CN114523260A - Gear hot-charging equipment and gear hot-charging method for piston engine of unmanned aerial vehicle - Google Patents

Abstract

The invention discloses a gear hot-fitting device and a gear hot-fitting method for a piston engine of an unmanned aerial vehicle. The gear hot-fitting device comprises: a press; on the lateral cantilever; a first positioning tool, the first positioning tool is installed on the base, the first positioning tool initially has an installation slot, and the gear to be installed is placed in the installation slot; the second Positioning tooling, the second positioning tooling is installed on the bottom end of the lifting arm, and the equipment to be installed that cooperates with the gear to be installed is detachably installed on the second positioning tooling; the lifting arm is installed on the power component It moves up and down in the vertical direction under the driving of the gear, and when the lifting arm moves to the lowest position, the gear to be installed is press-fitted into the installation hole of the device to be installed. The technical problem of easy connection failure caused by the use of glue or interference connection for gears in the prior art is solved.

Description

Gear hot-packing equipment and gear hot-packing method for unmanned aerial vehicle piston engine

technical field

The invention relates to the technical field of unmanned aerial vehicle parts assembly, and in particular relates to a gear hot-fitting device and a gear hot-fitting method for a piston engine of an unmanned aerial vehicle.

Background technique

With the rapid development of science and technology, the application of drones in various industries has become increasingly widespread in recent years. The application of UAV has involved aerial photography, agriculture, forestry and plant protection, geological exploration, electric power inspection, oil and gas pipeline inspection, highway accident management, forest fire inspection, polluted environment investigation, emergency rescue and rescue, emergency rescue and disaster relief, coastline inspection and other fields .

The engine is an important part of the UAV, and its gear installation effect directly affects the working ability of the engine. Most of the gears of the existing oil-driven piston engine of the UAV are glued or connected by interference. However, under the actual working conditions of the engine, the internal temperature is extremely high. After working for a long time in a high temperature environment, the structural glue on the glued gear will be damaged. Aging failure will lead to the failure of the gear with rotation, and the interference connection will also lead to the failure of the connection form with the wear of the internal structural components and the failure of the gear with the rotation, which will eventually cause the engine to stop working, and the aircraft will crash as the engine stops working.

Therefore, an installation method for a UAV engine gear is provided to solve the technical problem of easy connection failure caused by the use of adhesive bonding or interference connection for the gears in the prior art.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a gear hot-fitting device and a gear hot-fitting method for a UAV piston engine, so as to at least partially solve the technical problem of poor engine working ability caused by poor engine gear installation effect. This purpose is achieved through the following technical solutions:

The present invention proposes a gear hot-packing device for a UAV piston engine, and the gear hot-packing equipment includes:

a press, the press comprising a base, a connection riser mounted on the base, and a lateral cantilever disposed on the connection riser, the lateral cantilever being located above the base;

a lift arm, the lift arm is slidably mounted on the lateral cantilever along the vertical direction;

a first positioning tool, the first positioning tool is installed on the base, the first positioning tool initially has an installation slot, and the gear to be installed is placed in the installation slot;

a second positioning tool, the second positioning tool is installed on the bottom end of the lifting arm, and the to-be-installed equipment matched with the to-be-installed gear is detachably installed on the second positioning tool;

The lift arm moves up and down in the vertical direction under the driving of the power component, and when the lift arm moves to the lowest position, the gear to be installed is press-fitted into the installation hole of the device to be installed.

Further, the power components include:

handle;

a gear, which is connected with the handle and rotates under the drive of the handle;

A rack, which forms the lift arm, and which meshes with the gear.

Further, the second positioning tool is welded to the bottom of the rack.

Further, a quick release lock is also included, and the device to be installed is installed on the second positioning tool through the quick release lock.

Further, the quick release lock is mounted on the second positioning tool by spot welding.

Further, the equipment to be installed is a gear box or a starter motor of an engine.

The present invention also provides a gear hot-loading method for the UAV piston engine, the method comprising the following steps:

Install the first positioning tool on the base of the press, and install the second positioning tool on the bottom end of the lifting arm of the press;

Open the quick release lock, install the equipment to be installed on the second positioning tool, and lock the quick release lock after installation;

Continuously heating the gear to be installed for a first preset period of time, and raising the temperature of the gear to be installed to a preset temperature;

Quickly put the gear to be installed heated to the preset temperature into the installation slot of the first positioning tool;

Pull the handle down to drive the gear connected to the handle to rotate, thereby driving the rack meshing with the gear to move downward, and the rack drives the equipment to be installed to move downward until the gear to be installed is pressed against the gear of the equipment to be installed. on the assembly shaft;

Lift the handle upward, install the gear to be installed on the device to be installed, and move out of the first positioning tool with the device to be installed;

Remove the quick release lock, take out the installed equipment to be installed, and cool it down to room temperature for the second preset time at room temperature.

Further, the first preset duration is 2min-3min.

Further, the preset temperature is 1000°C-1300°C.

Further, the second preset duration is 15min-20min.

The gear hot-fitting equipment and gear hot-fitting method for the piston engine of the drone provided by the present invention are processed according to the assembly shaft in the process of designing and processing the gear. During the assembly, the gear is heated at high temperature to make the inner hole of the gear Expanded to the assembly size, the gear is press-fitted onto the assembly shaft by the equipment provided in this article. After cooling at room temperature, the size of the gear shaft hole returns to the lower difference, so as to achieve a tight fit with the assembly shaft. In this way, since the working temperature of the engine is much lower than the heating temperature when the gear is assembled, the gear will not fail due to high temperature when the engine works for a long time, thereby improving the reliability of the engine and thus the reliability of the aircraft. At the same time, the gear hot-fitting equipment can assemble the gears simply and quickly, which improves the production efficiency. The technical problem of poor engine working ability caused by poor engine gear installation effect is solved.

Description of drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are for the purpose of illustrating preferred embodiments only and are not to be considered limiting of the invention. Also, the same components are denoted by the same reference numerals throughout the drawings. In the attached image:

FIG. 1 is a schematic structural diagram of a specific embodiment of the gear hot-loading equipment provided by the present invention;

FIG. 2 is a schematic structural diagram of the gear shrink-fit equipment shown in FIG. 1 at another angle;

Fig. 3 is the front view of the gear shrink-fit equipment shown in Fig. 1;

Fig. 4 is a side view of the gear shrink-fit equipment shown in Fig. 1;

FIG. 5 is a state diagram of the gear shrink-fit equipment shown in FIG. 1 in use.

Description of reference numbers:

1-base, 2-connecting vertical plate, 3-transverse cantilever, 4-first positioning tool, 5-installation slot;

6-Second positioning tool, 7-handle, 8-rack, 9-quick release lock, 10-gear to be installed;

11- Equipment to be installed.

Detailed ways

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that the present disclosure will be more thoroughly understood, and will fully convey the scope of the present disclosure to those skilled in the art.

The hot-loading equipment and hot-loading method provided by the invention can be used for the pinion gear and the sun gear in the piston engine of the unmanned aerial vehicle to improve the connection reliability between the gear and the assembly shaft, and to avoid the heat loss when the engine is working. The resulting gear falls off to ensure the normal operation of the drone engine.

In a specific embodiment, the gear shrink-fit equipment provided by the present invention is used for a UAV piston engine, specifically for a reduction box or a starter motor of the engine, that is to say, the equipment 11 to be installed in this embodiment is a reduction box or the starter motor of the engine.

As shown in FIGS. 1-5 , the gear shrink-fit equipment includes a press, a lifting arm, a first positioning tool 4 and a second positioning tool 6 . Wherein, the press comprises a base 1, a connecting vertical plate 2 mounted on the base 1, and a lateral cantilever 3 arranged on the connecting vertical plate 2, and the lateral cantilever 3 is located above the base 1. The vertical plate and the lateral cantilever 3 can be an integral structure or a fixed connection structure. The base 1 is used to support the gear 10 to be installed and the first positioning tool 4 for fixing the gear 10 to be installed, and the connecting vertical plate 2 and the lateral cantilever 3 are also supported by the base 1. Therefore, the base 1 needs to be relatively stable. The structure has high structural strength to ensure stability.

The lift arm is slidably mounted on the lateral cantilever 3 along the vertical direction, the second positioning tool 6 is mounted on the bottom end of the lift arm, and the to-be-installed device 11 that cooperates with the to-be-installed gear 10 is detachable installed on the second positioning tool 6 . During the working process, the device 11 to be installed is fixed on the second positioning tool 6, and the device 11 to be installed and the second positioning tool 6 are lifted and lowered with the lifting arm synchronously, so that the device to be installed 11 moves in the direction of approaching or the principle base 1, and also That is, the device 11 to be installed is moved toward or away from the gear 10 to be installed.

The above-mentioned first positioning tool 4 is installed on the base 1. The first positioning tool 4 initially has an installation slot 5, and the gear 10 to be installed is placed in the installation slot 5. During the working process, the to-be-installed gear 10 is placed in the installation slot 5 The gear 10 is fixed in the installation slot 5 so as to realize the fixed position of the gear 10 to be installed.

The lift arm moves up and down in the vertical direction under the driving of the power component, and when the lift arm moves to the lowest position, the gear to be installed 10 is pressed into the installation hole of the device to be installed 11 . That is to say, during the press-fitting process, the gear 10 to be installed and the equipment 11 to be installed are respectively fixed on its positioning tool, the equipment 11 to be installed moves downward with the lifting arm, and when it moves to the lowest position, the gear to be installed 10 Press into the mounting hole. Then, the lifting arm is driven to move upward, driving the equipment 11 to be installed with the gear 10 to be installed to move upward and to be separated from the base 1 , and then the equipment 11 to be installed that has been pressed can be removed and cooled at room temperature.

In some embodiments, the power component includes a handle 7, a gear and a rack 8, wherein the gear is connected with the handle 7 and rotates under the drive of the handle 7, and the rack 8 forms The lift arm, the rack 8 mesh with the gear. During the working process, the handle 7 is manually pulled, and the handle 7 rotates to drive the gear to rotate, thereby driving the rack 8 engaged with the gear to move up and down. In order to ensure sufficient telescopic stroke, the length of the rack 8 is 650mm-700mm, preferably 680mm, at this time, the stroke of the rack 8 can be guaranteed to be about 460mm.

Theoretically speaking, the power component is not limited to the above-mentioned form, and the power component can also be a motor, a gear connected to the motor and a rack 8 meshed with the gear. At this time, the electric motor is used to replace the handle 7 in the power component, which can reduce the labor intensity of the staff.

In order to improve the connection reliability between the second positioning tool 6 and the rack 8 , the second positioning tool 6 is welded to the bottom of the rack 8 . Optionally, the second positioning tool 6 may be installed on the bottom of the rack 8 by bolt connection, snap connection and other connection methods.

Further, the device also includes a quick release lock 9, the device 11 to be installed is installed on the second positioning tool 6 through the quick release lock 9, and the quick release lock 9 is installed on the second positioning tool 6 by spot welding. Two positioning tooling 6. During the working process, the quick release lock 9 is fixed on the second positioning tool 6, and the equipment 11 to be installed is installed on the second positioning tool 6 through the quick release lock 9, so as to realize the installation reliability and disassembly of the equipment to be installed 11. Packing convenience.

In addition to the above-mentioned gear shrink-fit equipment, the present invention also provides a gear shrink-fit method for a UAV piston engine, the method comprising the following steps:

S1: Install the first positioning tool 4 on the base 1 of the press, and install the second positioning tool 6 on the bottom end of the lifting arm of the press;

S2: Open the quick release lock 9, install the device 11 to be installed on the second positioning tool 6, and lock the quick release lock 9 after the installation is completed;

S3: Continue to heat the gear 10 to be installed for a first preset duration, and make the temperature of the gear 10 to be installed rise to a preset temperature;

S4: quickly put the gear to be installed 10 heated to the preset temperature into the installation slot 5 of the first positioning tool 4;

S5: Pull the handle 7 downward to drive the gear connected to the handle 7 to rotate, thereby driving the rack 8 engaged with the gear to move downward, and the rack 8 drives the equipment 11 to be installed to move downward until the gear 10 to be installed is moved downward. Press it on the gear assembly shaft of the equipment 11 to be installed;

S6: Lift the handle 7 upward, and the gear 10 to be installed on the device 11 to be installed is moved out of the first positioning tool 4 along with the device 11 to be installed;

S7: Disassemble the quick release lock 9, take out the installed equipment 11 to be installed, and cool it at room temperature for a second preset time to room temperature.

Wherein, the first preset duration is 2min-3min, the preset temperature is 1000°C-1300°C, and the second preset duration is 15min-20min.

In actual use, the shrink-fit method can be used for gear installation of a reduction box or gear installation of a starter motor of an engine. The implementation process of the hot charging method will be specifically described below through two embodiments.

Example 1

The method for shrinking the starter motor gear of the UAV engine includes the following steps:

Install the starter motor gear positioning tool on the base 1 of the universal manual press;

Open the quick release lock 9, install the starter motor on the starter motor/reduction box positioning tool, and lock the quick release lock 9 after installation;

Heating the starting motor gear for 2min-3min and the temperature rises to 1000℃-1300℃;

Quickly put the heated starter motor gear into the starter motor gear positioning tool;

Pull the handle 7 down, the gear connected to the handle 7 will drive the rack 8 to move down, and the rack 8 drives the starter motor in the starter motor/reduction box positioning tool to press down the starter motor gear on the starter motor shaft;

Lift the handle 7 up, at this time the starter motor gear has been installed on the starter motor shaft, and the starter motor gear positioning tool is moved out with the starter motor;

Remove the quick release lock 9, take out the starter motor with the gear installed, and place it in the designated position to cool at room temperature for 15min-20min to normal temperature, and complete the gear heat installation.

Example 2

The gear shrink-fit method of the reduction box of the UAV engine includes the following steps:

Install the gear box gear positioning tool on the base 1 of the universal manual press;

Open the quick release lock 9, install the reduction box on the starter motor/reduction box positioning tool, and lock the quick release lock 9 after installation;

Heating the gear box gear 2min-3min the temperature rises to 1000℃-1300℃;

Quickly put the heated gearbox gear into the gearbox gear positioning tool;

Pull the handle 7 downward, the gear connected to the handle 7 will drive the rack 8 to move downward, and the rack 8 drives the starter motor/reduction box in the reduction box positioning tool to press down the reduction box gear on the main shaft of the reduction box;

Lift the handle 7 upwards, at this time, the gear of the reduction box has been installed on the main shaft of the reduction box, and the reduction box gear is moved out with the reduction box to locate the gear;

Remove the quick release lock 9, take out the gear box with the gear installed, and place it in the designated position for cooling at room temperature for 15-20 minutes to complete the hot-installation of the gear.

In the above-mentioned specific embodiments, the gear shrink-fit equipment and gear shrink-fit method for the unmanned aerial vehicle piston engine provided by the present invention are processed according to the assembly shaft in the process of designing and processing the gears. The gear is heated so that the inner hole of the gear expands to the assembly size, and the gear is press-fitted onto the assembly shaft with the equipment provided in this article. After cooling at room temperature, the size of the gear shaft hole returns to the lower difference, so as to achieve a close fit with the assembly shaft. In this way, since the working temperature of the engine is much lower than the heating temperature when the gear is assembled, the gear will not fail due to high temperature when the engine works for a long time, thereby improving the reliability of the engine and thus the reliability of the aircraft. At the same time, the gear hot-fitting equipment can assemble the gears simply and quickly, which improves the production efficiency. The technical problem of poor engine working ability caused by poor engine gear installation effect is solved.

It is to be understood that the terminology used herein is for the purpose of describing particular example embodiments only and is not intended to be limiting. As used herein, the singular forms "a," "an," and "" can also be intended to include the plural forms unless the context clearly dictates otherwise. The terms "comprising", "comprising", "containing" and "having" are inclusive and thus indicate the presence of stated features, steps, operations, elements and/or components, but do not preclude the presence or addition of one or Various other features, steps, operations, elements, components, and/or combinations thereof. Method steps, procedures, and operations described herein are not to be construed as requiring that they be performed in the particular order described or illustrated, unless an order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.

Although the terms first, second, third, etc. may be used herein to describe various elements, components, regions, layers and/or sections, these elements, components, regions, layers and/or sections should not be restricted by these terms. These terms may only be used to distinguish one element, component, region, layer or section from another region, layer or section. Terms such as "first," "second," and other numerical terms when used herein do not imply a sequence or order unless clearly indicated by the context. Thus, a first element, component, region, layer or section discussed below could be termed a second element, component, region, layer or section without departing from the teachings of example embodiments.

For ease of description, spatially relative terms may be used herein to describe the relationship of one element or feature to another element or feature as shown in the figures, such as "inner", "outer", "inner" ", "outside", "below", "below", "above", "above", etc. This spatially relative term is intended to include different orientations of the device in use or operation other than the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" or "above the other elements or features" above features". Thus, the example term "below" can encompass both an orientation of above and below. The device may otherwise be oriented, rotated 90 degrees or at other orientations and the spatially relative descriptors used herein interpreted accordingly.

The above are only preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art who is familiar with the technical scope disclosed by the present invention can easily think of changes or substitutions, All should be included within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims (10)

1. A gear hot-fill equipment for unmanned aerial vehicle piston engine, its characterized in that, gear hot-fill equipment includes:

the press machine comprises a base (1), a connecting vertical plate (2) arranged on the base (1), and a transverse cantilever (3) arranged on the connecting vertical plate (2), wherein the transverse cantilever (3) is positioned above the base (1);

a lifting arm slidably mounted to the transverse boom (3) in a vertical direction;

the gear installing device comprises a first positioning tool (4), wherein the first positioning tool (4) is installed on the base (1), an installing slot (5) is formed in the first positioning tool (4), and a gear (10) to be installed is placed in the installing slot (5);

the second positioning tool (6) is installed at the bottom end of the lifting arm, and equipment (11) to be installed, matched with the gear (10) to be installed, is detachably installed on the second positioning tool (6);

the lifting arm moves up and down in the vertical direction under the driving of the power component, and when the lifting arm moves to the lowest position, the gear (10) to be installed is pressed into the installation hole of the equipment (11) to be installed.

2. The gear shrink-fitting apparatus of claim 1, wherein said power component comprises:

a handle (7);

the gear is connected with the handle (7) and driven by the handle (7) to rotate;

a rack (8), the rack (8) forming the lifting arm, the rack (8) being in engagement with the gear.

3. The gear shrink-fitting device according to claim 2, characterized in that the second positioning tooling (6) is welded to the bottom of the rack (8).

4. The gear shrink-fitting equipment according to claim 3, characterized by further comprising a quick-release lock (9), wherein the equipment to be installed (11) is installed on the second positioning tool (6) through the quick-release lock (9).

5. Gear shrink-fitting equipment according to claim 4, characterised in that said quick-release lock (9) is mounted on said second positioning tooling (6) by spot welding.

6. A gear shrink-fitting apparatus according to claim 4, characterised in that the apparatus (11) to be mounted is a starter motor of a reduction gearbox or an engine.

7. A gear shrink-fitting method for a piston engine of an unmanned aerial vehicle, the method comprising the steps of:

mounting a first positioning tool (4) on a base (1) of a press machine, and mounting a second positioning tool (6) at the bottom end of a lifting arm of the press machine;

opening the quick-release lock (9), installing the equipment (11) to be installed on the second positioning tool (6), and locking the quick-release lock (9) after the installation is finished;

continuously heating the gear (10) to be installed for a first preset time, and raising the temperature of the gear (10) to be installed to a preset temperature;

rapidly placing the gear (10) to be installed, which is heated to a preset temperature, into the installation groove (5) of the first positioning tool (4);

the handle (7) is pulled downwards to drive the gear connected with the handle (7) to rotate, so that the rack (8) meshed with the gear is driven to move downwards, and the rack (8) drives the equipment to be installed (11) to move downwards until the gear to be installed (10) is pressed on the gear assembly shaft of the equipment to be installed (11);

the handle (7) is lifted upwards, the gear (10) to be installed on the equipment (11) to be installed moves out of the first positioning tool (4) along with the equipment (11) to be installed;

and (4) disassembling the quick-release lock (9), taking out the equipment (11) to be installed after the installation, and cooling the equipment to be installed at the normal temperature for a second preset time to the normal temperature.

8. The gear shrink-fitting method according to claim 7, wherein the first predetermined period of time is 2min to 3 min.

9. The gear shrink-fitting method according to claim 7, characterized in that the preset temperature is 1000 ℃ to 1300 ℃.

10. The gear shrink-fitting method according to claim 7, wherein the second predetermined period of time is 15-20 min.

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