CN109987219B - Flat type integrated composite rudder system - Google Patents
Flat type integrated composite rudder system Download PDFInfo
- Publication number
- CN109987219B CN109987219B CN201910224020.XA CN201910224020A CN109987219B CN 109987219 B CN109987219 B CN 109987219B CN 201910224020 A CN201910224020 A CN 201910224020A CN 109987219 B CN109987219 B CN 109987219B
- Authority
- CN
- China
- Prior art keywords
- rudder system
- rocker arm
- ball nut
- connecting rod
- ball
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
Abstract
The invention discloses a flat type integrated composite rudder system, which comprises a base body, a motor, a gear reducer, a composite screw assembly and a rocker arm assembly, wherein the motor, the gear reducer, the composite screw assembly and the rocker arm assembly are jointly installed on the base body; the rocker arm assembly comprises a connecting rod, a sliding block II and a rocker arm. The flat integrated composite rudder system realizes the integrated design of the rudder system and the wings, thereby realizing the aims of reducing the system quality, improving the transmission precision, improving the installation precision, improving the output torque and the like.
Description
Technical Field
The invention belongs to the technical field of servo systems, and particularly relates to a flat type integrated composite rudder system.
Background
In recent years, with the continuous progress of modern technology level, servo systems are being developed toward miniaturization, long-life, high-efficiency, maintenance-free design. The research on the technologies of big airplanes, unmanned planes, cruise guidance missiles and the like in China has become one of the current hotspots. Because the flat type ailerons are arranged, the internal space path is distributed flatly, and the functional layout of the system is difficult. Therefore, the flat rotary rudder system integrally designed with the exoskeleton frame is produced, and compared with the traditional electric rudder system, the volume and the mass of the system are greatly reduced on the basis of ensuring various performances of wing and steering engine structures. From the perspective of the system, it has more excellent dynamic output characteristics, electric power characteristics and control performance, and is one of the major development trends in the industry at present.
The rudder system is an executive function component for realizing rudder sheet deflection in the flying process of an aircraft, the traditional rudder system is limited by a transmission mode, large torque is difficult to output in a flat narrow space, and if the output torque is increased in a multi-stage transmission mode, system errors are increased too much in a transmission link, so that the precision of the rudder system is influenced. If the mode through improving certain link speed reduction ratio is adopted, there are the demand installation space big, the steering wheel quality increase scheduling problem, to realizing equipment miniaturization formation restrictions such as unmanned aerial vehicle, cruise guidance guided missile.
Disclosure of Invention
Aiming at the defects or improvement requirements in the prior art, the invention provides a flat integrated composite rudder system, which aims to realize the integrated design of a rudder system and a wing through a composite lead screw technology, thereby realizing the aims of reducing the system quality, improving the transmission precision, improving the installation precision, improving the output torque and the like.
In order to achieve the above object, according to one aspect of the present invention, there is provided a flat type integrated compound rudder system, comprising a base body, and a motor, a gear reducer, a compound screw assembly, an anti-rotation guide rail and a rocker arm assembly which are commonly mounted on the base body, wherein,
the composite screw assembly comprises a ball screw I, a ball nut I, a ball screw II and a ball nut II, wherein the ball screw I and the ball screw II are parallel to each other, the ball screw I is connected with the motor through the gear reducer, the ball nut I is installed on the ball screw I, the ball nut I and the ball nut II are fixedly connected together, a slide block I is arranged on the ball nut I, and the slide block I is installed on the anti-rotation guide rail;
the rocker arm assembly comprises a connecting rod, a sliding block II and a rocker arm, one end of the connecting rod is mounted on the ball screw II, the other end of the connecting rod is hollow, the sliding block II extends into the inner part of one end, far away from the ball screw II, of the connecting rod and can move longitudinally along the connecting rod, and the rocker arm is mounted on the sliding block II.
Preferably, a linear sensor is mounted on the ball nut II for obtaining position information of the ball nut II.
Preferably, the position information is fed back to a card-inserted control board of the controller through an electric signal, so that the position closed-loop control of the ball nut II is realized, and the closed-loop control of the position of the compound rudder system is realized.
Preferably, the linear sensor is a non-contact potentiometer.
Preferably, the gear reducer comprises an input gear, an intermediate gear and an output gear, the input gear is connected with a motor shaft of the motor, and the input gear is connected with the output gear through the intermediate gear, so that the output speed of the motor shaft is reduced.
Preferably, the rocker arm assembly is provided in plurality.
In general, compared with the prior art, the above technical solution contemplated by the present invention can achieve the following beneficial effects:
1) this compound rudder system of flat integration adopts the motor to drive the ball I rotation of compound lead screw compound screw subassembly, then cooperates through ball nut I and ball nut II's linear motion again, truns ball I's rotation into ball II's rotary motion again, and then can drive the rocking arm subassembly and realize rotatoryly, through the transmission of such multistage lead screw, can make the rocking arm subassembly produce great moment, and the precision is high moreover, and the transmission is steady reliable.
2) The flat integrated composite rudder system can realize the integrated design of the rudder system and the wings, thereby realizing the aims of lightening the system quality, improving the transmission precision, improving the installation precision, improving the output torque and the like. On the basis of meeting the technical indexes of products, the system has the characteristics of high system integration level, high reliability, low element consumption cost and the like.
3) The flat type integrated composite rudder system can apply pretightening force to the lead screw of the composite screw frame, and can effectively eliminate system clearance, thereby effectively reducing the shaking phenomenon which is easy to occur in the rudder system.
Drawings
FIG. 1 is a perspective view of the present invention;
fig. 2 is a schematic view of the internal structure of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
As shown in fig. 1 and fig. 2, a flat type integrated compound rudder system comprises a base body 6, and a motor 1, a gear reducer 2, a compound screw assembly 3, an anti-rotation guide rail 15 and a rocker arm assembly 5 which are jointly mounted on the base body 6, wherein,
the compound screw assembly 3 comprises a ball screw I11, a ball nut I12, a ball screw II14 and a ball nut II13, wherein the ball screw I11 and the ball screw II14 are parallel to each other, the ball screw I11 is connected with the motor 1 through the gear reducer 2, the ball nut I12 is mounted on the ball screw I11, the ball nut I12 is fixedly connected with the ball nut II13, a slide block I16 is arranged on the ball nut I12, the slide block I16 is mounted on the anti-rotation guide rail 15, and the anti-rotation guide rail 15 and the slide block I16 jointly form a guide rail assembly 4; the guide rail component 4 is arranged beside the compound screw component 3 to realize the rotation-proof output of the ball nut I12.
The rocker arm assembly 5 comprises a connecting rod 17, a sliding block II18 and a rocker arm 19, wherein one end of the connecting rod 17 is mounted on the ball screw II, the other end of the connecting rod 17 is hollow, the sliding block II18 is mounted inside one end of the connecting rod 17 far away from the ball screw II14 and can move along the longitudinal direction of the connecting rod 17, and the rocker arm 19 is mounted on the sliding block II 18. The sliding block II18 can move along the longitudinal direction of the connecting rod 17, so that the position of the rocker arm 19 can be adjusted, meanwhile, the sliding block II18 can only move in the connecting rod 17 and can not rotate, and the anti-rotation function is also realized, so that the rocker arm 19 can normally rotate.
Further, a linear sensor 7 is mounted on the ball nut II13 for obtaining position information of the ball nut II 13. Preferably, the linear sensor 7 is a non-contact potentiometer.
Further, the position information is fed back to a card-inserting type control board of the controller through an electric signal, so that the position closed-loop control of the ball nut II13 is realized, and the closed-loop control of the position of the compound rudder system is realized. The invention feeds back the signal to the card-inserting type control board through the electric signal, thereby realizing the closed-loop control of the position of the rudder system. The flat integrated composite rudder system receives a steering engine control signal sent by a controller, generates a PWM square wave signal according to a certain control rule by the control signal and a steering engine feedback signal, drives a motor to rotate after power amplification of a power circuit, realizes deflection of a steering engine output shaft by two-stage support and a composite screw rod to realize angle and torque output, detects position information of a screw nut by a non-contact linear potentiometer, converts the position information into an electric signal and feeds the electric signal back to the control circuit, and realizes steering engine position closed-loop control.
Further, the gear reducer 2 comprises an input gear 8, an intermediate gear 9 and an output gear 10, the input gear 8 is connected with the motor 1 shaft of the motor 1, and the input gear 8 is connected with the output gear 10 through the intermediate gear 9, so that the output speed of the motor 1 shaft is reduced.
The base body 6 of the invention not only completes the internal installation and support of the rudder system, but also needs to realize the function of a wing support framework;
the gear reducer 2 is arranged in the base body 6, and an input gear 8, an intermediate gear 9, an output gear 10 and the like of the gear reducer jointly form a first-stage speed reducing device; the compound screw assembly 3 is arranged in the base body 6, and a ball screw I11, a ball nut I12, a ball nut II13, a ball screw II14 and the like of the compound screw assembly jointly form a second-stage speed reduction device; the rocker arm assembly 5 is arranged in the base body 6, the connecting rod 17, the sliding block 18, the rocker arm 19 and the like of the rocker arm assembly jointly form a third-stage speed reduction device and achieve output of torque, and the components are jointly matched, namely the rotating input of the motor 1 is converted into rotation of the rocker arm 19 again, and the output of relatively large torque rotating speed is achieved through the rocker arm 19.
The flat integrated composite rudder system adopts a design scheme of system function integration, the control panel is designed into a card-inserting type control circuit 20 to realize the overall control integrated design, the overall transmission layout adopts a composite screw rod type layout, and the rudder system shell and the wing framework are integrally designed. By adopting the composite screw rod technology, the system clearance can be effectively eliminated by applying pretightening force on the ball screw, so that the shaking phenomenon which is easy to occur in the electric steering engine is effectively reduced.
The invention mainly aims at the requirements of the aileron type aircraft on large torque output, high dynamic characteristic requirement and high control precision requirement. Due to the adoption of the composite screw rod technology, the system clearance can be effectively eliminated by applying pretightening force, so that the shaking phenomenon easily occurring in the electric steering engine is effectively reduced. Therefore, the structure has higher reliability and practicability. On the basis of meeting the requirement of the technical index of the product, the invention has the characteristics of high system integration level, small volume, high reliability, low consumption cost of components and parts and the like.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (6)
1. A flat type integrated composite rudder system, the housing of the rudder system and a wing framework are designed in an integrated way, and the rudder system is characterized by comprising a base body, and a motor, a gear reducer, a composite lead screw component, an anti-rotation guide rail and a rocker arm component which are arranged on the base body together, wherein,
the composite screw assembly comprises a ball screw I, a ball nut I, a ball screw II and a ball nut II, wherein the ball screw I and the ball screw II are parallel to each other, the ball screw I is connected with the motor through the gear reducer, the ball nut I is installed on the ball screw I, the ball nut I and the ball nut II are fixedly connected together, a slide block I is arranged on the ball nut I, and the slide block I is installed on the anti-rotation guide rail;
the rocker arm component comprises a connecting rod, a sliding block II and a rocker arm, one end of the connecting rod is installed on the ball screw II, the other end of the connecting rod is hollow, the sliding block II stretches into the inside of one end, far away from the ball screw II, of the connecting rod and can move longitudinally along the connecting rod, the rocker arm is installed on the sliding block II, the sliding block II can only move inside the connecting rod and cannot rotate, the rotation preventing effect is achieved, and the rocker arm can normally rotate.
2. The flat type integrated compound rudder system according to claim 1, wherein a linear sensor is mounted on the ball nut II for obtaining position information of the ball nut II.
3. The flat type integrated compound rudder system according to claim 2, wherein the position information is fed back to a card type control board of a controller through an electric signal, so that the position closed-loop control of the ball nut II is realized, and the closed-loop control of the position of the compound rudder system is realized.
4. The flat integrated compound rudder system according to claim 2, wherein the linear sensor is a non-contact potentiometer.
5. The flat type integrated compound rudder system according to claim 1, wherein the gear reducer includes an input gear, an intermediate gear and an output gear, the input gear is connected with a motor shaft of the motor, and the input gear is connected with the output gear through the intermediate gear, so that the output speed of the motor shaft is reduced.
6. The flat type integrated composite rudder system according to claim 1, wherein a plurality of rocker arm assemblies are provided.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910224020.XA CN109987219B (en) | 2019-03-22 | 2019-03-22 | Flat type integrated composite rudder system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910224020.XA CN109987219B (en) | 2019-03-22 | 2019-03-22 | Flat type integrated composite rudder system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109987219A CN109987219A (en) | 2019-07-09 |
| CN109987219B true CN109987219B (en) | 2020-11-13 |
Family
ID=67130781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910224020.XA Active CN109987219B (en) | 2019-03-22 | 2019-03-22 | Flat type integrated composite rudder system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109987219B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111272024B (en) * | 2020-01-20 | 2022-06-07 | 湖北三江航天红峰控制有限公司 | Harmonic drive crank rocker arm rotary steering engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5163534A (en) * | 1990-04-25 | 1992-11-17 | British Aerospace Plc | Lubricating apparatus |
| JP3694742B2 (en) * | 2002-02-12 | 2005-09-14 | 防衛庁技術研究本部長 | Dynamic wind test model with control surface drive mechanism |
| CN105337447A (en) * | 2015-11-27 | 2016-02-17 | 湖北三江航天红峰控制有限公司 | Pancake electric steering engine |
| CN105398565A (en) * | 2015-10-23 | 2016-03-16 | 庆安集团有限公司 | Rear wing modification mechanism for flying wing aircraft |
| CN206117409U (en) * | 2016-09-30 | 2017-04-19 | 北京自动化控制设备研究所 | Flat long and narrow steering wheel drive mechanism |
| CN107061657A (en) * | 2017-06-06 | 2017-08-18 | 上海航天控制技术研究所 | A kind of high rigidity anti-rotation guider for ball-screw |
| CN108275259A (en) * | 2017-12-22 | 2018-07-13 | 兰州空间技术物理研究所 | A kind of flat aileron steering engine mechanism |
| CN108612819A (en) * | 2018-04-04 | 2018-10-02 | 湖北三江航天红峰控制有限公司 | A kind of rotary rudder system of slender type |
-
2019
- 2019-03-22 CN CN201910224020.XA patent/CN109987219B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5163534A (en) * | 1990-04-25 | 1992-11-17 | British Aerospace Plc | Lubricating apparatus |
| JP3694742B2 (en) * | 2002-02-12 | 2005-09-14 | 防衛庁技術研究本部長 | Dynamic wind test model with control surface drive mechanism |
| CN105398565A (en) * | 2015-10-23 | 2016-03-16 | 庆安集团有限公司 | Rear wing modification mechanism for flying wing aircraft |
| CN105337447A (en) * | 2015-11-27 | 2016-02-17 | 湖北三江航天红峰控制有限公司 | Pancake electric steering engine |
| CN206117409U (en) * | 2016-09-30 | 2017-04-19 | 北京自动化控制设备研究所 | Flat long and narrow steering wheel drive mechanism |
| CN107061657A (en) * | 2017-06-06 | 2017-08-18 | 上海航天控制技术研究所 | A kind of high rigidity anti-rotation guider for ball-screw |
| CN108275259A (en) * | 2017-12-22 | 2018-07-13 | 兰州空间技术物理研究所 | A kind of flat aileron steering engine mechanism |
| CN108612819A (en) * | 2018-04-04 | 2018-10-02 | 湖北三江航天红峰控制有限公司 | A kind of rotary rudder system of slender type |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109987219A (en) | 2019-07-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9643716B2 (en) | Air vehicle, actuator assembly and associated method of manufacture | |
| CN105151278B (en) | A kind of rudder face differential driving mechanism suitable for unmanned plane | |
| US10527142B2 (en) | Hydraulic rotary ball screw actuator | |
| CN105129074A (en) | Two-channel electric steering engine | |
| CN109987219B (en) | Flat type integrated composite rudder system | |
| CN105270619A (en) | Oil-drive variable-pitch quad-rotor unmanned aerial vehicle | |
| US20210214069A1 (en) | Three-dimensional extension linkage | |
| CN102229357A (en) | Empennage with installing angle and adjustable horizontal tail | |
| CN102815394A (en) | Light aircraft rudder spring centering positioning mechanism | |
| CN107792345B (en) | Compact steering engine and rudder engine room | |
| EP3998199B1 (en) | Civil aircraft equipped with actuator for primary flight control surface | |
| CN101612481A (en) | Slide type airplane model steering engine | |
| CN108612819B (en) | Slender rotary rudder system | |
| CN112173073B (en) | Single steering engine control double vertical fin control structure | |
| KR20140079174A (en) | Blade pitch control device for Airplane propeller | |
| CN110297430B (en) | Microminiature high-precision digital electric steering engine system and design method thereof | |
| CN211018536U (en) | Novel integrated linear displacement output electromechanical actuator | |
| CN204985586U (en) | Electronic sharp actuator of multistage planet transmission | |
| CN101870356A (en) | Parallel type worm gear and worm screw high-torque actuator | |
| CN111017197A (en) | Servo actuating device for differential rudder of airplane | |
| CN210526881U (en) | Long fork type control surface driving mechanism | |
| CN210526882U (en) | Small-size wide stroke electric steering engine of big power arm | |
| CN204089444U (en) | A kind of electrical servo system | |
| CN202622817U (en) | External structure for steering engine | |
| CN110254752A (en) | A kind of small-sized big arm of force wide row journey electric steering engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |