Propeller power output meshing device for aircraft engine

Abstract

The invention provides a propeller power output meshing device for an aircraft engine. The power output shaft is sleeved with the fixing support to achieve fixed connection, the fixing support comprises an upper installation section and a lower installation section, the upper installation section is of a tubular structure, the lower installation section is of a plane structure, and a step structure is arranged between the upper installation section and the lower installation section; the meshing outer rotor is arranged on the outer side of the fixing support, and the upper mounting section of the fixing support is matched with the meshing outer rotor through a double-row groove ball bearing; the double-row groove ball bearing is installed on the fixed support through a support nut, a friction block assembly is arranged on a lower installation section of the fixed support, and the rotary support is installed on the end portion of the meshing outer rotor through a bolt. The propeller is started after the unmanned aerial vehicle is launched and lifted off under the action of the boosting device, the integration degree of the power device is improved, and a solution is provided for overall integration, part removal and cost reduction design of the unmanned aerial vehicle power device.

Description

Technical Field

[0001] The invention belongs to the field of unmanned aerial vehicle power systems, and in particular relates to a propeller power output engagement 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;

[0003] The current UAV power system cannot meet the propeller horizontal static condition under the ground engine starting idling condition. Summary of the invention

[0004] In view of this, the present invention aims to propose a propeller power output engagement device for an aircraft engine, which realizes the propeller start-up after the UAV is launched into the air under the action of a 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.

[0005] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0006] A propeller power output meshing device for an aircraft engine, comprising a power output shaft, a fixed bracket, a bracket nut, a double-row groove ball bearing, a friction block assembly, a meshing outer rotor, and a rotating bracket;

[0007] The power output shaft is sleeved into the fixed bracket to achieve fixed connection, wherein the fixed bracket includes an upper mounting section and a lower mounting section, the upper mounting section is a tubular structure, the lower mounting section is a planar structure, and a step structure is provided between the upper mounting section and the lower mounting section;

[0008] The meshing outer rotor is arranged on the outside of the fixed bracket, and the mounting section on the fixed bracket cooperates with the meshing outer rotor through a double-row groove ball bearing; the double-row groove ball bearing is mounted to the fixed bracket through a bracket nut,

[0009] The lower mounting section of the fixed bracket is provided with a friction block assembly, the lower mounting section is provided with a dustproof groove, and the end surface of the meshing outer rotor is provided with a dustproof protrusion that matches the dustproof groove;

[0010] The rotating bracket is mounted to the end of the meshing outer rotor by bolts.

[0011] Furthermore, the friction block assembly comprises a plurality of friction block bodies and springs, wherein the plurality of friction block bodies are connected to the fixed bracket via positioning pins, a hook is provided in the middle of the friction block body, and the tail end of the first friction block body is connected to the hook of the second friction block body via a spring; the plurality of friction block bodies are connected in pairs via springs;

[0012] The friction block body can contact the inner wall of the meshing outer rotor.

[0013] Furthermore, when the power output shaft is in an idling state, the friction block body and the meshing outer rotor are separated; when the power output shaft is in a cruising state, the friction block body and the meshing outer rotor are in contact.

[0014] Furthermore, a plurality of the friction block bodies can form a circular trajectory.

[0015] 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.

[0016] Furthermore, the connection method between the fixed bracket and the power output shaft includes but is not limited to a spline or conical surface connection to achieve a coaxial tight connection.

[0017] Compared with the prior art, the propeller power output engagement device for an aircraft engine according to the present invention has the following advantages:

[0018] (1) The present invention provides a propeller power output engagement device for an aircraft engine, which can ensure that the engine of a single-engine UAV or a multi-engine UAV can operate reliably before operation, and can reliably engage and output power after launch; thus solving the problem of a UAV crashing due to difficulty in starting the engine after launch.

[0019] (2) The present invention provides a propeller power output engagement 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.

[0020] (3) The propeller power output engagement 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

[0021] 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:

[0022] Figure 1 A schematic diagram of a propeller power output engagement device for an aircraft engine according to an embodiment of the present invention;

[0023] Figure 2 It is a schematic diagram of the friction block assembly described in an embodiment of the present invention.

[0024] Description of reference numerals:

[0025] 1. Power output shaft; 2. Fixed bracket; 3. Bracket nut; 4. Double-row deep groove ball bearing; 5. Friction block assembly; 51. Friction block body; 52. Spring; 6. Engaging outer rotor; 7. Rotating bracket; 8. Bracket bolt. DETAILED DESCRIPTION

[0026] 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.

[0027] 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.

[0028] 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.

[0029] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0030] A propeller power output engagement device for an aircraft engine, such as Figure 1 Figure 2As shown, it includes a power output shaft 1, a fixed bracket 2, a bracket nut 3, a double-row groove ball bearing, a friction block assembly 5, a meshing outer rotor 6, and a rotating bracket 7;

[0031] The power output shaft 1 is sleeved into the fixed bracket 2 to achieve fixed connection, wherein the fixed bracket 2 includes an upper mounting section and a lower mounting section, the upper mounting section is a tubular structure, the lower mounting section is a planar structure, and a step structure is provided between the upper mounting section and the lower mounting section;

[0032] The meshing outer rotor 6 is arranged on the outside of the fixed bracket 2, and the mounting section on the fixed bracket 2 cooperates with the meshing outer rotor 6 through a double-row groove ball bearing; the double-row groove ball bearing is mounted to the fixed bracket 2 through a bracket nut 3,

[0033] The lower mounting section of the fixed bracket 2 is provided with a friction block assembly 5, and the lower mounting section is provided with a dustproof groove. The end surface of the meshing outer rotor 6 is provided with a dustproof protrusion that cooperates with the dustproof groove to play a dustproof role.

[0034] The rotating bracket 7 is mounted to the end of the meshing outer rotor 6 by bolts.

[0035] Preferably, the friction block assembly 5 comprises a plurality of friction block bodies 51 and springs 52, wherein the plurality of friction block bodies 51 are connected to the fixed bracket 2 via positioning pins, a hook is provided in the middle of the friction block body 51, and the tail end of the first friction block body 51 is connected to the hook of the second friction block body 51 via the spring 52; and the plurality of friction block bodies 51 are connected in pairs via the springs 52;

[0036] The friction block body 51 can contact the inner wall of the meshing outer rotor 6 .

[0037] Preferably, when the power output shaft 1 is in an idling state, the friction block body 51 and the meshing outer rotor 6 are separated; when the power output shaft 1 is in a cruising state, the friction block body 51 and the meshing outer rotor 6 are in contact.

[0038] Preferably, a plurality of the friction block bodies 51 can form a circular trajectory.

[0039] Preferably, the engine power output shaft 1 is the power output part for the UAV, 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 idling speed (n≤3500r / min), cruising speed (n=3500~5000r / min), and maximum speed (determined according to engine characteristics). An electronic speed sensor is provided on it to collect the engine speed in real time.

[0040] Preferably, the connection method between the fixed bracket 2 and the power output shaft 1 includes but is not limited to a spline or a conical surface connection to achieve a coaxial fastening connection.

[0041] Under the engine idling condition (n≤3500r / min), the friction block assembly 5 is in a fixed rotation state under the action of the spring 52 force and the damping action; as the engine speed increases, when the cruising speed (n=3500~5000r / min) and the maximum speed (determined according to the engine characteristics) operating condition are reached, the friction block overcomes the spring 52 force and the damping force under the action of the centrifugal force, and the friction block body 51 meshes with the meshing outer rotor 6 and operates synchronously, thereby driving the propeller rotating bracket 7 and the propeller to operate and output power; as the engine speed decreases, when the idling condition (n≤3500r / min) is reached, the friction block assembly 5 is in a fixed rotation state under the action of .... / min), the combined force of the spring 52 of the friction block body 51 and the damping force is greater than the centrifugal force, the friction surface of the friction block body 51 is disengaged from the meshing outer rotor 6, and the power output interruption function is realized, which satisfies the reliable operation of the engine before the operation of single-engine UAV and multi-engine UAV, and the reliable meshing for power output after launching. It not only solves the problem of UAV crash caused by the difficulty of engine starting after launching, 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, thereby improving the space utilization rate of the aircraft and the number of installed units per unit volume, and realizing a highly compact and highly integrated structural design.

[0042] 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 propeller power output engagement device for an aircraft engine, characterized in that: It includes a power output shaft, a fixed bracket, a bracket nut, a double-row groove ball bearing, a friction block assembly, a meshing outer rotor, and a rotating bracket; The power output shaft is sleeved into the fixed bracket to achieve fixed connection, wherein the fixed bracket includes an upper mounting section and a lower mounting section, the upper mounting section is a tubular structure, the lower mounting section is a planar structure, and a step structure is provided between the upper mounting section and the lower mounting section; The meshing outer rotor is arranged on the outside of the fixed bracket, and the mounting section on the fixed bracket cooperates with the meshing outer rotor through a double-row groove ball bearing; the double-row groove ball bearing is mounted to the fixed bracket through a bracket nut, The lower mounting section of the fixed bracket is provided with a friction block assembly, the lower mounting section is provided with a dustproof groove, and the end surface of the meshing outer rotor is provided with a dustproof protrusion that matches the dustproof groove; The rotating bracket is mounted to the end of the meshing outer rotor by bolts.

2. A propeller power take-off engagement device for an aircraft engine according to claim 1, characterized in that: The friction block assembly comprises a plurality of friction block bodies and springs, wherein the plurality of friction block bodies are connected to a fixed bracket through positioning pins, a hook is provided in the middle of the friction block body, and the tail end of the first friction block body is connected to the hook of the second friction block body through a spring; the plurality of friction block bodies are connected in pairs through springs; The friction block body can contact the inner wall of the meshing outer rotor.

3. A propeller power take-off engagement device for an aircraft engine according to claim 2, characterized in that: When the power output shaft is in idling state, the friction block body and the meshing outer rotor are separated; when the power output shaft is in cruising state, the friction block body and the meshing outer rotor are in contact.

4. A propeller power take-off engagement device for an aircraft engine according to claim 2, characterized in that: A plurality of the friction block bodies can form a circular trajectory.

5. The propeller power output engagement 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.

6. The propeller power output engagement device for an aircraft engine according to claim 1, characterized in that: The connection method between the fixed bracket 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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