Aircraft pulley linkage boarding mechanism

Abstract

The utility model belongs to the field of aircraft structure design provides an aircraft pulley linkage boarding mechanism, including fuselage footwell mechanism 1, relay mechanism 2, ground footrest mechanism 3, the fuselage footwell mechanism 1 is used for pilot from wing footboard to enter aircraft cabin, and fixedly installs in the fuselage one side near wing place, ground footrest mechanism 3 is used for pilot from ground footboard to board aircraft wing, and fixedly installs in the fuselage one side abdomen position, the relay mechanism 2 is connected footrest device 3 and fuselage footwell mechanism 1, realizes the over device of linkage, is through the pulley 20 and the cable 22 connection ground footrest mechanism 3 and fuselage footwell mechanism 1, to realize boarding linkage and boarding device's automatic recovery, provides the use of the aircraft random boarding device for pilot and ground crew with simple structure, easy operation, not prone to jam, can realize automatic recovery, and does not influence the aircraft appearance aerodynamic characteristic.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft structural design, specifically relating to an aircraft pulley linkage boarding mechanism. Background Technology

[0002] Ground crew members need to use boarding stairs to maintain aircraft and for pilots to board and disembark. Boarding stairs are divided into regular boarding stairs and random boarding stairs. Random boarding stairs allow pilots and ground crew members to board and disembark the aircraft quickly and independently without relying on a dedicated boarding stairs. Boarding and disembarking are not affected by the parking environment and also provide convenience for maintenance personnel. Among the closest existing technologies, patent CN115973405A relates to an automatic retractable boarding device for small aircraft. It retracts automatically after being stepped on, eliminating the need for manual operation and facilitating boarding and disembarking for pilots or ground crew. However, its limiting strut assembly is complex, requires high precision, and is prone to jamming. Furthermore, it is only suitable for small aircraft and cannot accommodate personnel boarding and disembarking for higher-altitude aircraft. Patent CN206288227U relates to a folding and flipping random boarding ladder, designed to address the issue of conventional boarding ladders failing to meet the needs of pilots operating in harsh and complex field environments, particularly for military aircraft that frequently take off and land in the field. This boarding ladder has four steps, requiring significant installation space and has a complex structure. Additionally, one or two steps are prone to swaying due to being suspended, hindering ground crew and pilots from boarding and disembarking. Moreover, its retraction process requires manual operation and cannot achieve automatic retrieval. Therefore, current existing random boarding ladders suffer from problems such as complex structure, susceptibility to jamming, limited height, and inability to achieve automatic retrieval. Summary of the Invention

[0003] This invention proposes an aircraft pulley linkage boarding mechanism, which can effectively solve the technical problems of complex structure, easy jamming, unreliable boarding device, and inability to achieve automatic retrieval in random boarding ladders.

[0004] This utility model provides an aircraft pulley-linked boarding mechanism, including a fuselage footrest mechanism 1, a transition mechanism 2, and a ground footrest mechanism 3. The fuselage footrest mechanism 1, transition mechanism 2, and ground footrest mechanism 3 are all fixedly installed on the same side of the aircraft. The fuselage footrest mechanism 1 is used by the pilot to enter the aircraft cockpit from the wing footrest and is fixedly installed on one side of the fuselage near the wing. The ground footrest mechanism 3 is used by the pilot to board the aircraft wing from the ground footrest and is fixedly installed on one side of the fuselage near the belly. The transition mechanism 2 is a transitional device connecting the footrest mechanism 3 and the fuselage footrest mechanism 1 to achieve linkage. It connects the ground footrest mechanism 3 and the fuselage footrest mechanism 1 via a pulley 20 and a steel cable 22 to achieve boarding linkage and automatic retraction of the footrest mechanism.

[0005] Furthermore, the fuselage footrest mechanism 1 includes a corner box 10, a rocker arm 11, a planetary gear 12, a flip cover 13, a footrest box 14, a spring 15, and a hinge 16; the corner box 10 and the footrest box 14 are respectively fixedly installed on the fuselage frame edge and the belly plate of the aircraft. The corner box 10 is fixedly connected to the flip cover 13 through the hinge 16. The hinge 16, the spring 15, and the rocker arm 11 are connected in series by a pin. The rocker arm 11 is fixed between the spring and the hinge teeth. The planetary gear 12 is fixedly connected to the rotating shaft of the rocker arm 11.

[0006] Furthermore, the hinge 16 is divided into upper and lower hinges. The corner box 10 is fixedly connected to the upper hinge of the hinge 16, the flip cover 13 is fixedly connected to the lower hinge of the hinge 16, and the upper and lower ends of the spring 15 overlap with the upper and lower hinges of the hinge 16, respectively.

[0007] Furthermore, the planetary gear 12 includes a rocker arm 121 and a pendulum 122. The rocker arm 121 is fixed to the steel cable 22, and the pendulum 122 forms a motion pair with the boss 131 on the flip cover 13. The pendulum can roll along the boss.

[0008] Furthermore, the upper surface of the foot pedal box (14) has an anti-slip toothed structure.

[0009] Furthermore, the ground foot pedal mechanism 3 includes a gas spring 30, a connecting rod 34, a T-shaped sleeve 35, a pull rod 36, a support 37, and a foot pedal 39. One end of the gas spring 30 is fixedly connected to the aircraft fuselage frame plate, and the other end is fixed to the foot pedal 39. The foot pedal 39 is fixedly installed on the fuselage frame plate through the support 37, and the foot pedal 39 can rotate around the pivot of the support 37. The foot pedal 39 is equipped with a pull rod 36, which is inserted into the T-shaped sleeve 35 and can slide up and down along the inner wall of the sleeve. The other end of the sleeve 35 has a single ear, which is fixed to the fuselage frame plate through the connecting rod 34. A limit rod 32 and a compression spring 33 are installed on the vertical end face of the T-shaped sleeve 35, and the limit rod 32 is connected to the steel cable 22.

[0010] Furthermore, the gas spring 30 and the foot pedal 39 are fixedly connected by an earring bolt 38;

[0011] Furthermore, the pull rod 36 is mounted on the foot pedal 39, the foot pedal 39 has a double ear 391 at the pivot, and one end of the pull rod 36 has a single ear 361, which is inserted into the double ear 391 through pin for fixed connection.

[0012] Furthermore, the upper surface of the pedal 39 is the pedal stepping area 392, which has a toothed structure.

[0013] Furthermore, the transfer mechanism 2 includes pulleys 20, U-shaped corner pieces 21, steel cables 22, L-shaped supports 23, fixing rods 24, and small supports 25; wherein the small supports 26 are fixedly connected to the corner box 10 with rivets, and the L-shaped supports 23 and fixing rods 24 are fixedly installed on the aircraft fuselage frame; the pulleys 20 and U-shaped corner pieces appear in pairs, a total of 3 pairs, and are respectively installed on the small supports 26, L-shaped supports 23 and fixing rods 24, and the steel cables 22 pass through the 3 pulleys 20, one end is fixed to the rocker arm 121, and the other end is fixed to the limiting rod 32.

[0014] Beneficial effects of the invention

[0015] This utility model provides an aircraft with a random linkage boarding mechanism. It features a simple structure, easy operation, and is less prone to jamming. It is not limited by aircraft altitude and can achieve automatic recovery, greatly facilitating pilots and ground crew. Furthermore, it does not affect the aircraft's aerodynamic characteristics. Specific benefits include:

[0016] 1. This utility model, by setting up a ground foot pedal mechanism, keeps the foot pedal stable under the action of the limiting rod, preventing shaking, and the foot pedal stepping area is arranged with a toothed structure to increase friction and have an anti-slip effect, helping pilots or ground crew to board the wing.

[0017] 2. This utility model, by setting a footrest mechanism on the fuselage, allows the flip cover to rotate inwards under external force, and relevant personnel to step on the footrest box on the wing to enter the cockpit. At the same time, the protrusion on the flip cover pushes the planetary gear to rotate, thereby stretching the steel cable.

[0018] 3. This utility model achieves linkage between the ground foot pedal mechanism and the fuselage footrest mechanism by setting up a transfer mechanism. When relevant personnel complete boarding using the footrest device, the steel cable is stretched, and the pulley pulls the limit rod under the steering action. The limit rod disengages from the connecting rod, the foot pedal is unlocked, and the ground foot pedal mechanism is automatically retracted under the counter-pull action of the gas spring. This utility model is simple to use and operate, can be opened and closed at will, and does not affect the aerodynamic characteristics of the aircraft. It facilitates ground staff to board the aircraft for routine maintenance and pilots to board the aircraft. Moreover, by adjusting the length of the steel cable and the number of pulleys in the transfer mechanism, linkage between different positions of the ground foot pedal mechanism and the fuselage footrest mechanism can be achieved. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of a pulley-linked boarding mechanism;

[0020] Figure 2 This is a schematic diagram of the fuselage footrest mechanism;

[0021] Figure 3 This is a schematic diagram of the transfer mechanism;

[0022] Figure 4 This is a schematic diagram of the ground foot pedal mechanism;

[0023] Figure 5 This is a diagram showing the foot pedal, flip cover, and planetary gears;

[0024] Figure 6 This is a schematic diagram of the opening of the aircraft's pulley-linked boarding mechanism;

[0025] Figure 7 This is a diagram illustrating the retraction of an airplane's pulley-linked boarding mechanism;

[0026] Figure 8 This is a schematic diagram of the installation of an aircraft pulley-linked boarding mechanism;

[0027] Among them, 1—body footrest mechanism, 10—corner box, 11—rocker arm, 12—planetary gear, 13—flip cover, 14—foot pedal box, 15—spring, 16—hinge, 121—crank handle, 122—circular pendulum, 131—protrusion

[0028] 2—Transfer mechanism, 20—Pulley, 21—U-shaped corner piece, 22—Steel cable, 23—L-shaped support, 24—Fixed rod, 25—Small support.

[0029] 3—Ground foot pedal mechanism, 30—Gas spring, 31—Screw cap, 32—Limit rod, 33—Compression spring, 34—Connecting rod, 35—L-shaped sleeve, 36—Pull rod, 37—Support, 38—Earring bolt, 39—Foot pedal, 321

[0030] —Limiting rod ramp, 361—Single ear, 362—Pull rod ramp, 391—Double ear, 392—Step area.

[0031] 4-9 upper half frame, 5-floor, 6-9 lower half frame, 7-8 frame, 8-7 frame, 9-6 frame. Detailed Implementation

[0032] This section describes embodiments of the present invention, used to explain and illustrate the technical solutions of the present invention. Unless otherwise specified, the embodiments and features described herein can be combined with each other.

[0033] The specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples. The following examples are used to illustrate this utility model, but are not intended to limit its scope.

[0034] like Figures 1-5As shown, the aircraft pulley linkage boarding mechanism of this utility model consists of a fuselage footrest mechanism 1, a transfer mechanism 2, and a ground foot pedal mechanism 3. The fuselage footrest mechanism 1 is installed on the left side of the fuselage frame 6-7 near the wing and includes a corner box 10, a rocker arm 11, a planetary gear 12, a flip cover 13, a foot pedal box 14, a spring 15, and a hinge 16. The corner box 10 and footrest box 14 are positioned according to the fuselage height and personnel accessibility. The corner box 10 is used for the support installation of the transfer mechanism and to improve the structural rigidity. The footrest box 14 is used by the pilot to step on it. The upper surface of the footrest box (14) has an anti-slip toothed structure and is riveted to the frame edge and web plate of the fuselage frame 6 and frame 7 respectively. The hinge 16 is divided into upper and lower hinges. After the hinge 16, spring 15 and rocker arm 11 are connected together by a pin, the upper hinge is riveted to the corner box 10 and the lower hinge is riveted to the flip cover 13. The upper and lower ends of the two springs 15 overlap with the upper and lower hinges respectively. The rocker arm 11 is installed between the spring and the hinge teeth near the frame 7. Planetary gear 12 is mounted on the pivot of rocker arm 11 and includes rocker arm 121 and pendulum 122. One end of rocker arm 121 is fixed with steel cable 22. Pendulum 122 and boss 131 on flip cover 13 form a kinematic pair, and pendulum can roll along boss. When flip cover 13 flips inward under external force, boss 131 pushes pendulum 122 to rotate, planetary gear rotates, rocker arm 121 winds steel cable 22, and finally unlocks foot pedal 39, and foot pedal returns to its original position. After the force is released, under the reaction force of spring, flip cover returns to its original position and overlaps the frame edges of frames 6 and 7 of fuselage.

[0035] like Figure 3 As shown, the adapter mechanism 2 is installed in the left side structure of frame 6-9 of the fuselage, including pulleys 20, U-shaped corner pieces 21, steel cables 22, L-shaped supports 23, fixing rods 24, and small supports 25. The small supports 25 are riveted to the corner box 10, the L-shaped supports 23 are riveted to the web plate of the upper half frame 4 of frame 9, and the fixing rods 24 are fixed to the web plate of the lower half frame 6 of frame 9 by nuts. The pulleys 20 and U-shaped corner pieces appear in pairs, a total of 3 pairs. One pair is fixed to the small supports 25 by bolt and nut assembly, one pair is fixed to the L-shaped supports 23 by nuts, and one pair is fixed to the fixing rods 24 by nuts. The steel cables 22 are rotated by the 3 pulleys 20, one end is fixed to the rocker arm 121, and the other end is fixed to the limiting rod 32.

[0036] like Figure 4As shown, the ground foot pedal mechanism 3 is installed on the left side of the fuselage frame 8-9, and includes a gas spring 30, a screw cap 31, a limiting rod 32, a compression spring 33, a connecting rod 34, a T-shaped sleeve 35, a pull rod 36, a support 37, an ear bolt 38, and a foot pedal 39. One end of the gas spring 30 is fixed to the rib of the fuselage frame 8 via a bolt and nut assembly, and the other end is fixed to the ear bolt 38 via the bolt and nut assembly. The ear bolt 38 is fixed to the foot pedal 39 via a nut. The foot pedal 39 is fixed to the support 37 via a bolt and nut assembly and rotates around the support's pivot. The support 37 is fixed to the web plate of the lower half of the fuselage frame 9 via bolts and nuts. The foot pedal 39 has double ears 391 at its pivot, and the lower end of the pull rod 36 has a single ear 361. The single ear 361 is inserted into the double ears 391 and fixed by a pin. The pull rod 36 is installed at the bottom of the T-shaped sleeve 35 and can slide up and down along the inner wall of the sleeve. Screw caps 31 are screwed to both ends of the sleeve 35. Limiting rod 32 and compression spring 33 are installed at the other end of the sleeve 35. Compression spring 33 is used to reset the limiting rod 32. A single ear extends from one end of the bottom of the sleeve 35 and is fixed to the connecting rod 34 by a nut. The other end of the connecting rod 34 is fixed to the web plate of the lower half frame of the machine body 9 by a nut.

[0037] like Figures 2-5 As shown, in this utility model, an aircraft pulley-linked boarding mechanism, the gas spring 30 is in a retracted state within its stroke, pulling the foot pedal 39 back to its original position. The U-shaped corner piece 21 is used to prevent the steel cable 22 from detaching from the pulley 20. The foot pedal area 392 has a toothed structure, which has an anti-slip function to prevent people from slipping. Among the three devices, the ground foot pedal mechanism 3 is installed on the left side of the fuselage frame 8-9, which is used by pilots or ground crew to climb onto the wing. The fuselage footrest mechanism 1 is installed on the left side of the fuselage frame 6-7 near the wing, which is used by people to enter the aircraft cockpit from the wing. The transition mechanism 2 is a transition device that connects the ground foot pedal mechanism 3 and the fuselage footrest mechanism 1 through the pulley 20 and the steel cable 22, realizing the linkage between the fuselage footrest mechanism 1 and the boarding ladder device 3. The steel cable 22 pulls the limit rod 32. Under the counter-pull of the gas spring 30, the pull rod 36 disengages from the limit rod 32, the foot pedal 39 returns to its original position, and the foot pedal device completes automatic retraction.

[0038] Installation embodiments of this utility model: such as Figure 8As shown, firstly, according to the positioning requirements, the fuselage footrest mechanism 1 in the linkage boarding device is installed on the fuselage frames 6 and 7 respectively by rivets, thus completing the installation of the fuselage footrest mechanism; secondly, the ground foot pedal mechanism 3 is fixed to the support, connecting rod and gas spring on the web plate of the lower half frame of the fuselage frames 8 and 9 respectively by bolt and nut assembly, thus completing the installation of the ground foot pedal mechanism 3; finally, the adapter mechanism 2 is riveted to the small support and L-shaped support on the corner box and the upper half frame of the fuselage frame 9 by rivets, the fixing rod is fixed to the web plate of the lower half frame of the fuselage frame 9 by nuts, the steel cable passes through the floor, and the two ends are tied to the planetary gear and the limit rod with anti-detachment measures, thus completing the installation of the adapter mechanism. After each device is installed in place, the linkage boarding device of this utility model is installed.

[0039] Examples of application of this utility model: Figures 6-7 As shown, when pilots or ground crew members board or disembark, they pull the foot pedal 39 outwards from the fuselage. The foot pedal rotates around the pivot of the support 37, extending the gas spring 30. The protruding double ears 391 on the foot pedal push the lever 36 upwards along the L-shaped sleeve 35 through the single ear 361 on the lever 36 until the lever's inclined surface 362 contacts the inclined surface 321 of the limit rod 32. The lever continues to slide along the inclined surface 321 of the limit rod, compressing the compression spring 33. The limit rod slides upwards until the inclined surface of the lever disengages from the inclined surface of the limit rod. At this point, due to the spring's rebound, the limit rod engages with the lever, fixing the foot pedal in a stable state. The foot pedal device is activated, and pilots or ground crew members can board the aircraft wing using the foot pedal area 392 of the boarding ladder. After boarding the aircraft, the pilot or ground crew enters the cockpit by stepping on the footrest box 14 in the footrest device. At the same time, as the footrest cover 13 flips inward, the protrusion 131 on the cover slides relative to the pendulum 122 on the planetary gear 12. The planetary gear rotates, and the crank 121 winds the steel cable 22. The steel cable, with the help of the pulley 20, pulls the limit rod, compresses the compression spring, and causes the limit rod to disengage from the pull rod. Due to the retraction of the gas spring, the footrest is pulled in the opposite direction to rotate, causing the pull rod to completely disengage from the limit rod, and the footrest is retracted. At the same time, due to the rebound of the compression spring and the spring 15, the components of the footrest device return to their original positions, and the boarding device returns to the retracted position.

[0040] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the scope of protection of this application is intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application. Obviously, those skilled in the art can make various alterations and variations to this application without departing from the spirit and scope of this application. Thus, if these modifications and variations of this application fall within the scope of protection of this application and its equivalents, this application also intends to include these modifications and variations.

Claims

1. An aircraft pulley-linked boarding mechanism, characterized in that... It includes a fuselage footrest mechanism (1), a transfer mechanism (2), and a ground footrest mechanism (3); the fuselage footrest mechanism (1), the transfer mechanism (2), and the ground footrest mechanism (3) are all fixedly installed on the same side of the aircraft; The fuselage footrest mechanism (1) is used for the pilot to enter the aircraft cockpit from the wing footrest and is fixedly installed on one side of the fuselage near the wing; The ground foot pedal mechanism (3) is used by the pilot to step onto the aircraft wing from the ground and is fixedly installed on the belly side of the fuselage. The transfer mechanism (2) is a transitional device that connects the ground foot pedal mechanism (3) and the fuselage footrest mechanism (1) to achieve linkage. It connects the ground foot pedal mechanism (3) and the fuselage footrest mechanism (1) through pulleys (20) and steel cables (22) to achieve boarding linkage and automatic retrieval of the boarding device.

2. The aircraft pulley linkage boarding mechanism according to claim 1, characterized in that... The fuselage footrest mechanism (1) includes a corner box (10), a rocker arm (11), a planetary gear (12), a flip cover (13), a footrest box (14), a spring (15), and a hinge (16). The corner box (10) and the footrest box (14) are respectively fixedly installed on the fuselage frame edge and the belly plate. The corner box (10) is fixedly connected to the flip cover (13) through the hinge (16). The hinge (16), the spring (15), and the rocker arm (11) are connected in series through a pin. The rocker arm (11) is fixed between the spring and the hinge teeth. The planetary gear (12) is fixedly connected to the rotating shaft of the rocker arm (11).

3. An aircraft pulley linkage boarding mechanism according to claim 2, wherein The hinge (16) is divided into upper and lower hinges. The corner box (10) is fixedly connected to the upper hinge of the hinge (16), the flip cover (13) is fixedly connected to the lower hinge of the hinge (16), and the upper and lower ends of the spring (15) are respectively connected to the upper and lower hinges of the hinge (16).

4. An aircraft pulley linkage boarding mechanism according to claim 2, wherein The planetary gear (12) includes a rocker arm (121) and a pendulum (122). The rocker arm (121) is fixed to the steel cable (22). The pendulum (122) and the boss (131) on the flip cover (13) form a kinematic pair. The pendulum can roll along the boss.

5. The aircraft pulley linkage boarding mechanism according to claim 2, characterized in that... The upper surface of the foot pedal box (14) has an anti-slip toothed structure.

6. An aircraft pulley linkage boarding mechanism according to claim 1 wherein The ground foot pedal mechanism (3) includes a gas spring (30), a connecting rod (34), a T-shaped sleeve (35), a pull rod (36), a support (37), and a foot pedal (39). One end of the gas spring (30) is fixedly connected to the aircraft fuselage frame plate, and the other end is fixed to the foot pedal (39). The foot pedal (39) is fixedly installed on the fuselage frame plate through the support (37). The foot pedal (39) can rotate around the pivot of the support (37). The foot pedal (39) is equipped with a pull rod (36). The pull rod (36) is inserted into the T-shaped sleeve (35) and can slide up and down along the inner wall of the sleeve. The other end of the sleeve (35) has a single ear that is fixed to the fuselage frame plate through the connecting rod (34). The vertical end face of the T-shaped sleeve (35) is equipped with a limit rod (32) and a compression spring (33). The limit rod (32) is connected to the steel cable (22).

7. An aircraft pulley linkage boarding mechanism according to claim 6, wherein The pull rod (36) is installed on the pedal (39). The pedal (39) has a double ear (391) at the pivot. One end of the pull rod (36) has a single ear (361). The single ear (361) is inserted into the double ear (391) through pin for fixed connection.

8. An aircraft pulley linkage boarding mechanism according to claim 5, wherein The upper surface of the pedal (39) is the pedal stepping area (392), which has a toothed structure.

9. An aircraft pulley linkage boarding mechanism according to claim 1 wherein The transfer mechanism (2) includes pulleys (20), U-shaped corner pieces (21), steel cables (22), L-shaped supports (23), fixing rods (24), and small supports (25); wherein the small supports (25) are rivet-fixed to the corner box (10), and the L-shaped supports (23) and fixing rods (24) are fixedly installed on the aircraft fuselage frame; the pulleys (20) and U-shaped corner pieces appear in pairs, a total of 3 pairs, and are respectively installed on the small supports (25), L-shaped supports (23) and fixing rods (24). The steel cables (22) pass through the 3 pulleys (20), one end is fixed to the rocker arm (121), and the other end is fixed to the limiting rod (32).

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