Aero-engine teaching aid
By designing an aero engine teaching aid containing brushless motors, turbofans and thrust reversers, the problem of lack of intuitive teaching aids in teaching in aviation fields is solved, and vivid display and data collection of aircraft engine operation forms and fault identification are realized, improving Teaching effects and data support capabilities.
Patent Information
- Application Number
- CN202420697489.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-07
- Publication Date
- 2025-02-14
- Estimated Expiration
- 2034-04-07
AI Technical Summary
In the teaching and talent training in the field of aviation, there is a lack of intuitive teaching aids, making it difficult to effectively demonstrate the operation form of aircraft engines and the principles of maintenance and maintenance.
Aero engine teaching aids are designed, including brushless motors and turbofans, which simulate the motion state of the aero engine, and the reverse direction of the airflow is realized through the thrust reversal and the flow blocking plate to form real thrust and reverse thrust. The teaching aid is also equipped with a sound pickup head and a machine learning algorithm, which can collect sound data and perform fault identification.
The teaching aids can effectively demonstrate the working form and maintenance methods of aircraft engines, improve students' interest in learning, and provide new tools for teaching in aviation colleges. At the same time, by simulating the fault situation, collecting data, and forming a large number of data samples, providing data support for the actual research and development of aircraft engines.
Smart Images
Figure CN222482857U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of teaching aids, in particular to an aviation engine teaching aid. Background Art
[0002] Aircraft engines are an important part of aircraft, and their performance and reliability directly affect the safety and performance of aircraft. Since the working sound of aircraft engines can reflect the operating status of the engine to a certain extent, maintenance personnel can judge whether there are obvious signs of engine failure by listening to the working sound of the engine before the aircraft takes off and lands and during the flight. However, aircraft engines are very dangerous when working, and it is generally impossible to check them manually.
[0003] Moreover, in the teaching and talent training in the aviation field, it is difficult for students to intuitively understand the operation mode and maintenance principles of aircraft engines only through books. For this reason, we propose an aircraft engine teaching aid. Utility Model Content
[0004] In view of this, the utility model provides an aeroengine teaching aid, which is used to solve the problem of lack of teaching aids and inability to teach intuitively in teaching and talent training in the aviation field in the prior art.
[0005] An aeroengine teaching aid, comprising a brushless motor and a turbofan, wherein the brushless motor is installed in an inner duct, a rotating shaft with one end extending outward is rotatably installed in the inner duct; the turbofan is arranged at one end in the outer duct, and the turbofan is fixedly installed at one end of the rotating shaft;
[0006] A tail nozzle is arranged at the tail of the outer duct, and the tail nozzle is sleeved on the outside of the inner duct and can be aligned and communicated with one end of the outer duct; a thrust reverser is installed on the outer duct and the tail nozzle; the thrust reverser and the brushless motor are both controlled by a control panel.
[0007] Preferably, a pickup head is installed on the control panel.
[0008] Preferably, the thrust reverser comprises a screw, a screw motor and a screw nut, wherein the screw is rotatably mounted on the outer wall of the outer duct through a bearing, the screw motor is fixedly mounted on the outer wall of the outer duct, and the screw motor is transmission-connected to the screw; the screw motor is controlled by the control panel, and the screw nut on the screw is fixedly connected to the outer side wall of the tail nozzle;
[0009] The thrust reverser also includes a spoiler, one end of which is hingedly mounted on the inner wall of one end of the tail nozzle, and a movable pull rod is hingedly mounted in the middle of the spoiler, one end of which is hingedly mounted on the outer wall of the inner duct, wherein the spoiler can block the airflow of the outer duct when the movable pull rod is tightened.
[0010] Preferably, a front outer shell is fixedly connected to the outer wall of the outer duct, a rear outer shell is fixedly connected to the outer wall of the tail nozzle, and the inner duct is fixed to the inside of the outer duct by a connecting rod; a reverse thrust gas discharge port is reserved between the front outer shell and the rear outer shell; a reverse thrust guide plate is fixedly connected to the outer side of one end of the tail nozzle.
[0011] Preferably, a plurality of guide rods are fixedly connected to the outer wall of the outer duct, and a plurality of guide sleeves are fixedly connected to the outer wall of the tail nozzle, the guide rods correspond to the guide sleeves one by one, and the guide rods are slidably inserted in the guide sleeves.
[0012] Preferably, the front housing is fixedly connected to a support base, and the control panel is mounted on the support base.
[0013] Preferably, the front outer shell, the outer duct side wall and the inner duct side wall are all provided with wire holes.
[0014] Preferably, the inner duct is fixed inside the outer duct by a connecting rod.
[0015] Implementing the embodiments of the present utility model will have the following beneficial effects:
[0016] The above-mentioned aircraft engine teaching aids can serve as models to show students the working form and maintenance and overhaul methods of aircraft engines; improve students' learning interest, provide new teaching aids for teaching in aviation colleges, and facilitate the cultivation of talents in the aviation field from an early age;
[0017] The aircraft engine teaching aid of the present application can simulate the motion state of a real aircraft engine and provide a reliable experimental platform for studying the operating state of an aircraft engine;
[0018] The aircraft engine teaching aid of the present application can collect sound data through the pickup head; and can load a machine learning algorithm in the control panel to train the working sound of the aircraft engine teaching aid, and can accurately identify and judge the motion state and fault of the aircraft engine;
[0019] The aircraft engine teaching aid of the present application can simulate the failure conditions during the operation of an aircraft, thereby collecting data and forming a large number of data samples, which can provide data support for the actual research and development of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.
[0021] in:
[0022] Figure 1 A schematic diagram of the external structure of an aircraft engine teaching aid in one embodiment;
[0023] Figure 2 A schematic diagram of the internal structure of an aircraft engine teaching aid during forward propulsion in one embodiment;
[0024] Figure 3 The figure is a schematic diagram of the internal structure of an aero-engine teaching aid during reverse thrust in one embodiment.
[0025] Description of the drawings: 100, support seat; 200, control panel; 201, pickup head; 300, front shell; 400, reverse thrust gas exhaust port; 401, guide plate; 500, rear shell; 600, tail nozzle; 601, outer duct; 602, inner duct; 700, turbofan; 701, brushless motor; 702, rotating shaft; 800, spoiler; 801, movable pull rod; 900, screw motor; 901, screw; 902, screw nut; 903, guide rod; 904, guide sleeve. DETAILED DESCRIPTION
[0026] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by technicians in the technical field of the present application; the terms used in the specification of the application herein are only for the purpose of describing specific embodiments and are not intended to limit the present application; the terms "including" and "having" and any variations thereof in the specification and claims of the present application and the above-mentioned drawings are intended to cover non-exclusive inclusions. The terms "first", "second", etc. in the specification and claims of the present application or the above-mentioned drawings are used to distinguish different objects, not to describe a specific order.
[0027] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.
[0028] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings.
[0029] Example 1
[0030] See also Figure 1-3, an aircraft engine teaching aid, including a brushless motor 701 and a turbofan 700, wherein the brushless motor 701 is installed in an inner duct 602, and a rotating shaft 702 with one end extending outward is rotatably installed in the inner duct 602; the turbofan 700 is arranged at one end in the outer duct 601, and the turbofan 700 is fixedly installed at one end of the rotating shaft 702; a tail nozzle 600 is arranged at the tail of the outer duct 601, and the tail nozzle 600 is spaced and sleeved on the outside of the inner duct 602, and can be aligned and communicated with one end of the outer duct 601; a reverse thruster is installed on the outer duct 601 and the tail nozzle 600; the reverse thruster and the brushless motor 701 are both controlled by a control panel 200, and during implementation, the brushless motor 701 adopts a D2216KV1250 aircraft model brushless motor.
[0031] Specifically, the front housing 300 is fixedly connected to the support base 100, and the control panel 200 is installed on the support base 100. Wire holes are provided on the front housing 300, the side wall of the outer duct 601, and the side wall of the inner duct 602. The inner duct 602 is fixed inside the outer duct 601 through a connecting rod.
[0032] When working, the brushless motor 701 and the turbofan 700 can suck a large amount of airflow and eject it, thereby using the reaction force of the airflow to form a positive thrust; and the reverse thruster can guide the airflow to guide and propel it in the opposite direction, forming an airflow in the opposite direction and a reverse thrust. The entire teaching aid can well teach students to understand the working form of aircraft engines.
[0033] In the specific implementation, all parts of the aircraft engine teaching aids that can be manufactured using 3D printing technology are manufactured using 3D printing technology. Through precise design and assembly, the part curves and features of the real aircraft engine are restored, so that the model aircraft engine can highly simulate the movement state of the real aircraft engine.
[0034] Example 2
[0035] Different from Example 1, this example specifically discloses a thrust reverser during implementation. Figure 2 and Figure 3 The thrust reverser includes a screw 901, a screw motor 900 and a screw nut 902. The screw 901 is rotatably mounted on the outer wall of the outer duct 601 through a bearing. The screw motor 900 is fixedly mounted on the outer wall of the outer duct 601. The screw motor 900 is transmission-connected to the screw 901. The screw motor 900 is controlled by the control panel 200. The screw nut 902 on the screw 901 is fixedly connected to the outer wall of the tail nozzle 600.
[0036] The thrust reverser also includes a spoiler 800, one end of which is hingedly mounted on the inner wall of one end of the tail nozzle 600, and a movable pull rod 801 is hingedly mounted in the middle of the spoiler 800, and one end of the movable pull rod 801 is hingedly mounted on the outer wall of the inner duct 602, wherein the spoiler 800 can block the airflow of the outer duct 601 when the movable pull rod 801 is tightened.
[0037] During implementation, the front outer shell 300 is fixedly connected to the outer wall of the outer duct 601, the rear outer shell 500 is fixedly connected to the outer wall of the tail nozzle 600, and the inner duct 602 is fixed to the inside of the outer duct 601 through a connecting rod; a reverse thrust gas exhaust port 400 is left between the front outer shell 300 and the rear outer shell 500; a reverse thrust guide plate 401 is fixedly connected to the outer side of one end of the tail nozzle 600.
[0038] like Figure 2 As shown in , a plurality of guide rods 903 are fixedly connected to the outer wall of the outer duct 601 , and a plurality of guide sleeves 904 are fixedly connected to the outer wall of the tail nozzle 600 . The guide rods 903 correspond to the guide sleeves 904 one by one, and the guide rods 903 are slidably inserted into the guide sleeves 904 .
[0039] During operation, the screw motor 900 and the screw 901 are driven. Figure 2 As shown in , one end of the tail nozzle 600 can be aligned with one end of the outer duct 601 to form an airflow channel; finally, the airflow in the outer duct 601 and the airflow in the inner duct 602 are combined and ejected at the tail nozzle 600 to form a positive thrust;
[0040] At the same time, the tail nozzle 600 can be separated from the outer duct 601. Figure 3 As shown in , after separation to the preset position, the spoiler 800 can block the airflow of the outer duct 601 and make the airflow ejected from the reverse direction to form a reverse thrust.
[0041] Example 3
[0042] Different from Example 2, in this embodiment, a sound pickup head 201 is installed on the control panel 200. At the same time, a machine learning algorithm (neural network algorithm) is loaded in the control panel 200, and sound data is collected through the sound pickup head 201, and then the data is statistically learned and processed; thereby, the operation status recognition and fault judgment are realized. The sound data include the sound data of the aircraft engine teaching aid at different speeds during forward thrust (in actual operation, it is reasonably divided into three sections: low speed, medium speed, and high speed), the sound data of the aircraft engine teaching aid at different speeds during reverse thrust, the sound data when a paper ball is thrown at the aircraft engine teaching aid to simulate a bird collision, and the sound data in the shutdown state.
[0043] Obviously, the embodiments described above are only some embodiments of the present application, rather than all embodiments. The preferred embodiments of the present application are given in the accompanying drawings, but they do not limit the patent scope of the present application. The present application can be implemented in many different forms. On the contrary, the purpose of providing these embodiments is to make the understanding of the disclosure of the present application more thorough and comprehensive. Although the present application is described in detail with reference to the aforementioned embodiments, for those skilled in the art, it is still possible to modify the technical solutions recorded in the aforementioned specific implementation methods, or to perform equivalent replacement of some of the technical features therein. Any equivalent structure made using the contents of the specification and drawings of this application, directly or indirectly used in other related technical fields, is similarly within the scope of patent protection of this application.
Claims
1. An aeroengine teaching aid, characterized in that: include: A brushless motor (701), the brushless motor (701) being mounted in the inner channel (602), and a rotating shaft (702) having one end extending outwardly being rotatably mounted in the inner channel (602); A turbofan (700), wherein the turbofan (700) is disposed at one end of the outer duct (601), and the turbofan (700) is fixedly mounted on one end of a rotating shaft (702); A tail nozzle (600) is provided at the tail of the outer duct (601), and the tail nozzle (600) is sleeved at intervals on the outside of the inner duct (602) and can be aligned and communicated with one end of the outer duct (601); a thrust reverser is installed on the outer duct (601) and the tail nozzle (600); The thrust reverser and the brushless motor (701) are both controlled by a control panel (200).
2. An aeroengine teaching aid according to claim 1, characterized in that: A sound pickup head (201) is installed on the control panel (200).
3. The aircraft engine teaching aid according to claim 1, characterized in that: The thrust reverser comprises a screw (901), a screw motor (900) and a screw nut (902); the screw (901) is rotatably mounted on the outer wall of the outer duct (601) via a bearing; the screw motor (900) is fixedly mounted on the outer wall of the outer duct (601); the screw motor (900) is transmission-connected to the screw (901); and the screw motor (900) is controlled by the control panel (200); the screw nut (902) on the screw (901) is fixedly connected to the outer wall of the tail nozzle (600); The thrust reverser also includes a spoiler (800), one end of which is hingedly mounted on the inner wall of one end of the tail nozzle (600), and a movable pull rod (801) is hingedly mounted in the middle of the spoiler (800), and one end of the movable pull rod (801) is hingedly mounted on the outer wall of the inner duct (602), wherein the spoiler (800) can block the airflow of the outer duct (601) when the movable pull rod (801) is tightened.
4. An aeroengine teaching aid according to claim 3, characterized in that: The front outer shell (300) is fixedly connected to the outer wall of the outer duct (601), the rear outer shell (500) is fixedly connected to the outer wall of the tail nozzle (600), and the inner duct (602) is fixed to the inside of the outer duct (601) through a connecting rod; a reverse thrust gas discharge port (400) is reserved between the front outer shell (300) and the rear outer shell (500); and a reverse thrust guide plate (401) is fixedly connected to the outer side of one end of the tail nozzle (600).
5. An aeroengine teaching aid according to claim 4, characterized in that: A plurality of guide rods (903) are fixedly connected to the outer wall of the outer duct (601), and a plurality of guide sleeves (904) are fixedly connected to the outer wall of the tail nozzle (600). The guide rods (903) correspond to the guide sleeves (904) one by one, and the guide rods (903) are slidably inserted into the guide sleeves (904).
6. An aeroengine teaching aid according to claim 4, characterized in that: The front housing (300) is fixedly connected to the support base (100), and the control panel (200) is installed on the support base (100).
7. An aeroengine teaching aid according to claim 4, characterized in that: The front housing (300), the side wall of the outer duct (601) and the side wall of the inner duct (602) are all provided with wire holes.
8. The aircraft engine teaching aid according to claim 1, characterized in that: The inner duct (602) is fixed inside the outer duct (601) via a connecting rod.