Self-locking lifting system for lifting equipment in cabin

Abstract

The self-locking lifting system comprises a rocker arm rotationally arranged on a machine and a drag parachute bay, an L-shaped connecting rod is arranged between the rocker arm and the drag parachute bay, and the two ends of the L-shaped connecting rod are connected with the rocker arm and the drag parachute bay through hinges respectively. The machine is provided with a high-speed rotation actuator used for driving the rocker arm to rotate. The device has the beneficial effects that high-speed lifting of equipment in the cabin and self-locking of the lifting position and the embedding position are achieved, and a position locking mechanism does not need to be additionally arranged.

Description

Technical Field

[0001] The invention relates to the technical field of flight equipment, in particular to a self-locking lifting system used for lifting equipment in a cabin. Background Art

[0002] During the flight of an aircraft, in order to ensure the aerodynamic shape of the aircraft, the equipment used under specific flight conditions of the aircraft is buried in the fuselage. When needed, the equipment in the cabin is raised to a specified height and locked through the lifting system.

[0003] At present, the lifting and lowering of the drag parachute cabin of fixed-wing aircraft mostly adopts a hydraulic cylinder (or electric cylinder) and a locking device to form a lifting system. When the drag parachute cabin is raised, the combined load reaches the maximum due to the aerodynamic load and the drag parachute pulling force, and there is a tendency for the drag parachute cabin to be buried in the aircraft body. In order to overcome the drag parachute pulling force and aerodynamic load, a locking device is often installed at the raised position.

[0004] When the drag parachute cabin is buried in the fuselage, the hydraulic cylinder (or electric cylinder) needs to lock the drag parachute cabin to prevent the drag parachute cabin from rising and damaging the aerodynamic shape of the aircraft. In order to reliably hold the drag parachute cabin, a locking device is often used to lock it. Therefore, existing mechanisms often use one set of lifting devices and two sets of locking devices to achieve the lifting of equipment in the cabin. Summary of the invention

[0005] The purpose of the present invention is to overcome the shortcomings of the prior art and to propose a self-locking lifting system for lifting equipment in a cabin, which realizes high-speed lifting of the equipment in the cabin and self-locking of the lifting position and the buried position without the need for an additional position locking mechanism.

[0006] The objective of the present invention is achieved through the following technical solutions: a self-locking lifting system for lifting equipment in a cabin, comprising a rocker arm and a drag parachute compartment rotatably arranged on the aircraft, an L-shaped connecting rod is arranged between the rocker arm and the drag parachute compartment, the two ends of the L-shaped connecting rod are respectively connected to the rocker arm and the drag parachute compartment for rotation, and a high-speed rotary actuator for driving the rocker arm to rotate is arranged on the aircraft.

[0007] The drag parachute compartment is rotatably connected with the aircraft through a parachute compartment rotating hinge.

[0008] The L-shaped connecting rod is provided with a connecting rod hinge, and the connecting rod hinge is rotatably connected to the drag parachute cabin.

[0009] The L-shaped connecting rod is provided with a connecting rod adjusting nut for adjusting the pre-tightening force of the device embedded in the machine body.

[0010] A hinge pin is arranged at one end of the L-shaped connecting rod, and the rocker arm is rotatably sleeved on the hinge pin.

[0011] The rocker arm is fixedly sleeved with a rocker arm shaft at one end away from the L-shaped connecting rod, and the output end of the high-speed rotary actuator is connected to the rocker arm shaft.

[0012] It also includes a first fixed upper limit block and a second fixed upper limit block provided on the machine; When the drag parachute cabin is raised to the highest point, the rocker arm contacts the upper limit block of the first fixed machine, and the line connecting the rotation centers of the two ends of the L-shaped connecting rod and the end of the rocker arm away from the L-shaped connecting rod should be greater than 180° and less than 185°; When the drag parachute compartment is lowered to the lowest point, the rocker arm abuts against the upper limit block of the second fixed machine, and the line connecting the rotation centers of the two ends of the L-shaped connecting rod and the end of the rocker arm away from the L-shaped connecting rod should be greater than 180° and less than 185°.

[0013] The beneficial effects of the present invention are: (1) The present invention is based on a four-bar mechanism as the core of the lifting, and utilizes the dead point characteristics of the bar mechanism to achieve the locking of the lifting position and the buried position, without the need to add a position locking mechanism; (2) The present invention is based on the quick return characteristic of the four-bar mechanism, so that the high-speed rotary actuator has better starting characteristics.

[0014] (3) Based on the quick return characteristic of the four-bar mechanism, the equipment in the cabin can be quickly raised. Since the position is close to the dead point, the rotation angle of the high-speed rotary actuator has little effect on the lifting angle of the equipment in the cabin, thereby reducing the impact of the equipment in the cabin at high speed.

[0015] (4) The present invention utilizes the two dead points of the four-bar mechanism to optimize the equipment lifting system in the cabin and improves the system reliability through the self-locking of the mechanism.

[0016] (5) The present invention has a compact structure, high reliability, light weight, and simple control (only the rotation of the high-speed rotary actuator is needed to control the lifting and lowering of the equipment in the cabin); the four-bar mechanism is adopted, and the two position locking mechanisms can be eliminated, and the lifting position and the buried position can be locked through the dead point of the four-bar mechanism; by setting a mechanical limit at the position where the four-bar mechanism is rotated to, the four-bar mechanism can bear the load after lifting and embedding, which can reduce the structural strength of the high-speed rotary actuator; the output shaft of the high-speed rotary actuator provides a small braking torque, which can enable the self-locking lifting system to withstand a load that is several times greater than the braking torque. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the drag parachute cabin of the present invention being raised into place; Figure 2 This is a schematic diagram of the drag parachute cabin of the present invention being buried in place; Figure 3 This is a schematic diagram of the drag parachute cabin of the present invention being raised into position; Figure 4 This is a schematic diagram of the drag parachute cabin of the present invention being buried in place; Figure numerals: 1. rocker arm; 11. rocker arm shaft; 2. drag parachute compartment; 21. parachute compartment rotary hinge; 3. L-shaped connecting rod; 31. connecting rod hinge; 32. connecting rod adjusting nut; 33. hinge pin; 4. high-speed rotating actuator; 5. first fixed machine upper limit block; 6. second fixed machine upper limit block. DETAILED DESCRIPTION

[0018] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0019] It is to be noted that the concepts of directions “left”, “right”, “up”, “down”, “front”, “back”, “inside” and “outside” in the following schemes are all relative directions and will not be listed one by one here.

[0020] A self-locking lifting system for lifting equipment in a cabin, reference Figure 1 and Figure 2 , including a rocker arm 1. One end of the rocker arm 1 is fixedly connected to a rocker arm shaft 11. The output end of the high-speed rotary actuator 4 is connected to one end of the rocker arm shaft 11. The high-speed rotary actuator 4 is arranged on the aircraft. The end of the rocker arm shaft 11 away from the high-speed rotary actuator 4 is rotatably arranged on the aircraft. The rocker arm 1 is fixedly sleeved on the rocker arm shaft 11. The end of the rocker arm 1 away from the rocker arm shaft 11 is rotatably sleeved with a connecting rod pin 33. One end of the L-shaped connecting rod 3 is fixedly sleeved on the connecting rod pin 33, so as to be rotatably connected to one end of the rocker arm 1. The other end of the L-shaped connecting rod 3 is sequentially provided with a connecting rod adjustment nut 32 and a connecting rod hinge 31 for adjusting the preload force of the device embedded in the fuselage. The other end of the L-shaped connecting rod 3 is rotatably connected to the drag parachute compartment 2 through the connecting rod hinge 31. A parachute compartment rotating hinge 21 is provided at one end of the drag parachute compartment 2. The parachute compartment rotating hinge 21 is hinged to the aircraft, so that the drag parachute compartment 2 is rotatably connected to the aircraft. The aircraft is provided with a first fixed upper limit block 5 and a second fixed upper limit block 6. When the drag parachute compartment 2 is raised into place, the rocker arm 1 abuts against the first fixed upper limit block 5; when the drag parachute compartment 2 is buried in place, the rocker arm 1 abuts against the second fixed upper limit block 5. When the rocker arm 1 abuts against the first fixed upper limit block 5 or the second fixed upper limit block 6, the line connecting the rotation centers of the rocker arm shaft 11, the hinge pin shaft 33, and the connecting rod hinge 31 is greater than 180° and less than 185°. Since the present embodiment is in the self-locking position of the L-shaped connecting rod 3 after being raised into place, the high-speed rotating actuator 4 provides a small resistance, so that the present embodiment can withstand a load several times higher than the output load.

[0021] Through the above mechanism, this embodiment can quickly lift the equipment in the cabin to the raised position and lock the position. When this embodiment is away from the buried body, the dead point characteristics of the four-bar mechanism can be used to lock the position. Since the rotation angle of the equipment in the cabin is amplified by the four-bar mechanism to amplify the output angle of the rotary actuator, and the quick return characteristics of the four-bar mechanism are used, the equipment in the cabin can be quickly lifted, and the deceleration stage has little effect on the lifting angle, reducing the risk of high-speed impact.

[0022] refer to Figure 3 When the drag parachute compartment 2 is raised to its position, BC is the L-shaped connecting rod 3, point A is the rocker arm shaft 11, AB is the rocker arm 1, point C is the connecting rod hinge 31, and point M is the parachute compartment rotating hinge 21. After being buried in place, the angle θ is 182°~185°. When the drag parachute compartment 2 has a tendency to be buried in the fuselage, the rocker arm 1 has a tendency to rotate counterclockwise. Since the first fixed upper limit block 5 limits the counterclockwise movement of the L-shaped connecting rod 3, when the drag parachute compartment 2 has a tendency to rise, the rocker arm 1 has a tendency to rotate clockwise. When it moves to 180°, the L-shaped connecting rod 3 is pulled and cannot drive the rocker arm 1 to rotate. Therefore, this embodiment has the ability to lock the position when it is raised to its position.

[0023] refer to Figure 4 When the drag parachute compartment 2 is embedded in place, BC is the L-shaped connecting rod 3, point A is the rocker arm shaft 11, AB is the rocker arm 1, point C is the connecting rod hinge 31, and point M is the parachute compartment rotating hinge 21. After being embedded in place, the angle θ is 178°~175°. When the drag parachute compartment 2 has a tendency to be embedded in the fuselage, the rocker arm 1 has a tendency to rotate counterclockwise. When it moves to 180°, the L-shaped connecting rod 3 is pulled and cannot drive the rocker arm 1 to rotate. When the parachute compartment has a tendency to rise, since the angle θ is less than 180°, the rocker arm 1 has a tendency to rotate clockwise. Since the second fixed upper limit block 6 limits the clockwise movement of the L-shaped connecting rod 3, this embodiment has the ability to lock the position when embedded in place.

[0024] The above is only a preferred embodiment of the present invention. It should be understood that the present invention is not limited to the form disclosed herein, and should not be regarded as excluding other embodiments, but can be used in various other combinations, modifications and environments, and can be modified within the scope of the concept described herein through the above description or the technology or knowledge of the relevant field. The changes and modifications made by those skilled in the art shall not deviate from the spirit and scope of the present invention, and shall be within the scope of protection of the claims attached to the present invention.

Claims

1. A self-locking lifting system for lifting equipment in a cabin, characterized in that: The invention comprises a rocker arm (1) and a drag parachute compartment (2) which are rotatably arranged on a machine, an L-shaped connecting rod (3) being arranged between the rocker arm (1) and the drag parachute compartment (2), two ends of the L-shaped connecting rod (3) being respectively rotatably connected to the rocker arm (1) and the drag parachute compartment (2), and a high-speed rotary actuator (4) for driving the rocker arm (1) to rotate is arranged on the machine.

2. A self-locking lifting system for lifting equipment in a cabin according to claim 1, characterized in that: The drag parachute compartment (2) is rotatably connected to the aircraft via a parachute compartment rotating hinge (21).

3. A self-locking lifting system for lifting equipment in a cabin according to claim 1, characterized in that: The L-shaped connecting rod (3) is provided with a connecting rod hinge (31), and the connecting rod hinge (31) is rotatably connected to the drag parachute cabin (2).

4. A self-locking lifting system for lifting equipment in a cabin according to claim 1, characterized in that: The L-shaped connecting rod (3) is provided with a connecting rod adjustment nut (32) for adjusting the pre-tightening force of the device embedded in the machine body.

5. The self-locking lifting system for lifting equipment in a cabin according to claim 1, characterized in that: A hinge pin shaft (33) is provided at one end of the L-shaped connecting rod (3), and the rocker arm (1) is rotatably sleeved on the hinge pin shaft (33).

6. A self-locking lifting system for lifting equipment in a cabin according to claim 1, characterized in that: A rocker arm rotating shaft (11) is fixedly sleeved on one end of the rocker arm (1) away from the L-shaped connecting rod (3), and an output end of the high-speed rotary actuator (4) is connected to the rocker arm rotating shaft (11).

7. The self-locking lifting system for lifting equipment in a cabin according to claim 1, characterized in that: It also includes a first fixed upper limit block (5) and a second fixed upper limit block (6) arranged on the machine; When the drag parachute compartment (2) is raised to the highest point, the rocker arm (1) abuts against the first fixed upper limit block (5), and the angle between the rotation centers of the two ends of the L-shaped connecting rod (3) and the end of the rocker arm (1) away from the L-shaped connecting rod (3) is greater than 180° and less than 185°; When the drag parachute compartment (2) is lowered to the lowest point, the rocker arm (1) abuts against the second fixed upper limit block (6), and the angle between the rotation centers of the two ends of the L-shaped connecting rod (3) and the end of the rocker arm (1) away from the L-shaped connecting rod (3) is greater than 180° and less than 185°.

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