CN114198471A - Single-motor two-section driving rotary actuator - Google Patents

Single-motor two-section driving rotary actuator Download PDF

Info

Publication number
CN114198471A
CN114198471A CN202111609574.5A CN202111609574A CN114198471A CN 114198471 A CN114198471 A CN 114198471A CN 202111609574 A CN202111609574 A CN 202111609574A CN 114198471 A CN114198471 A CN 114198471A
Authority
CN
China
Prior art keywords
rotating shaft
motor
transmission shaft
rotary actuator
shaft
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.)
Granted
Application number
CN202111609574.5A
Other languages
Chinese (zh)
Other versions
CN114198471B (en
Inventor
唐昌宁
张威
杨晓东
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Chengdu Feiya Airborne Equipment Application Research Co ltd
Original Assignee
Chengdu Feiya Airborne Equipment Application Research Co ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Chengdu Feiya Airborne Equipment Application Research Co ltd filed Critical Chengdu Feiya Airborne Equipment Application Research Co ltd
Priority to CN202111609574.5A priority Critical patent/CN114198471B/en
Publication of CN114198471A publication Critical patent/CN114198471A/en
Application granted granted Critical
Publication of CN114198471B publication Critical patent/CN114198471B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H37/00—Combinations of mechanical gearings, not provided for in groups F16H1/00 - F16H35/00
    • F16H37/02—Combinations of mechanical gearings, not provided for in groups F16H1/00 - F16H35/00 comprising essentially only toothed or friction gearings
    • F16H37/06—Combinations of mechanical gearings, not provided for in groups F16H1/00 - F16H35/00 comprising essentially only toothed or friction gearings with a plurality of driving or driven shafts; with arrangements for dividing torque between two or more intermediate shafts
    • F16H37/065—Combinations of mechanical gearings, not provided for in groups F16H1/00 - F16H35/00 comprising essentially only toothed or friction gearings with a plurality of driving or driven shafts; with arrangements for dividing torque between two or more intermediate shafts with a plurality of driving or driven shafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H3/00—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion
    • F16H3/001—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion convertible for varying the gear-ratio, e.g. for selecting one of several shafts as the input shaft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H3/00—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion
    • F16H3/44—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion using gears having orbital motion
    • F16H3/70—Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion using gears having orbital motion in which the central axis of the gearing lies inside the periphery of an orbital gear
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/0018—Shaft assemblies for gearings
    • F16H57/0037—Special features of coaxial shafts, e.g. relative support thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/08—General details of gearing of gearings with members having orbital motion
    • F16H57/10—Braking arrangements
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/003—Couplings; Details of shafts
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/10—Structural association with clutches, brakes, gears, pulleys or mechanical starters
    • H02K7/116—Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H2057/02039—Gearboxes for particular applications
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H2057/02086—Measures for reducing size of gearbox, e.g. for creating a more compact transmission casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H2057/02091—Measures for reducing weight of gearbox
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H2200/00—Transmissions for multiple ratios
    • F16H2200/20—Transmissions using gears with orbital motion
    • F16H2200/2002—Transmissions using gears with orbital motion characterised by the number of sets of orbital gears
    • F16H2200/2005—Transmissions using gears with orbital motion characterised by the number of sets of orbital gears with one sets of orbital gears
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H2200/00—Transmissions for multiple ratios
    • F16H2200/20—Transmissions using gears with orbital motion
    • F16H2200/203—Transmissions using gears with orbital motion characterised by the engaging friction means not of the freewheel type, e.g. friction clutches or brakes
    • F16H2200/2035—Transmissions using gears with orbital motion characterised by the engaging friction means not of the freewheel type, e.g. friction clutches or brakes with two engaging means

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Power Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Retarders (AREA)

Abstract

The invention discloses a single-motor two-section driving rotary actuator which comprises a first rotating shaft, a transmission shaft, a motor and a second rotating shaft, wherein a first external gear is arranged on the first rotating shaft, the rotatable transmission shaft is sleeved in one end of the first rotating shaft, the motor connected with the transmission shaft is installed on one side of the first rotating shaft, a sun wheel is sleeved on the transmission shaft, an installation part is formed on the first rotating shaft outside the sun wheel, a plurality of rotatable planet wheels are machined on the installation part and meshed with the sun wheel, a second rotating shaft in clearance fit is sleeved outside the first rotating shaft, an inner gear ring meshed with the planet wheels is coaxially installed at one end of the second rotating shaft, a second external gear is arranged on the second rotating shaft, a first brake is installed on the first rotating shaft, and a second brake is installed on the second rotating shaft. The rotary actuator has the characteristics of small occupied space and light weight, can be arranged in the wing, has small influence on the wing structure, and cannot damage the aerodynamic performance of the wing surface.

Description

Single-motor two-section driving rotary actuator
Technical Field
The invention relates to the field of wing folding, in particular to a single-motor two-section driving rotary actuator.
Background
The wings of the existing aviation equipment are mainly folded by adopting a hydraulic cylinder for driving, the output torque of a rotating mechanism for controlling the folding of the wings is large enough when the wings are folded, and the wings also have the characteristics of small volume and light weight. However, the existing hydraulic cylinder drives the wing to fold and has the following problems: the hydraulic cylinder is large in size and heavy, so that the weight of the aviation equipment is increased; secondly, the moment radius of the pushing action of the hydraulic cylinder is small, and when larger pushing force is needed, the size of the hydraulic cylinder needs to be further enlarged, so that the weight can be increased again; thirdly, the hydraulic cylinder occupies the span-wise size of the wing, so that on one hand, the layout of a wing oil tank is influenced, and on the other hand, the aerodynamic performance of the wing is damaged; and fourthly, the hydraulic cylinder can only realize single folding of the wing, and the hydraulic cylinder has poor capability of holding the position of the wing, thereby influencing the stability of the wing in the unfolding process.
Disclosure of Invention
The invention aims to provide a single-motor two-section driving rotary actuator, which adopts gear transmission, can realize two-section driving controlled by a single motor and has the characteristics of small volume, light weight and the like.
The purpose of the invention is realized by the following technical scheme:
a single-motor two-section driving rotary actuator comprises a first rotating shaft, a transmission shaft, a motor and a second rotating shaft, wherein the first rotating shaft is hollow, the dead weight of the rotary actuator can be greatly reduced by the hollow first rotating shaft, at least one first external coupling gear is sleeved on the first rotating shaft, a rotatable transmission shaft is sleeved in one end of the first rotating shaft, the motor connected with the transmission shaft is installed on one side of the first rotating shaft, a sun wheel is sleeved on the transmission shaft, a raised installation part is formed on the first rotating shaft outside the sun wheel, a plurality of installation ports penetrating through the first rotating shaft and opposite to the transmission shaft are processed on the installation part, rotatable planet wheels are installed in each installation port, a plurality of planet wheels are meshed with the sun wheel, the second rotating shaft in clearance fit is sleeved on the outer side of the first rotating shaft, an inner gear ring meshed with the plurality of planet wheels is coaxially installed at one end of the second rotating shaft, the sun gear, the plurality of planet gears and the inner gear ring form a planet gear, at least one second external gear is sleeved on the second rotating shaft, a first brake is installed on the first rotating shaft and can play a role in locking the first rotating shaft so as to fix the planet gears, when the sun gear rotates, driving force is transmitted to the inner gear ring through the autorotation of the planet gears so as to drive the second rotating shaft to rotate, a second brake is installed on the second rotating shaft and can play a role in locking the second rotating shaft so as to fix the inner gear ring, and when the sun gear rotates, the planet gears rotate in the inner gear ring so as to drive the first rotating shaft to rotate.
The transmission shaft is hollow, a limit hole matched with the profile of the output shaft of the motor is machined in one end, close to the motor, of the transmission shaft, the transmission shaft is hollow, the purpose of reducing the dead weight of the transmission shaft can be achieved, the limit hole can be used for avoiding a coupler, and the weight is further reduced.
The outer wall of the transmission shaft is provided with the teeth which are uniformly distributed in an annular shape to form the sun gear, and the teeth are processed on the outer wall of the transmission shaft to form the sun gear, so that the dead weight of the transmission shaft can be reduced, the size of the sun gear can be reduced, and the weight of the transmission shaft can be further reduced.
The bearing that supports the transmission shaft is overlapped on the first pivot inner wall at transmission shaft both ends, and the stability when the bearing can improve the transmission shaft and rotate.
The first external gears are arranged at two ends of the first rotating shaft, and the two first external gears are arranged at two ends of the first rotating shaft, so that the two first external gears are symmetrically supported and symmetrically output, and the stability of the wings during folding is improved.
The two second external gears are arranged at two ends of the second rotating shaft, and the two second external gears are adopted, so that the wing folding mechanism has symmetrical support and symmetrical output, and the stability of the wing during folding is improved.
The single-motor two-section driving rotary actuator provided by the invention has the beneficial effects that:
(1) the rotary actuator has the characteristics of small occupied space and light weight, can be arranged in the wing, has small influence on the wing structure, and cannot damage the aerodynamic performance of the wing surface;
(2) compared with the prior art that the wing is driven to fold through a hydraulic cylinder, the motor control technology is more mature, and the performance is more stable;
(3) the rotary actuator can realize multi-section folding through a single motor, has large output torque and better wing supporting performance;
(4) by applying the rotary actuator, two first external gears on the first rotating shaft can output driving force to one wing, two second external gears on the second rotating shaft can output driving force to the other group of wings, a simply supported beam structure for the wings is formed under the action of the first rotating shaft and the second rotating shaft, supporting force for the wings is provided, the rotary actuator has stronger force transmission performance, and the stability of the wings can be improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram provided in an embodiment of the present invention.
Fig. 2 is a side view provided by an embodiment of the present invention.
Fig. 3 is a cross-sectional view taken along line a-a of fig. 2.
Fig. 4 is a cross-sectional view taken along line B-B of fig. 2.
Fig. 5 is a schematic structural diagram of a first rotating shaft according to an embodiment of the present invention.
Fig. 6 is a schematic structural diagram of a transmission shaft according to an embodiment of the present invention.
Fig. 7 is a schematic view of a wing according to an embodiment of the present invention in a folded state.
FIG. 8 is a schematic view of a first section of an airfoil according to an embodiment of the invention in an extended position.
FIG. 9 is a schematic view of a second wing section according to an embodiment of the invention in an extended position.
Fig. 10 is a schematic view illustrating the installation of a rotary actuator when the wing is folded according to an embodiment of the present invention.
Fig. 11 is a schematic view illustrating installation of a rotary actuator when a wing is deployed according to an embodiment of the present invention.
Reference numerals: 1. a first rotating shaft; 11. a planet wheel; 12. an installation part; 13. an installation port; 2. a drive shaft; 21. a bearing; 22. a sun gear; 23. a limiting hole; 3. a motor; 4. a second rotating shaft; 41. an inner gear ring; 5. a first external gear; 6. a second external gear; 7. a first brake; 8. a second brake; 101. a first component; 1011. a hinge point A; 1012. a hinge point B; 1013. a hinge point C; 102. a second component; 103. a third component; 104. a fourth component; 105. a fifth component; 106. a first rocker arm; 107. and a second rocker arm.
Detailed Description
Examples
As shown in fig. 1 to 6, the single-motor two-stage driving rotary actuator provided in this embodiment includes a first rotating shaft 1, a transmission shaft 2, a motor 3, and a second rotating shaft 4, where the first rotating shaft 1 is hollow and can greatly reduce the dead weight of the rotary actuator, two first external gears 5 are installed on the first rotating shaft 1, the first external gears 5 are used to drive the wings to fold for the first time, the transmission shaft 2 is sleeved inside one end of the first rotating shaft 1, the transmission shaft 2 is hollow and is used to reduce the dead weight, the motor 3 connected to the transmission shaft 2 is installed on one side of the first rotating shaft 1, a limiting hole 23 adapted to the profile of the output shaft of the motor 3 is processed on the transmission shaft 2 to avoid the arrangement of a coupler, so as to ensure that the weight of the rotary actuator is not increased, a sun gear 22 formed by teeth is processed on the transmission shaft 2, a convex installation portion 12 is formed on the first rotating shaft 1 outside the sun gear 22, a plurality of mounting holes 13 which penetrate through the first rotating shaft 1 and are opposite to the transmission shaft 2 are processed on the mounting part 12, a rotatable planet wheel 11 is mounted in each mounting hole 13, the planet wheels 11 are meshed with a sun wheel 22 processed on the transmission shaft 2, a second rotating shaft 4 in clearance fit is sleeved on the outer side of the first rotating shaft 1, an inner gear ring 41 meshed with the planet wheels 11 is coaxially mounted at one end of the second rotating shaft 4, the sun wheel 22, the planet wheels 11 and the inner gear ring 41 form a planet gear, two second external gears 6 are sleeved on the second rotating shaft 4 and used for controlling the secondary folding of the wing, a first brake 7 is mounted on the first rotating shaft 1, the first brake 7 can play a role of locking the first rotating shaft 1, so as to fix the planet wheels 11, when the sun wheel 22 rotates, the planet wheels 11 rotate to transmit driving force to the inner gear ring 41 for driving the second rotating shaft 4 to rotate, the second rotating shaft 4 is provided with a second brake 8, the second brake 8 can play a role of locking the second rotating shaft 4, so that the inner gear ring 41 is fixed, when the sun gear 22 rotates, the planet gear 11 rotates in the inner gear ring 41 to drive the first rotating shaft 1 to rotate, two first external gears 5 and two second external gears 6 are adopted, the two first external gears 5 and the two second external gears 6 are symmetrical along the middle part of the first rotating shaft 1, the two second external gears 6 between the two first external gears 5 are connected with one section of wing, the two first external gears 5 are connected with the other section of wing, symmetrical support and symmetrical output of the wing are realized, and the stability of the wing during folding is ensured. In addition, when the wing is folded, the first rotating shaft 1 and the second rotating shaft 2 form a corbel structure to support the wing, and the stability of the wing can be improved under the condition of ensuring the force transmission performance.
The use state of the invention is as follows:
during installation: the rotary actuator is installed at the hinged position of the wing, as shown in fig. 7, the wing comprises a first component 101, a second component 102, a third component 103, a fourth component 104 and a fifth component 105, wherein the first component 101 is triangular, the triangles of the first component 101 are hinged points which are respectively a hinged point a1011, a hinged point B1012 and a hinged point C1013, the hinged point a1011 is a fixed point, one end of the second component 102 is connected with the hinged point a1011, the other end of the second component is fixed, the rotary actuator is installed at the hinged point C1013, a first external gear 5 of the rotary actuator is connected with a first rocker arm 106, a second external gear 6 of the rotary actuator is connected with a second rocker arm 107, the third component 103 is connected between the fixed end of the second component 102 and the extending end of the first rocker arm 106, the hinged point is hinged with one end of the fifth component 105, the other end of the fifth component 105 is hinged with the fourth component 104, and the other end of the fourth component 104 is hinged with the second rocker arm 107. A hinge point A1011, a hinge point C1013, a second component 102, a third component 103 and a first rocker arm 106 in the first component 101 are sequentially hinged to form a first section of four-bar linkage mechanism of the wing; and a hinge point B1012 and a hinge point C1013 of the first component 101, a fourth component 104, a fifth component 105 and a second rocker arm 107 are sequentially hinged to form a second section of four-bar linkage mechanism of the wing. As shown in fig. 10 and 11, the first section of the four-bar linkage after installation is connected to one of the wings at one end, and the second section of the four-bar linkage is connected to the other wing, which is embodied on the rotary actuator as that the rocker arm on the first external gear 5 is connected to one of the wings at one end, and the rocker arm on the second external gear 6 is connected to the other wing at the other end, by applying the rotary actuator, the two first external gears 5 on the first rotating shaft 1 can output driving force to one wing, and simultaneously the two second external gears 6 on the second rotating shaft 2 can output driving force to the other wing, and form a beam structure to the wings and provide supporting force to the wings under the action of the first rotating shaft 1 and the second rotating shaft 2, so that the rotary actuator has strong force transmission performance, and can also improve the stability of the wings.
When the wing moves, the second brake 8 brakes, the first brake 7 opens, at this time, the second rotating shaft 4 is locked, which is equivalent to the fixed inner gear ring 41, the motor 3 drives the transmission shaft 2 to rotate, the transmission shaft 2 drives the planet gear 11 to rotate in the inner gear ring 41 when rotating, so as to push the first rotating shaft 1 to rotate, and when the first rotating shaft 1 rotates, as shown in fig. 8, the first section of the four-bar linkage mechanism of the wing is driven to unfold, that is, the third component 103 rotates to be straight with the first rocker arm 106; then the second brake 8 is opened, the first brake 7 brakes, at this time, the first rotating shaft 1 is locked, which is equivalent to locking of the planetary gear 11, the motor 3 drives the transmission shaft 2 to rotate, the planetary gear 11 rotates when the rotating shaft rotates, the driving force acts on the internal gear ring 41, the internal gear ring 41 drives the second rotating shaft 4 to rotate, and when the second rotating shaft 4 rotates, as shown in fig. 9, the second section of the four-bar linkage mechanism of the wing is driven to be unfolded, that is, the third component 103, the first rocker 106, the second rocker 107 and the fourth component 104 are straight, and the unfolding operation of the complete wing is completed. And the wing folding can be completed by reversely repeating the steps.
This patent is through rotary actuator output power, can make two four connecting rod wing folding angle be more than or equal to 150, make the structure after the wing folding little, compact.
The above description is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any modification and replacement based on the technical solution and inventive concept provided by the present invention should be covered within the scope of the present invention. It should be noted that structures or components illustrated in the drawings are not necessarily drawn to scale, and descriptions of well-known components and processing techniques and procedures are omitted to avoid unnecessarily limiting the invention.

Claims (6)

1. A single-motor two-section drive rotary actuator is characterized in that: comprises a first rotating shaft (1), a transmission shaft (2), a motor (3) and a second rotating shaft (4), wherein the first rotating shaft (1) is hollow, at least one first externally-connected gear (5) is sleeved on the first rotating shaft (1), the inside of one end of the first rotating shaft (1) is sleeved with the rotatable transmission shaft (2), the motor (3) connected with the transmission shaft (2) is installed on one side of the first rotating shaft (1), a sun wheel (22) is sleeved on the transmission shaft (2), a raised installation part (12) is formed on the first rotating shaft (1) outside the sun wheel (22), a plurality of installation openings (13) penetrating through the first rotating shaft (1) and opposite to the transmission shaft (2) are processed on the installation part (12), a rotatable planet wheel (11) is installed in each installation opening (13), the plurality of planet wheels (11) are meshed with the sun wheel (22), and the second rotating shaft (4) is sleeved outside the first rotating shaft (1) and in clearance fit, the planetary gear transmission mechanism is characterized in that an inner gear ring (41) meshed with a plurality of planetary gears (11) is coaxially installed at one end of the second rotating shaft (4), at least one second external gear (6) is sleeved on the second rotating shaft (4), a first brake (7) is installed on the first rotating shaft (1), and a second brake (8) is installed on the second rotating shaft (4).
2. The single motor two stage drive rotary actuator of claim 1, wherein: the transmission shaft (2) is hollow, and a limiting hole (23) matched with the outline of an output shaft of the motor (3) is machined in one end, close to the motor (3), of the transmission shaft (2).
3. The single motor two stage drive rotary actuator of claim 1, wherein: the outer wall of the transmission shaft (2) is provided with teeth which are uniformly distributed in an annular shape to form a sun gear (22).
4. The single motor two stage drive rotary actuator of claim 1, wherein: the inner walls of the first rotating shafts (1) at the two ends of the transmission shaft (2) are sleeved with bearings (21) for supporting the transmission shaft (2).
5. The single motor two stage drive rotary actuator of claim 1, wherein: the number of the first external gears (5) is two, and the two first external gears (5) are arranged at two ends of the first rotating shaft (1).
6. The single motor two stage drive rotary actuator of claim 1, wherein:
the number of the second external gears (6) is two, and the two second external gears (6) are arranged at two ends of the second rotating shaft (4).
CN202111609574.5A 2021-12-24 2021-12-24 Single-motor two-section driving rotary actuator Active CN114198471B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202111609574.5A CN114198471B (en) 2021-12-24 2021-12-24 Single-motor two-section driving rotary actuator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202111609574.5A CN114198471B (en) 2021-12-24 2021-12-24 Single-motor two-section driving rotary actuator

Publications (2)

Publication Number Publication Date
CN114198471A true CN114198471A (en) 2022-03-18
CN114198471B CN114198471B (en) 2024-04-12

Family

ID=80656591

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202111609574.5A Active CN114198471B (en) 2021-12-24 2021-12-24 Single-motor two-section driving rotary actuator

Country Status (1)

Country Link
CN (1) CN114198471B (en)

Citations (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0161240A1 (en) * 1982-12-28 1985-11-21 Zahnradfabrik Friedrichshafen Braking device in a wheel head.
JP2009008239A (en) * 2007-06-29 2009-01-15 Shinko Electric Co Ltd Gear transmission device
CN102826220A (en) * 2012-09-14 2012-12-19 西北工业大学 Thrust device capable of balancing reactive torque
CN203651469U (en) * 2013-12-10 2014-06-18 郑州宇通客车股份有限公司 Electric vehicle speed change gear and driving system and electric vehicle with same used
CN104442771A (en) * 2014-11-27 2015-03-25 芜湖伯特利汽车安全系统有限公司 Electronic parking executing mechanism with reduced noise
JP2015061334A (en) * 2013-09-17 2015-03-30 オリエンタルモーター株式会社 Linear actuator
WO2016146067A1 (en) * 2015-03-16 2016-09-22 刘刚 Planetary gear torque apparatus
CN207265810U (en) * 2017-09-05 2018-04-20 东风德纳车桥有限公司 A kind of integrated driving gear motor assembly
CN108953539A (en) * 2018-09-05 2018-12-07 恒大法拉第未来智能汽车（广东）有限公司 Two speed transmission and electric car
CN109823536A (en) * 2019-04-02 2019-05-31 西北工业大学 A kind of prismatic pair driving mechanism for flapping wing based on external toothing planetary reducer
CN110770472A (en) * 2017-06-21 2020-02-07 谐波传动系统有限公司 Rotary actuator and linear actuator
CN111043248A (en) * 2019-12-04 2020-04-21 湖北科峰传动设备有限公司 Planetary reducer with shell rotation for dragging system
US20200124150A1 (en) * 2018-10-19 2020-04-23 Hamilton Sundstrand Corporation Jam-tolerant electric rotary actuator
CN111486224A (en) * 2020-05-27 2020-08-04 成都飞亚航空设备应用研究所有限公司 Transmission mechanism of wing electric folding system
CN111503226A (en) * 2019-01-30 2020-08-07 南京高精齿轮集团有限公司 Gear box and hard rock heading machine
CN111828551A (en) * 2020-07-09 2020-10-27 成都飞亚航空设备应用研究所有限公司 Electric driving mechanism suitable for wing folding system
CN212225966U (en) * 2020-05-27 2020-12-25 成都飞亚航空设备应用研究所有限公司 Transmission mechanism of wing electric folding system
CN112693593A (en) * 2021-03-23 2021-04-23 成都飞亚航空设备应用研究所有限公司 Flat straight airfoil folding mechanism
DE102019132941A1 (en) * 2019-12-04 2021-06-10 Schaeffler Technologies AG & Co. KG Drive unit and drive arrangement
CN113037007A (en) * 2021-02-22 2021-06-25 深圳市合涟聚电子科技有限责任公司 Driving device for starting and generating power for automobile

Patent Citations (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0161240A1 (en) * 1982-12-28 1985-11-21 Zahnradfabrik Friedrichshafen Braking device in a wheel head.
JP2009008239A (en) * 2007-06-29 2009-01-15 Shinko Electric Co Ltd Gear transmission device
CN102826220A (en) * 2012-09-14 2012-12-19 西北工业大学 Thrust device capable of balancing reactive torque
JP2015061334A (en) * 2013-09-17 2015-03-30 オリエンタルモーター株式会社 Linear actuator
CN203651469U (en) * 2013-12-10 2014-06-18 郑州宇通客车股份有限公司 Electric vehicle speed change gear and driving system and electric vehicle with same used
CN104442771A (en) * 2014-11-27 2015-03-25 芜湖伯特利汽车安全系统有限公司 Electronic parking executing mechanism with reduced noise
WO2016146067A1 (en) * 2015-03-16 2016-09-22 刘刚 Planetary gear torque apparatus
CN110770472A (en) * 2017-06-21 2020-02-07 谐波传动系统有限公司 Rotary actuator and linear actuator
CN207265810U (en) * 2017-09-05 2018-04-20 东风德纳车桥有限公司 A kind of integrated driving gear motor assembly
CN108953539A (en) * 2018-09-05 2018-12-07 恒大法拉第未来智能汽车（广东）有限公司 Two speed transmission and electric car
US20200124150A1 (en) * 2018-10-19 2020-04-23 Hamilton Sundstrand Corporation Jam-tolerant electric rotary actuator
CN111503226A (en) * 2019-01-30 2020-08-07 南京高精齿轮集团有限公司 Gear box and hard rock heading machine
CN109823536A (en) * 2019-04-02 2019-05-31 西北工业大学 A kind of prismatic pair driving mechanism for flapping wing based on external toothing planetary reducer
CN111043248A (en) * 2019-12-04 2020-04-21 湖北科峰传动设备有限公司 Planetary reducer with shell rotation for dragging system
DE102019132941A1 (en) * 2019-12-04 2021-06-10 Schaeffler Technologies AG & Co. KG Drive unit and drive arrangement
CN111486224A (en) * 2020-05-27 2020-08-04 成都飞亚航空设备应用研究所有限公司 Transmission mechanism of wing electric folding system
CN212225966U (en) * 2020-05-27 2020-12-25 成都飞亚航空设备应用研究所有限公司 Transmission mechanism of wing electric folding system
CN111828551A (en) * 2020-07-09 2020-10-27 成都飞亚航空设备应用研究所有限公司 Electric driving mechanism suitable for wing folding system
CN113037007A (en) * 2021-02-22 2021-06-25 深圳市合涟聚电子科技有限责任公司 Driving device for starting and generating power for automobile
CN112693593A (en) * 2021-03-23 2021-04-23 成都飞亚航空设备应用研究所有限公司 Flat straight airfoil folding mechanism

Also Published As

Publication number Publication date
CN114198471B (en) 2024-04-12

Similar Documents

Publication Publication Date Title
CN102431644B (en) Plane main undercarriage space retraction/extension mechanism and retraction/extension method
EP1794051B1 (en) Compact pylon actuation system for tiltrotor aircraft
US6802475B2 (en) Flight surface actuator
WO2019085148A1 (en) Unmanned aerial vehicle and lifting and landing gear thereof
EP3789289B1 (en) Double over center crankshaft flap mechanism
CN111486224A (en) Transmission mechanism of wing electric folding system
CN107914864A (en) Aircraft wing rotates jack and its accommodation method
CN109606634B (en) Double-shaft wing folding mechanism
CN111169620B (en) Telescopic wing mechanism with slotted flap and continuously variable wingspan
EP2731866B1 (en) Leading edge rib assembly
CN115402506A (en) Large unmanned aerial vehicle wing flap actuator and mounting structure thereof
CN107771151B (en) Aircraft landing gear
CN114198471A (en) Single-motor two-section driving rotary actuator
CN212225966U (en) Transmission mechanism of wing electric folding system
CN109505668A (en) Compressor stator regulating mechanism
CN109353489B (en) Multifunctional flap structure of unmanned aerial vehicle
CN215155593U (en) Symmetrical wing surface folding and unfolding mechanism of morphing aircraft
CN110588955A (en) Ball screw pair rotary actuator device
CN115593160A (en) Folding and unfolding type drag reduction flow guide cover applied to planetary gear set type amphibious robot
CN210707861U (en) Ball screw pair rotary actuator device
KR100217936B1 (en) Outboard door for aircraft landing apparatus
CN110733632A (en) landing gear retraction structure
CN221163311U (en) Folding system of aerocar rotor wing
CN113251127B (en) Landing lamp driving mechanism
CN115447764B (en) Lifting rotating wheel type landing gear

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