CN101811572A - Coaxial-inversion birotor eight-rotary wing aircraft - Google Patents

Abstract

The invention discloses a coaxial reverse dual-rotor eight-rotor aircraft, which relates to the technical field of unmanned aerial vehicles. The aircraft includes a body (1), four support arms (2), four dual rotors (3), landing gear (4) and electronic control System (5), the four support arms (2) are connected to the periphery of the body (1), the geometric center lines of the four support arms (2) are on the same plane, and the geometric centers of the two adjacent support arms (2) The angle between the lines is 90 degrees; the four double rotors (3) are respectively arranged at the ends of the four support arms (2), the landing gear (4) is symmetrically connected to the body (1), and the electric control system (5) is arranged on Inside the machine body (1), four double rotors (3) are controlled and connected. The aircraft of the present invention has a high lift-to-weight ratio and load carrying capacity.

Description

Coaxial inverted dual-rotor octorotor aircraft

technical field

The invention belongs to the technical field of unmanned aerial vehicles, and relates to a novel structure of a coaxial reversing dual-rotor multi-rotor aircraft.

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 have vertical take-off and landing functions, and can also hover in the air. They have a wide range of needs in military reconnaissance, anti-terrorism, public security, fire protection, forest inspection, nuclear leak detection, and disaster relief. In particular, the micro-rotor aircraft has very broad application prospects in both military and civilian applications, including reconnaissance and surveillance under complex terrain conditions for field operations; communication relay; detection of nuclear pollution or detection in special environments; reconnaissance buildings The internal situation of objects; surveillance, monitoring, hostage rescue and anti-terrorist operations. In terms of civil use, micro-rotor aircraft can be used in various applications such as searching for disaster survivors, toxic gas or chemical pollution, building monitoring and evaluation, inspection of oil and power pipelines, and civil aviation photography. At present, winged aircraft mainly include single-rotor (main rotor + tail rotor) helicopters, double-suspended-wing (coaxial inversion) helicopters, and four-rotor aircraft. -29 helicopters, four-rotor aircraft of the German Microdrone company, etc. The lift and weight of the above-mentioned rotorcraft are relatively low, and the carrying capacity is very poor when designed as a micro-miniature aircraft, which greatly restricts its application in various fields.

Contents of the invention

The purpose of the present invention is to solve the problems of low lift/weight ratio and insufficient miniaturized carrying capacity of existing aircraft with vertical take-off and landing and hovering functions, and propose a coaxial reverse dual Rotor octocopter.

In order to achieve the above object, the technical scheme of the present invention is as follows:

Coaxial inverted dual-rotor octo-rotor aircraft, including the body, four support arms, four dual rotors, landing gear and electronic control system, the four support arms are connected around the body, and the geometric centerlines of the four support arms are at the same On the plane, the angle between the geometric centerlines of two adjacent support arms is 90°; the four double rotors are respectively arranged at the ends of the four support arms, the landing gear is connected to the body, and the electronic control system is arranged in the body. Controls and connects four twin rotors.

The above-mentioned dual-rotor is composed of two rotors and a motor or an oil engine that is directly connected to the rotors. The two rotors of each dual-rotor have the same rotational speed and the opposite direction of rotation. One of the two rotors of each dual-rotor is a forward propeller and the other is a reverse The lift direction generated by the rotation of the two rotors of each dual rotor is upward, and the motor or oil engine has two separate output shafts respectively connected to the two rotors of each dual rotor.

Each dual rotor is directly driven by a motor or a diesel engine, which eliminates the efficiency loss of the transmission system and improves the energy utilization efficiency and the lift-to-weight ratio of the aircraft. The two rotors of each dual rotor rotate at the same speed and rotate in opposite directions, and the torsional force generated on the body is equal in size but opposite in direction, so the sum torsion moment on the body is zero, ensuring the stability of the body attitude. At the same time reduce the rotational speed of two rotors of a dual rotor, the aircraft will fly along the geometric centerline of the support arm connecting the dual rotors from the body to the direction of the rotors, and reduce the rotational speed of any dual rotor, so that the aircraft can complete forward flight, inverted flight, Fly left and fly right. When the rotational speeds of the respective two rotors of the two adjacent dual rotors are reduced simultaneously, the aircraft can fly in any direction along the plane where the geometric centerline of the support arm is located. Four dual-rotors are installed at the ends of the four support arms and two rotors of each dual-rotor are connected to the two ends of the motor, which improves the space utilization rate and energy utilization rate of the aircraft, so the aircraft of the present invention has high lift /weight ratio and carrying capacity, it has broad application prospects in military and civilian use.

Description of drawings

Fig. 1 is the structural representation of coaxial inversion dual-rotor eight-rotor aircraft of the present invention;

Fig. 2 is a schematic diagram of the double rotor structure of the present invention.

Among the figure, 1. Airframe, 2. Support arm, 3. Dual rotors, 4. Landing gear, 5. Electronic control system, 301, first rotor, 302, second rotor, 303, drive mechanism.

Detailed ways

The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

As shown in Fig. 1, the coaxial reverse dual-rotor eight-rotor aircraft of the present invention comprises: a body 1, four support arms 2 connected around the body 1, four support arms 2 respectively arranged on the ends of each support arm 2 The double rotor 3, the landing gear 4 connected to the body 1, and the electronic control system 5 arranged in the body 1 to control and connect the rotors, the geometric centerlines of the four support arms 2 are on the same plane, each adjacent The included angle between the geometric centerlines of the two support arms 2 is 90°. The landing gear 4 is symmetrically connected to the body 1, provides support for the aircraft, and protects the rotor from colliding with the ground when the aircraft takes off and lands.

As shown in Figure 2, the above-mentioned dual rotor 3 is composed of a first rotor 301, a second rotor 302 and a drive mechanism 303 directly connected to the first rotor 301 and the second rotor 302. The drive mechanism 303 is a motor or an oil machine. One of the first rotor 301 and the second rotor 302 is a forward propeller and the other is a reverse propeller, and the first rotor 301 and the second rotor 302 are respectively connected to two output shafts of the driving mechanism 303 .

As shown in FIGS. 1 and 2 , the rotation planes of the first rotor 301 and the second rotor 302 of each dual rotor 3 are parallel to the plane where the geometric centerlines of the four support arms 2 are located.

Claims (4)

1. coaxial reverse dual-rotor eight-rotor aircraft, it is characterized in that, this aircraft comprises body (1), four support arms (2), four dual-rotors (3), landing gear (4) and electronic control system ( 5), the four support arms (2) are connected to the periphery of the body (1), the geometric center lines of the four support arms (2) are on the same plane, and the geometric center lines of the adjacent two support arms (2) are clamped The angle is 90 degrees; the four double rotors (3) are respectively arranged at the ends of the four support arms (2), the landing gear (4) is symmetrically connected to the body (1), and the electric control system (5) is arranged on the body ( 1), control and connect four double rotors (3). 2. coaxial reverse dual-rotor eight-rotor aircraft as claimed in claim 1, is characterized in that, described dual-rotor (3) is made up of first rotor (301), second rotor (302) and driving mechanism (303) ), the rotational speed of the first rotor (301) and the second rotor (302) are the same and the direction of rotation is opposite, and the drive mechanism (303) is provided with two separate output shafts, which are respectively connected to the first rotor (301) and the second rotor (302). 3. The coaxial reversing dual-rotor octorotor aircraft according to claim 2, characterized in that, the driving mechanism (303) is a motor or an oil generator. 4. The coaxial inverted dual-rotor eight-rotor aircraft as claimed in claim 1 or 2, characterized in that, the planes of rotation of the first rotor (301) and the second rotor (302) are compatible with the four support arms The plane where the geometric centerline of (2) is located is parallel to.

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