left input shaft of the first actuator (102) through a spline; the output shaft of the first actuator (102) is connected with the inner flap through a track; the inner side position sensor (101) is fixedly connected to the first actuator (102) through a flange plate and a spline, and a position signal of the inner side position sensor (101) is fed back to the slat control computer (123).
3. A system according to claim 2, further comprising N actuators between the third actuator (105) and the outboard wingtip brake device (106), where N is a positive integer, the N actuators being connected in series and the output shaft being connected to the outboard flap by a track.
4. The system according to claim 2, further comprising N actuators between the third actuator (105) and the outboard wingtip brake device (106), where N is a positive integer, the N actuators being connected in series and the output shaft being connected to the inner flap by a track.
5. The system according to claim 1, characterized in that the left and right drive systems each comprise an inner position sensor (101), a first actuator (102), a second actuator (104), a third actuator (105), a fourth actuator (107), an outer position sensor (108), a power drive (109), wherein the first actuator (102), the second actuator (104), the third actuator (105) and the fourth actuator (107) are each provided with a non-return mechanism,
a left end output shaft of the power driving device (109) is fixedly connected with a right end input shaft of the third actuator (105) through a spline, a right end output shaft of the power driving device (109) is fixedly connected with a left end input shaft of the second actuator (104) through a spline, and the power driving device (109) is controlled by a slat control computer (123); a left input shaft of the third actuator (105) is fixedly connected with a right input shaft of the fourth actuator (107) through a spline, and an output shaft of the third actuator (105) is connected with the outer flap (111) through a track; the output shaft of the fourth actuator (107) is connected with the outer flap (111) through a track; the outer side position sensor (108) is fixedly connected with the fourth actuator (107) through a flange plate, and a position signal of the outer side position sensor (108) is fed back to the slat control computer (123); the right input shaft of the second actuator (104) is fixedly connected with the left input shaft of the first actuator (102) through a spline, and the output shaft of the second actuator (104) is connected with the inner flap through a track; the output shaft of the first actuator (102) is connected with the inner flap through a track; the inner side position sensor (101) is fixedly connected with the first actuator (102) through a flange plate, and a position signal of the inner side position sensor (101) is fed back to the slat control computer (123).
6. System according to claim 2 or 5, characterized in that, in the case of flaps comprising a central flap, the left and right drive systems each further comprise a fifth and a sixth actuator, which are connected in series between the output shaft of the power drive and the second actuator or the output shaft of the power drive and the third actuator (105), the output shafts of the fifth and sixth actuators being connected to the central flap by rails, respectively.
7. The system of claim 6, wherein, where the flap comprises a center flap, the left and right drive systems further comprise N actuators, where N is a positive integer, the N actuators being connected in series and the output shaft being connected to the center flap by a track.
8. System according to claim 2 or 5, characterized in that the power drive (109) comprises a first motor (114), a second motor (115), a gearbox (118), an outboard brake module (112) and an inboard brake module (117), wherein the first motor (114) is connected to the gearbox (118) and the second motor (115) is connected to the gearbox (118); the left end of the gear box (118) is connected with the outer side brake module (112), and the right end of the gear box (118) is connected with the inner side brake module (117).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010362850.1A CN111516857A (en) | 2020-04-30 | 2020-04-30 | Flap distributed driving system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010362850.1A CN111516857A (en) | 2020-04-30 | 2020-04-30 | Flap distributed driving system |
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| CN111516857A true CN111516857A (en) | 2020-08-11 |
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| CN202010362850.1A Pending CN111516857A (en) | 2020-04-30 | 2020-04-30 | Flap distributed driving system |
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|---|---|---|---|---|
| US20040200928A1 (en) * | 2003-04-14 | 2004-10-14 | Arthur Degenholtz | Actuator and flap arrangement with actuator interconnection |
| CN102046467A (en) * | 2008-05-05 | 2011-05-04 | 空中客车营运有限公司 | Error tolerant adjustment system for adjusting servo tabs of an aircraft, comprising a control mechanism with a fixed rotational axis |
| CN103153791A (en) * | 2010-10-05 | 2013-06-12 | 空中客车德国运营有限责任公司 | High lift system for an aircraft with a separate drive unit for each wing half |
| FR2997922A1 (en) * | 2012-11-14 | 2014-05-16 | Liebherr Aerospace Gmbh | DEVICE FOR ADJUSTING SHUTTERS OF AIRCRAFT SURFACES |
| US20150083852A1 (en) * | 2013-09-24 | 2015-03-26 | The Boeing Company | Variable camber flap system and method |
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2020
- 2020-04-30 CN CN202010362850.1A patent/CN111516857A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040200928A1 (en) * | 2003-04-14 | 2004-10-14 | Arthur Degenholtz | Actuator and flap arrangement with actuator interconnection |
| CN102046467A (en) * | 2008-05-05 | 2011-05-04 | 空中客车营运有限公司 | Error tolerant adjustment system for adjusting servo tabs of an aircraft, comprising a control mechanism with a fixed rotational axis |
| CN103153791A (en) * | 2010-10-05 | 2013-06-12 | 空中客车德国运营有限责任公司 | High lift system for an aircraft with a separate drive unit for each wing half |
| FR2997922A1 (en) * | 2012-11-14 | 2014-05-16 | Liebherr Aerospace Gmbh | DEVICE FOR ADJUSTING SHUTTERS OF AIRCRAFT SURFACES |
| US20150083852A1 (en) * | 2013-09-24 | 2015-03-26 | The Boeing Company | Variable camber flap system and method |
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