A continuously adjustable center of gravity aircraft lifting device

Abstract

This invention belongs to the technical field of aircraft auxiliary structure design, and specifically relates to an aircraft lifting device with stepless adjustment of the center of gravity. The lifting device comprises a main beam, lifting straps, a safety mechanism, a gear and rack transmission mechanism, a rear lifting block, a gear limiting mechanism, a transition beam, a front lifting block, and multiple sets of roller mechanisms. The transition beam is made of cold-formed, inwardly rolled channel steel; the lifting straps are made of synthetic fiber and woven onto the main beam; the safety mechanism is fixed to the main beam; the gear and rack transmission mechanism is fixed to the sides of both the main beam and the transition beam; the roller mechanisms are fixed to the two outer rolled edges of the main beam and roll within the guide rails of the transition beam; the rear and front lifting blocks are both fixed to the bottom of the transition beam; and the gear limiting mechanism is used to limit and fix the device after center of gravity adjustment. This invention achieves stepless adjustment of the aircraft lifting device's center of gravity through the gear and rack transmission mechanism and the roller moving mechanism; it achieves fixation after center of gravity adjustment through the gear limiting mechanism; and it provides safety protection in case of accidental release during center of gravity adjustment through the safety mechanism. The aircraft lifting device proposed in this invention can achieve accurate positioning of the aircraft's center of gravity by coarsely adjusting the center of gravity and precisely adjusting the center of gravity, thereby ensuring that the lifting aircraft is in a stable state.

Description

Technical Field

[0001] This invention belongs to the field of aircraft auxiliary structure design technology, and in particular relates to an aircraft lifting device with a continuously adjustable center of gravity. Background Technology

[0002] Currently, aircraft lifting devices are generally equipped with multiple holes. By moving the lifting ring between different holes, the center of gravity of the aircraft can be adjusted. Before lifting, the position of the lifting ring is generally adjusted to be directly above the center of gravity mark of the aircraft.

[0003] Because it is impossible to adjust the lifting ring of the aircraft spreader to be directly above the aircraft's center of gravity mark by visual inspection, and because the aircraft spreader itself has mass, the combined center of gravity after lifting is not directly above the aircraft's center of gravity mark. Furthermore, the aircraft spreader has holes whose spacing cannot be infinitely adjusted to lift the center of gravity. Adjusting the center of gravity must be done when the aircraft spreader is not under stress. Therefore, it is necessary to lift the aircraft repeatedly to adjust it to a relatively level state, which makes the operation quite cumbersome. Summary of the Invention

[0004] Purpose of the invention: This invention proposes a continuously adjustable center of gravity lifting device for aircraft, which enables the adjustment of the center of gravity during aircraft lifting; thus achieving continuously adjustable lifting center of gravity.

[0005] Technical Solution: A continuously adjustable center of gravity aircraft lifting device, comprising a main beam, lifting belts, a safety mechanism, a gear and rack transmission mechanism, a rear lifting block, a gear limiting mechanism, a transition beam, a front lifting block, and multiple sets of roller mechanisms; wherein, the transition beam is cold-formed inwardly rolled channel steel, the lifting belt is made of synthetic fiber and woven onto the main beam, the safety mechanism is fixed to the main beam, the gear and rack transmission mechanism is fixed to the sides of both the main beam and the transition beam, the roller mechanisms are fixed to the two outer rolled edges of the main beam and roll within the guide rails of the transition beam, the rear lifting block and the front lifting block are both fixed to the bottom of the transition beam, and the gear limiting mechanism is used to achieve limiting and fixing after center of gravity adjustment.

[0006] Furthermore, the gear and rack transmission mechanism consists of a drive shaft with a handwheel, a fixed frame, a rack, and a drive wheel. The rack is welded to the side of the main beam, the fixed frame is welded to the side of the transition beam, the drive shaft with a handwheel passes through the fixed frame and is fixed to the fixed frame by a nut and a cotter pin, the drive wheel passes through the drive shaft with a handwheel and is fixed to the drive shaft with a key, and the rack meshes with the drive wheel.

[0007] Furthermore, the gear limiting mechanism consists of a gear limiting block, a guide cylinder, a first compression spring, a slotted adapter cylinder, and a gripper. The guide cylinder is welded to the fixed frame, the slotted adapter cylinder is welded to the guide cylinder, the first compression spring is sleeved on the gear limiting block, the gear limiting block passes through the guide cylinder, one end is engaged with the gear teeth of the drive wheel, and the other end is welded to the gripper. The slotted adapter cylinder is provided with shallow and deep slots in a cross shape, and the gripper is engaged in the shallow or deep slots of the slotted adapter cylinder.

[0008] Furthermore, the roller mechanism consists of a roller, an axle, and two supports. The supports are welded to the outer rolled edge of the main beam, the axle passes through the two supports and is fixed to the supports by cotter pins, and the roller passes through the axle and is fixed to the axle by a deep groove ball bearing.

[0009] Furthermore, the safety mechanism consists of a handle, a safety pin, a sleeve, and a second compression spring. The sleeve is welded to the main beam, the second compression spring is fitted onto the safety pin, and the safety pin passes through the sleeve and is welded to the handle.

[0010] Furthermore, the transition beam structure adopts cold-formed inwardly rolled channel steel, with a set of guide rails welded on each inwardly rolled edge for guiding the rolling of the rollers in the roller mechanism. Multiple sets of waist-shaped holes are evenly arranged along the length direction for limiting the safety pins in the safety mechanism.

[0011] Furthermore, the main beam is made of cold-formed, externally rolled channel steel.

[0012] Furthermore, the fixing method adopts welding fixing.

[0013] Technical benefits: The aircraft lifting device achieves stepless adjustment of its center of gravity through a gear and rack transmission mechanism and a roller movement mechanism; a gear limiting mechanism ensures fixation after center of gravity adjustment; and a safety mechanism provides protection in case of accidental release during center of gravity adjustment. The aircraft lifting device proposed in this invention can achieve accurate positioning of the aircraft's center of gravity through coarse adjustment and precise adjustment, ensuring the aircraft is in a stable state during lifting. Attached Figure Description

[0014] Figure 1 A schematic diagram of a continuously adjustable center of gravity (COP) aircraft lifting device.

[0015] Figure 2 Schematic diagram of gear and rack transmission and limit mechanism;

[0016] Figure 3 Schematic diagram of the roller movement mechanism and safety mechanism;

[0017] Figure 4 This is a structural diagram of the transition beam;

[0018] Figure 5 This is a diagram showing the hoisting of an aircraft.

[0019] Among them, 1-main beam, 2-lifting belt, 3-safety mechanism, 4-gear and rack transmission mechanism, 5-roller mechanism, 6-rear lifting block, 7-gear limiting mechanism, 8-transfer beam, 9-front lifting block, 10-drive shaft with handwheel, 11-fixed frame, 12-rack, 13-drive wheel, 14-gear limiting block, 15-guide cylinder, 16-first compression spring, 17-transfer cylinder with slot, 18-handle, 19-bracket, 20-axle, 21-roller, 22-handle, 23-safety pin, 24-sleeve, 25-second compression spring. Detailed Implementation

[0020] To more clearly illustrate the technical solutions of the embodiments of the present invention, the present invention will be described in detail below with reference to the accompanying drawings or specific implementation examples. It should be noted that some (but not all) of the disclosed examples are shown in the drawings. In fact, many different examples can be described, and these examples should not be construed as limited to the examples set forth herein. Rather, these examples are described to better demonstrate the positive effects of the present invention, and all aspects not detailed herein are considered to be well-known or conventional techniques in the art.

[0021] See appendix Figures 1-5 This invention comprises a main beam 1, a lifting belt 2, a safety mechanism 3, a gear and rack transmission mechanism 4, a roller mechanism 5, a rear lifting block 6, a gear limiting mechanism 7, a transfer beam 8, and a front lifting block 9, with the following external shape. Figure 1 As shown.

[0022] Safety mechanism 3 operation process: Lift handle 22 to move safety pin 23 upward, the second compression spring 25 is in a compressed state. After releasing handle 22, safety pin 23 moves downward under the action of the rebound force of the second compression spring 25 until handle 22 contacts sleeve.

[0023] Operation process of gear and rack transmission mechanism 4 and roller mechanism 5: Rotate the handwheel with handwheel drive shaft 10 to drive drive wheel 13 to rotate. Through the meshing of drive wheel 13 and rack 12, the main beam 1 and the transition beam 8 move relative to each other in the axial direction. The contact point for the relative movement of the main beam 1 and the transition beam 8 is multiple sets of roller mechanism 5. Through the rolling of multiple rollers 21 on the guide rail on the transition beam, the friction is reduced, so that a single person can easily drive the relative movement of the main beam 1 and the transition beam 8 by rotating the handwheel with handwheel drive shaft 10.

[0024] Operation process of gear limiting mechanism 7: Pinch the handle 18 in gear limiting mechanism 7 and rotate it so that the handle 18 is engaged in the shallow groove in the adapter cylinder 17 with groove, so that the gear limiting block 14 is moved away from the driving wheel 13, and the limiting of the gear rack transmission mechanism 4 is released; Pinch the handle 18 and rotate it 90° so that the handle 18 is engaged in the deep groove in the adapter cylinder 17 with groove, so that the gear limiting block 14 is engaged in the gear teeth of the driving wheel 13, and the limiting of the gear rack transmission mechanism 4 is achieved.

[0025] Coarse adjustment of the center of gravity process: The gantry crane / crane hooks onto the lifting strap 2 of the aircraft lifting device and lifts the aircraft lifting device directly above the aircraft, fixing the front and rear lifting interfaces of the aircraft onto the front lifting block 9 and the rear lifting block 6 respectively. The lever 18 in the gear limiting mechanism 7 is gripped and rotated, causing the lever 18 to engage in the shallow groove in the adapter cylinder 17 with a groove, moving the gear limiting block 14 away from the drive wheel 13, releasing the limitation on the gear and rack transmission mechanism 4. The handwheel with the handwheel drive shaft 10 is rotated, causing the main beam 1 to move axially. During this process, if the safety pin 23 in the safety mechanism 3 gets stuck... When the main beam 1 cannot move due to the oblong hole of the transition beam 8, lift the handle 22 in the safety mechanism 3 to disengage the safety pin 23 from the oblong hole of the transition beam 8, continue to rotate the handwheel with the drive shaft 10 until the center of the hoisting belt 2 is on the same vertical line as the center of gravity mark painted on the surface of the aircraft, stop rotating the handwheel with the drive shaft 10, pinch the handle 18 in the gear limiting mechanism 7 and rotate it so that the handle 18 is engaged in the deep groove in the transition cylinder 17 with the groove, so that the gear limiting block 14 is engaged in the gear teeth of the drive wheel 13, thereby limiting the gear rack transmission mechanism 4.

[0026] Precise adjustment of the center of gravity process: Control the gantry crane / crane to slowly lift the aircraft. After suspending it in the air, observe the horizontal state of the lifted aircraft. If the aircraft tilts at a large angle, hold the handwheel with the drive shaft 10 with one hand and squeeze the handle 18 in the gear limiting mechanism 7 with the other hand and rotate it so that the handle 18 is engaged in the shallow groove in the adapter cylinder 17 with the groove. After releasing the limit on the gear and rack transmission mechanism 4, rotate the handwheel with the drive shaft 10 to move the adapter beam 8 along the direction of the aircraft's nose-up. During this process, if the safety pin 2 in the safety mechanism 3... When the main beam 1 cannot move due to the oblong hole of the transition beam 8 being stuck in the safety mechanism 3, lift the handle 22 in the safety mechanism 3 to disengage the safety pin 23 from the oblong hole of the transition beam 8. Continue rotating the handwheel with the drive shaft 10 until the aircraft returns to a horizontal state. Then, stop rotating the handwheel with the drive shaft 10, pinch the lever 18 in the gear limiting mechanism 7 and rotate it to make the lever 18 engage in the deep groove in the transition cylinder 17 with the slot, so that the gear limiting block 14 engages in the gear teeth of the drive wheel 13, thereby limiting the gear and rack transmission mechanism 4. Figure 5 As shown.

[0027] Safety protection process: When the center of gravity is precisely adjusted, if the control of the handwheel with the drive shaft 10 is accidentally released when the gear limit mechanism is released from the gear limit, the transfer beam 8 will move along the axial direction due to the tilt angle of the aircraft during lifting. The tilt angle of the aircraft will become larger and larger. When the transfer beam 8 moves to the point where the safety pin 23 in the safety mechanism 3 is engaged in the waist-shaped hole of the transfer beam 8, the movement of the transfer beam 8 is limited, thereby preventing the tilt angle of the aircraft from becoming larger and larger, and realizing the safety protection of the aircraft.

[0028] The above specific embodiments or examples are only used to explain the technical solutions of the present invention and are not intended to limit the present application. Parts not described in detail are considered to be conventional technical means or common knowledge in the field. It can be understood by those skilled in the art that, based on the design concept of the present application, the technical solutions described in the foregoing embodiments can be adapted or some or all of the technical features can be equivalently replaced. These modifications, equivalent replacements, and adaptive improvements do not depart from the technical essence of the present invention and should all be covered within the protection scope of the present application.

Claims

1. A continuously adjustable center of gravity aircraft lifting device, characterized in that, The lifting device consists of a main beam (1), a lifting belt (2), a safety mechanism (3), a gear and rack transmission mechanism (4), a rear lifting block (6), a gear limiting mechanism (7), a transfer beam (8), a front lifting block (9), and multiple sets of roller mechanisms (5). The transfer beam (8) is made of cold-formed inner rolled channel steel, the lifting belt (2) is made of synthetic fiber and is woven on the main beam (1), the safety mechanism (3) is fixed on the main beam (1), the gear and rack transmission mechanism (4) is fixed on the sides of both the main beam (1) and the transfer beam (8), the roller mechanism (5) is fixed on the two outer rolled edges of the main beam (1) and rolls in the guide rail of the transfer beam (8), the rear lifting block (6) and the front lifting block (9) are both fixed on the bottom of the transfer beam (8), and the gear limiting mechanism (7) is used to achieve limiting and fixing after the center of gravity is adjusted. The gear and rack transmission mechanism (4) consists of a drive shaft (10) with a handwheel, a fixed frame (11), a rack (12) and a drive wheel (13). The rack (12) is welded to the side of the main beam (1), and the fixed frame (11) is welded to the side of the transition beam (8). The drive shaft (10) with a handwheel passes through the fixed frame (11) and is fixed to the fixed frame (11) by a nut and a cotter pin. The drive wheel (13) passes through the drive shaft (10) with a handwheel and is fixed to the drive shaft (10) with a key. The rack (12) meshes with the drive wheel (13). The gear limiting mechanism (7) consists of a gear limiting block (14), a guide cylinder (15), a first compression spring (16), a slotted adapter cylinder (17), and a handle (18). The guide cylinder (15) is welded to the fixed frame (11), and the slotted adapter cylinder (17) is welded to the guide cylinder (15). The first compression spring (16) is sleeved on the gear limiting block (14). The gear limiting block (14) passes through the guide cylinder (15), with one end inserted into the gear teeth of the drive wheel (13) and the other end welded to the handle (18). The slotted adapter cylinder (17) is provided with shallow and deep slots in a cross shape. The handle (18) is engaged in the shallow or deep slot of the slotted adapter cylinder (17).

2. The aircraft lifting device with continuously adjustable center of gravity as described in claim 1, characterized in that, The roller mechanism (5) consists of a roller (21), axle (20) and two supports (19). The supports (19) are welded to the outer rolled edge of the main beam (1). The axle (20) passes through the two supports (19) and is fixed to the supports (19) by a cotter pin. The roller passes through the axle (20) and is fixed to the axle (20) by a deep groove ball bearing.

3. The aircraft lifting device with continuously adjustable center of gravity as described in claim 1, characterized in that, The safety mechanism (3) consists of a handle (22), a safety pin (23), a sleeve (24) and a second compression spring (25). The sleeve (24) is welded to the main beam (1), the second compression spring (25) is sleeved on the safety pin (23), and the safety pin (23) passes through the sleeve (24) and is welded to the handle (22).

4. The aircraft lifting device with continuously adjustable center of gravity as described in claim 1, characterized in that, A set of guide rails is welded on the inner rolled edge of the transition beam (8) structure to guide the rolling of the roller (21) in the roller mechanism (5). Multiple sets of waist-shaped holes are evenly arranged along the length direction to limit the safety pin (23) in the safety mechanism (3).

5. The aircraft lifting device with continuously adjustable center of gravity as described in claim 1, characterized in that, The main beam (1) is a cold-formed outer-rolled channel steel.

6. The aircraft lifting device with continuously adjustable center of gravity as described in claim 1, characterized in that, The main structure is fixed by welding.

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