TWM558222U - Multi-rotor aircraft structure improvement - Google Patents

Abstract

A multi-rotor flight carrier is improved in structure, mainly on a main mechanism arm of the vehicle, and is provided with a control airfoil surface, and the control airfoil is linearly arranged with the main mechanism arm side view system, and the control airfoil is subjected to A servo drive performs front-rear angle switching with the vertical direction of the main mechanism arm as a reference zero degree, thereby changing the amount of wind received by the control airfoil; thereby, the light flow direction is controlled by a light force servo motor driving the control airfoil angle change In turn, the steering attitude of the steering is adjusted to reduce the power output.

Description

Multi-rotor flight vehicle structure improvement

This creation provides a structural improvement of a multi-rotor flight vehicle, especially a multi-rotor flight vehicle that is capable of controlling flight attitude with light power.

Press, four-rotor or multi-rotor aircraft, has become a very popular remote-controlled flight vehicle, generally used for recreational flight, or can be used for aerial photography, surveillance, recording important information. All kinds of multi-rotor aircraft are made of aluminum alloy or mixed materials, powered by electric servos, using high-energy density lithium-ion (Li-Po) batteries as the power source, and designed as a simple operation flight control system. If an electronic camera is equipped, it will become an aerial camera that is popular among players.

Patent No. M529656 "Hybrid High-paid Double Quadrotor Aircraft System" patent case (hereinafter referred to as the "Knowledge Case"), created by the applicant, is mainly composed of two four-rotor aircraft, one of which uses a gasoline engine. Designed for power, taking advantage of the powerful power of the gasoline engine, using a shorter arm length to concentrate the downward thrust, forming a stable strong and lasting lift contribution, increasing the weight of the payload; the other is an electric servo Designed for power, it is easy and flexible to operate. It uses a longer arm length. In addition to providing partial lift contribution, it will be responsible for flight control and attitude operation with a large cantilever torque. However, in the change control of the flight attitude (such as steering), the conventional method uses the acceleration of one motor propeller to meet the turning demand, for example, to accelerate the speed of the right propeller when the left corner is turned, and to accelerate the left side when the right corner is bent. The speed of the propeller. This kind of propeller acceleration method to control the flight attitude will cause power consumption and reduce flight time.

The creator has the above-mentioned lack of existence in the application of the case, but it is designed and improved, and the creation of this creation.

The main purpose of this creation is to provide a multi-rotor flight vehicle that can control flight attitude with light power.

The main feature of the present invention is that the carrier is radiated outwardly to pivotally connect the main mechanism arm of the propeller, and the main mechanism arm is pivotally connected with a control airfoil, and the control airfoil and the main mechanism arm side view system are Linearly arranged, the control airfoil is driven by a servo motor, and the vertical direction of the main mechanism arm is changed by an angle of reference zero, thereby changing the airflow direction of the control airfoil; thereby driving the control airfoil with a light force servo motor The angle is changed to control the direction of the airflow, thereby adjusting the flight attitude of the steering to reduce the power output.

Referring to FIGS. 1 to 3, the multi-rotor flight vehicle 1 of the present embodiment is exemplified by the same core combination of two quadrotors. The center of the flight carrier 1 has a core unit 2 including an engine and the like. The periphery of the core unit 2 radiates a plurality of main arm 3s extending outwardly, and the outermost top surface of the main mechanism arms 3 is disposed. There is a DC motor and a propeller 30 that is driven to rotate by the DC motor. The main improvement of the present invention is on the main mechanism arms 3, which are individually provided with a control airfoil 4 and a servo motor 5. among them,

The control airfoil 4, please also refer to Figures 2 and 3. It is made of a lightweight and durable board, and each control airfoil 4 is divided into two parts: a fixed plate 40 and a movable plate 41. The movable plate 40 and the movable plate 41 are arranged up and down, and are arranged in a straight line in a side view. The two are connected by a flexible segment 42 so that the movable plate 41 can be driven to move forward or backward. The top end of the fixed plate 40 is fixed to the bottom end of the main mechanism arm 3, and the control airfoil 4 and the main mechanism arm 3 side are regarded as a straight line arrangement.

The servo motor 5 is a forward/reverse servo. Attached to the fixed plate 40, the drive shaft of the drive servo 5 is coupled to the movable plate 41, and has the movable plate 41 controlled to deflect or vertically downward with the flexible segment 42 as a fulcrum to control flight. The direction of the airflow.

In application, by controlling the servo motor 5, the direction and magnitude of the movable plate 40 of the control airfoil 4 controlled by the servo motor 5 can be adjusted to control the airflow direction in the direction (see FIGS. 2 and 3). Control or turn control and other flights.

Because the above control method can drive the deflection angle of the movable plate 41 with the light force servo motor, the output power is small, and the power source can be saved.

In summary, this creation is not only novel, but also practical and industrially useful. It proposes a new type of patent application according to law.

1‧‧‧ flying vehicle
2‧‧‧ core unit
3‧‧‧Main body arm
30‧‧‧propeller
4‧‧‧Control airfoil
5‧‧‧Servo motor
40‧‧‧No moving board
41‧‧‧ movable plate
42‧‧‧ flexible section

Figure 1 is a perspective view of the present embodiment. Figure 2 is a side elevational view of the control airfoil of the present inventive embodiment. FIG. 3 is a schematic view showing the operation of the control airfoil of the present embodiment.

Claims (3)

A multi-rotor flight vehicle includes a core unit and a plurality of main arm arms radiating outwardly from a periphery of the core unit, the outermost top surface of the main mechanism arms is provided with a DC motor, and the DC motor is a driven propeller; characterized in that: a plurality of control airfoils are disposed, the control airfoil is disposed on the main mechanism arm, and the control airfoil is arranged in line with the main mechanism arm in a side view; The control airfoil is driven by a servo motor that controls the deflection angle of the control airfoil to control the direction of the airflow. The multi-rotor flight vehicle of claim 1, wherein the control airfoil is divided into a fixed plate and a movable plate; the fixed plate and the movable plate are arranged in a line, and the side view is linearly arranged. Connected by a flexible section; the top end of the fixed plate is fixed to the bottom end of the main mechanism arm. The multi-rotor flight vehicle of claim 2, wherein the servo motor is fixed to the stationary plate, and a drive shaft of the servo motor is coupled to the movable plate.