CN112211974A - Backstop for aviation electric actuator - Google Patents
Backstop for aviation electric actuator Download PDFInfo
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- CN112211974A CN112211974A CN202011020527.2A CN202011020527A CN112211974A CN 112211974 A CN112211974 A CN 112211974A CN 202011020527 A CN202011020527 A CN 202011020527A CN 112211974 A CN112211974 A CN 112211974A
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- cylinder
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- backstop
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- 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
- F16H25/00—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms
- F16H25/18—Gearings comprising primarily only cams, cam-followers and screw-and-nut mechanisms for conveying or interconverting oscillating or reciprocating motions
- F16H25/20—Screw mechanisms
- F16H25/22—Screw mechanisms with balls, rollers, or similar members between the co-operating parts; Elements essential to the use of such members
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- 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
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D41/00—Freewheels or freewheel clutches
- F16D41/20—Freewheels or freewheel clutches with expandable or contractable clamping ring or band
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The embodiment of the invention discloses a backstop of an aviation electric actuator, wherein a driven sleeve and a driving sleeve are oppositely arranged, and a rectangular-section spring is sleeved on a middle small-end cylinder formed by the driven sleeve and the driving sleeve; one end of the input shaft is nested in the driving sleeve and fixedly connected with the driving sleeve, one end of the output shaft is nested in the driven sleeve and fixedly connected with the driven sleeve, and the output shaft is embedded in a small-end cylinder of the driven sleeve and inserted into a hole of the input shaft; the end cover is sleeved outside the driven sleeve, the driving sleeve and the rectangular-section spring; the aviation electric actuator backstop is characterized in that a driving sleeve is sleeved on an input shaft, a driven sleeve is sleeved on an output shaft, and a matching structure of the driven sleeve, the driving sleeve, a rectangular-section spring and an end cover is used for power transmission. The embodiment of the invention solves the problem that the design requirement of the avionic actuator is difficult to meet due to the large weight and volume and poor environmental adaptability of the conventional backstop.
Description
Technical Field
The invention relates to the technical field of an aviation electric actuator, in particular to a backstop of the aviation electric actuator.
Background
At present, an aviation electric actuator is mainly braked by an electromagnetic clutch, a single-end worm gear or trapezoidal screw pair transmission is used as an anti-reverse check mechanism, and the aviation electric actuator adopting the anti-reverse check mechanism is large in size and weight and low in efficiency.
With the development of the aviation electric actuator towards the direction of small volume, light weight and high precision, the precise ball screw pair or the planetary roller screw pair with high efficiency and large bearing capacity is gradually adopted in the aviation electric actuator to replace the trapezoidal screw pair for transmission, and because the precise ball screw pair or the planetary roller screw pair replaces the trapezoidal screw pair for transmission with high efficiency and is not self-locked, an anti-reverse non-return mechanism is required to be adopted. However, the existing backstop has large weight and volume and poor environmental adaptability and cannot meet the requirements of an aviation electric actuator.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a backstop for an avionic actuator, which aims to solve the problem that the design requirement of the avionic actuator is difficult to meet due to the fact that the existing backstop is large in weight and volume and poor in environmental adaptability.
The technical scheme of the invention is as follows:
the embodiment of the invention provides an aviation electric actuator backstop, which comprises: the device comprises an output shaft 1, a driven sleeve 3, a rectangular section spring 4, an input shaft 5, a driving sleeve 6 and an end cover 8;
the driven sleeve 3 and the driving sleeve 6 are oppositely arranged to form a sleeve structure with a middle small-end cylinder, and the rectangular-section spring 4 is sleeved on the middle small-end cylinder; one end of the input shaft 5 is nested in a central round hole 6e of the driving sleeve 6 and fixedly connected with the same, one end of the output shaft 1 is nested in a central round hole 3e of the driven sleeve 3 and fixedly connected with the same, one end of the input shaft 5 embedded in the driving sleeve 6 is provided with a hole, and the small-end cylinder of the output shaft 1 embedded in the driven sleeve 3 is inserted into the hole of the input shaft 5; the end cover 8 is sleeved outside the driven sleeve 3, the driving sleeve 6 and the rectangular section spring 4;
the aviation electric actuator backstop is sleeved with a driving sleeve 6 on an input shaft 5 and a driven sleeve 3 on an output shaft 1 through a matching structure of the driving sleeve 6, the driven sleeve 3, the driving sleeve 6, a rectangular-section spring 4 and an end cover 8 to transmit power.
Optionally, in the avionic actuator backstop as described above, further comprising: a first cylindrical pin 2 and a second cylindrical pin 7;
the output shaft 1 is fixedly connected with a driven sleeve 3 through a first cylindrical pin 2;
the input shaft 5 is fixedly connected with a driving sleeve 6 through a second cylindrical pin 7.
Alternatively, in an avionic actuator backstop as described above,
the driven sleeve 3 is of a hollow step shaft structure with a central round hole 3e, the first step is a large-end cylinder, a pin hole 3d penetrating through the cylinder walls of the cylinders on two sides is formed in the large-end cylinder, and the first cylindrical pin 2 penetrates through the pin hole 3d and a through hole in the output shaft 1 to fixedly connect the output shaft 1 and the driven sleeve 3; the second step is an arc cylinder, one end of the side wall of one side of the arc cylinder, which is connected with the large-end cylinder, is provided with an inner-end rectangular notch 3f, one end of the side wall of the other side of the arc cylinder, which is far away from the large-end cylinder, is provided with an outer-end rectangular notch 3a, and the inner-end rectangular notch 3f and the outer-end rectangular notch 3a are radially and symmetrically arranged for 180 degrees; wherein, the cylinder diameter of the circular arc cylinder is smaller than the cylinder diameter of the first step.
Alternatively, in an avionic actuator backstop as described above,
the driving sleeve 6 is of a hollow step shaft structure with a central round hole 6e, the first step is a large-end cylinder, a pin hole 6c penetrating through the cylinder walls of the cylinders on two sides is formed in the large-end cylinder, and a second cylindrical pin 7 penetrates through the pin hole 6c and a through hole in the input shaft 5 to fixedly connect the input shaft 5 and the driving sleeve 6; the second step is an arc cylinder, and the diameter of the cylinder of the arc cylinder is smaller than that of the cylinder of the first step.
Alternatively, in an avionic actuator backstop as described above,
driven sleeve 3 and the relative buckle cooperation of initiative sleeve 6's circular arc cylinder form that both ends have an open-ended tip cylinder respectively, an opening is located driven sleeve 3's tip cylinder inboard, another opening is located initiative sleeve 6's tip cylinder inboard, the tip cylinder outside that driven sleeve 3 and initiative sleeve 6 formed is established to rectangular cross section spring 4 cover, rectangular cross section spring 4's both ends have a boss respectively, two boss one-to-one are embedded into in two openings at tip cylinder both ends.
Alternatively, in an avionic actuator backstop as described above,
the inner side end face 3c of the large-end cylinder of the driven sleeve 3 is attached to one side end face 4h of the rectangular-section spring 4, and the inner side end face 6b of the large-end cylinder of the driving sleeve 6 is attached to the other side end face 4g of the rectangular-section spring 4;
the outer face of cylinder 4g and the laminating of rectangular cross section spring hole 4b of driven sleeve 3's circular arc cylinder, the outer face of cylinder 6f and the laminating of rectangular cross section spring hole 4b of the circular arc cylinder of initiative sleeve 6.
Alternatively, in an avionic actuator backstop as described above,
the outer end rectangular notch 3a of the driven sleeve 3 is in relative clearance fit with the outer side surface 4d of one boss of the rectangular section spring 4, and the inner end rectangular notch 3f is in relative clearance fit with the outer side surface 4f of the other boss of the rectangular section spring 4;
and an arc cylindrical plane 6a at one side of the driving sleeve 6 is attached to the inner side surface 4c of one boss of the rectangular-section spring 4, and an arc cylindrical plane 6d at the other side of the driving sleeve is attached to the inner side surface 4e of the other boss of the rectangular-section spring 4.
Alternatively, in an avionic actuator backstop as described above,
the end cover 8 is sleeved outside the large-end cylinders of the driven sleeve 3 and the driving sleeve 6, and the large-end cylinders are in small clearance fit with the inner holes of the end cover 8; the excircle of the spring 4 with the rectangular section is attached to the end cover 8.
The invention has the advantages that:
the embodiment of the invention provides a backstop for an avionic actuator, which is characterized in that through an output shaft 1 nested in a driven sleeve 3, an input shaft 5 nested in a driving sleeve 6, the assembly relation of the driven sleeve 3 and the driving sleeve 6, the transmission mode of the output shaft 1 and the input shaft 5 and the assembly relation of a rectangular section spring 4 and an external end cover 8 arranged in an integral structure, the backstop function is realized through the tension and contraction of the rectangular section spring, the structure is greatly simplified, the size is reduced, the weight is lightened, and the requirement of the avionic actuator is met.
Description of the drawings:
the accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.
Fig. 1 is a schematic structural diagram of a backstop of an avionic actuator according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a driven sleeve in an avionic actuator backstop provided in accordance with an embodiment of the present invention;
FIG. 3 is a schematic three-dimensional view of the driven socket of FIG. 2 in accordance with an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of an active sleeve in an avionic actuator backstop according to an embodiment of the present invention;
FIG. 5 is a schematic three-dimensional structure diagram of the active sleeve of FIG. 4 according to an embodiment of the present invention;
FIG. 6 is a schematic view of an assembly structure of a driven sleeve and a driving sleeve in the brake of the avionic actuator provided by the embodiment of the invention;
fig. 7 is a schematic structural diagram of a rectangular-section spring in an avionic actuator backstop according to an embodiment of the invention.
The specific implementation mode is as follows:
in order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
The problem that design requirements of an aviation electric actuator are difficult to meet due to the fact that a backstop in the background technology is large in weight and size and poor in environmental adaptability is solved. The backstop adopting the rectangular-section spring structure has the advantages of compact structure, small volume, light weight and strong environmental adaptability, and meets the requirements of the avionic actuator.
Fig. 1 is a schematic structural diagram of an avionic actuator backstop according to an embodiment of the present invention. As shown in fig. 1, an avionic actuator backstop provided by an embodiment of the present invention may include: the device comprises an output shaft 1, a driven sleeve 3, a rectangular section spring 4, an input shaft 5, a driving sleeve 6 and an end cover 8;
the driven sleeve 3 and the driving sleeve 6 are oppositely arranged to form a sleeve structure with a middle small-end cylinder, and the rectangular-section spring 4 is sleeved on the middle small-end cylinder; one end of the input shaft 5 is nested in a central round hole 6e of the driving sleeve 6 and fixedly connected with the same, one end of the output shaft 1 is nested in a central round hole 3e of the driven sleeve 3 and fixedly connected with the same, one end of the input shaft 5 embedded in the driving sleeve 6 is provided with a hole, and the small-end cylinder of the output shaft 1 embedded in the driven sleeve 3 is inserted into the hole of the input shaft 5; the end cover 8 is sleeved outside the driven sleeve 3, the driving sleeve 6 and the rectangular section spring 4;
the backstop of the aviation electric actuator in the embodiment of the invention transmits power through the driving sleeve 6 sleeved on the input shaft 5, the driven sleeve 3 sleeved on the output shaft 1 and the matching structures of the driven sleeve 3, the driving sleeve 6, the rectangular section spring 4 and the end cover 8.
In practical application, the check device for the avionic actuator provided by the embodiment of the invention further comprises: a first cylindrical pin 2 and a second cylindrical pin 7.
The output shaft 1 is fixedly connected with the driven sleeve 3 through a first cylindrical pin 2;
the input shaft 5 is fixedly connected with the driving sleeve 6 through a second cylindrical pin 7.
The following describes a specific implementation of the avionic actuator brake provided by the embodiment of the invention through a detailed description of components in the embodiment of the invention.
Fig. 2 is a schematic structural diagram of a driven sleeve in an avionic actuator backstop provided by an embodiment of the invention, and fig. 3 is a schematic three-dimensional structural diagram of the driven sleeve provided by the embodiment of the invention in fig. 2. Referring to fig. 2 and 3, a driven sleeve 3 in the embodiment of the present invention is a hollow stepped shaft structure having a central circular hole 3e, a first step is a large-end cylinder, a pin hole 3d penetrating through the cylinder walls of the two sides is formed in the large-end cylinder, and a first cylindrical pin 2 penetrates through the pin hole 3d and a through hole in the output shaft 1 to fixedly connect the output shaft 1 and the driven sleeve 3; the second step is the circular arc cylinder, and the one end that circular arc cylinder one side lateral wall and main aspects cylinder are connected is provided with inner rectangle notch 3f, and the cylindrical one end of main aspects is kept away from to circular arc cylinder opposite side lateral wall is provided with outer end rectangle notch 3a, and makes the radial 180 symmetry settings of inner rectangle notch 3f and outer end rectangle notch 3 a.
It should be noted that the cylindrical diameter of the circular arc cylinder is smaller than that of the first step. As shown in FIG. 2, the upper half part of the left end of the arc-shaped cylindrical plane 3b is provided with an inner-end rectangular notch 3f, and the lower half part of the right end is provided with an outer-end rectangular notch 3 a.
Fig. 4 is a schematic structural diagram of a driving sleeve in an avionic actuator backstop provided by an embodiment of the invention, and fig. 5 is a schematic three-dimensional structural diagram of the driving sleeve provided by the embodiment of the invention in fig. 4. Referring to fig. 4 and 5, the driving sleeve 6 in the embodiment of the present invention is a hollow stepped shaft structure having a central circular hole 6e, the first step is a large-end cylinder, a pin hole 6c penetrating through the cylinder walls of the two sides is formed in the large-end cylinder, and a second cylindrical pin 7 penetrates through the pin hole 6c and a through hole in the input shaft 5 to fixedly connect the input shaft 5 and the driving sleeve 6; the second step is an arc cylinder, and the diameter of the cylinder of the arc cylinder is smaller than that of the cylinder of the first step.
Fig. 6 is a schematic view of an assembly structure of a driven sleeve and a driving sleeve in an avionic actuator brake provided by an embodiment of the invention, and fig. 7 is a schematic view of a structure of a rectangular-section spring in the avionic actuator brake provided by an embodiment of the invention. Referring to fig. 6 and 7, the driven socket 3 and the driving socket 6 according to the embodiment of the present invention are assembled in a manner that:
driven sleeve 3 and the relative buckle cooperation of the circular arc cylinder of initiative sleeve 6 form that both ends have an open-ended tip cylinder respectively, an opening is located driven sleeve 3's main aspects cylinder inboard, another opening is located initiative sleeve 6's main aspects cylinder inboard, the tip cylinder outside that driven sleeve 3 and initiative sleeve 6 formed is established to rectangular cross section spring 4 cover, rectangular cross section spring 4's both ends have a boss respectively, two boss one-to-one are embedded into in two openings at tip cylinder both ends.
After the driven sleeve 3, the driving sleeve 6 and the rectangular-section spring 4 are installed, the inner side end face 3c of the large-end cylinder of the driven sleeve 3 is attached to one side end face 4h of the rectangular-section spring 4, and the inner side end face 6b of the large-end cylinder of the driving sleeve 6 is attached to the other side end face 4g of the rectangular-section spring 4;
in addition, the outer cylindrical surface 4g of the circular arc cylinder of the driven sleeve 3 is attached to the rectangular-section spring inner hole 4b, and the outer cylindrical surface 6f of the circular arc cylinder of the driving sleeve 6 is attached to the rectangular-section spring inner hole 4 b.
In an actual assembly structure, an outer end rectangular notch 3a of the driven sleeve 3 is in relative clearance fit with an outer side surface 4d of one boss of the rectangular-section spring 4, and an inner end rectangular notch 3f is in relative clearance fit with an outer side surface 4f of the other boss of the rectangular-section spring 4.
In addition, the arc-shaped cylindrical plane 6a on one side of the driving sleeve 6 is attached to the inner side surface 4c of one boss of the rectangular-section spring 4, and the arc-shaped cylindrical plane 6d on the other side is attached to the inner side surface 4e of the other boss of the rectangular-section spring 4.
Further, the circular arc cylindrical plane 3b of the driven socket 3 is opposed to the circular arc cylindrical planes 6a and 6d of both sides of the driving socket 6.
As shown in fig. 1, in the embodiment of the present invention, the end cover 8 is sleeved outside the large-end cylinders of the driven sleeve 3 and the driving sleeve 6, and the large-end cylinders are in small clearance fit with the inner holes of the end cover 8; the excircle of the spring 4 with the rectangular section is attached to the end cover 8.
The operation of the check device for an avionic actuator according to the above-described embodiment of the present invention will be described in detail below.
When the input shaft 5 rotates clockwise, the driving sleeve 6 fastened on the input shaft 5 drives the driven sleeve 3 fastened on the output shaft 1 to rotate and output, and meanwhile, the driving sleeve 6 fastened with the input shaft 5 drives the rectangular section spring 4 to contract inwards; similarly, when the input shaft 5 rotates in the counterclockwise direction, the driving sleeve 6 fastened to the input shaft 5 drives the driven sleeve 3 fastened to the output shaft 1 to rotate and output, and the driving sleeve 6 fastened to the input shaft 5 drives the rectangular section spring 4 to contract inwards.
The above described working mode is the normal working and non-braking condition. The operation of the brake will be described below.
When the output shaft 1 rotates clockwise, the driven sleeve 3 on the output shaft 1 drives the rectangular section spring 4 to expand outwards, friction torque is generated between the rectangular section spring 4 and the inner hole of the end cover 8 to transmit power provided by the output shaft 1 to the end cover 8, and therefore torque on the output shaft 1 is braked through the end cover 8.
When the output shaft 1 rotates counterclockwise, the driven sleeve 3 on the output shaft 1 drives the rectangular section spring 4 to expand outwards, friction torque is generated between the rectangular section spring 4 and the inner hole of the end cover 8, the power provided by the output shaft 1 is transmitted to the end cover 8, and therefore the torque on the output shaft 1 is braked through the end cover 8.
According to the backstop of the aviation electric actuator provided by the embodiment of the invention, through the output shaft 1 nested in the driven sleeve 3, the input shaft 5 nested in the driving sleeve 6, the assembly relation between the driven sleeve 3 and the driving sleeve 6, the transmission mode of the output shaft 1 and the input shaft 5 and the assembly relation between the rectangular section spring 4 and the external end cover 8 arranged on the integral structure, the backstop function is realized through the tensioning and contraction of the rectangular section spring, the structure is greatly simplified, the size is reduced, the weight is lightened, and the requirement of the aviation electric actuator is met.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. The utility model provides an aviation electric actuator backstop which characterized in that includes: the device comprises an output shaft (1), a driven sleeve (3), a rectangular section spring (4), an input shaft (5), a driving sleeve (6) and an end cover (8);
the driven sleeve (3) and the driving sleeve (6) are oppositely arranged to form a sleeve structure with a middle small-end cylinder, and the rectangular-section spring (4) is sleeved on the middle small-end cylinder; one end of the input shaft (5) is nested in a central round hole (6e) of the driving sleeve (6) and fixedly connected, one end of the output shaft (1) is nested in a central round hole (3e) of the driven sleeve (3) and fixedly connected, one end of the input shaft (5) embedded in the driving sleeve (6) is provided with a hole, and a small-end cylinder of the output shaft (1) embedded in the driven sleeve (3) is inserted into the hole of the input shaft (5); the end cover (8) is sleeved outside the driven sleeve (3), the driving sleeve (6) and the rectangular section spring (4);
the aviation electric actuator backstop is sleeved with a driving sleeve (6) on an input shaft (5) and a driven sleeve (3) on an output shaft (1) through a matching structure of the driving sleeve (6), the driven sleeve (3), the driving sleeve (6), a rectangular-section spring (4) and an end cover (8) to transmit power.
2. The avionic actuator backstop of claim 1, further comprising: a first cylindrical pin (2) and a second cylindrical pin (7);
the output shaft (1) is fixedly connected with the driven sleeve (3) through a first cylindrical pin (2);
the input shaft (5) is fixedly connected with the driving sleeve (6) through a second cylindrical pin (7).
3. The avionic actuator backstop of claim 2,
the driven sleeve (3) is of a hollow step shaft structure with a central circular hole (3e), the first step is a large-end cylinder, a pin hole (3d) penetrating through the cylinder walls of the cylinders on two sides is formed in the large-end cylinder, and the first cylindrical pin (2) penetrates through the pin hole (3d) and a through hole in the output shaft (1) to fixedly connect the output shaft (1) and the driven sleeve (3); the second step is an arc cylinder, one end of the side wall of one side of the arc cylinder, which is connected with the large-end cylinder, is provided with an inner-end rectangular notch (3f), one end of the side wall of the other side of the arc cylinder, which is far away from the large-end cylinder, is provided with an outer-end rectangular notch (3a), and the inner-end rectangular notch (3f) and the outer-end rectangular notch (3a) are radially and symmetrically arranged for 180 degrees; wherein, the cylinder diameter of the circular arc cylinder is smaller than the cylinder diameter of the first step.
4. The avionic actuator backstop of claim 3,
the driving sleeve (6) is of a hollow step shaft structure with a central round hole (6e), the first step is a large-end cylinder, a pin hole (6c) penetrating through the cylinder walls of the cylinders on two sides is formed in the large-end cylinder, and a second cylindrical pin (7) penetrates through the pin hole (6c) and a through hole in the input shaft (5) to fixedly connect the input shaft (5) and the driving sleeve (6); the second step is an arc cylinder, and the diameter of the cylinder of the arc cylinder is smaller than that of the cylinder of the first step.
5. The avionic actuator backstop of claim 4,
the relative buckle cooperation of the circular arc cylinder of driven sleeve (3) and initiative sleeve (6), it has an open-ended tip cylinder respectively to form both ends, an opening is located the main aspects cylinder inboard of driven sleeve (3), another opening is located the main aspects cylinder inboard of initiative sleeve (6), the tip cylinder outside that driven sleeve (3) and initiative sleeve (6) formed is established to rectangle cross-section spring (4) cover, the both ends of rectangle cross-section spring (4) have a boss respectively, two boss one-to-one are embedded into two openings at tip cylinder both ends.
6. The avionic actuator backstop of claim 5,
the inner side end face (3c) of the large-end cylinder of the driven sleeve (3) is attached to one side end face (4h) of the rectangular-section spring (4), and the inner side end face (6b) of the large-end cylinder of the driving sleeve (6) is attached to the other side end face (4g) of the rectangular-section spring (4);
the outer face of cylinder (4g) and the laminating of rectangular cross section spring hole (4b) of the circular arc cylinder of driven sleeve (3), outer face of cylinder (6f) and the laminating of rectangular cross section spring hole (4b) of the circular arc cylinder of initiative sleeve (6).
7. The avionic actuator backstop of claim 6,
the outer end rectangular notch (3a) of the driven sleeve (3) is in relative clearance fit with the outer side surface (4d) of one boss of the rectangular section spring (4), and the inner end rectangular notch (3f) is in relative clearance fit with the outer side surface (4f) of the other boss of the rectangular section spring (4);
and an arc cylinder plane (6a) at one side of the driving sleeve (6) is attached to the inner side surface (4c) of one boss of the rectangular-section spring (4), and an arc cylinder plane (6d) at the other side is attached to the inner side surface (4e) of the other boss of the rectangular-section spring (4).
8. The avionic actuator backstop of claim 7,
the end cover (8) is sleeved outside the large-end cylinders of the driven sleeve (3) and the driving sleeve (6), and the large-end cylinders are in small clearance fit with the inner holes of the end cover (8); the excircle of the spring (4) with the rectangular section is attached to the end cover (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011020527.2A CN112211974A (en) | 2020-09-25 | 2020-09-25 | Backstop for aviation electric actuator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011020527.2A CN112211974A (en) | 2020-09-25 | 2020-09-25 | Backstop for aviation electric actuator |
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| Publication Number | Publication Date |
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| CN112211974A true CN112211974A (en) | 2021-01-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011020527.2A Pending CN112211974A (en) | 2020-09-25 | 2020-09-25 | Backstop for aviation electric actuator |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113357286A (en) * | 2021-06-08 | 2021-09-07 | 北京航空航天大学 | Anti-jamming device of electromechanical actuator and jamming fault determination method |
| CN113839515A (en) * | 2021-09-30 | 2021-12-24 | 兰州万里航空机电有限责任公司 | Dual-redundancy roller screw pair actuator with anti-reversion mechanism |
| CN115095240A (en) * | 2022-05-25 | 2022-09-23 | 兰州万里航空机电有限责任公司 | Manual emergency cabin opening mechanism with double channels |
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| CN113839515A (en) * | 2021-09-30 | 2021-12-24 | 兰州万里航空机电有限责任公司 | Dual-redundancy roller screw pair actuator with anti-reversion mechanism |
| CN115095240A (en) * | 2022-05-25 | 2022-09-23 | 兰州万里航空机电有限责任公司 | Manual emergency cabin opening mechanism with double channels |
| CN115095240B (en) * | 2022-05-25 | 2023-08-15 | 兰州万里航空机电有限责任公司 | Two-channel manual emergency cabin opening mechanism |
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Application publication date: 20210112 |
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