CN111017197A - Servo actuating device for differential rudder of airplane - Google Patents
Servo actuating device for differential rudder of airplane Download PDFInfo
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- CN111017197A CN111017197A CN201911144754.3A CN201911144754A CN111017197A CN 111017197 A CN111017197 A CN 111017197A CN 201911144754 A CN201911144754 A CN 201911144754A CN 111017197 A CN111017197 A CN 111017197A
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- steering engine
- direction steering
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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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Abstract
The invention discloses a servo actuating device for a differential rudder of an airplane, and belongs to the field of servo steering engine control. The aircraft comprises resistance rudders, a transmission assembly, resistance direction steering engines, a steering engine controller and an aircraft management computer, wherein the resistance rudders are symmetrically arranged on wings at two sides of an aircraft, and two resistance rudders which are arranged in parallel are arranged on the wings at each side; the transmission assemblies are respectively arranged corresponding to each resistance rudder, and the resistance rudder is respectively arranged corresponding to each transmission assembly; the transmission assembly comprises a coupler and a bush, the coupler and the bush are connected and fixed with each other through keys, the bush is fixedly connected with a control surface rotating shaft of a corresponding resistance rudder through a flange, and a rudder end of the coupler is coaxially connected with a corresponding resistance direction steering engine. The device adopts a differential rudder layout, is suitable for a light and thin wing aircraft, adopts a coaxial transmission assembly for actuation control, simplifies a transmission mechanism and realizes precise transmission.
Description
Technical Field
The invention relates to the field of servo steering engine control, in particular to a differential rudder servo actuating device of an airplane.
Background
The servo device of the airplane is an indispensable component in an automatic flight control system and is mainly used for controlling a control surface according to an electric signal output by an instruction model device or a sensitive component so as to realize stability augmentation and control of airplane angular motion or track motion. The main energy sources of the existing airplane servo devices comprise a pneumatic servo device, a hydraulic servo device and an electric servo device, wherein the pneumatic servo device and the hydraulic servo device are widely applied to traditional airplanes and missiles.
In the flying wing layout, the outer side of the aircraft wing is provided with a resistance rudder, and more specifically, the resistance rudder is generally arranged at the trailing edge of the wing and at the outer side of an elevon. The differential deflection of the resistance rudder can provide extra resistance to generate yawing moment, thereby achieving the effects of course stability augmentation and resistance augmentation. The conventional unmanned aerial vehicle flying wing layout adopts a wing body fusion technology, and a vertical tail and a horizontal tail are eliminated, so that the aerodynamic performance and the stealth performance are greatly improved, but the horizontal course stability is poor, a servo system is required to have the characteristics of high frequency response and small gap in the flight control stability augmentation control process, and higher requirements are provided for the performance of the servo system.
For solving the unstable problem of unmanned aerial vehicle lateral course, as the publication number is CN204775999U among the prior art, the publication number is 11 months 18 days 2015 year, the name is the chinese utility model patent of "aircraft formula rudder servo system of actuating", its technical scheme is: a servo actuating system for a split rudder of an airplane aims to solve the problem that an existing servo control system cannot meet the actuating requirement of the split resistance rudder. The servo actuating system of the airplane cracking type rudder comprises an aircraft management computer, a servo controller, a resistance direction steering engine, an actuating cylinder assembly and the like, and is used for independently controlling four resistance rudders which are arranged on the upper left, the lower left, the upper right and the lower right.
Although the problem that the horizontal course of the unmanned aerial vehicle with the tailless flying wing layout is unstable is well solved, the upper and lower two split control surfaces are required to be arranged at the same position of the control surfaces of the split resistance rudder, and are split upwards and downwards respectively, so that the air resistance is increased. However, the light and thin wing requires the thickness of the control surface to be only half of the thickness of the wing surface by adopting the layout mode, and the rigidity requirement of the control surface design is difficult to ensure. Therefore, the application designs a differential rudder servo actuating device suitable for light and thin wings.
Disclosure of Invention
The invention aims to solve the problem that a cracking type rudder in the prior art cannot be suitable for a light and thin wing, and provides an airplane differential type rudder servo actuating device suitable for the light and thin wing.
In order to achieve the above object, the technical solution of the present invention is as follows:
the utility model provides a servo device of actuating of aircraft differential type rudder, includes resistance rudder, drive assembly, is used for controlling drive assembly's resistance direction steering wheel, is used for controlling the steering wheel controller of resistance direction steering wheel and is used for controlling servo controller's aircraft management computer, its characterized in that: the resistance rudders are symmetrically arranged on wings at two sides of the airplane, and two resistance rudders which are arranged in parallel are arranged on each wing; the transmission assemblies are respectively arranged corresponding to each resistance rudder, and the resistance rudder is respectively arranged corresponding to each transmission assembly; the transmission assembly comprises a coupler and a bush, the coupler and the bush are connected and fixed with each other through keys, the bush is fixedly connected with a control surface rotating shaft of a corresponding resistance rudder through a flange, and a rudder end of the coupler is coaxially connected with a corresponding resistance direction steering engine.
Furthermore, all be equipped with angle displacement potentiometer sensor on the resistance direction steering wheel, resistance direction steering wheel and angle displacement potentiometer sensor all with steering wheel controller electric connection.
Furthermore, the steering engine controller is powered by an electric device and is connected with the aircraft management computer through a bus.
Further, the resistance direction steering engine is a harmonic reducer electric steering engine.
The invention has the beneficial effects that:
1. the differential rudder layout adopted by the invention is suitable for light and thin wing type small and medium sized airplanes, two control surfaces which are arranged in parallel on the outer wing of the airplane are respectively deflected upwards and downwards in a differential mode, the aerodynamic resistance is increased, and the rigidity of the control surfaces can be effectively ensured;
2. the power of the resistance direction steering engine is transmitted to the resistance direction rudder by the transmission assembly so as to drive the control surface to rotate; the transmission assembly comprises a coupler and a bushing, the coupler is in key connection with the bushing, the bushing is in flange connection with a corresponding resistance rudder control surface, the steering gear end of the coupler is connected with a corresponding electric steering gear in a coaxial mode, the connection mode simplifies a transmission mechanism, precise transmission is achieved, meanwhile, the transmission assembly has certain resistance to structural deformation of the rudder control surface, skin bulging can be effectively reduced, and transmission precision is guaranteed.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the differential resistance rudder according to the present invention;
FIG. 3 is a schematic view of the drive form of the drive assembly of the present invention;
wherein the content of the first and second substances,
1. aircraft management computer, 2, steering engine controller, 21, left steering engine controller, 22, right steering engine controller, 3, resistance direction steering engine, 31, left outer resistance direction steering engine, 32, left inner resistance direction steering engine, 33, right inner resistance direction steering engine, 34, right outer resistance direction steering engine, 4, transmission assembly, 41, left outer transmission assembly, 42, left inner transmission assembly, 43, right inner transmission assembly, 44, right outer transmission assembly, 5, resistance direction rudder, 51, left outer resistance direction rudder, 52, left inner resistance direction rudder, 53, right inner resistance direction rudder, 54, right outer resistance direction rudder, 6, electrical device.
Detailed Description
The present invention will be described in further detail with reference to examples, but the embodiments of the present invention are not limited thereto.
The embodiment provides a differential rudder servo actuating device of an airplane as shown in fig. 1, which is used for solving the problem that the traditional cracking type servo actuating device cannot be applied to small and medium-sized airplanes with light and thin wing profiles. The differential rudder servo actuating device specifically comprises a resistance rudder 5, a transmission component 4, a resistance direction steering engine 3 for controlling the transmission component 4, a steering engine controller 2 for controlling the resistance direction steering engine 3 and an aircraft management computer 1 for controlling the servo controller.
As shown in fig. 2, the resistance rudders 5 are symmetrically arranged on two wings of the airplane, and each wing is provided with two resistance rudders 5 arranged in parallel, namely a left outer resistance rudder 51, a left inner resistance rudder 52, a right outer resistance rudder 54 and a right inner resistance rudder 53.
As shown in fig. 1, the transmission assemblies 4 are respectively arranged corresponding to each resistance rudder 5 and are divided into a left inner transmission assembly 42, a left outer transmission assembly 41, a right inner transmission assembly 43 and a right outer transmission assembly 44; the resistance direction steering engines 3 are respectively arranged corresponding to each transmission component 4 and are divided into a left outer resistance direction steering engine 31, a left inner resistance direction steering engine 32, a right outer resistance direction steering engine 34 and a right inner resistance direction steering engine 33.
As shown in figure 3, the invention adopts the transmission assembly 4 to transmit the power of the resistance direction steering engine 3 to the resistance direction rudder 5 so as to drive the control surface of the resistance direction rudder 5 to rotate. The transmission assembly 4 comprises a coupler and a bush, the coupler and the bush are fixed with each other by key connection, the bush is fixedly connected with a control surface rotating shaft of the corresponding resistance rudder 5 by a flange, a rudder end of the coupler is coaxially connected with the corresponding resistance direction steering engine 3, and a dotted line in the figure 3 represents a rotating center; and each resistance direction steering engine 3 is provided with an angular displacement potentiometer sensor, and the angular displacement potentiometer sensors are used for feeding back the shaft angular displacement output by the resistance direction steering engines 3 to the corresponding steering engine controllers 2 to form a control closed loop. The transmission assembly 4 adopts a coaxial installation form, simplifies a transmission mechanism, realizes precise transmission under the coordination with an angular displacement potentiometer sensor, and meanwhile, the transmission assembly 4 has certain capacity of resisting structural deformation of a control surface, so that the phenomenon of skin bulging can be effectively reduced, and the transmission precision is ensured.
The resistance direction steering engine 3 is selected according to requirements, for example, the maximum output torque of the resistance direction steering engine 3 is calculated according to the hinge torque of the control surface of the resistance direction steering engine 5, an empirical formula and a corresponding mechanical formula, the maximum stroke and frequency response of the resistance direction steering engine 3 are calculated according to the use requirement of the control surface, and the parameters of the resistance electric steering engine are designed according to the maximum stroke and frequency response. Preferably, the resistance direction steering engine 3 is a harmonic reducer electric steering engine which adopts electric single redundancy and has a system fault power-off loosening and floating function.
As shown in fig. 1, the steering engine controller 2 includes a left steering engine controller 21 and a right steering engine controller 22, the left steering engine controller 21 is used for controlling a left outer resistance direction steering engine 31 and a left inner direction steering engine, and the right steering engine controller 22 is used for controlling the left outer resistance direction steering engine 31 and the left inner direction steering engine; the left steering engine controller 21 and the right steering engine controller 22 are powered by the electric device 6, the left steering engine controller 21 and the right steering engine controller 22 are connected with the aircraft management computer 1 through buses, receive steering engine instruction values of the aircraft management computer 1, control and drive the corresponding resistance direction steering engines 3 to rotate, and monitor the working states of the resistance direction steering engines 3.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (4)
1. The utility model provides a servo device of actuating of aircraft differential rudder, includes resistance rudder (5), drive assembly (4), is used for controlling resistance direction steering wheel (3) of drive assembly (4), is used for controlling steering wheel controller (2) of resistance direction steering wheel (3) and is used for controlling servo controller's aircraft management computer (1), its characterized in that: the resistance rudders (5) are symmetrically arranged on wings at two sides of the airplane, and two resistance rudders (5) which are arranged in parallel are arranged on each wing; the transmission assemblies (4) are respectively arranged corresponding to each resistance rudder (5), and the resistance direction steering engines (3) are respectively arranged corresponding to each transmission assembly (4); the transmission assembly (4) comprises a coupler and a bushing, the coupler and the bushing are connected and fixed with each other in a key mode, the bushing is fixedly connected with a control surface rotating shaft of the corresponding resistance rudder (5) in a flange mode, and the end of the rudder of the coupler is coaxially connected with the corresponding resistance direction steering engine (3).
2. A differential rudder servo actuator as claimed in claim 1 wherein: and the resistance direction steering engine (3) is provided with an angular displacement potentiometer sensor, and the resistance direction steering engine (3) and the angular displacement potentiometer sensor are electrically connected with the steering engine controller (2).
3. A differential rudder servo actuator as claimed in claim 2 wherein: the steering engine controller (2) is powered by an electric device (6), and the steering engine controller (2) is connected with the aircraft management computer (1) through a bus.
4. A differential rudder servo actuator as claimed in claim 3 wherein: the resistance direction steering engine (3) is a harmonic reducer electric steering engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911144754.3A CN111017197A (en) | 2019-11-21 | 2019-11-21 | Servo actuating device for differential rudder of airplane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911144754.3A CN111017197A (en) | 2019-11-21 | 2019-11-21 | Servo actuating device for differential rudder of airplane |
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| Publication Number | Publication Date |
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| CN111017197A true CN111017197A (en) | 2020-04-17 |
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| CN201911144754.3A Pending CN111017197A (en) | 2019-11-21 | 2019-11-21 | Servo actuating device for differential rudder of airplane |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184166A (en) * | 2021-03-31 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Stability augmentation control method for flying wing layout unmanned aerial vehicle |
| CN115783241A (en) * | 2023-02-08 | 2023-03-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Asynchronous deflection course control combined rudder control method of fusion body aircraft |
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| CN102126559A (en) * | 2010-01-18 | 2011-07-20 | 空中巴士营运公司 | Flight control system for an aircraft |
| US20150129715A1 (en) * | 2013-04-03 | 2015-05-14 | The Boeing Company | Shape Memory Alloy Rods for Actuation of Continuous Surfaces |
| CN204399465U (en) * | 2015-01-14 | 2015-06-17 | 西北工业大学 | A kind of anury all-wing aircraft many controlsurfaces unmanned plane |
| CN204775999U (en) * | 2015-04-13 | 2015-11-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Servo system of actuating of aircraft fracture formula rudder |
| CN105083537A (en) * | 2015-08-05 | 2015-11-25 | 北京韦加航通科技有限责任公司 | Control surface control device and aircraft |
| CN205998116U (en) * | 2016-09-06 | 2017-03-08 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of Flying-wing's aircraft flight gesture stability structure |
| CN107472511A (en) * | 2017-08-03 | 2017-12-15 | 北京航空航天大学 | The pneumatic rudder face of the Flying-wing's aircraft coordinated based on spoiler and trailing edge rudder face |
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2019
- 2019-11-21 CN CN201911144754.3A patent/CN111017197A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2454255A1 (en) * | 2001-08-14 | 2003-02-27 | Northrop Grumman Corporation | System and method for controlling an aircraft |
| CN102126559A (en) * | 2010-01-18 | 2011-07-20 | 空中巴士营运公司 | Flight control system for an aircraft |
| US20150129715A1 (en) * | 2013-04-03 | 2015-05-14 | The Boeing Company | Shape Memory Alloy Rods for Actuation of Continuous Surfaces |
| CN204399465U (en) * | 2015-01-14 | 2015-06-17 | 西北工业大学 | A kind of anury all-wing aircraft many controlsurfaces unmanned plane |
| CN204775999U (en) * | 2015-04-13 | 2015-11-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Servo system of actuating of aircraft fracture formula rudder |
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| CN107472511A (en) * | 2017-08-03 | 2017-12-15 | 北京航空航天大学 | The pneumatic rudder face of the Flying-wing's aircraft coordinated based on spoiler and trailing edge rudder face |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184166A (en) * | 2021-03-31 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Stability augmentation control method for flying wing layout unmanned aerial vehicle |
| CN115783241A (en) * | 2023-02-08 | 2023-03-14 | 中国空气动力研究与发展中心计算空气动力研究所 | Asynchronous deflection course control combined rudder control method of fusion body aircraft |
| CN115783241B (en) * | 2023-02-08 | 2023-05-16 | 中国空气动力研究与发展中心计算空气动力研究所 | Asynchronous deflection course control combined rudder control method of fusion aircraft |
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Application publication date: 20200417 |
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