Aircraft air guide flow channel shutter opening and closing mechanism based on worm transmission

Abstract

The utility model belongs to the field of airplane structure design, and particularly relates to an airplane air guide flow channel shutter opening and closing mechanism based on worm transmission. The mechanism is mainly composed of a worm, a worm gear, blades, a worm support, a blade support, a worm gear support, a worm top cover, a grating base and other parts. The worm rotates to synchronously drive the multiple worm wheels to rotate, then the multiple blades are driven to rotate through the worm wheels, opening and closing of the shutter type blades are achieved, and therefore opening and closing of an air guide flow channel of an airplane are controlled. The mechanism provided by the utility model has the advantages of high transmission precision, good blade rotation synchronism, stable transmission and the like, and compared with a shutter form based on a parallelogram rocker arm mechanism, the mechanism provided by the utility model is driven by rotation, so that the structural reliability is higher, and the movement envelope of the mechanism is smaller.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aircraft structure design, and particularly relates to a worm transmission-based aircraft bleed air flow channel louver opening and closing mechanism. BACKGROUND

[0002] Aircraft internal equipment and cabin heat dissipation, ventilation and other functions are usually achieved by the method of bleeding air from the aircraft surface or the air inlet channel wall. Since the positions suitable for bleeding air from the aircraft surface or the air inlet channel wall are limited, and the internal equipment and cabin layout positions and the bleeding air positions may have a certain distance, a corresponding bleed air flow channel structure is usually designed in the aircraft body to guide air into the corresponding equipment or cabin. In some cases, the amount of bleed air of the on-board equipment and cabin needs to be increased or decreased, or the bleed air flow channel needs to be completely closed, for example, at high Mach numbers, the path of the equipment bleeding air from the air inlet channel needs to be shut off to ensure that the engine obtains sufficient flow. Therefore, an opening and closing mechanism needs to be arranged in the bleed air flow channel to achieve controllable adjustment of the bleed air flow channel. SUMMARY

[0003] The utility model discloses a worm transmission-based aircraft bleed air flow channel louver opening and closing mechanism, which meets the demand for controlling the flow of the bleed air flow channel under certain flight conditions of the aircraft, and can completely shut off the bleed air flow channel.

[0004] The utility model discloses a worm transmission-based aircraft bleed air flow channel louver opening and closing mechanism, which meets the demand for controlling the flow of the bleed air flow channel under certain flight conditions of the aircraft, and can completely shut off the bleed air flow channel.

[0005] The worm is provided with multiple segments of the same thread, the thread spacing, the starting position and the phase are consistent, the worm is engaged with the multiple worms, and the multiple worms are driven to rotate synchronously.

[0006] The multiple worms and the multiple blades are connected through the shaft and the key, so that the torque of the worm can be transmitted to the blade, and the blade is driven to rotate synchronously with the worm.

[0007] The worm support, the blade support, the worm support and the grid base are fixedly connected to form a fixed frame of the mechanism.

[0008] Further, the worm lead angle is designed to realize self-locking of the worm wheel, that is, only the worm can drive the worm wheel, and the worm wheel cannot drive the worm in the reverse direction, so that the blade cannot rotate unnecessarily when affected by the flow channel air flow, and is always fixed at the desired position, the locking function of the driving end can be cancelled, and the service life of the driving motor and other power sources is prolonged.

[0009] Further, the plurality of blades are consistent in spacing and overlap each other, and can realize relative sealing of the flow channel when closed.

[0010] Further, the worm upper cover is fixedly connected with the worm wheel support, so that the worm is protected, and dust and other excess substances in the flow channel are prevented from entering the transmission mechanism, so that the transmission mechanism is prevented from being stuck, the resistance is prevented from being increased, or dirt is prevented from being generated.

[0011] Further, in addition, a self-lubricating bushing can be installed in the middle of the worm upper cover, so that the worm is secondarily fixed in the middle section of the worm, deformation and bouncing of the worm under load are prevented, and the transmission reliability is ensured.

[0012] Further, the wall surface formed by the grid base, the blade support and the worm wheel support is inserted into the flow channel, or is connected with the machine body structure, so that the whole mechanism is installed and fixed.

[0013] Further, the grid base also has a flow regulating function.

[0014] The technical effects of the technical scheme are as follows:

[0015] a. The opening and closing mechanism of the aircraft bleed air flow channel louver based on the worm transmission can realize the following effects:

[0016] b. The mechanism adopts a transmission scheme in which a single worm synchronously drives a plurality of worm gears, the transmission is stable and reliable, compared with a common parallelogram linkage mechanism, the mechanism is compact and has a small motion envelope, and the mechanism is convenient to arrange in a narrow flow channel space of an aircraft;

[0017] c. The mechanism utilizes the characteristics of worm gear transmission, the lead angle of the worm can be designed, the worm gear is self-locked in rotation, the blades are prevented from freely rotating in the air flow, the blades are prevented from being held at one end of the power source, and the service life of the motor and other power sources can be prolonged;

[0018] d. The mechanism adopts worm rotation driving, the driving form is simple, the requirement for the power source form is low, and various power forms such as a rotary motor+coupling direct driving, bevel gear steering driving, gear+belt driving and the like can be adopted;

[0019] e. The transmission components such as the worm, the worm gear and the blades are fixed by bearings to reduce rotation resistance, torque is transmitted through key connection, the mechanism form is simple and reliable, and the use requirement of long-term rotation can be met. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 is the schematic diagram of the installation position of the mechanism;

[0021] Figure 2 is the detailed diagram of the mechanism composition-1;

[0022] Figure 3 is the detailed diagram of the mechanism composition-2;

[0023] Figure 4 is the detailed diagram of the mechanism composition-3;

[0024] Figure 5 is the schematic diagram of the connection of the transmission mechanism;

[0025] Figure 6 is the schematic diagram of the transmission principle;

[0026] Figure 7 is the schematic diagram of the blade overlap;

[0027] Figure 8 is the schematic diagram of the opening / closing state of the mechanism.

[0028] Wherein, 1 is a kind of aircraft based on worm drive air flow channel louver opening and closing mechanism, 2 is equipment / cabin, 3 is machine surface / intake passage, 4 is flow channel, 11 is worm, 12 is worm wheel, 13 is blade, 14 is worm wheel support, 15 is blade support, 16 is worm support, 17 is worm upper cover, 18 is grid base. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present application will be clearly and completely described below with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0030] Referring to the drawings Figures 1-8 A kind of aircraft based on worm drive air flow channel louver opening and closing mechanism 1 is installed in the flow channel 4 between equipment / cabin 2 and machine surface / intake passage 3. The installation position is as shown in the drawings Figure 1 .

[0031] As shown in the drawings Figure 2 ~the drawings Figure 4 A kind of aircraft based on worm drive air flow channel louver opening and closing mechanism 1 main parts include: worm 11, worm wheel 12, blade 13, worm wheel support 14, blade support 15, worm support 16, worm upper cover 17, grid base 18.

[0032] The worm 11 and the worm wheel 12 are mainly used for transmission. The plurality of blades 13 close to seal the flow channel 4 and overlap with each other, and open to open the flow channel 4. The worm wheel support 14, the blade support 15, the worm support 16 and the grid base 18 are fixedly connected with each other to form a fixed part of the mechanism, and are used for supporting the transmission components and the blades 13, and are connected with the flow channel 4 and the machine body structure to fix the whole mechanism, and the grid base 18 has a flow guiding function. The worm support 16 is located at both ends of the worm 11, and an angular contact bearing is arranged in the worm support 16 to fix the worm 11, so that the worm 11 can rotate around the axis of the worm 11, and the worm 11 is prevented from moving forward and backward along the axis of the worm 11 to a certain extent, so that the stability of transmission is ensured. The worm upper cover 17 is fixedly connected with the two worm wheel supports 14, and a self-lubricating bushing is arranged in the middle of the worm upper cover 17 to assist in positioning the worm 11, prevent the worm 11 from jumping and deforming, and affect the transmission, and meanwhile, the worm upper cover 17 covers the worm 11 to prevent dust and dirt in the flow channel 4 from entering the middle of the worm 11 and the worm wheel 12, so that additional transmission resistance is avoided, and oil sludge or transmission jamming is avoided.

[0033] The connection relationship of the transmission mechanism is as shown in the accompanying Figure 5 The worm 11 has a plurality of threads, and the worm 11 is meshed with the worm wheels 12 through the helical teeth on the worm 11 and the bevel teeth of the worm wheels 12. The worm wheels 12 are provided with a rotating shaft with a key groove, and the rotating shaft and the corresponding rolling bearings are arranged on the worm wheel supports 14 on both sides of the worm wheels 12. The blades 13 are connected with the worm wheels 12 through the rotating shaft and the key, and are synchronously rotated by the worm wheels 12. The free end of the blade 13 is connected with the blade support 15 through the rotating shaft of the blade 13 and the corresponding rolling bearings.

[0034] The transmission principle is as shown in the accompanying Figure 6 The worm 11 is meshed with the plurality of worm wheels 12, and when the worm 11 rotates, the plurality of worm wheels 12 can be synchronously driven to rotate, the angular velocity and the angle of each worm wheel are consistent, and all the blades 13 are synchronously driven to open and close.

[0035] As shown in the accompanying Figure 7 Each blade 13 has a certain overlap relationship, which can ensure that the blades 13 are relatively sealed when the blades 13 are closed, and has a movement limiting function, so that the blades 13 are prevented from being closed beyond the limit, and reverse air leakage is avoided.

[0036] The utility model is applied to the bleed air flow channel of an airplane, can control the opening and closing of various bleed air flow channels of the airplane, realizes the control of the heat dissipation and ventilation functions of some radiators, finished products or cabin radiators of the airplane. The opening and closing states of the mechanism are as shown in the accompanying Figure 8 .

[0037] The above merely describes specific embodiments of the present application, and the detailed description of the present application is not exhaustive of conventional technology. However, the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. The protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An aircraft bleed air flow passage shutter opening and closing mechanism based on a worm drive, characterized by, It comprises a worm (11), a worm wheel (12), a vane (13), a worm wheel support (14), a vane support (15), a worm support (16), and a grid base (18). The worm (11) is provided with multiple identical threads, and the thread spacing, starting position, and phase are consistent to ensure engagement with multiple worm wheels (12) and drive the multiple worm wheels (12) to rotate synchronously. The multiple worm wheels (12) and the multiple vanes (13) are connected through a rotating shaft and a key, so that the torque of the worm wheel (12) can be transmitted to the vane (13) to drive the vane (13) to rotate synchronously with the worm wheel (12). The worm wheel support (14), the vane support (15), the worm support (16), and the grid base (18) are fixedly connected to form a fixed frame of the mechanism.

2. An aircraft bleed air flow door shutter opening and closing mechanism based on a worm drive as claimed in claim 1, characterized in that, Through the design of the worm lead angle, self-locking of the worm wheel (12) is achieved, i.e., only the worm wheel (12) can be driven by the worm (11), and the worm wheel (12) cannot drive the worm (11) in reverse, which ensures that the vane (13) will not rotate unnecessarily when affected by the airflow in the flow channel (4) and is always fixed at the desired position. The locking and holding function of the drive end can be cancelled to prolong the service life of the drive motor.

3. An aircraft bleed air flow door shutter opening and closing mechanism based on a worm drive as claimed in claim 2, characterized in that The multiple vanes (13) have consistent spacing and overlap each other, and can achieve relative sealing of the flow channel (4) when closed.

4. An aircraft bleed air flow door shutter opening and closing mechanism based on a worm drive as claimed in claim 1, characterized in that, It also comprises a worm upper cover (17) that is fixedly connected with the worm wheel support (14) to protect the worm (11).

5. An aircraft bleed air flow door shutter opening and closing mechanism based on a worm drive as claimed in claim 4, characterized in that, A self-lubricating bushing can be installed in the middle of the worm upper cover (17) to assist in fixing the worm (11) at the middle section of the worm (11).

6. A worm drive based aircraft bleed air flow door opening and closing mechanism as claimed in claim 1, wherein, The wall surface formed by the grid base (18), the vane support (15), and the worm wheel support (14) is inserted into the flow channel or connected with the machine body structure to achieve installation and fixation of the entire mechanism.

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