CN112793764A

CN112793764A - Linkage mechanism for airplane pedal

Info

Publication number: CN112793764A
Application number: CN202110298416.6A
Authority: CN
Inventors: 王威; 石雅丹
Original assignee: Kunshan Hangli Airborne Equipment Co ltd
Current assignee: Kunshan Hangli Airborne Equipment Co ltd
Priority date: 2021-03-19
Filing date: 2021-03-19
Publication date: 2021-05-14
Anticipated expiration: 2041-03-19
Also published as: CN112793764B

Abstract

The application relates to an airplane pedal linkage mechanism, which comprises a base and a pedal arranged on one side of the base; the two pedals are arranged, an installation part is arranged between the two pedals, and the two pedals are both connected with the installation part; the mounting part is rotatably arranged on the base; one side of the base is also provided with a linear displacement sensor for measuring the displacement of one of the pedals. The airplane pedal linkage mechanism has high operation convenience, effectively reduces the probability of misoperation of a pilot, and is convenient for training and learning; the complexity of an airplane control system is effectively reduced, and the failure rate is favorably reduced; and has high operation accuracy.

Description

Linkage mechanism for airplane pedal

Technical Field

The invention relates to the technical field of airplane control equipment, in particular to an airplane pedal linkage mechanism.

Background

Aircraft maneuvering systems typically include manual maneuvering and automated control systems. The manual control system can be divided into a main control system and an auxiliary control system, wherein the main control system comprises a steering column (or steering wheel) for controlling an elevator of the airplane and a foot pedal for controlling a rudder of the airplane, so as to control the flight track and the attitude of the airplane.

The two pedals of the airplane generally work independently and respectively control two different courses, when a driver pedals the left foot, the rudder deflects to the left, and the nose deflects to the left; otherwise, the machine head is deviated to the right.

Because the pilot needs two feet to control two pedals respectively when operating the aircraft to because two pedals are independent each other, consequently need set up comparatively complicated electron auxiliary control system on the aircraft and prevent two pedals mutual interference, consequently can increase aircraft control system's complexity and fault rate.

Simultaneously, to the pilot that experience is not enough, two pedals are mutually independent, and the pilot can trample two pedals simultaneously easily to increase the probability of maloperation, the convenience of operation is relatively poor, and the study degree of difficulty is higher.

Disclosure of Invention

In order to facilitate pilot operation and study, the complexity and the fault rate of an airplane control system are reduced, and the airplane pedal linkage mechanism is provided.

The application provides an aircraft pedal link gear adopts following technical scheme:

an airplane pedal linkage mechanism comprises a base and a pedal arranged on one side of the base; the two pedals are arranged, an installation part is arranged between the two pedals, and the two pedals are both connected with the installation part; the mounting part is rotatably arranged on the base; and one side of the base is also provided with a linear displacement sensor for measuring the displacement of one pedal.

Through adopting above-mentioned technical scheme, because two pedal used installation department rotate the setting on the base, consequently two pedal needs rotate simultaneously to two pedal moving direction are the same, consequently when the staff trampled a pedal and operates, another pedal can follow the linkage, makes the pilot be difficult for carrying out the maloperation, is convenient for train and study. On the other hand, because two pedals are linked, the linear displacement sensor only needs to measure the displacement of one pedal during operation, and the complexity of the aircraft control system is effectively reduced, so that the failure rate is reduced.

Preferably, the mounting part comprises a mounting seat rotatably arranged on the base and a main connecting rod arranged on the mounting seat, one end of the main connecting rod extends to one side of the mounting seat, and the other end of the main connecting rod extends to the other side of the mounting seat; the two pedals are respectively arranged at two ends of the main connecting rod.

Through adopting above-mentioned technical scheme, two steps on through main connecting rod interconnect for two steps on can form an organic whole, thereby the pilot operation of being convenient for.

Preferably, the main connecting rod comprises two first supporting rods respectively arranged at two sides of the mounting seat; one end of the first support rod is hinged with the mounting seat; and an adjusting component used for adjusting an included angle between the two first supporting rods and fixing the first supporting rods on the mounting seat is arranged on the mounting seat.

Through adopting above-mentioned technical scheme, two first jibs can rotate relatively, are convenient for adjust the contained angle between two first jibs to change pedal initial position, the pilot operation of the difference of being convenient for is pedal.

Preferably, the adjusting assembly comprises an adjusting screw rotatably arranged on the mounting seat and a connecting block in threaded fit with the adjusting screw; the adjusting screw rod is positioned between the two first supporting rods; the connecting block is arranged on the mounting seat in a sliding manner; two all be provided with the push rod between first branch and the connecting block, the both ends of push rod are articulated with connecting block and first branch respectively.

Through adopting above-mentioned technical scheme, rotate adjusting screw, adjusting screw drives the connecting block and removes, and the connecting block drives two first branchs through the push rod and rotates simultaneously again, and the pilot of being convenient for operates.

Preferably, one side of the main connecting rod is provided with an auxiliary connecting rod, the auxiliary connecting rod comprises two second supporting rods, the two second supporting rods are respectively positioned at two sides of the mounting seat, and one end of each second supporting rod is hinged with the base; a third supporting rod is arranged between the second supporting rod and the first supporting rod, and the first supporting rod and the second supporting rod are hinged with the third supporting rod; the pedal is arranged on the third supporting rod.

Through adopting above-mentioned technical scheme, form four-bar linkage between first branch, second branch, third branch and the mount pad, stability when can effectively guaranteeing pedal removal to can improve the pedal linkage's of aircraft intensity, promote the pedal linkage's of aircraft life-span. And the two second struts work independently to facilitate adjustment of the angle between the two first struts.

Preferably, a parallelogram four-bar mechanism is formed among the first support bar, the second support bar, the third support bar and the mounting seat.

Through adopting above-mentioned technical scheme, when pedal the removal, the orientation that can guarantee pedal by parallelogram four-bar linkage's setting does not change, consequently the pilot only need to step on pedal to a direction can to pedal more easily with pilot's instep laminating, the pilot's of being convenient for operation.

Preferably, the pedal is hinged to the third supporting rod, a first return spring is further arranged between the pedal and the third supporting rod, and two ends of the first return spring are connected with the pedal and the third supporting rod respectively.

Through adopting above-mentioned technical scheme, pilot's instep is laminated with pedal surface more easily, and the pilot of being convenient for promotes the convenience of operation to pedal application of force.

Preferably, a reset assembly is arranged on one side of the base and comprises a fixed seat arranged on one side of the mounting part and a second reset spring arranged between the mounting part and the fixed seat; the two second return springs are arranged and are respectively positioned on two sides of the rotating axis of the mounting part; and two ends of the second reset spring are respectively arranged on the mounting part and the fixing seat.

Through adopting above-mentioned technical scheme, under second reset spring's effect, pedal can reset, and the staff of being convenient for controls the aircraft. And two second reset springs can guarantee the uniformity of two pedal atress, are convenient for guarantee the precision that pedal reset, promote the convenience of pilot's operation.

Preferably, the rotation axis both sides of installation department all are provided with the dead lever, two the dead lever and two second reset spring one-to-one, reset spring keeps away from and is provided with the installation pole between the one end of fixing base and the dead lever, the one end and the dead lever of installation pole are articulated, and the other end and second reset spring are connected.

Through adopting above-mentioned technical scheme, second reset spring is when flexible, and the dead lever can guarantee that second reset spring's orientation can not take place too big change, guarantees that second reset spring steadily works.

Preferably, the linear displacement sensor is positioned on one side of one of the mounting rods, the linear displacement sensor comprises a main body and a telescopic rod arranged on the main body, and the main body and the telescopic rod are parallel to the mounting rods; the main body is fixed on one side of the base; and a connecting plate is arranged between the telescopic rod and the mounting rod, and two ends of the connecting plate are respectively fixed on the mounting rod and the telescopic rod.

Through adopting above-mentioned technical scheme, linear displacement sensor can keep being parallel to each other with dead lever and second reset spring all the time at the during operation for the straight line is located the flexible volume that the sensor can the accurate measurement spring, thereby guarantees aircraft pedal interlock mechanism's operating accuracy.

In summary, the invention includes at least one of the following beneficial technical effects:

1. when a pilot steps on one pedal for operation, the other pedal is linked with the other pedal, so that the pilot cannot simultaneously step on the two pedals, the probability of misoperation of the pilot is reduced, and the training and learning are facilitated; in addition, because the two pedals are linked, the linear displacement sensor only needs to measure the displacement of one pedal during operation, thereby effectively reducing the complexity of the airplane control system and being beneficial to reducing the failure rate;

2. the first support rod, the second support rod, the third support rod and the mounting seat form a parallelogram four-bar mechanism, so that the stability of the pedal during movement can be effectively ensured; when the pedals move, the direction of the pedals is not changed, the foot surface of a pilot is more easily attached to the surfaces of the pedals, and the operation is convenient;

3. the linear displacement sensor can be always parallel to the fixed rod and the second return spring during working, so that the linear displacement sensor can accurately measure the extension amount of the spring, and the operation precision of the airplane pedal linkage mechanism is guaranteed.

Drawings

FIG. 1 is a schematic structural diagram of an aircraft step linkage mechanism in a top view in an embodiment of the present application;

FIG. 2 is a schematic structural view of an aircraft step linkage mechanism in a bottom view in an embodiment of the present application;

FIG. 3 is an enlarged partial schematic view of portion A of FIG. 2;

FIG. 4 is a schematic view for showing the connection relationship between the base, the mounting portion, the foothold and the adjustment assembly;

fig. 5 is a partially enlarged schematic view of a portion B in fig. 4.

In the drawings, the reference numbers: 1. a base; 2. an installation part; 21. a mounting seat; 211. a chute; 22. a rotating shaft; 23. a first support bar; 24. a second support bar; 25. a third support bar; 26. a first return spring; 27. fixing the rod; 3. pedaling; 4. a linear displacement sensor; 41. a main body; 42. a telescopic rod; 5. an adjustment assembly; 51. adjusting the screw rod; 52. connecting blocks; 53. a push rod; 54. a knob; 6. a reset assembly; 61. a fixed seat; 62. a second return spring; 63. mounting a rod; 64. a connecting plate.

Detailed Description

The present invention is described in further detail below with reference to figures 1-5.

The embodiment of the application discloses aircraft pedal interlock mechanism. Referring to fig. 1, the aircraft pedal linkage mechanism includes a base 1, a mounting portion 2 provided on the base 1, and a pedal 3 provided on the mounting portion 2. The mounting portion 2 is rotatably mounted on the base 1 such that the mounting portion 2 can rotate in the horizontal direction. The footholds 3 are provided in two, and the mounting portion 2 is located between the two footholds 3, so that when the pilot controls one of the footholds 3, the other foothold 3 is moved in synchronization. Base 1 one side is provided with linear displacement sensor 4, and linear displacement sensor 4 can measure one of them pedal 3 displacement volume to change pedal 3's displacement volume into the supplementary control system of electron that the signal of telecommunication transmitted for the aircraft, thereby accomplish controlling the aircraft.

Referring to fig. 2 and 3, the mounting part 2 includes a mounting seat 21 at an upper end of the base 1. The lower end of mount pad 21 is connected with pivot 22, and pivot 22 sets up vertically and installs on base 1 for mount pad 21 can rotate in the horizontal direction. The mounting seat 21 is provided with a main connecting rod, the main connecting rod comprises two first supporting rods 23, and the two first supporting rods 23 are respectively arranged on two sides of the mounting seat 21. One end of the first supporting rod 23 is hinged to the mounting base 21, and the other end extends to one side of the mounting base 21 in the horizontal direction.

Referring to fig. 4 and 5, one side of the main link is provided with an auxiliary link, the auxiliary link includes two second struts 24, and the two second struts 24 are also respectively located at two sides of the mounting seat 21, so that the two second struts 24 and the two first struts 23 are in one-to-one correspondence. The second struts 24 and the corresponding first struts 23 are parallel to each other. One end of the second strut 24 is connected to the base 1 by a mounting shaft, and the two second struts 24 are mounted on the same mounting shaft so that the axes of rotation of the two second struts 24 coincide. The end of the second strut 24 remote from the base 1 is provided with a third strut 25. The third strut 25 is located between the second strut 24 and the first strut 23, and the end of the first strut 23 and the end of the second strut 24 are both hinged with the third strut 25.

Referring to fig. 4, since the two first struts 23 are both mounted on the mounting seat 21, the first, second, third struts 23, 24, 25 and the mounting seat 21 constitute a parallelogram four-bar mechanism therebetween. The pedals 3 are arranged on the third strut 25 on the side of the first strut 23 facing away from the second strut 24 in order to facilitate the pilot's operation of the pedals 3.

Referring to fig. 4, the pedals 3 are hinged to the third support rod 25, a first return spring 26 is arranged between the pedals 3 and the third support rod 25, the first return spring 26 is a torsion spring, the first return spring 26 is sleeved on a hinge shaft between the pedals 3 and the third support rod 25, and two ends of the first return spring 26 are respectively fixed on the pedals 3 and the third support rod 25, so that the pedals 3 can automatically return after the pilot releases the pedals 3, and the next operation is facilitated.

Referring to fig. 4 and 5, the mounting seat 21 is provided with an adjusting assembly 5, the adjusting assembly 5 includes an adjusting screw 51 rotatably disposed on the mounting seat 21, the adjusting screw 51 is horizontally disposed, and the two first struts 23 are symmetrically distributed on two sides of the adjusting screw 51 in the length direction. The mounting base 21 is provided with a sliding groove 211, the sliding groove 211 is internally matched with a connecting block 52 in a sliding manner, and the adjusting screw 51 is threaded through the connecting block 52, so that the adjusting screw 51 can rotate to drive the connecting block 52 to move in the sliding groove 211 along the length direction of the adjusting screw 51. The end of the adjusting screw 51 is also fixed with a knob 54 for the pilot to operate.

Referring to fig. 5, push rods 53 are arranged between the two first support rods 23 and the connecting block 52, and two ends of each push rod 53 are hinged to the connecting block 52 and the first support rod 23, so that the connecting block 52 can drive the two first support rods 23 to rotate relatively when moving, and the adjustment of the included angle between the two first support rods 23 is completed. And when the adjusting screw 51 stops rotating, the two first supporting rods 23 can be fixed on the mounting seat 21, so that the normal operation of the aircraft pedal linkage mechanism is ensured.

Referring to fig. 1 and 2, a reset assembly 6 is arranged on one side of the base 1, and the reset assembly 6 comprises a fixed seat 61 arranged on one side of the auxiliary connecting rod, which is back to the main connecting rod. Fixed rods 27 are fixed on both sides of the rotation axis of the mounting part 2, and the fixed rods 27 are positioned right below the main link. Two second return springs 62 are provided between the holder 61 and the fixing rod 27. The two second return springs 62 correspond to the two fixing rods 27 one by one, and one ends of the two second return springs 62 are fixed on the fixing seat 61. A mounting rod 63 is also provided between the second return spring 62 and the fixing rod 27. One end of the mounting rod 63 is fixed at one end of the second return spring 62 far away from the fixed seat 61, and the other end of the mounting rod 63 is hinged with the fixed rod 27. Therefore, after the pilot releases the pedals 3, the pedals 3 can automatically reset under the action of the second return spring 62, and the operation and the control are convenient.

Referring to fig. 1 and 2, the linear displacement sensor 4 includes a main body 41 and an expansion link 42 provided on the main body 41, and the expansion link 42 is capable of expanding and contracting on the main body 41. The main body 41 is fixed to one side of the base 1 by a fixing member, and both the main body 41 and the telescopic rod 42 are parallel to the installation rod 63. A connecting plate 64 is provided between the end of the telescopic rod 42 and the mounting rod 63, and both ends of the connecting plate 64 are fixed to the mounting rod 63 and the telescopic rod 42, respectively, so that the telescopic rod 42 is fixed to the mounting rod 63.

The implementation principle of an aircraft pedal interlock mechanism in this application embodiment is: when the pilot operates pedal 3, pedal 3 produces the displacement, thereby the telescopic link 42 follows pedal 3's removal and produces flexible volume, and flexible volume transmits for main part 41, and main part 41 forms the signal of telecommunication and transmits the electron auxiliary control system for the aircraft according to telescopic link 42's flexible volume, accomplishes controlling of aircraft.

The embodiments of the present invention are preferred embodiments of the present invention, and the scope of the present invention is not limited by these embodiments, so: all equivalent changes made according to the structure, shape and principle of the invention are covered by the protection scope of the invention.

Claims

1. The utility model provides an aircraft pedal link gear which characterized in that: comprises a base (1) and a pedal (3) arranged on one side of the base (1); the number of the pedals (3) is two, the mounting part (2) is arranged between the two pedals (3), and the two pedals (3) are connected with the mounting part (2); the mounting part (2) is rotatably arranged on the base (1); one side of the base (1) is also provided with a linear displacement sensor (4) for measuring the displacement of one of the pedals (3).

2. An aircraft foot pedal linkage mechanism as claimed in claim 1, wherein: the mounting part (2) comprises a mounting seat (21) rotatably arranged on the base (1) and a main connecting rod arranged on the mounting seat (21), one end of the main connecting rod extends to one side of the mounting seat (21), and the other end of the main connecting rod extends to the other side of the mounting seat (21); the two pedals (3) are respectively arranged at two ends of the main connecting rod.

3. An aircraft foot pedal linkage mechanism as claimed in claim 2, wherein: the main connecting rod comprises two first supporting rods (23) which are respectively arranged on two sides of the mounting seat (21); one end of the first support rod (23) is hinged with the mounting seat (21); and the mounting seat (21) is provided with an adjusting component (5) which is used for adjusting an included angle between the two first supporting rods (23) and fixing the first supporting rods (23) on the mounting seat (21).

4. An aircraft foot pedal linkage mechanism as claimed in claim 3, wherein: the adjusting assembly (5) comprises an adjusting screw rod (51) rotatably arranged on the mounting seat (21) and a connecting block (52) in threaded fit with the adjusting screw rod (51); the adjusting screw (51) is positioned between the two first supporting rods (23); the connecting block (52) is arranged on the mounting seat (21) in a sliding manner; two all be provided with push rod (53) between first branch (23) and connecting block (52), the both ends of push rod (53) are articulated with connecting block (52) and first branch (23) respectively.

5. An aircraft foot pedal linkage mechanism as claimed in claim 3, wherein: an auxiliary connecting rod is arranged on one side of the main connecting rod and comprises two second supporting rods (24), the two second supporting rods (24) are respectively positioned on two sides of the mounting seat (21), and one end of each second supporting rod (24) is hinged to the base (1); a third supporting rod (25) is arranged between the second supporting rod (24) and the first supporting rod (23), and the first supporting rod (23) and the second supporting rod (24) are hinged with the third supporting rod (25); the pedal (3) is arranged on the third supporting rod (25).

6. An aircraft foot pedal linkage mechanism as claimed in claim 5, wherein: a parallelogram four-bar mechanism is formed among the first supporting rod (23), the second supporting rod (24), the third supporting rod (25) and the mounting seat (21).

7. An aircraft foot pedal linkage mechanism as claimed in claim 5, wherein: pedal (3) are articulated with third branch (25), still be provided with first reset spring (26) between pedal (3) and third branch (25), the both ends of first reset spring (26) are connected with pedal (3) and third branch (25) respectively.

8. An aircraft foot pedal linkage mechanism as claimed in claim 1, wherein: a reset assembly (6) is arranged on one side of the base (1), and the reset assembly (6) comprises a fixed seat (61) arranged on one side of the mounting part (2) and a second reset spring (62) arranged between the mounting part (2) and the fixed seat (61); the two second return springs (62) are arranged and are respectively positioned at two sides of the rotating axis of the mounting part (2); and two ends of the second return spring (62) are respectively arranged on the mounting part (2) and the fixed seat (61).

9. An aircraft foot pedal linkage as claimed in claim 8, wherein: the axis of rotation both sides of installation department (2) all are provided with dead lever (27), two dead lever (27) and two second reset spring (62) one-to-one, be provided with between one end and dead lever (27) that fixing base (61) were kept away from in second reset spring (62) and install pole (63), the one end and the dead lever (27) of installation pole (63) are articulated, and the other end is connected with second reset spring (62).

10. An aircraft foot pedal linkage as claimed in claim 9, wherein: the linear displacement sensor (4) is positioned on one side of one of the mounting rods (63), the linear displacement sensor (4) comprises a main body (41) and a telescopic rod (42) arranged on the main body (41), and the main body (41) and the telescopic rod (42) are parallel to the mounting rods (63); the main body (41) is fixed on one side of the base (1); a connecting plate (64) is arranged between the telescopic rod (42) and the mounting rod (63), and two ends of the connecting plate (64) are respectively fixed on the mounting rod (63) and the telescopic rod (42).