Disc type power coupling device for aircraft engine

Abstract

The invention provides a disc type dynamic coupling device for an aircraft engine, which is characterized in that a meshing outer rotor is arranged outside a fixed hub, and the upper section of the meshing outer rotor is connected with the upper section of the fixed hub through a double-row deep groove ball bearing in a matched manner; the lower section of the meshed outer rotor is connected with the lower section of the fixed hub through a friction plate group and a friction block assembly; the fixing nut fixes the double-row deep groove ball bearing on the fixed hub, and a bottom plate is arranged between the meshed outer rotor and the bottom of the fixed hub to realize sealing; the propeller rotating bracket is connected to the top end of the meshed outer rotor through a bracket bolt; in an idling state, the fixed hub idles; and the idle speed is increased, internal meshing is achieved between the meshing outer rotor and the fixed wheel set, and then the propeller rotating support is driven to rotate. The unmanned aerial vehicle launching support and carrying space utilization rate and the loading number are effectively increased, and a solution is provided for overall integration, part removal and cost reduction design of an unmanned aerial vehicle power device.

Description

Technical Field

[0001] The invention belongs to the field of unmanned aerial vehicle power, and in particular relates to a disc-type power coupling device for an aircraft engine. Background Art

[0002] Modern UAV power plant devices are developing in the direction of integrated, electrified, intelligent, and highly maneuverable design, especially small highly maneuverable UAV equipment has put forward the development demand of cluster multi-configuration. In order to meet the rapid launch of highly maneuverable UAV clusters, a multi-machine arrangement configuration design is usually adopted. Since the UAV is driven by a blade propeller, the propeller running diameter usually exceeds the UAV height limit. Due to the launch conditions, the aircraft propeller is required to be in a horizontal static state on the ground. After the UAV is launched by elastic potential energy or gunpowder boost to a height of 20m above the ground, the propeller is allowed to start to avoid damage to the launch device or the aircraft body. Summary of the invention

[0003] In view of this, the present invention aims to propose a disc-type power coupling device for aircraft engines, which realizes the propeller start-up after the UAV is launched into the air under the action of the booster device, thereby improving the reliability of power transmission; improving the degree of integration of the power device, and providing a solution for the overall integration, de-componentization and cost reduction design of the UAV power device, and can also carry out serial product design and manufacturing according to the needs of UAV equipment.

[0004] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0005] A disc-type power coupling device for an aircraft engine, comprising a power output shaft, a fixed hub, a fixed nut, a double-row deep groove ball bearing, a friction block assembly, a friction plate group, an engaging outer rotor, a bracket bolt, and a propeller rotating bracket;

[0006] The meshing outer rotor is arranged outside the fixed hub, and the upper section of the meshing outer rotor and the upper section of the fixed hub are connected by a double-row deep groove ball bearing; the lower section of the meshing outer rotor and the lower section of the fixed hub are connected by a friction plate group and a friction block assembly;

[0007] The fixing nut fixes the double-row deep groove ball bearing on the fixed hub, and a bottom plate is provided between the meshing outer rotor and the bottom of the fixed hub to achieve sealing;

[0008] The propeller rotating bracket is connected to the top end of the meshing outer rotor by bracket bolts;

[0009] In the idling state, the power output shaft rotates, which drives the fixed wheel hub to idle;

[0010] As the idle speed increases, the friction block assembly applies pressure to the friction plate group, achieving internal engagement between the meshing outer rotor and the fixed wheel group, thereby driving the propeller rotating bracket to rotate.

[0011] Furthermore, the fixed hub is stepped, the upper section is a smooth circumferential surface, and the circumferential surface of the lower section is provided with splines;

[0012] The inner surface of the upper section of the meshing outer rotor is a smooth circumferential surface, and the inner circumferential surface of the lower section is also provided with splines;

[0013] The space formed by the lower section of the fixed hub, the lower section of the meshing outer rotor and the bottom plate is used to arrange the friction block assembly and the friction plate group.

[0014] Furthermore, the friction block assembly includes a plurality of friction block bodies, a cover plate and a sliding platform, the surface of the sliding platform is evenly provided with slideways, the slideways are arranged along the diameter direction, the friction block body is arranged in the slideways, the slideways correspond to the friction block body one by one, and the cover plate is used to cover the friction block body to achieve the limit of the friction block body;

[0015] The inner side of the circumference of the sliding platform is provided with a platform spline which matches with the fixed hub spline.

[0016] Furthermore, the friction plate group includes a first friction plate and a second friction plate, and the first friction plate and the second friction plate are arranged at intervals.

[0017] The outer circumferential surface of the No. 1 friction plate is provided with splines, and the inner circumference of the No. 2 friction plate is provided with splines. The No. 1 friction plate cooperates with the meshing outer rotor through the splines, and the No. 2 friction plate cooperates with the fixed wheel hub through the splines.

[0018] Furthermore, in the idle state, there is a gap between the first friction plate and the second friction plate.

[0019] As the idle speed increases, the friction block body slides axially along the slideway. Under the limitation of the slideway and the cover plate, the friction block body simultaneously moves axially toward the power output shaft, generating a clamping force to squeeze the friction plate group, so that the gap between the No. 1 friction plate and the No. 2 friction plate disappears, thereby achieving relative fixation between the fixed hub and the meshing outer rotor.

[0020] Furthermore, the power output shaft is the power output part, on which an electronic speed sensor is provided to collect the engine speed in real time.

[0021] Furthermore, the connection method between the fixed hub and the power output shaft includes but is not limited to a spline or a conical surface connection to achieve a coaxial tight connection.

[0022] Compared with the prior art, the disc-type power coupling device for an aircraft engine described in the present invention has the following advantages:

[0023] (1) The present invention provides a disc-type power coupling device for an aircraft engine, which can ensure that the engines of single-engine and multi-engine UAVs can operate reliably before operation and can be reliably engaged for power output after launch; thus solving the problem of UAV crashes caused by difficulty in starting the engine after launch.

[0024] (2) The present invention provides a disc-type power coupling device for an aircraft engine, which solves the problem that a wide launch bracket or box is used in the transportation and launch process of an unmanned aerial vehicle due to the large propeller diameter, thereby improving the aircraft space utilization rate and the number of installed units per unit volume, and realizing a highly compact and highly integrated structural design.

[0025] (3) The disc-type power coupling device for an aircraft engine of the present invention has a reasonable structural design, is simple and easy to implement, has the advantage of long-term storage, can be expanded according to the power conversion of the power system, and is easy to promote and use. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0027] Figure 1 A cross-sectional view of a disc-type power coupling device for an aircraft engine according to an embodiment of the present invention;

[0028] Figure 2 It is a schematic diagram of the cooperation between the friction block assembly and the friction plate group according to an embodiment of the present invention.

[0029] Description of reference numerals:

[0030] 1. Power output shaft; 2. Fixed wheel hub; 3. Fixed nut; 4. Double-row deep groove ball bearing; 5. Friction block assembly; 51. Friction block body; 52. Cover plate; 53. Sliding platform; 6. Friction plate group; 61. No. 1 friction plate; 62. No. 2 friction plate; 7. Engaging outer rotor; 8. Bracket bolts; 9. Propeller rotation bracket. DETAILED DESCRIPTION

[0031] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0032] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0033] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0034] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0035] A disc-type power coupling device for an aircraft engine, such as Figure 1 Figure 2 As shown, it includes a power output shaft 1, a fixed hub 2, a fixed nut 3, a double-row deep groove ball bearing 4, a friction block assembly 5, a friction plate group 6, an engaging outer rotor 7, a bracket bolt 8, and a propeller rotating bracket 9;

[0036] The meshing outer rotor 7 is arranged outside the fixed hub 2, and the upper section of the meshing outer rotor and the upper section of the fixed hub 2 are connected by a double-row deep groove ball bearing 4; the lower section of the meshing outer rotor and the lower section of the fixed hub 2 are connected by a friction plate group 6 and a friction block assembly 5;

[0037] The fixing nut 3 fixes the double-row deep groove ball bearing 4 on the fixed hub 2, and a bottom plate is provided between the meshing outer rotor 7 and the bottom of the fixed hub 2 to achieve sealing;

[0038] The propeller rotating bracket 9 is connected to the top of the meshing outer rotor 7 through a bracket bolt 8;

[0039] In the idle state, the power output shaft 1 rotates, which drives the fixed wheel hub 2 to idle;

[0040] As the idle speed increases, the friction block assembly 5 applies pressure to the friction plate group 6, thereby achieving internal meshing between the meshing outer rotor 7 and the fixed wheel group, thereby driving the propeller rotating bracket 9 to rotate.

[0041] Preferably, the fixed hub 2 is stepped, the upper section is a smooth circumferential surface, and the circumferential surface of the lower section is provided with splines;

[0042] The inner surface of the upper section of the meshing outer rotor 7 is a smooth circumferential surface, and the inner surface of the circumference of the lower section is also provided with splines;

[0043] The space formed by the lower section of the fixed hub 2 , the lower section of the meshing outer rotor 7 , and the bottom plate is used to arrange the friction block assembly 5 and the friction plate group 6 .

[0044] Preferably, the friction block assembly 5 comprises eight friction block bodies 51, a cover plate 52 and a sliding platform 53, the surface of the sliding platform 53 is evenly provided with slideways, the slideways are arranged along the diameter direction, the friction block bodies 51 are arranged in the slideways, the slideways correspond to the friction block bodies 51 one by one, and the cover plate 52 is used to cover the friction block bodies 51 to achieve the limit of the friction block bodies 51;

[0045] The inner side of the circumference of the sliding platform 53 is provided with platform splines that match the splines of the fixed hub 2.

[0046] Preferably, the friction plate group 6 includes a first friction plate 61 and a second friction plate 62, and the first friction plate 61 and the second friction plate 62 are arranged at intervals.

[0047] The outer circumferential surface of the No. 1 friction plate 61 is provided with splines, and the inner circumference of the No. 2 friction plate 62 is provided with splines. The No. 1 friction plate 61 cooperates with the meshing outer rotor 7 through the splines, and the No. 2 friction plate 62 cooperates with the fixed hub 2 through the splines.

[0048] Preferably, in the idle state, there is a gap between the first friction plate 61 and the second friction plate 62.

[0049] As the idling speed increases, the friction block body slides axially along the slideway. Under the limitation of the slideway and the cover plate 52, the friction block body 51 simultaneously moves axially toward the power output shaft 1, generating a clamping force to squeeze the friction plate group 6, so that the gap between the No. 1 friction plate 61 and the No. 2 friction plate 62 disappears, thereby achieving relative fixation between the fixed hub 2 and the meshing outer rotor 7.

[0050] Preferably, the power output shaft 1 is the power output part, which runs at high speed along the center of the crankshaft driven by the combustion pressure of each cylinder of the engine to achieve functions such as idle speed, cruising speed, and maximum speed (determined according to engine characteristics). An electronic speed sensor is provided on it to collect the engine speed in real time.

[0051] Preferably, the connection method between the fixed hub 2 and the power output shaft 1 includes but is not limited to a spline or a conical surface connection, so as to achieve a coaxial fastening connection and run at the same speed as the engine speed changes.

[0052] Preferably, the No. 1 friction plate 61 and the No. 2 friction plate 62 in the disc-type friction plate group 6 have a high friction coefficient, and the friction material can be metal or polymer composite friction material and other wear-resistant and high-temperature resistant materials. The inner and outer friction plates are arranged in parallel using splines but not limited to this method. Under the engine idling condition n≤3500r / min, the meshing outer rotor 7 is provided with a magnet, which can keep the sliding friction block assembly 5 in a fixed rotation state under the action of magnetic force; as the engine speed increases, reaching the cruising speed (n=3500~5000r / min) and the maximum speed (determined according to the engine characteristics) operating conditions, the friction plate group 6 can achieve meshing with the meshing outer rotor under the axial pressure generated by the friction block assembly 5 The rotor 7 is meshed and operates synchronously, further driving the propeller rotating bracket 9 and the propeller to operate and output power; as the engine speed decreases and reaches the operating condition under the idle condition (n≤3500r / min), the friction plate group 6 is disengaged from the meshing outer rotor 7, realizing the power output interruption function, satisfying the reliable operation of the engine before the operation of single-engine UAV and multi-engine UAV, and reliable meshing for power output after launch; it not only solves the problem of UAV crash caused by difficulty in starting the engine after launch, but also solves the problem of UAV transportation and launching process being forced to use a wide launch bracket or box due to the large propeller diameter, improves the aircraft space utilization rate and the number of installed units per unit volume, and realizes a highly compact and highly integrated structural design.

[0053] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A disc-type power coupling device for an aircraft engine, characterized in that: It includes a power output shaft, a fixed hub, a fixed nut, a double-row deep groove ball bearing, a friction block assembly, a friction plate group, an engaging outer rotor, a bracket bolt, and a propeller rotating bracket; The meshing outer rotor is arranged outside the fixed hub, and the upper section of the meshing outer rotor and the upper section of the fixed hub are connected by a double-row deep groove ball bearing; the lower section of the meshing outer rotor and the lower section of the fixed hub are connected by a friction plate group and a friction block assembly; The fixing nut fixes the double-row deep groove ball bearing on the fixed hub, and a bottom plate is provided between the meshing outer rotor and the bottom of the fixed hub to achieve sealing; The propeller rotating bracket is connected to the top end of the meshing outer rotor by bracket bolts; In the idling state, the power output shaft rotates, which drives the fixed wheel hub to idle; As the idle speed increases, the friction block assembly applies pressure to the friction plate group, achieving internal engagement between the meshing outer rotor and the fixed wheel group, thereby driving the propeller rotating bracket to rotate.

2. A disc-type power coupling device for an aircraft engine according to claim 1, characterized in that: The fixed hub is stepped, the upper section is a smooth circumferential surface, and the circumferential surface of the lower section is provided with splines; The inner surface of the upper section of the meshing outer rotor is a smooth circumferential surface, and the inner circumferential surface of the lower section is also provided with splines; The space formed by the lower section of the fixed hub, the lower section of the meshing outer rotor and the bottom plate is used to arrange the friction block assembly and the friction plate group.

3. A disc-type power coupling device for an aircraft engine according to claim 2, characterized in that: The friction block assembly comprises a plurality of friction block bodies, a cover plate and a sliding platform. The surface of the sliding platform is evenly provided with slideways, the slideways are arranged along the diameter direction, the friction block bodies are arranged in the slideways, the slideways correspond to the friction block bodies one by one, and the cover plate is used to cover the friction block bodies to achieve the limit of the friction block bodies; The inner side of the circumference of the sliding platform is provided with a platform spline which matches with the fixed hub spline.

4. A disc-type power coupling device for an aircraft engine according to claim 3, characterized in that: The friction plate group includes a first friction plate and a second friction plate, and the first friction plate and the second friction plate are arranged at intervals. The outer circumferential surface of the No. 1 friction plate is provided with splines, and the inner circumference of the No. 2 friction plate is provided with splines. The No. 1 friction plate cooperates with the meshing outer rotor through the splines, and the No. 2 friction plate cooperates with the fixed wheel hub through the splines.

5. A disc-type power coupling device for an aircraft engine according to claim 4, characterized in that: In the idle state, there is a gap between the first friction plate and the second friction plate. As the idle speed increases, the friction block body slides axially along the slideway. Under the limitation of the slideway and the cover plate, the friction block body simultaneously moves axially toward the power output shaft, generating a clamping force to squeeze the friction plate group, so that the gap between the No. 1 friction plate and the No. 2 friction plate disappears, thereby achieving relative fixation between the fixed hub and the meshing outer rotor.

6. The disc-type power coupling device for an aircraft engine according to claim 1, characterized in that: The power output shaft is the power output part, on which an electronic speed sensor is arranged to collect the engine speed in real time.

7. The disc-type power coupling device for an aircraft engine according to claim 1, characterized in that: The connection method between the fixed hub and the power output shaft includes but is not limited to a spline or a conical surface connection to achieve a coaxial tight connection.

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