CN101704413A - Six-rotor flying machine with rolling function - Google Patents

Abstract

The invention relates to an unmanned aerial vehicle, especially a six-rotor aircraft with a rolling function, which includes a body, six support arms connected around the body, six rotors respectively arranged on each support arm, and a control system arranged in the body. Connect the electronic control system of each rotor, and its geometric center planes are three support rings with equal ring diameters that are orthogonal to each other; the geometric center lines of the six support arms are on the same plane, and the two adjacent The angle between the geometric centerlines of the support arms is 60 degrees. One end of each support arm is fixedly connected to the body, and the other end is fixedly connected to one of the three support rings. The geometric center of the supporting ring coincides with the geometric center of the body. The aircraft can realize vertical take-off and landing, fast forward flight, inverted flight, hovering, and can also roll forward along the ground or the vertical outer wall of a building.

Description

Six-rotor aircraft with rolling function

technical field

The invention relates to an unmanned aircraft, in particular to a multi-rotor aircraft with a new structure and rolling function.

Background technique

Most of the current aircraft are fixed-wing aircraft. This aircraft cannot complete vertical take-off and landing, and needs a special runway or launching device, and its maneuverability is limited. Winged aircraft has vertical take-off and landing functions, and can also hover in the air. It has a wide range of needs in military reconnaissance, anti-terrorism, public security, fire protection, forest inspection, nuclear leak detection, and disaster relief. However, the current winged aircraft Mobility and stability are not enough. In particular, most of the current military conflicts in the world are small-scale military conflicts on a local scale. Battles mostly take place in urban settings, especially in the increasingly fierce anti-terrorism war. The enemy's reconnaissance, surveillance and position determination And other requirements are becoming more and more important, requiring the aircraft used to have ultra-high maneuverability. At present, winged aircraft mainly include single-rotor (main rotor + tail rotor) helicopters, double-suspension (coaxial inversion) helicopters, and four-rotor aircrafts. -29 helicopter, four-rotor aircraft of Microdrone Company of Germany, etc. The above-mentioned rotorcraft itself is a kinematic coupling system, the direction and attitude in flight are coupled, the flexibility and stability are poor, and the lift and weight of the aircraft are relatively low, and the carrying capacity is very poor when designed as a small aircraft.

Contents of the invention

The purpose of the present invention is to propose a six-rotor aircraft with rolling function to overcome the coupling of motion and attitude change, poor flexibility and stability, low lift and weight ratio and small size of the current aircraft with vertical take-off and landing and hovering functions Insufficient chemical performance and other defects.

The six-rotor aircraft with rolling function of the present invention comprises a body, six support arms connected around the body, six rotors respectively arranged on each support arm, an electric control system arranged in the body to control and connect the rotors, and The geometric center planes are three support rings of equal ring diameter connected to each other orthogonally; the geometric center lines of the six support arms are on the same plane, and the geometric center lines of the two adjacent support arms are on the same plane. The included angle is 60 degrees, one end of each support arm is fixedly connected to the body, and the other end is fixedly connected to one of the three support rings, the geometry of the three support rings is The center coincides with the geometric center of the machine body, and the six rotors are respectively arranged on the six support arms equidistant along the geometric center of the machine body.

The rotor is composed of a rotor and a motor or an oil engine that directly drives the rotor.

The angle between the plane of rotation of each rotor rotor and the plane where the geometric centerlines of the six support arms are located is equal, and the planes of rotation of the two rotor rotors on the same diagonal are coplanar, and the rotation of two adjacent rotor rotors in the opposite direction.

Each rotor is directly driven by a motor or an oil engine, which eliminates the efficiency loss of the transmission system, improves the energy utilization efficiency and the lift/weight ratio of the aircraft. The rotation directions of two adjacent rotors are opposite, and the forward and reverse rotating rotors have a positive effect on the body. The torque is opposite, so the speed of the six rotors can be adjusted to achieve zero torque on the body. The angle between the rotation plane of the rotor blade and the plane of the body makes the resultant force and moment of the lift of the six rotors on the body in three axes The six components of the direction are respectively controllable, so the aircraft can change the direction of motion while maintaining the same attitude in the air, or adjust the attitude while keeping the direction of motion unchanged, and can also change the direction of motion while changing the direction of motion. The change of attitude realizes the complete decoupling of motion and attitude. Three supporting rings with equal ring diameters connected as a whole with the geometric center plane being orthogonal to each other provide a suitable shell for the aircraft, so that the aircraft can Rolling along the ground or walls can not only save its own precious energy, but also has a high degree of concealment, and has an attractive prospect in military and anti-terrorism applications where information reconnaissance and acquisition are the main goals.

The aircraft with the structure of the present invention not only improves the lift/weight ratio, but also realizes the complete decoupling of three-axis motion and attitude through the speed control of six non-coplanar rotors, and has a high degree of maneuverability, and can realize vertical take-off and landing, Fly forward quickly, fly backward, hover, change any direction during flight, and roll along the ground or the vertical outer wall of a building. Therefore, this aircraft provided by the present invention has high maneuverability that any aircraft currently in use does not possess.

Description of drawings

Fig. 1 is the structural representation of the six-rotor aircraft with rolling function of the present invention;

Fig. 2 is a schematic diagram of the structure of the rotor shown in Fig. 1 .

Detailed ways

The present invention will be described in further detail below in conjunction with the embodiment given with accompanying drawing.

Referring to Fig. 1 , a six-rotor aircraft with a rolling function includes a body 1, six support arms 2 connected to the periphery of the body 1, six rotors 3 respectively arranged on each support arm 2, and six rotors 3 arranged in the body 1. The electronic control system 7 that controls and connects each rotor, its geometric center plane is mutually orthogonal and connected as a whole three support rings 4, 5, 6 of equal ring diameter; the geometric center lines of the six support arms 2 On the same plane, the angle between the geometric centerlines of two adjacent support arms is 60 degrees, one end of each support arm is fixedly connected to the body 1, and the other end is fixedly connected to the three support rings On one of the support rings 4, the geometric centers of the three support rings 4, 5, 6 coincide with the geometric center of the body 1, and the six rotors 3 are equidistant along the geometric center of the body. They are respectively arranged on the six support arms 2 described above.

Referring to Fig. 2, the rotor 3 is composed of a rotor 3.1 and a motor or an oil generator 3.2 directly driven and connected to the rotor 3.1.

The angle between the rotation plane of each rotor rotor 3.1 and the plane where the geometric centerlines of the six support arms 2 are located is equal, and the rotation planes of the two rotor rotors on the same diagonal are coplanar, and the two adjacent rotor rotors direction of rotation is opposite.

Claims (3)

1. six-rotor aircraft with rolling function is characterized in that comprising body (1), is connected six roots of sensation hold-down arm (2) that body (1) goes up on every side, is separately positioned on six rotors (3) on each hold-down arm (2), the support annulus (4,5,6) in ring footpath such as the electric-control system (7) that is arranged on each rotor of control linkage in the body (1), its geometric centre face are quadrature each other three of connecting as one; The geometric center lines of described six roots of sensation hold-down arm (2) at grade, angle is 60 degree between the geometric center lines of two hold-down arms that each is adjacent, one end of every hold-down arm is connected on the body (1), the other end is connected in described three of supporting in the annulus and supports on the annulus (4), described three are supported the geometric centre of annulus (4,5,6) and the geometric centre of body (1) coincides, and described six rotors (3) are separately positioned on the described six roots of sensation hold-down arm (2) along the geometric centre equiarm distance of body.

2. the six-rotor aircraft with rolling function according to claim 1 is characterized in that described rotor (3) is motor or oily machine (3.2) formation that is connected rotor (3.1) by rotor (3.1) with direct drive.

3. six-rotor aircraft according to claim 2, it is characterized in that: the plane of rotation of described each rotor rotor (3.1) equates with the interplanar angle in geometric center lines place of described six roots of sensation hold-down arm (2), and the plane of rotation coplane of two rotor rotors on the same diagonal line, the hand of rotation of adjacent two rotor rotors is opposite.

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