Operation and structure of three-blade fixed wing (propeller) steering gear box of (electric engine aircraft)

Abstract

The invention belongs to the technical field of engine adjusting devices, and discloses a (electric engine aircraft) three-blade fixed wing (propeller) steering gear operation and structure which comprises a left mounting plate and a right mounting plate, a transverse shaft is rotatably erected on the two mounting plates, a first driving assembly is arranged to drive the transverse shaft to rotate, the middle section of the transverse shaft is a platform section, and the platform section is rotatably connected with a vertical shaft. The vertical shaft is perpendicular to the transverse shaft, a second driving assembly is arranged between the platform section and the vertical shaft, and the second driving assembly drives the vertical shaft to rotate. The first driving assembly drives the transverse shaft to rotate and controls the elevation angle of the electric engine mechanism, the second driving assembly drives the longitudinal vertical shaft to rotate and controls the horizontal orientation of the electric engine mechanism, the power direction of the electric engine mechanism can be flexibly adjusted through combination of the first driving assembly and the second driving assembly, and the aircraft has better maneuverability.

Description

Technical Field

[0001] The invention belongs to the technical field of engine regulating devices, and in particular relates to the operation and structure of a three-blade fixed-wing (propeller) steering machine (electric engine aircraft). Background Art

[0002] With the rapid development of aircraft technology, its application areas have penetrated into many key areas such as manned, agricultural plant protection, logistics distribution, emergency rescue, military reconnaissance, etc. In these diversified applications, the flexibility and adaptability of aircraft have become one of the important indicators to measure its performance. Especially in complex and changing environmental conditions, such as shuttling between urban buildings, exploring mountainous terrain, and maritime rescue operations, aircraft need to have higher maneuverability and directional control capabilities to ensure efficient execution of missions and safe return.

[0003] Based on this, we develop the operation and structure of the three-blade fixed-wing (propeller) steering gear (electric engine aircraft) to flexibly adjust the aircraft engine, aiming to improve the environmental adaptability, flight efficiency, precise control capabilities and overall performance of the aircraft through technological innovation. Summary of the invention

[0004] In order to overcome the above technical problems, the present invention provides (electric engine aircraft) three-blade fixed-wing (propeller) steering gear operation and structure, which can flexibly adjust the power direction of the engine and enable the aircraft to have better maneuverability.

[0005] The present invention adopts the following technical solutions:

[0006] (Electric engine aircraft) The operation and structure of a three-blade fixed-wing (propeller) steering machine includes a mounting plate for connecting to the front end wall of the aircraft wing, two mounting plates are provided, a horizontal transverse axis is set between the two mounting plates, the transverse axis is rotatably connected to the mounting plate, a drive component 1 is provided to drive and connect the transverse axis, the middle section of the transverse axis is a platform section, the platform section is rotatably connected to a vertical axis, the vertical axis is perpendicular to the transverse axis, the platform section is provided with a drive component 2 to drive and connect the vertical axis, and the bottom end of the vertical axis is the engine mounting site.

[0007] Preferably, the driving assembly 1 comprises an electro-hydraulic telescopic rod arranged on the front end wall of the aircraft wing, the side wall of the transverse axis has a rocker arm, and the electro-hydraulic telescopic rod drives and connects the rocker arm.

[0008] Preferably, the second driving component comprises a motor with a brake arranged above the platform section, the motor with a brake is connected to a worm, a worm wheel is arranged outside the vertical shaft, and the worm is meshed with the worm wheel.

[0009] Preferably, the transverse shaft is coaxially connected to a meter gear one, a needle seat one is installed on the mounting plate, a meter needle one is elastically and telescopically arranged in the needle seat one, the tip of the meter needle one is located in the tooth gap of the meter gear one, and when the transverse shaft rotates, the teeth of the meter gear one continuously touch the meter needle one; similarly, the vertical shaft is coaxially connected to a meter gear two, a needle seat two is installed on the platform section, the needle seat two is connected to the meter needle two, and when the vertical shaft rotates, the teeth of the meter gear two continuously touch the meter needle two.

[0010] Preferably, the mounting plate is provided with a longitudinal mounting hole for being bolted to the front end of an aircraft wing.

[0011] (Electric engine aircraft) Three-blade fixed-wing (propeller) steering gear operation and structure usage:

[0012] The mounting plate is mounted on the front end of the aircraft wing through the mounting hole, so that the transverse axis is in the transverse direction and the vertical axis is in the vertical direction, and the device is symmetrically mounted on both sides of the aircraft wings;

[0013] The engine is mounted on the bottom of the vertical shaft through a suspension to provide power to the aircraft;

[0014] The lateral axis is rotated by driving the rocker arm through the electro-hydraulic telescopic rod to adjust the elevation angle of the engine. The vertical axis is rotated by driving the worm gear through the brake motor to adjust the left and right angles of the engine, so as to adjust the angle of the engine and further enable the aircraft to achieve vertical take-off and landing, flexible steering and other actions.

[0015] During the engine angle adjustment process, the rotation of the horizontal axis causes the meter gear one to continuously touch and press the meter needle one, and the rotation of the longitudinal axis causes the meter gear two to continuously touch and press the meter needle two. Each set of meter needles and meter gears are connected to the meter circuit in the form of a switch, and the controller of the meter circuit measures the number of times the meter needle and the meter gear touch and are energized.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] The present invention is provided with an upper angle adjustment mechanism and a lower electric engine mechanism. The angle adjustment mechanism drives the lateral axis to rotate through a driving component 1 to control the elevation angle of the electric engine mechanism. The angle adjustment mechanism drives the longitudinal axis to rotate through a driving component 2 to control the horizontal orientation of the electric engine mechanism. The combination of the two can flexibly adjust the power direction of the electric engine mechanism, so that the aircraft equipped with the engine has better maneuverability, and can realize vertical take-off and landing, flexible steering, inverted flight and other actions;

[0018] In the present invention, a meter gear 1, a meter needle 1 and a meter gear 2, a meter needle 2 are arranged to monitor the angles of the horizontal axis and the vertical axis respectively, which can further ensure the accuracy and stability of the adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0020] Description of reference numerals:

[0021] 1 Mounting plate; 2 Transverse axis; 3 Rocker arm; 4 Electro-hydraulic telescopic rod; 5 Platform segment; 6 Worm gear; 7 Vertical axis; 8 Motor with brake; 9 Worm; 10 Mounting hole; 15 Metering gear 1; 16 Metering gear 2; 17 Metering needle 1; 18 Metering needle 2; 19 Engine mounting position. DETAILED DESCRIPTION

[0022] The embodiments of the present invention are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. Unless otherwise specified, the raw materials and equipment used can be purchased from the market or are commonly used in the art. The methods in the embodiments are conventional methods in the art unless otherwise specified. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0023] (Electric engine aircraft) The operation and structure of a three-blade fixed-wing (propeller) steering machine includes two left and right mounting plates 1. The mounting plates 1 are provided with longitudinal mounting holes 10. The device is mounted on the front end of the aircraft wing through the mounting holes 10. The two mounting plates 1 are rotatably mounted with a transverse transverse axis 2. A driving component 1 is arranged to drive the transverse axis 2 to rotate. The middle section of the transverse axis 2 is a platform section 5. The platform section 5 is rotatably connected to a vertical vertical axis 7. The vertical axis 7 is perpendicular to the transverse axis 2. A driving component 2 is arranged between the platform section 5 and the vertical axis 7. The driving component 2 drives the vertical axis 7 to rotate. The bottom end of the vertical axis 7 is an engine mounting site, where the engine mechanism is suspended and mounted.

[0024] The driving component 1 includes an electro-hydraulic telescopic rod 4 arranged on the front end wall of the aircraft wing, and the side wall of the transverse axis 2 has an L-shaped rocker arm 3. The electro-hydraulic telescopic rod 4 drives and connects to the rocker arm 3, and the connection between the two is connected by a universal ball joint. By controlling the extension and retraction of the electro-hydraulic telescopic rod 4, the transverse axis 2 can be driven to rotate through the rocker arm 3, thereby adjusting the elevation angle of the electric engine mechanism; the driving component 2 includes a brake motor 8 arranged above the platform section 5, the brake motor 8 is connected to a worm 9, and a worm gear 6 is sleeved on the vertical axis 7. The worm 9 is meshed with the worm gear 6. By controlling the brake motor 8 to drive the worm 9 to rotate, the vertical axis 7 can be driven to rotate, thereby adjusting the left and right direction of the electric engine mechanism; in this way, the direction of the electric engine mechanism can be flexibly adjusted, thereby realizing the vertical take-off and landing, rapid turning and inverted flight of the aircraft.

[0025] In order to accurately feedback the rotation angle, the horizontal shaft 2 is coaxially connected to the meter gear 15, the mounting plate is installed with a needle seat 1, the needle seat 1 is elastically retracted to set the meter needle 17, the tip of the meter needle 17 is located in the tooth gap of the meter gear 15, when the horizontal shaft 2 rotates, the teeth of the meter gear 15 continuously touch the meter needle 17, the meter gear 15 and the meter needle 17 are connected to the detection circuit, and the detection circuit can judge the rotation angle of the horizontal shaft 8 according to the number of times the two are in contact and energized; similarly, the vertical shaft 7 is coaxially connected to the meter gear 2 16, the platform section 5 is installed with a needle seat 2, the needle seat 2 is connected to the meter needle 2 18, when the vertical shaft 7 rotates, the teeth of the meter gear 2 16 continuously touch the meter needle 2 18. The meter gear 2 16 and the meter needle 2 18 are connected to the detection circuit, and the detection circuit judges the rotation angle of the vertical shaft 7 according to the number of times the two are in contact and energized.

[0026] (Electric engine aircraft) Three-blade fixed-wing (propeller) steering gear operation and structure usage:

[0027] The mounting plate 1 is mounted on the front end of the aircraft wing through the mounting hole 10, so that the transverse axis 2 is in the transverse direction and the vertical axis 7 is in the vertical direction, and the device is symmetrically mounted on both sides of the aircraft wings;

[0028] The engine is mounted on the bottom end of the vertical shaft 7 through a suspension to provide power to the aircraft;

[0029] The electric hydraulic telescopic rod 4 drives the rocker arm 3 to drive the lateral axis 2 to rotate, so as to adjust the elevation angle of the engine. The brake motor 8 drives the worm 9 to drive the worm wheel 6 to drive the vertical axis 7 to rotate, so as to adjust the left and right angles of the engine, thereby realizing the angle adjustment of the engine, and further enabling the aircraft to realize vertical ascent and descent, flexible steering and other actions;

[0030] During the engine angle adjustment process, the horizontal shaft 2 rotates so that the meter gear 15 continuously touches and presses the meter needle 17, and the longitudinal shaft 7 rotates so that the meter gear 2 16 continuously touches and presses the meter needle 2 18. Each set of meter needles and meter gears are connected to the meter circuit in the form of a switch, and the controller of the meter circuit measures the number of times the meter needle and the meter gear touch and are energized.

[0031] Although the embodiments of the present invention have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the above embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. (Electric engine aircraft) Three-blade fixed wing (propeller) steering gear operation and structure, including a mounting plate for connection to the front wall of the aircraft wing, characterized in that: Two mounting plates are provided, and a horizontal transverse axis is set between the two mounting plates. The transverse axis is rotatably connected to the mounting plate. A driving component 1 is provided to drive and connect the transverse axis. The middle section of the transverse axis is a platform section. The platform section is rotatably connected to a vertical axis. The vertical axis is perpendicular to the transverse axis. A driving component 2 is provided on the platform section to drive and connect the vertical axis. The bottom end of the vertical axis is the engine mounting position.

2. The operation and structure of the three-blade fixed-wing (propeller) steering machine (electric engine aircraft) according to claim 1, characterized in that: The driving assembly 1 comprises an electro-hydraulic telescopic rod arranged on the front end wall of the aircraft wing, the side wall of the transverse axis has a rocker, and the electro-hydraulic telescopic rod drives and connects the rocker.

3. The operation and structure of the three-blade fixed-wing (propeller) steering machine (electric engine aircraft) according to claim 2, characterized in that: The second driving component comprises a motor with a brake arranged above the platform section, the motor with a brake is connected to a worm, a worm wheel is externally arranged on the vertical shaft, and the worm is meshed with the worm wheel.

4. The operation and structure of the three-blade fixed-wing (propeller) steering machine (electric engine aircraft) according to claim 3, characterized in that: The transverse axis is coaxially connected to a meter gear one, and a needle seat one is installed on the mounting plate. A meter needle one is elastically and telescopically arranged in the needle seat one, and the tip of the meter needle one is located in the tooth gap of the meter gear one. When the transverse axis rotates, the teeth of the meter gear one continuously touch the meter needle one. Similarly, the vertical axis is coaxially connected to a meter gear two, and a needle seat two is installed on the platform section. The needle seat two is connected to a meter needle two. When the vertical axis rotates, the teeth of the meter gear two continuously touch the meter needle two.

5. The operation and structure of the three-blade fixed-wing (propeller) steering machine (electric engine aircraft) according to claim 4, characterized in that: The mounting plate is provided with a longitudinal mounting hole for being connected with the front end bolts of the aircraft wing.

6. (Electric engine aircraft) Three-blade fixed wing (propeller) steering gear operation and structure use method, characterized in that: The three-blade fixed-wing (propeller) steering machine operation and structure of (electric engine aircraft) according to claim 5 also includes: S1. Install the mounting plate on the front end of the aircraft wing through the mounting hole so that the transverse axis is in the transverse direction and the vertical axis is in the vertical direction. The wings on both sides of the aircraft are installed symmetrically (electric engine aircraft) three-blade fixed wing (propeller) steering machine operation and structure; S2. Install the engine at the bottom of the vertical shaft through the suspension to provide power to the aircraft; S3. The lateral axis is rotated by driving the rocker arm through the electro-hydraulic telescopic rod to adjust the elevation angle of the engine. The vertical axis is rotated by driving the worm gear through the brake motor to adjust the left and right angles of the engine, thereby achieving the angle adjustment of the engine and further enabling the aircraft to achieve vertical take-off and landing, flexible steering and other actions; S4. Each set of meter needles and meter gears is connected to the meter circuit in the form of a switch. During the engine angle adjustment process, the horizontal axis rotates so that meter gear one continuously touches and presses meter needle one, and the vertical axis rotates so that meter gear two continuously touches and presses meter needle two. The controller of the meter circuit measures the number of times the meter needle and the meter gear touch and are energized.

Images