Aero seat actuating cylinder with limiting function

Abstract

The aero seat actuating cylinder with the limiting function comprises an actuating cylinder body, an actuating cylinder stroke shaft, a limiting bush, a base, a first connecting rod, a second connecting rod and a limiting ring, the actuating cylinder body is connected with the limiting bush through the actuating cylinder stroke shaft, the base is installed at the bottom of the limiting bush, and the limiting ring is installed on the base. The telescopic length of the actuator cylinder body on the actuator cylinder stroke shaft can be adjusted through the adjusting button, the inclination angle of the seat is determined according to the stroke of the actuator cylinder body, when the stroke of the actuator cylinder body changes, the first connecting rod and the second connecting rod cooperate with the movement of the actuator cylinder body in a folding mode, and after the actuator cylinder body is fixed, the seat is fixed. And the limiting ring is moved to the connecting position of the first connecting rod and the second connecting rod, so that the first connecting rod and the second connecting rod are kept in the same straight line state, the fixed distance is kept between the actuator cylinder body and the base, and then the failed aero seat can be kept in the upright posture all the time.

Description

Technical Field

[0001] The utility model relates to the field of aviation seat actuators, in particular to an aviation seat actuator with a limiting function. Background Art

[0002] The aircraft uses a seat adjustment mechanism to adjust the seat inclination angle to improve the passenger's riding comfort. Figure 1 As shown, the seat adjustment mechanism includes an adjustment button and a steel cable installed inside the armrest, an actuator body 100 installed at the aircraft backrest, a limit bushing 300 coaxially installed on the actuator stroke shaft 200, and a base 400. The adjustment button can adjust the telescopic length of the actuator body 100 on the stroke shaft 200, and the seat tilt angle is determined by the stroke of the actuator body 100. The actuator body 100 is retracted downward, and the backrest tilts backward; the actuator body 100 is extended upward, and the backrest is fixed in an upright position. When the seat adjustment mechanism fails, the actuator body 100 will usually be retracted and pressed against the limit bushing 300. At this time, the faulty seat is in a reclining state, which will affect the entry and exit of adjacent passengers and the safety of navigation. Therefore, when releasing the aircraft, the airline can only label the faulty seat to meet the airworthiness standard. At the same time, in order not to affect the entry and exit of passengers in other seats in the safety channel, the faulty seat needs to be fixed in an upright position through some temporary binding measures. However, temporary binding measures cannot effectively ensure that the faulty seat remains in an upright position for a long time, and it is also easy to be touched by other passengers, which is unstable and unsafe. Therefore, an aviation seat actuator with a limiting function is needed to ensure that the faulty seat remains in an upright position. Utility Model Content

[0003] 1. Technical issues to be resolved

[0004] In order to solve the above problems in the prior art, the utility model provides an aviation seat actuator with a limiting function.

[0005] (II) Technical solution

[0006] In order to achieve the above-mentioned purpose, the main technical solutions adopted by the utility model include:

[0007] An aviation seat actuator with a limiting function comprises an actuator body, an actuator stroke shaft, a limiting bushing, a base, a first connecting rod, a second connecting rod and a limiting ring;

[0008] The actuator body is connected to the limit bushing via an actuator stroke shaft;

[0009] The base is mounted on the bottom of the limit bushing;

[0010] A plurality of mounting grooves are equidistantly arranged along the circumferential direction at the bottom of the outer wall of the actuator body;

[0011] One end of the first connecting rod is hinged in the mounting groove, and the other end of the first connecting rod is hinged to the second connecting rod;

[0012] The end of the second connecting rod away from the first connecting rod is hinged to the limiting bushing;

[0013] When the limiting ring moves to the connection between the first connecting rod and the second connecting rod, a fixed distance is maintained between the actuator body and the base.

[0014] Preferably, a magnetic ring is arranged inside the limiting ring, and the limiting ring is magnetically attracted and fixed on the actuator body through the magnetic ring.

[0015] Preferably, a limiting rod is arranged on the second connecting rod. When the bottom of the limiting ring contacts the limiting rod, the limiting ring is located at the connection between the first connecting rod and the second connecting rod.

[0016] Preferably, a connection groove is formed on one side of the bottom of the first connecting rod close to the actuator stroke shaft. One end of the top of the second connecting rod is rotatably installed in the connection groove, and under the limitation of the groove wall on the side of the connection groove away from the actuator stroke shaft, the second connecting rod can only rotate towards the actuator stroke shaft.

[0017] (III) Beneficial effects

[0018] The beneficial effects of the present utility model are as follows: By adopting the above technical solution, the telescopic length of the actuator body on the actuator stroke shaft can be adjusted through the adjustment button. The tilt angle of the seat is determined by the stroke of the actuator body. When the stroke of the actuator body changes, the first connecting rod and the second connecting rod move in a folded manner to cooperate with the movement. After the actuator body is fixed, the limiting ring is moved to the connection between the first connecting rod and the second connecting rod, so that the first connecting rod and the second connecting rod are kept in a straight-line state, thereby keeping a fixed distance between the actuator body and the base, and further enabling the faulty aircraft seat to always maintain an upright posture. Description of the drawings

[0019] Figure 1 It is a schematic diagram of the working principle of the aircraft seat adjustment mechanism in the background technology;

[0020] Figure 2 It is a schematic structural diagram of an aircraft seat actuator with a limiting function;

[0021] Figure 3 It is a front view structural diagram of an aircraft seat actuator with a limiting function;

[0022] Figure 4 Schematic diagram of the usage state of an aircraft seat actuator with a limiting function Figure 1 ;

[0023] Figure 5 Schematic diagram of the usage state of an aircraft seat actuator with a limiting function Figure 2 ;

[0024] Figure 6 Schematic diagram of the connection structure of the first connecting rod and the second connecting rod

[0025] Explanation of reference numerals:

[0026] 100, actuator body;

[0027] 200, actuator stroke shaft;

[0028] 300, limiting bushing;

[0029] 400, base;

[0030] 500, first connecting rod; 501, connecting groove;

[0031] 600, second connecting rod;

[0032] 700, limiting ring;

[0033] 800, limiting rod. Detailed implementation manners

[0034] For better explaining the present invention for easy understanding, the present invention will be described in detail below with reference to the accompanying drawings through specific implementation manners.

[0035] Please refer to Figures 2 to 6 , the present invention provides an aircraft seat actuator with a limiting function, including an actuator body 100, an actuator stroke shaft 200, a limiting bushing 300, a base 400, a first connecting rod 500, a second connecting rod 600, and a limiting ring 700;

[0036] The actuator body 100 is connected to the limiting bushing 300 through the actuator stroke shaft 200;

[0037] The base 400 is installed at the bottom of the limiting bushing 300;

[0038] A plurality of installation grooves are equidistantly arranged along the circumferential direction at the bottom of the outer wall of the actuator body 100;

[0039] One end of the first connecting rod 500 is hinged in the installation groove, and the other end of the first connecting rod 500 is hinged to the second connecting rod 600;

[0040] One end of the second connecting rod 600 away from the first connecting rod 500 is hinged to the limiting bushing 300;

[0041] When the limiting ring 700 moves to the connection between the first connecting rod 500 and the second connecting rod 600, a fixed distance is maintained between the actuator body 100 and the base 400;

[0042] In use, the telescopic length of the actuator body 100 on the actuator stroke shaft 200 can be adjusted through the adjustment button. The tilt angle of the seat is determined by the stroke of the actuator body 100. When the stroke of the actuator body 100 changes, the first connecting rod 500 and the second connecting rod 600 move in a folded manner to cooperate with its movement. After the actuator body 100 is fixed, the limiting ring 700 is moved to the connection between the first connecting rod 500 and the second connecting rod 600, so that the first connecting rod 500 and the second connecting rod 600 are kept in a straight line state, thereby keeping a fixed distance between the actuator body 100 and the base 400, and further enabling the faulty aircraft seat to always maintain an upright posture.

[0043] In this embodiment, a magnetic ring is arranged inside the limiting ring 700. The limiting ring 700 is magnetically fixed on the actuator body 100 through the magnetic ring. The magnetically fixed limiting ring 700 is beneficial to be removed from the actuator body 100 and moved to the connection between the first connecting rod 500 and the second connecting rod 600.

[0044] In this embodiment, a limiting rod 800 is arranged on the second connecting rod 600. When the bottom of the limiting ring 700 contacts the limiting rod 800, the limiting ring 700 is located at the connection between the first connecting rod 500 and the second connecting rod 600. The arrangement of the limiting rod 800 is beneficial to quickly move the limiting ring 700 to the connection between the first connecting rod 500 and the second connecting rod 600.

[0045] In this embodiment, a connection groove 501 is formed on one side of the bottom of the first connecting rod 500 close to the actuator stroke shaft 200. One end of the top of the second connecting rod 600 is rotatably installed in the connection groove 501. And under the limitation of the groove wall on the side of the connection groove 501 away from the actuator stroke shaft 200, the second connecting rod 600 can only rotate towards the actuator stroke shaft 200. The arrangement of the connection groove 501 can prevent the second connecting rod 600 from flipping outwards, so as to better cooperate with the limiting ring 700 to realize the fixed limiting function of the first connecting rod 500 and the second connecting rod 600.

[0046] The working principle of the present utility model is as follows:

[0047] The telescopic length of the actuator body 100 on the actuator stroke shaft 200 can be adjusted by the adjustment button. The seat tilt angle is determined by the stroke of the actuator body 100. When the stroke of the actuator body 100 changes, the first connecting rod 500 and the second connecting rod 600 move in a folded manner to cooperate with its movement. After the actuator body 100 is fixed, the limit ring 700 is moved to the connection between the first connecting rod 500 and the second connecting rod 600, so that the first connecting rod 500 and the second connecting rod 600 are kept in a straight line state, thereby keeping a fixed distance between the actuator body 100 and the base 400, and further enabling the faulty aviation seat to always maintain an upright posture.

[0048] The circuits, electronic components and modules involved are all prior arts and can be fully realized by those skilled in the art without further elaboration. The content protected by the present utility model does not involve the improvement of software and methods either.

[0049] The above are only the embodiments of the present utility model, and thus do not limit the patent scope of the present utility model. Any equivalent transformation made by using the content of the specification and drawings of the present utility model, or directly or indirectly applied in the relevant technical fields, shall be similarly included in the patent protection scope of the present utility model.

[0050] In addition, it should be understood that although this specification is described according to the embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An aviation seat actuator with a limiting function, characterized in that: It includes an actuator body, an actuator stroke shaft, a limit bushing, a base, a first connecting rod, a second connecting rod and a limit ring; The actuator body is connected to the limit bushing via an actuator stroke shaft; The base is mounted on the bottom of the limit bushing; The bottom of the outer wall of the actuator body is provided with a plurality of mounting grooves at equal intervals along its circumference; One end of the first connecting rod is hinged in the mounting groove, and the other end of the first connecting rod is hinged to the second connecting rod; One end of the second connecting rod away from the first connecting rod is hinged on the limit bushing; When the limiting ring moves to the connection point between the first connecting rod and the second connecting rod, a fixed distance is maintained between the actuator body and the base.

2. The aviation seat actuator with a limiting function according to claim 1, characterized in that: A magnetic ring is arranged inside the limiting ring, and the limiting ring is fixed on the actuator cylinder body by magnetic attraction of the magnetic ring.

3. The aviation seat actuator with a position limiting function according to claim 1, characterized in that: A limiting rod is arranged on the second connecting rod. When the bottom of the limiting ring contacts the limiting rod, the limiting ring is located at the connection between the first connecting rod and the second connecting rod.

4. The aviation seat actuator with a position limiting function according to claim 1, characterized in that: A connecting groove is provided on the side of the bottom of the first connecting rod close to the stroke axis of the actuator cylinder, and one end of the top of the second connecting rod is rotatably installed in the connecting groove, and under the limitation of the groove wall on the side of the connecting groove away from the stroke axis of the actuator cylinder, the second connecting rod can only rotate in the direction of the stroke axis of the actuator cylinder.

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