Airplane turning angle feedback mechanism

Abstract

The invention belongs to the field of structural design, and particularly relates to an aircraft turning angle feedback mechanism which comprises a turning clamp, an angle sensor, a first connecting rod, a second connecting rod and a supporting column outer cylinder. The other end of the second connecting rod is hinged with the first connecting rod; the other end of the first connecting rod is hinged to a support of the supporting column outer cylinder, the upper end of the first connecting rod is fixedly connected with a position controller, and the position controller is connected with an angle sensor. When the airplane controls the front wheel to turn, the turning hoop drives the second connecting rod, the first connecting rod and the position controller to transmit a turning angle to the angle sensor, and the angle sensor transmits the turning angle to the cabin display according to a transmission ratio. The structure is simple, the size of the mechanism is small, the needed space is small, the weight is light, the feedback angle is accurate, and misjudgment of an operator on the turning angle caused by damage or precision deviation of one angle sensor is prevented; the structure cost is low.

Description

Technical Field

[0001] This application belongs to the field of structural design, and specifically relates to an aircraft turning angle feedback mechanism. Background Technology

[0002] To allow pilots to easily observe the angle the aircraft turns during a turn from the cockpit, a feedback mechanism is needed to relay this angle of the nose landing gear to them. To achieve this, a turning feedback mechanism is typically designed on the nose landing gear to provide feedback on the nose wheel's turning angle. However, current methods commonly use angle sensors to measure the nose wheel's turning angle. Since the nose wheel is located on the outside, this makes the angle sensor susceptible to damage or inaccuracy, leading to misjudgments of the turning angle by the operator.

[0003] Therefore, improving the accuracy of the front wheel turning angle feedback is a problem that needs to be solved. Summary of the Invention

[0004] The purpose of this application is to provide an aircraft turning angle feedback mechanism to solve the problem that existing front wheel turning angle feedback is prone to causing angle sensor damage or accuracy deviation, leading to misjudgment of the turning angle by the operator.

[0005] The technical solution of this application is: an aircraft turning angle feedback mechanism, including a turning clamp, an angle sensor, a first link, a second link, and a strut outer cylinder; the turning clamp is installed on the strut outer cylinder, one end of the second link is hinged to the turning clamp, and the other end is hinged to the first link; the other end of the first link is hinged to a support on the strut outer cylinder, and a position controller is fixedly connected to the upper end of the first link, the position controller can rotate with the first link, and an angle sensor is connected to the position controller; the strut outer cylinder can rotate relative to the first link, and the first and second links can rotate with the turning clamp.

[0006] Preferably, the first link, the second link, the position controller, and the angle sensor are all in two sets and are symmetrically arranged on both sides of the turning clamp along the symmetrical surface of the support.

[0007] Preferably, both the first link and the second link are circular arc bent rod structures, and the circular arc portions of the first link and the second link are arranged correspondingly to each other.

[0008] Preferably, the height of the second link gradually increases from the end of the turning clamp to the end of the first link, and the height of the first link gradually increases from the end of the second link to the end of the support cylinder of the column.

[0009] Preferably, there are two sets of supports, which are respectively located on the upper and lower sides of the turning clamp.

[0010] Preferably, a sliding ring is provided on the inner wall of the turning clamp, and a sliding groove is provided on the outer cylinder of the support column at the position corresponding to the turning clamp, which slides in cooperation with the sliding ring.

[0011] Preferably, both the first connecting rod and the second connecting rod are made of lightweight alloy material.

[0012] Preferably, the lightweight alloy is made of aluminum alloy or titanium alloy.

[0013] Preferably, the angle sensor's measurement range covers the maximum designed turning angle of the front wheels, and the resolution reaches within 0.1°.

[0014] Preferably, it also includes a signal amplifier, whose input is connected to the angle sensor and whose output is connected to the cockpit display.

[0015] The aircraft turn angle feedback mechanism of this application, when the aircraft maneuvers its nose wheel to turn, the turn clamp drives the second link, the second link pushes the first link, causing one end of the first link to rotate around the outer cylinder of the strut. This rotation transmits the turn angle to an angle sensor via a position controller. The angle sensor then transmits the turn angle to the cockpit display according to the transmission ratio, thus providing feedback to the pilot on the nose wheel turn angle. The mechanism features a simple structure, small size, minimal space requirements, and light weight. It provides accurate angle feedback and can achieve dual backup and mutual calibration functions, preventing misjudgments of the turn angle by the operator due to damage or inaccuracy of a single angle sensor. The structural cost is also low. Attached Figure Description

[0016] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0017] Figure 1 This is a schematic diagram of the overall structure of this application;

[0018] Figure 2 This is a cross-sectional view of the overall structure of this application.

[0019] 1. Turning clamp; 2. Angle sensor; 3. First link; 4. Second link; 5. Support outer cylinder; 6. Support. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] An aircraft turning angle feedback mechanism, such as Figures 1-2 As shown, the system includes a turning clamp 1, an angle sensor 2, a first connecting rod 3, a second connecting rod 4, and a support outer cylinder 5. The turning clamp 1 is mounted on the support outer cylinder 5. One end of the second connecting rod 4 is hinged to the turning clamp 1, and the other end is hinged to the first connecting rod 3. The other end of the first connecting rod 3 is hinged to a support 6 on the support outer cylinder 5. A position controller is fixed to the upper end of the first connecting rod 3, and the position controller can rotate with the first connecting rod 3. The angle sensor 2 is connected to the position controller. The support outer cylinder 5 can rotate relative to the first connecting rod 3, and the first connecting rod 3 and the second connecting rod 4 can rotate with the turning clamp 1.

[0022] When the aircraft maneuvers the nose wheel to turn, the turning clamp 1 drives the second link 4, the second link 4 pushes the first link 3, causing one end of the first link 3 to rotate around the outer cylinder 5 of the strut, and transmits the turning angle to the angle sensor 2 through the position controller. The angle sensor 2 transmits the turning angle to the cockpit display according to the transmission ratio, thereby realizing the function of feeding back the nose wheel turning angle to the pilot.

[0023] It features a simple structure, small size, small space requirement, light weight, and accurate feedback angle. It can achieve dual backup and mutual calibration functions to prevent the operator from misjudging the turning angle due to damage or accuracy deviation of one angle sensor 2. It also has low structural cost.

[0024] Preferably, the first link 3, the second link 4, the position controller and the angle sensor 2 are all in two sets and symmetrically arranged on both sides of the turning clamp 1 along the symmetrical surface of the support column, so as to realize dual position acquisition and improve accuracy.

[0025] Preferably, both the first link 3 and the second link 4 are circular arc bent rod structures, and the circular arc portions of the first link 3 and the second link 4 are arranged correspondingly to each other, so as to more efficiently bear the rotational torque.

[0026] Preferably, the height of the second link 4 gradually increases from the end of the turning clamp 1 to the end of the first link 3, and the height of the first link 3 gradually increases from the end of the second link 4 to the end of the support 6 of the outer cylinder 5 of the support column, so that the angle sensor 2 can be stably fixed on the support 6 of the outer cylinder 5 of the support column.

[0027] Preferably, there are two sets of supports 6, which are respectively located on the upper and lower sides of the turning clamp 1, so as to simultaneously limit the turning clamp 1.

[0028] Preferably, a sliding ring is provided on the inner wall of the turning clamp 1, and a sliding groove is provided on the outer cylinder 5 of the support column at the position corresponding to the turning clamp 1 to slide and cooperate with the sliding ring, so as to reduce the friction between the turning clamp 1 and the outer cylinder 5 of the support column.

[0029] Preferably, the first link 3 and the second link 4 are both made of lightweight alloy, such as aluminum alloy or titanium alloy, to reduce the weight of the overall mechanism.

[0030] Preferably, the angle sensor 2 has a measurement range that covers the maximum designed turning angle of the front wheel, and a resolution of less than 0.1°.

[0031] Preferably, it also includes a signal amplifier, whose input is connected to the angle sensor and whose output is connected to the cockpit display, for enhancing the strength of the electrical signal and filtering out interference noise.

[0032] Through the above design, this application has the following advantages:

[0033] 1. The entire mechanism is located within the space connecting the front landing gear turning clamp and the outer tube of the strut, occupying little space;

[0034] 2. Simple structure, reliable function, and convenient maintenance and inspection;

[0035] 3. Rigid connection and high precision.

[0036] Finally, it should be noted that the accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0037] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An aircraft turning angle feedback mechanism, characterized in that: The system includes a turning clamp (1), an angle sensor (2), a first connecting rod (3), a second connecting rod (4), and a support outer cylinder (5). The turning clamp (1) is installed on the support outer cylinder (5). One end of the second connecting rod (4) is hinged to the turning clamp (1), and the other end is hinged to the first connecting rod (3). The other end of the first connecting rod (3) is hinged to the support (6) of the support outer cylinder (5). A position controller is fixed to the upper end of the first connecting rod (3). The position controller can rotate with the first connecting rod (3). An angle sensor (2) is connected to the position controller. The support outer cylinder (5) can rotate relative to the first connecting rod (3). The first connecting rod (3) and the second connecting rod (4) can rotate with the turning clamp (1).

2. The aircraft turning angle feedback mechanism as described in claim 1, characterized in that: The first link (3), the second link (4), the position controller and the angle sensor (2) are all in two sets and are symmetrically arranged on both sides of the turning clamp (1) along the symmetrical surface of the support.

3. The aircraft turning angle feedback mechanism as described in claim 1, characterized in that: The first link (3) and the second link (4) are both circular arc bent rod structures, and the circular arc parts of the first link (3) and the second link (4) are arranged correspondingly to each other.

4. The aircraft turning angle feedback mechanism as described in claim 1, characterized in that: The height of the second link (4) gradually increases from the turning clamp (1) to the first link (3), and the height of the first link (3) gradually increases from the second link (4) to the support (6) of the outer cylinder (5) of the support column.

5. The aircraft turning angle feedback mechanism as described in claim 1, characterized in that: The support (6) consists of two sets, which are respectively located on the upper and lower sides of the turning clamp (1).

6. The aircraft turning angle feedback mechanism as described in claim 1, characterized in that: A sliding ring is provided on the inner wall of the turning clamp (1), and a sliding groove is provided on the outer cylinder (5) of the support column at the position corresponding to the turning clamp (1) to slide and cooperate with the sliding ring.

7. The aircraft turning angle feedback mechanism as described in claim 1, characterized in that: Both the first link (3) and the second link (4) are made of lightweight alloy.

8. The aircraft turning angle feedback mechanism as described in claim 7, characterized in that: The lightweight alloy is made of aluminum alloy or titanium alloy.

9. The aircraft turning angle feedback mechanism as described in claim 1, characterized in that: The angle sensor (2) has a measurement range that covers the maximum designed turning angle of the front wheel and a resolution of less than 0.1°.

10. The aircraft turning angle feedback mechanism as described in claim 1, characterized in that: It also includes a signal amplifier, whose input is connected to the angle sensor and whose output is connected to the cockpit display.

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