CN115163746B - Counterweight balancing device and counterweight balancing method in aircraft assembly process - Google Patents
Counterweight balancing device and counterweight balancing method in aircraft assembly process Download PDFInfo
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- CN115163746B CN115163746B CN202210688174.6A CN202210688174A CN115163746B CN 115163746 B CN115163746 B CN 115163746B CN 202210688174 A CN202210688174 A CN 202210688174A CN 115163746 B CN115163746 B CN 115163746B
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- weight
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/28—Counterweights, i.e. additional weights counterbalancing inertia forces induced by the reciprocating movement of masses in the system, e.g. of pistons attached to an engine crankshaft; Attaching or mounting same
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
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Abstract
A counterweight balancing device and a counterweight balancing method in the aircraft assembly process are provided, wherein the counterweight balancing device is formed by superposing a plurality of counterweight boxes, each counterweight box is of an independent box body structure, idler wheels, traction sleeves, balancing weights, positioning structures, connecting lock catches and hanging rings are arranged on the counterweight boxes, the counterweight balancing device is respectively hung on two sides of an aircraft body through process connectors and used for balancing the weight of the aircraft, the center of the aircraft is kept in a preset position range, and the central connecting line of the process connectors on the two sides is perpendicular to the central axis of the aircraft.
Description
Technical Field
The invention belongs to the technical field of aircraft manufacturing, and particularly relates to a counterweight balancing device and a counterweight balancing method in an aircraft assembly process.
Background
The aircraft assembly is an important link in the aircraft production and manufacturing process, and the gravity center of a large aircraft can deviate in different assembly stages due to the fact that the size, the appearance and the weight of the components of the large aircraft are large, and gravity center adjustment is needed to be carried out through a counterweight balancing device in the aircraft assembly process, so that the stability of the gravity center of the aircraft in the assembly stage is ensured. The balance weight balancing method adopted at present meets the balance requirement in the aircraft assembly process by stacking balancing weights in the aircraft cockpit and the cargo hold, the method completely depends on manual transportation, the safety in the operation process is extremely poor, and the working space in the aircraft is occupied, so that the normal development of other works is influenced; because of the non-fixed stacking position, the gravity center position can not be fixed in the aircraft assembly process.
Disclosure of Invention
Aiming at the technical defects of a counterweight balancing device and a counterweight balancing method in the prior aircraft assembly process, the invention provides the counterweight balancing device and the counterweight balancing method in the aircraft assembly process. A counterweight balance device is hung on the process support joints on two sides of the aircraft body respectively, and the counterweight balance device is easy to pull and has controllable weight, so that the problem of gravity center deviation in the assembly process of different stations of a large aircraft can be effectively solved.
In order to achieve the above purpose, the present invention proposes the following technical solution.
The utility model provides a counter weight balancing unit in aircraft assembly process, its characterized in that, this counter weight balancing unit is by a plurality of weight boxes stack constitution, and every weight box is an independent box structure, and the weight box bottom is equipped with the gyro wheel, and the front side of weight box is equipped with the traction cover that matches with the tractor, has the recess in the railway carriage of weight box, inlays in the recess has the balancing weight, and the box upper surface of weight box is equipped with the location structure of being connected with another weight box lower surface, and the box side of weight box is equipped with the connection hasp of mutually stacking usefulness with another weight box, and the box both sides of weight box still are equipped with symmetrical rings.
A counterweight balancing method in the aircraft assembly process is characterized in that the gravity centers of aircraft bodies at different assembly stations can be changed along the central axis of an aircraft, and the counterweight balancing method is characterized in that: and a counterweight balancing device is respectively hung on two sides of the aircraft body through the process joints to balance the weight of the aircraft, so that the gravity center of the aircraft is kept in a preset position range, and the central connecting line of the process joints on two sides is perpendicular to the central axis of the aircraft.
The counterweight balancing device in the aircraft assembly process is used; according to the requirement of the aircraft counterweight, selecting a counterweight box with matched weight to be overlapped and assembled into a counterweight balancing device; the counterweight balancing device is towed to two sides of the aircraft body through an auxiliary tractor; the counterweight balance devices on two sides are respectively hung on the process joints on two sides of the aircraft body by using hanging straps.
The two side hanging belts are respectively connected with a chain block, the upper ends of the hanging belts are fixed on the process joints, the process joints are connected to the frame structure of the aircraft, and the counterweight balancing device is hung on the process joints on the two sides of the aircraft body through the length of the chain block shortened hanging belts, so that the weight balance of the aircraft body is realized.
The beneficial effects of this application lie in:
1) The box body, the balancing weight, the roller wheels, the traction sleeve and the hanging ring are integrated into a whole to form a single weight box, so that the local integrity of the device body is ensured, the weight boxes are positioned and assembled by adopting the bolts, the jacks and the connecting lock catches, and the operability and the safety of the device body are improved;
2) The counterweight balancing device adopts a mode of modularly superposing a plurality of mating boxes, can meet the requirements of easy traction, adjustable and controllable weight and automatic load braking of the counterweight balancing device, improves the safety and stability of the counterweight balancing device, and is suitable for stability under different assembly environments;
3) The method has the advantages that the defects of the traditional balancing weight stacking method are overcome, the working space in the aircraft is saved, a balancing weight balancing device is respectively hung on two sides of the aircraft body through process support joints according to the actual assembly requirements of the aircraft, a triangular stabilizing mechanism is formed between the balancing weight balancing device and the aircraft body so as to ensure the stability of the center of gravity of the aircraft, the balancing weight is not required to be repeatedly transported, the safety of products and personnel is improved, and the production efficiency is improved;
4) The invention has novel design thought, convenient implementation and wide applicability, provides a technical scheme for the problem of gravity center deviation in the assembly process of aerospace products, and has extremely high application value and popularization.
The present application is described in further detail below with reference to the drawings of embodiments.
Drawings
Fig. 1 is a schematic view of a single weight box structure.
Fig. 2 is a schematic structural view of a counterweight balancing device formed by overlapping two counterweight boxes.
FIG. 3 is a schematic diagram of a method of balancing weights during aircraft assembly.
Fig. 4 is a schematic diagram of a traction counterweight balancing apparatus for a tractor.
The numbering in the figures illustrates: 1 weight box, 2 balancing weights, 3 traction sleeves, 4 positioning seats, 5 idler wheels, 6 hanging rings, 7 upper lock bodies, 8 lower lock bodies, 9 positioning pins, 10 balancing weights, 11 hanging belts, 12 chain blocks, 13 tractors, 14 aircraft and 15 process joints.
Detailed Description
Referring to the drawings, the invention provides a counterweight balancing device and a counterweight balancing method in the aircraft assembly process, wherein the counterweight balancing device is symmetrically hung at process support joints on two sides of an aircraft body to balance the weight of the aircraft, the counterweight balancing device is used for producing and assembling the aircraft in a first station and a second station in a pulsating manner in the example, the invention is described in detail below with reference to the drawings, and the implementation mode is as follows:
fig. 1 is a schematic illustration of a weight box structure constituting a weight balancing device 10, the weight boxes 1 are of a module structure capable of being overlapped with each other, each weight box is an independent box module, rollers 5 are arranged at the bottoms of the weight boxes 1, traction sleeves 3 matched with tractors 13 are arranged on the front sides of the weight boxes 1, grooves are formed in the carriages of the weight boxes 1, balancing weights 2 are inlaid in the grooves, positioning structures connected with the lower surfaces of the other weight boxes are arranged on the upper surfaces of the boxes of the weight boxes 1, each positioning structure comprises a positioning seat 4 and a positioning pin 9, a positioning hole is formed in the center of each positioning seat 4, each positioning pin 9 is matched with each positioning hole, in the embodiment, each positioning seat 4 is arranged on the upper surface of each box of the weight boxes 1, and each positioning pin 9 is arranged on the lower surface of each box of the weight boxes 1. Of course, the positioning seat 4 may be provided on the lower surface of the body of the weight box 1, and the positioning pin 9 may be provided on the upper surface of the body of the weight box 1. The two are relatively matched and positioned.
The side of the box body of the weight box 1 is provided with a connecting lock catch for overlapping with another weight box, the connecting lock catch comprises an upper lock catch 7 and a lower lock catch 8, the upper lock catch 7 is connected with the lower lock catch 8 of the side of the box body of the weight box overlapped above, and the lower lock catch 8 is connected with the upper lock catch 7 of the side of the box body of the weight box overlapped below. Symmetrical hanging rings 6 are further arranged on two sides of the box body of the weight box 1, and in the embodiment, two hanging rings are respectively arranged on each side of the weight box.
A method of performing weight balancing during aircraft assembly using a weight balancing apparatus as described above; according to the requirement of the aircraft weight, two weight boxes 1 are selected to be overlapped and assembled into a weight balancing device 10; the auxiliary tractor 13 pulls the counterweight balancing device 10 to two sides of the body of the aircraft 14; the counterweight balance devices 19 on two sides are respectively hung on the process joints 15 on two sides of the body of the airplane 14 by the hanging belt 11.
The two side hanging straps 11 are respectively connected with a chain block 12, the upper ends of the hanging straps 11 are fixed on a process joint 15, the process joint 15 is connected to the frame structure of the aircraft 14, and the counterweight balancing device 10 is hung on the process joints 15 on two sides of the aircraft 14 body through the length of the hanging straps 11 shortened by the chain block 12, so that the weight balancing of the aircraft 14 body is realized.
In the embodiment, when the aircraft is assembled at a station, according to the weight characteristics of the aircraft, the weight required by hanging the counterweight device at the process joint of the frame 23 on the outer side of the aircraft is simulated and verified, the counterweight balancing device 10 is pulled to a working area by the auxiliary tractor 13, and the length of the hanging belt 11 is controlled by the chain block 12, so that the lifting of the counterweight balancing device 10 is realized, and the weight of the aircraft is balanced. According to the assembly requirement, when the aircraft is transferred to a two-station position for assembly, the self weight characteristics of the aircraft are changed, the weight required by hanging the counterweight device at the process joint of the frame 23 on the outer side of the aircraft body is obtained through simulation verification, and the counterweight 2 of the counterweight box 1 is reduced by adopting the method so as to carry out weight matching.
The weight characteristics of the aircraft under different stations can be obtained, and when the aircraft is assembled under different stations, the counterweight balancing device and the counterweight balancing method provided by the invention are adopted, and the corresponding relation between the assembly station of the aircraft and the number of the required counterweight boxes is as follows:
when the assembly station is located at one station, the number of the weight boxes required by one side is two, and four balancing weights are arranged in each weight box;
when the assembly stations are positioned at the two stations, the number of the weight boxes required by one side is one, and four balancing weights are arranged in each weight box;
when the assembly stations are positioned at the three stations, the number of the weight boxes required by one side is one, two balancing weights are arranged in each weight box, and the two balancing weights are obliquely and diagonally placed;
when the assembly station is at the four stations, a counterweight device is not needed.
Claims (4)
1. The weight balancing method in the aircraft assembly process is characterized in that the gravity center of an aircraft body can change along the central axis of the aircraft in different assembly stations, and the weight balancing method comprises the following steps of 1) respectively hanging a weight balancing device on two sides of the aircraft body through process connectors to balance the weight of the aircraft, keeping the gravity center of the aircraft within a preset position range, wherein the central connecting line of the process connectors on two sides is perpendicular to the central axis of the aircraft, the weight balancing device is formed by superposing a plurality of weight boxes, each weight box is of an independent box structure, rollers are arranged at the bottom of each weight box, traction sleeves matched with a tractor are arranged on the front side of each weight box, a groove is formed in the carriage of each weight box, a balancing weight is inlaid in the groove, the upper surface of the box body of each weight box is provided with a positioning structure connected with the lower surface of the other weight box, connecting lock catches mutually superposed with the other weight box are arranged on the side surfaces of the weight box, and symmetrical hanging rings are also arranged on the two sides of the box body of each weight box; 2) According to the requirement of the aircraft counterweight, selecting a counterweight box with matched weight to be overlapped and assembled into a counterweight balancing device; 3) The counterweight balancing device is towed to two sides of the aircraft body through an auxiliary tractor; 4) The counterweight balance devices on two sides are respectively hung on the process joints on two sides of the aircraft body by using hanging straps.
2. The method of balancing weight in aircraft assembly according to claim 1, wherein the positioning structure of the weight box comprises a positioning seat and a positioning pin, a positioning hole is formed in the center of the positioning seat, the positioning pin is matched with the positioning hole, the positioning seat is arranged on the upper surface of the weight box body, and the positioning pin is arranged on the lower surface of the weight box body.
3. The method of balancing weight in aircraft assembly according to claim 1, wherein the connecting latches on the sides of the weight boxes comprise upper latches and lower latches, the upper latches are connected with the lower latches on the sides of the other weight box stacked above, and the lower latches are connected with the upper latches on the sides of the other weight box stacked below.
4. The method for balancing weight in the process of assembling an aircraft according to claim 1, wherein two side hanging belts are respectively connected with a chain block, the upper ends of the hanging belts are fixed on process joints, the process joints are connected to a frame structure of the aircraft, and the weight balancing device is hung on the process joints on two sides of the aircraft body through the effective length of the chain blocks to realize weight balancing of the aircraft body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210688174.6A CN115163746B (en) | 2022-06-17 | 2022-06-17 | Counterweight balancing device and counterweight balancing method in aircraft assembly process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210688174.6A CN115163746B (en) | 2022-06-17 | 2022-06-17 | Counterweight balancing device and counterweight balancing method in aircraft assembly process |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115163746A CN115163746A (en) | 2022-10-11 |
| CN115163746B true CN115163746B (en) | 2023-07-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210688174.6A Active CN115163746B (en) | 2022-06-17 | 2022-06-17 | Counterweight balancing device and counterweight balancing method in aircraft assembly process |
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| CN (1) | CN115163746B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117508419B (en) * | 2023-10-24 | 2024-05-17 | 暨南大学 | Counterweight loading system of airplane passing simulation loading vehicle |
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2022
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| Publication number | Publication date |
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| CN115163746A (en) | 2022-10-11 |
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