CN112407330A - Vibration sensitive conduction device applied to rotating control surface - Google Patents
Vibration sensitive conduction device applied to rotating control surface Download PDFInfo
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- CN112407330A CN112407330A CN202011350269.4A CN202011350269A CN112407330A CN 112407330 A CN112407330 A CN 112407330A CN 202011350269 A CN202011350269 A CN 202011350269A CN 112407330 A CN112407330 A CN 112407330A
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- control surface
- sliding block
- vibration
- sliding
- conduction device
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Abstract
The invention discloses a vibration sensitive conduction device applied to a rotary control surface, which comprises a control surface, a vibration sensitive conduction device and a steering engine device, wherein the control surface is provided with a vibration sensitive conduction device; the vibration sensitive conduction device is arranged in the control surface and the steering engine device. The vibration sensitive conduction device comprises a spring, a first sliding block, a second sliding block, a guide bearing, a first connecting rod, a second connecting rod, a stop block, a rare earth permanent magnet, a linear Hall sensor and a sensor cover plate; the flutter of the control surface caused by high-speed flight is represented by that the control surface rotates back and forth around the control shaft in a tiny amplitude, so that the first sliding block is driven to slide back and forth along the sliding groove in the control surface, and the rare earth permanent magnet is driven to slide in the sliding groove of the control shaft at the flutter frequency through the transmission mechanism; the linear Hall sensor is arranged at the tail end of the rudder shaft, measures the magnetic field intensity change in real time, and calculates the sliding frequency of the linear Hall sensor through calibration data, namely the flutter frequency of the rudder surface. The invention can monitor the flutter frequency of the control surface of the aircraft in real time, has strong practicability and small occupied space, and greatly improves the flight reliability of the aircraft.
Description
Technical Field
The invention relates to a vibration sensitive conduction device, in particular to a vibration sensitive conduction device applied to a rotary control surface.
Background
In recent years, with the increasing demands for high speed and miniaturization of modern aircrafts, the flight environment of a servo system is increasingly severe, and due to the fact that internal and external uncertainty factors are difficult to control in the flight process, the flutter phenomenon of a control surface structure is easy to generate, so that power consumption is increased rapidly, the system generates heat seriously, and even the control of a flight control system is dispersed.
Due to the fact that existing complex flight environments have nonlinear variable high coupling of all states, a controllable object presents strong nonlinear dynamic characteristics, actual flight environments cannot be simulated completely through simulation, and the design of a servo control system is greatly influenced. In the actual engineering design process, the measures are mainly adopted to guide the design of the filter through missile mode identification, in order to pursue the test accuracy, the ground test is carried out after the structure is assembled, the design iteration period is long, and the heaven-earth consistency of the mode frequency is difficult to ensure. And the software adopts the measures of filter design, bandwidth reduction and the like, and the control stability is actually ensured at the expense of the dynamic performance of the servo system.
Aiming at the limitation of the method, the invention researches a vibration sensitive conduction device applied to the rotary control surface, can monitor and feed back the flutter frequency of the control surface system in real time in a flight state, and finally actively inhibits the flutter of the control surface by a high-precision control technology.
Disclosure of Invention
The invention aims to provide a vibration sensitive conduction device applied to a rotating control surface, which comprises the following components: the problem that the flutter frequency of the control surface is obtained in real time in the flying process of an aircraft with the rotary control surface, and buffeting of the control surface is effectively inhibited through online parameter adjustment of a controller can be solved.
In order to solve the above-described problems, the present invention is achieved by the following technical means.
A vibration-sensitive conducting device applied to a rotating control surface comprising: a control surface, a vibration sensitive conduction device and a steering engine device; the vibration sensitive conduction device is arranged in the control surface and the steering engine device.
Further, the steering gear device comprises a steering gear frame, a motor, a speed reduction transmission mechanism and a feedback mechanism, wherein the speed reduction transmission mechanism comprises a transmission mechanism, a rudder shaft, a rocker arm, a first bearing and a second bearing. The motor output power drives the rudder shaft to rotate through a transmission mechanism and a rocker arm, and the rudder shaft is installed on the steering engine frame through a first bearing and a second bearing.
Further, the vibration sensitive conduction device comprises a spring, a first slide block, a second slide block, a guide bearing, a first connecting rod, a second connecting rod, a stop block, a rare earth permanent magnet, a linear Hall sensor and a sensor cover plate; in the flying process of the aircraft, the flutter of the control surface caused by a high-speed state is expressed as the back-and-forth rotation of the control surface around the control shaft with a very small amplitude, so that the first sliding block is driven to slide along the sliding groove in the control surface in a reciprocating manner through the guide bearing arranged on the first sliding block; the first connecting rod is connected with the first sliding block and the second sliding block through a first screw pin and a second screw pin respectively; the second sliding block is driven by the first sliding block to slide up and down at the same frequency through a guide bearing arranged on the second sliding block; thereby driving the second connecting rod connected with the second sliding block by a third screw pin to slide up and down; the guide bearing is arranged at the contact part of the first sliding block and the second sliding block with the sliding groove, and has the functions of reducing resistance and facilitating sliding.
Further, the stop block is connected with the second connecting rod through threads.
Furthermore, the rare earth permanent magnet is fixedly arranged on the stop block and slides up and down at the flutter frequency of the control surface.
Further, the linear Hall sensor is arranged at the tail end of the rudder shaft and is vertically arranged at a certain distance from the rare earth permanent magnet, the magnetic field intensity at the position of the linear Hall sensor is changed regularly along with the up-and-down sliding of the rare earth permanent magnet, and the sliding frequency of the rare earth permanent magnet, namely the flutter frequency of the rudder surface, can be calculated in real time through the calibration data of the sensor.
Compared with the prior art, the method has the advantages that:
the method measures the magnetic field intensity change through the linear Hall sensor, thereby measuring the buffeting frequency of the control surface, feeding back online monitoring data to the controller, and effectively inhibiting the buffeting of the control surface through online adjusting control parameters.
Drawings
The invention will be further explained with reference to the drawings and examples.
Fig. 1 is a schematic view of the application of a vibration sensitive conducting device of an embodiment of the present invention in a rudder system.
Fig. 2 is a schematic diagram of the complete structure of the rudder system according to the embodiment of the present invention.
FIG. 3 is a schematic diagram of a first slider structure according to an embodiment of the invention.
FIG. 4 is a schematic diagram of a second slider structure according to an embodiment of the present invention.
Detailed Description
The invention will be further described with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, 2, 3 and 4, wherein: 1-a spring; 2-a first slide; 3-a guide bearing; 4-a first screw pin; 5-a first link; 6-a second screw pin; 7-control surface; 8-a second stop; 9-a first bearing; 10-a steering engine frame; 11-a second bearing; 12-a sensor cover plate; 13-a linear hall sensor; 14-rare earth permanent magnets; 15-a block; 16-a rocker arm; 17-rudder shaft; 18-a second link; 19-a third screw pin; 20-a second slide; 21-transmission mechanism.
The vibration sensitive conduction device applied to the rotary control surface comprises a control surface 7, a vibration sensitive conduction device and a steering engine device; the vibration sensitive conduction device is arranged in the control surface 7 and the steering engine device. The vibration sensitive conduction device comprises a spring 1, a first sliding block 2, a second sliding block 20, a guide bearing 3, a first connecting rod 5, a second connecting rod 18, a stop block 15, a rare earth permanent magnet 14, a linear Hall sensor 13 and a sensor cover plate 12.
The first sliding block 2 slides back and forth along a sliding groove in the control surface 7 through a guide bearing 3 arranged on the first sliding block when the control surface vibrates;
the first connecting rod 5 is respectively connected with the first sliding block 2 and the second sliding block 20 through a first screw pin 4 and a second screw pin 6;
the second sliding block 20 is driven by the first sliding block 2 to slide up and down at the same frequency through the guide bearing 3 arranged on the second sliding block; thereby driving the second connecting rod connected with the second sliding block 20 by the third screw pin 19 to slide up and down;
the guide bearings are arranged at the contact parts of the first sliding block 2 and the second sliding block 20 and the sliding groove, and play a role in reducing resistance and facilitating sliding
As shown in fig. 2, the steering engine device includes a steering engine frame 10, a motor, a speed reduction transmission mechanism and a feedback mechanism, wherein the speed reduction transmission mechanism includes a transmission mechanism 21, a rudder shaft 17, a rocker arm 16, a first bearing 9 and a second bearing 11.
As shown in fig. 1 and 2, when the control surface 7 flutters, the first slider 2 installed inside the control surface 7 slides back and forth along the sliding groove in the control surface 7 through the guide bearing 3; the reciprocating linear motion of the first slide block 2 drives the second slide block 20 and the stop block 15 to carry out reciprocating linear motion in the axis direction of the rudder shaft 17 through the first connecting rod 5 and the second connecting rod 18 respectively; the guide bearing 3 is arranged at the contact part of the first sliding block 2 and the second sliding block 20 with the sliding chute, so that the effects of reducing resistance and facilitating sliding are achieved; the rare earth permanent magnet 14 is fixedly arranged on a stop block 15 and slides in a reciprocating manner at the flutter frequency of the control surface 7.
The linear Hall sensor 13 is arranged at the tail end of the rudder shaft 17 and is vertically arranged at a certain distance from the rare earth permanent magnet 14, the magnetic field intensity at the position of the linear Hall sensor 13 shows regular change along with the up-and-down sliding of the rare earth permanent magnet 14, and the sliding frequency of the rare earth permanent magnet 14, namely the flutter frequency of the rudder surface 7, can be calculated in real time through calibration data of the sensor. Finally, the on-line monitoring data is fed back to the controller, the parameters can be adjusted in real time, and the flutter of the control surface can be restrained on line.
Although the present invention has been described with reference to the above embodiments, it should be understood that the present invention is not limited to the above embodiments, and therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention are within the scope of the present invention.
Claims (6)
1. A vibration-sensitive conducting device for a rotating control surface, comprising: a control surface, a vibration sensitive conduction device and a steering engine device;
the vibration sensitive conduction device is arranged in the control surface and the steering engine device.
2. The vibration sensitive conduction device applied to the rotating control surface is characterized by comprising a steering engine frame, a motor, a speed reduction transmission mechanism and a feedback mechanism, wherein the steering engine frame is arranged on the rotating control surface;
the speed reduction transmission mechanism comprises a transmission mechanism, a rudder shaft, a rocker arm, a first bearing and a second bearing;
the motor outputs power to drive the rudder shaft to rotate through a transmission mechanism and a rocker arm, and the rudder shaft is arranged on a steering engine frame through a first bearing and a second bearing;
the rudder shaft is fixedly connected with the rudder surface.
3. A vibration-sensitive conducting device applied to a rotating control surface according to claim 2, characterized in that: the vibration sensitive conduction device comprises a spring, a first sliding block, a second sliding block, a guide bearing, a first connecting rod, a second connecting rod, a stop block, a rare earth permanent magnet, a linear Hall sensor and a sensor cover plate;
the first sliding block slides back and forth along the inner sliding groove of the control surface through a guide bearing arranged on the first sliding block when the control surface vibrates;
the first connecting rod is connected with the first sliding block and the second sliding block through a first screw pin and a second screw pin respectively;
the second sliding block is driven by the first sliding block to slide up and down at the same frequency through a guide bearing arranged on the second sliding block; thereby driving the second connecting rod connected with the second sliding block by a third screw pin to slide up and down;
the guide bearing is arranged at the contact part of the first sliding block and the second sliding block with the sliding groove, and has the functions of reducing resistance and facilitating sliding.
4. A vibration-sensitive conducting device applied to a rotating control surface according to claim 3, characterized in that: the stop block is connected with the second connecting rod through threads.
5. The vibration sensitive conducting device applied to the rotating control surface according to claim 3 or 4, wherein the rare earth permanent magnet is fixedly installed on the stopper and slides up and down at the flutter frequency of the control surface.
6. A vibration-sensitive conducting device applied to a rotating control surface according to claim 5, characterized in that: the linear Hall sensor is arranged at the tail end of the rudder shaft and is vertically arranged at a certain distance from the rare earth permanent magnet, the magnetic field intensity at the position of the linear Hall sensor shows regular change along with the up-and-down sliding of the rare earth permanent magnet, and the sliding frequency of the rare earth permanent magnet, namely the flutter frequency of the rudder surface, can be calculated in real time through the calibration data of the sensor.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011350269.4A CN112407330B (en) | 2020-11-26 | 2020-11-26 | Vibration sensitive conduction device applied to rotating control surface |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011350269.4A CN112407330B (en) | 2020-11-26 | 2020-11-26 | Vibration sensitive conduction device applied to rotating control surface |
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| CN112407330A true CN112407330A (en) | 2021-02-26 |
| CN112407330B CN112407330B (en) | 2022-07-01 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB515318A (en) * | 1937-05-31 | 1939-12-01 | Ernst Heinkel | Improvements in or relating to vibration dampers |
| JPH06336199A (en) * | 1993-05-28 | 1994-12-06 | Mitsubishi Heavy Ind Ltd | Member damage detecting device for aircraft |
| CN205209736U (en) * | 2015-12-09 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Manipulation rudder face that shimmys suppression device and have it model that shimmys |
| US20180162556A1 (en) * | 2016-12-14 | 2018-06-14 | The Boeing Company | Nano-energetic applications for aircraft |
| CN109341948A (en) * | 2018-11-28 | 2019-02-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft wing rudder face and rudder rotational inertia measuring device and measurement method |
| CN109383761A (en) * | 2018-11-14 | 2019-02-26 | 中国空空导弹研究院 | A kind of integration involute rocker arm electric steering engine |
-
2020
- 2020-11-26 CN CN202011350269.4A patent/CN112407330B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB515318A (en) * | 1937-05-31 | 1939-12-01 | Ernst Heinkel | Improvements in or relating to vibration dampers |
| JPH06336199A (en) * | 1993-05-28 | 1994-12-06 | Mitsubishi Heavy Ind Ltd | Member damage detecting device for aircraft |
| CN205209736U (en) * | 2015-12-09 | 2016-05-04 | 中国航空工业集团公司沈阳飞机设计研究所 | Manipulation rudder face that shimmys suppression device and have it model that shimmys |
| US20180162556A1 (en) * | 2016-12-14 | 2018-06-14 | The Boeing Company | Nano-energetic applications for aircraft |
| CN109383761A (en) * | 2018-11-14 | 2019-02-26 | 中国空空导弹研究院 | A kind of integration involute rocker arm electric steering engine |
| CN109341948A (en) * | 2018-11-28 | 2019-02-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft wing rudder face and rudder rotational inertia measuring device and measurement method |
Non-Patent Citations (1)
| Title |
|---|
| 吕继航等: "超音速舵面热气动弹性仿真", 《计算机仿真》 * |
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Effective date of registration: 20230705 Address after: 1555 Zhongchun Road, Minhang District, Shanghai, 201109 Patentee after: SHANGHAI AEROSPACE CONTROL TECHNOLOGY INSTITUTE Patentee after: SHANGHAI ACADEMY OF SPACEFLIGHT TECHNOLOGY Address before: 1555 Zhongchun Road, Minhang District, Shanghai, 201109 Patentee before: SHANGHAI AEROSPACE CONTROL TECHNOLOGY INSTITUTE |
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