CN211685587U - Stepless transmission ratio adjusting mechanism - Google Patents
Stepless transmission ratio adjusting mechanism Download PDFInfo
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- CN211685587U CN211685587U CN201922029845.4U CN201922029845U CN211685587U CN 211685587 U CN211685587 U CN 211685587U CN 201922029845 U CN201922029845 U CN 201922029845U CN 211685587 U CN211685587 U CN 211685587U
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- output shaft
- rocker arm
- actuating mechanism
- electric actuating
- frame rocker
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Abstract
The utility model relates to a transmission ratio stepless adjusting mechanism, which comprises a base, a frame rocker arm, an electric actuating mechanism, an input shaft and a first output shaft; the base is fixed on the aircraft, and the frame rocker arm is hinged to the base by taking the middle point of the long edge of the frame rocker arm as a fulcrum and can rotate around the fulcrum; the electric actuating mechanism is arranged on the frame rocker arm, the distance between the first output shaft and the fulcrum is changed through the extension and contraction of the output shaft of the electric actuating mechanism, and the transmission ratio between the output and the input is further changed in a stepless manner within a certain range. The utility model provides an aircraft machinery control system in the different problem of pilot's pilotage that leads to of different control surface control efficiency under different speed or height, realized that the action of pilot's control pilot lever is the pilotage of aircraft the same basically under the aircraft at the flight speed of difference and flight altitude condition, improved the flight quality.
Description
Technical Field
The invention belongs to the field of transmission mechanisms, and particularly relates to a transmission ratio stepless adjusting mechanism.
Background
Modern aircraft often have faster flight speed and higher flight altitude, under different flight speed and flight altitude conditions, the control plane action that control aircraft does the same flight action is different (for example need rudder deflection great angle to accomplish aircraft turn when low-speed flight and only need rudder deflection less angle can accomplish the turn when high-speed flight, flight altitude is different because the control efficiency of the different control planes of atmospheric pressure size is also different), this needs the pilot to drive the aircraft according to manipulation experience and flight experience.
In order to improve the driving quality and reduce the control difficulty of the pilot, a mechanism capable of steplessly changing the transmission ratio from the steering column to the control surface is needed to realize that the actions of the pilot for controlling the steering column, namely the piloting of the aircraft, are basically the same under different flight speeds and flight altitudes, (for example, when the rudder control channel is in a large transmission ratio state during low-speed flight, the control surface deflects greatly to realize the turning of the aircraft, and when the rudder control channel is switched to a small transmission ratio state during high-speed flight, the same pilot control instruction displacement controls the control surface to deflect slightly to realize the turning of the aircraft).
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides a transmission ratio stepless adjusting mechanism, which solves the problem that the aircrafts cannot have the same piloting technique under the conditions of different flight speeds and flight heights, and improves the control quality of the aircrafts.
The technical scheme of the invention is as follows: a stepless transmission ratio adjusting mechanism is characterized in that: the electric actuator comprises a base, a frame rocker arm, an electric actuator and a first output shaft; the base is used for supporting the whole adjusting mechanism and fixing the adjusting mechanism on an aircraft, the bottom of the base is of a flat plate structure, two lugs are symmetrically arranged on the upper surface of the flat plate, and first through holes axially parallel to the flat plate are formed in the upper ends of the lugs;
the frame rocker arm is of a rectangular frame structure, and the centers of the long edges on two opposite sides of the frame rocker arm are hinged to the first through holes of the base lugs through pins, so that the frame rocker arm can rotate by taking the center line of the long edge of the frame rocker arm as the center of a circle; the short edge of one side of the frame rocker arm is used as an input shaft, and the distance from the pin joint to the input shaft is used as an input arm of the adjusting mechanism; the two sliding grooves are positioned between the hinged part of the pin and the short edge at the other side of the frame rocker arm and are arranged close to the short edge at the other side;
the electric actuating mechanism is fixed in the frame of the frame rocker arm, and an output shaft of the electric actuating mechanism is perpendicular to the short side of the frame rocker arm; the first output shaft is vertically fixed at the end of the output shaft of the electric actuating mechanism, two ends of the first output shaft are respectively installed in the two sliding grooves through bearings, and the distance from the hinged position of the pin to the first output shaft is used as an output arm of the adjusting mechanism; the output shaft of the electric actuating mechanism can do linear motion along the axial direction of the electric actuating mechanism, and meanwhile, the first output shaft is driven to slide along the length direction of the sliding groove, so that the length of the output arm is further changed.
The further technical scheme of the invention is as follows: the electric actuating mechanism comprises a motor, and an output shaft of the electric actuating mechanism is controlled by the motor to do linear motion along the axial direction.
The further technical scheme of the invention is as follows: the bottom surface of the U-shaped plate is fixed at the end of the output shaft of the electric actuating mechanism, and two support arms of the U-shaped plate are arranged in parallel to the axial direction of the output shaft of the electric actuating mechanism; and second through holes are formed in the two support arms of the U-shaped plate, and the first output shaft penetrates through the second through holes to be fixed on the output shaft of the electric actuating mechanism.
Advantageous effects
The invention has the beneficial effects that: the invention controls the length proportion of the input end and the output end by controlling the releasing or withdrawing amount of the electric actuating mechanism, realizes the transmission ratio adjustment of the output displacement relative to the input displacement, solves the problem of different pilot piloting techniques caused by different control efficiency of the control surface of the mechanical control system of the airplane at different speeds or altitudes, realizes the action of the pilot for operating the steering column by the pilot under the conditions of different flight speeds and flight altitudes of the airplane, namely the piloting techniques of the airplane are basically the same, and improves the flight quality.
Drawings
Fig. 1 is a schematic structural view of a transmission ratio stepless adjustment mechanism of the present invention.
Fig. 2 is a schematic view of the operating principle of the transmission ratio stepless adjusting mechanism of the invention.
Description of reference numerals: 1-base: 2-an input shaft; 3, an electric actuator; 4-frame rocker arm; 5-a bearing; 6-first output shaft.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Referring to fig. 1, the transmission ratio stepless adjusting mechanism of the present invention comprises a base 1, a frame rocker arm 4, an electric actuator 3, a bearing 5 and a first output shaft 6; the bottom of the base 1 is of a flat plate structure, two lugs are symmetrically arranged on the upper surface of the flat plate, and first through holes axially parallel to the flat plate are formed in the top ends of the lugs; the flat plate of the base 1 is fixed on an aircraft mechanism;
the frame rocker arm 2 is of a rectangular frame structure, the centers of the long edges on two opposite sides of the frame rocker arm are hinged to the first through hole of the base lug through pins, the hinged positions of the pins are used as fulcrums, and the frame rocker arm 2 can rotate around the fulcrums; the short edge of one side of the frame rocker arm 2 is used as an input shaft 2, and the distance from the pin joint to an input shaft 4 is used as an input arm of the adjusting mechanism; the opposite positions of the long sides of the two sides of the frame rocker arm 2 are both provided with sliding chutes, and the two sliding chutes are positioned between the hinged part of the pin and the short side of the other side of the frame rocker arm 2 and are arranged close to the short side of the other side;
the electric actuating mechanism 3 is fixed in the frame of the frame rocker arm 2, and the output shaft of the electric actuating mechanism is controlled by a motor to do linear motion along the axial direction; and can be held in any position after stopping at that position. The output shaft of the rocker arm is vertical to the short side of the frame rocker arm 2; the first output shaft 6 is vertically fixed at the end of the output shaft of the electric actuating mechanism through a U-shaped plate, the bottom surface of the U-shaped plate is fixed at the end of the output shaft of the electric actuating mechanism 3, and two support arms of the U-shaped plate are arranged in parallel to the axial direction of the output shaft of the electric actuating mechanism 3; and second through holes are formed in the two support arms of the U-shaped plate, and the first output shaft penetrates through the second through holes to be fixed on the output shaft of the electric actuating mechanism. Two ends of the first output shaft 6 are respectively installed in the two sliding grooves through bearings 5, and the distance from the hinged position of the pin to the first output shaft 6 is used as an output arm of the adjusting mechanism; the output shaft of the electric actuator 3 can stretch along the shaft by driving the electric actuator, and simultaneously drives the first output shaft 6 to slide along the length direction of the sliding chute, so that the length of the output arm is further changed. Since the distance between the input shaft 2 and the fulcrum of the frame rocker arm 2, namely the length of the input arm, is fixed, the transmission ratio between the output and the input can be steplessly changed within a certain range by controlling the extension or contraction of the output shaft of the electric actuator 3.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (3)
1. A stepless transmission ratio adjusting mechanism is characterized in that: the electric actuator comprises a base, a frame rocker arm, an electric actuator and a first output shaft; the base is used for supporting the whole adjusting mechanism and fixing the adjusting mechanism on an aircraft, the bottom of the base is of a flat plate structure, two lugs are symmetrically arranged on the upper surface of the flat plate, and first through holes axially parallel to the flat plate are formed in the upper ends of the lugs;
the frame rocker arm is of a rectangular frame structure, and the centers of the long edges on two opposite sides of the frame rocker arm are hinged to the first through holes of the base lugs through pins, so that the frame rocker arm can rotate by taking the center line of the long edge of the frame rocker arm as the center of a circle; the short edge of one side of the frame rocker arm is used as an input shaft, and the distance from the pin joint to the input shaft is used as an input arm of the adjusting mechanism; the two sliding grooves are positioned between the hinged part of the pin and the short edge at the other side of the frame rocker arm and are arranged close to the short edge at the other side;
the electric actuating mechanism is fixed in the frame of the frame rocker arm, and an output shaft of the electric actuating mechanism is perpendicular to the short side of the frame rocker arm; the first output shaft is vertically fixed at the end of the output shaft of the electric actuating mechanism, two ends of the first output shaft are respectively installed in the two sliding grooves through bearings, and the distance from the hinged position of the pin to the first output shaft is used as an output arm of the adjusting mechanism; the output shaft of the electric actuating mechanism can do linear motion along the axial direction of the electric actuating mechanism, and meanwhile, the first output shaft is driven to slide along the length direction of the sliding groove, so that the length of the output arm is further changed.
2. The gear ratio stepless adjustment mechanism according to claim 1, characterized in that: the electric actuating mechanism comprises a motor, and an output shaft of the electric actuating mechanism is controlled by the motor to do linear motion along the axial direction.
3. The gear ratio stepless adjustment mechanism according to claim 1, characterized in that: the bottom surface of the U-shaped plate is fixed at the end of the output shaft of the electric actuating mechanism, and two support arms of the U-shaped plate are arranged in parallel to the axial direction of the output shaft of the electric actuating mechanism; and second through holes are formed in the two support arms of the U-shaped plate, and the first output shaft penetrates through the second through holes to be fixed on the output shaft of the electric actuating mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922029845.4U CN211685587U (en) | 2019-11-22 | 2019-11-22 | Stepless transmission ratio adjusting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922029845.4U CN211685587U (en) | 2019-11-22 | 2019-11-22 | Stepless transmission ratio adjusting mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN211685587U true CN211685587U (en) | 2020-10-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922029845.4U Active CN211685587U (en) | 2019-11-22 | 2019-11-22 | Stepless transmission ratio adjusting mechanism |
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| CN (1) | CN211685587U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115447761A (en) * | 2022-10-12 | 2022-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Variable transmission ratio aircraft control system |
| CN115447762A (en) * | 2022-10-12 | 2022-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Emergency control system for seamless access of airplane |
-
2019
- 2019-11-22 CN CN201922029845.4U patent/CN211685587U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115447761A (en) * | 2022-10-12 | 2022-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Variable transmission ratio aircraft control system |
| CN115447762A (en) * | 2022-10-12 | 2022-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Emergency control system for seamless access of airplane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Stepless adjusting mechanism for transmission ratio Effective date of registration: 20211229 Granted publication date: 20201016 Pledgee: AVIC Finance Co.,Ltd. Xi'an Branch Pledgor: XI'AN QING'AN ELECTRIC CONTROL Co.,Ltd. Registration number: Y2021980017053 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20230106 Granted publication date: 20201016 Pledgee: AVIC Finance Co.,Ltd. Xi'an Branch Pledgor: XI'AN QING'AN ELECTRIC CONTROL Co.,Ltd. Registration number: Y2021980017053 |