CN102923301A - Rotor composite propeller of helicopter - Google Patents

Abstract

The invention discloses a rotor composite propeller of a helicopter. The propeller comprises a main propeller shaft, at least two main propeller arms, rotor blades and a rotor shaft, wherein the main propeller shaft is connected with a power shaft of the helicopter and supplies power for the whole propeller; one ends of the main propeller arms are fixed on the main propeller shaft and the rotor shaft is installed at the other ends of the main propeller arms; and the rotor blades are fixed on the rotor shaft and can rotate freely. The propeller has the advantages of vertical taking off and landing, hovering, good maneuverability, and capability of gliding landing in a rotorcraft mode when the main propeller shuts down due to faults and improving flying stability and security, and the like.

Description

A compound rotor helicopter propeller

technical field

The invention relates to the field of aircraft, in particular to a compound rotor helicopter propeller.

Background technique

Helicopters have the advantages of vertical take-off and landing, hovering in the air, etc., and are widely used. However, when the main propeller stops due to failure, it cannot stall and glide, which is dangerous, and consumes a lot of energy during normal flight. The gyroplane has the advantages of gliding, stable flight and low energy consumption, but it has a long take-off distance and poor maneuverability. Integrating the advantages of the above two aircraft propellers will greatly improve the maneuverability of the aircraft.

Contents of the invention

The purpose of the present invention is to overcome the shortcomings in the prior art, and provide a compound rotor helicopter propeller with good maneuverability and simple structure.

The object of the present invention is achieved through the following technical solutions:

A composite rotor helicopter propeller, comprising a main propeller shaft 1, two or more main propeller arms 2, rotor blades 3 and rotor shafts 4; the main propeller shaft 1 is connected with the helicopter power shaft to provide power for the entire propeller; One end of the main propeller arm 2 is fixed on the main propeller shaft 1, and the other end is equipped with a rotor shaft 4; the rotor blades 3 are fixed on the rotor shaft 4 and can rotate freely.

The number of the main propeller arms 2 is preferably 2, 3 or 4, which are symmetrically distributed in space.

The rotation plane of the rotor blade 3 forms an angle with the rotation direction of the main propeller arm 2, and the range of the angle is greater than 0° and less than 60°. The number of blades of the rotor blades 3 is 2 or more.

The working principle of the present invention is: main propeller shaft 1 is connected with helicopter power shaft, provides power for whole propeller; Under the action of wind force, it rotates and generates lift.

Compared with the prior art, the present invention has the following advantages and effects:

1. The main propeller shaft of the present invention can generate greater lift under relatively low speed conditions, which improves the application range of the engine, is beneficial to reduce loss and prolong life, and is especially suitable for flying at low altitude and low speed.

2. The present invention is applied to a helicopter. When the main propeller shaft stops rotating during flight, the rotor blades can provide lift to continue gliding and landing, which improves the flight reliability of the helicopter.

3. In the present invention, the outer edge of the main propeller arm with the highest linear velocity generates effective lift, which reduces the overall weight of the propeller.

Description of drawings

Fig. 1 is a schematic structural diagram of Embodiment 1 (4-spindle propeller arm).

Fig. 2 is a schematic structural diagram of Embodiment 2 (2 spindle propeller arms).

Fig. 3 is a schematic structural view of Embodiment 3 (3-spindle propeller arm).

Fig. 4 is a structural schematic diagram of three kinds of rotor blades.

Among them: 1. Main propeller shaft; 2. Main propeller arm; 3. Rotor blade; 4. Rotor shaft.

Detailed ways

The present invention will be described in further detail below in conjunction with the examples, but the embodiments of the present invention are not limited thereto.

Example 1

As shown in Figure 1, the composite rotor helicopter propeller includes main propeller shaft 1, 4 main propeller arms 2, rotor blades 3 and rotor shaft 4; main propeller shaft 1 is connected with the helicopter power shaft to provide power for the whole propeller; 4 Two main propeller arms 2 are symmetrically distributed in space, one end of the main propeller arm 2 is fixed on the main propeller shaft 1, and the other end is equipped with a rotor shaft 4; the rotor blades 3 are fixed on the rotor shaft 4.

When the main propeller shaft 1 with power drives the main propeller arm 2 to rotate, the rotor blades 3 at the ends of the four main propeller arms 2 are driven to rotate by air resistance, and the rotor shaft 4 is an unpowered shaft, so that the rotation plane of the rotor blade 3 is in line with the main propeller The advancing direction of the arm 2 is at a certain elevation angle to generate lift.

The aircraft is similar to a general helicopter when it takes off, lands and hovers normally. When the aircraft has forward thrust or forward inertial flight and landing, even if the main propeller arm 2 stops rotating, a certain lift will be generated on the 4 rotor blades 3, and the flight mode is the same as that of the rotorcraft.

As shown in FIG. 4 , the number of blades of the rotor blades 3 can be 2, 3 or 4.

Example 2

As shown in Figure 2, the composite rotor helicopter propeller includes a main propeller shaft 1, 2 main propeller arms 2, rotor blades 3 and a rotor shaft 4. The 2 main propeller arms 2 are symmetrically distributed in space, and others are the same as in Embodiment 1 .

Example 3

As shown in Figure 3, the composite rotor helicopter propeller comprises main propeller shaft 1, 3 main propeller arms 2, rotor blades 3 and rotor shaft 4. 3 main propeller arms 2 are distributed symmetrically in space, and others are the same as in embodiment 1 .

Claims (4)

1. A compound rotor helicopter propeller, is characterized in that: comprise main propeller shaft, 2 or more than 2 main propeller arms, rotor blade and rotor shaft; Main propeller shaft is connected with helicopter power shaft, provides power for whole propeller ; One end of the main propeller arm is fixed on the main propeller shaft, and the other end is equipped with a rotor shaft; the rotor blades are fixed on the rotor shaft and can rotate freely. 2. compound rotor helicopter propeller according to claim 1, is characterized in that: the quantity of described main propeller arm is 2, 3 or 4, and is symmetrically distributed in space. 3. The compound rotor helicopter propeller according to claim 1, characterized in that: the rotation plane of the rotor blade and the rotation direction of the main propeller arm form an angle, and the angle range is greater than 0 degrees and less than 60 degrees. 4. The compound rotor helicopter propeller according to claim 1, characterized in that: the number of blades of the rotor blades is 2 or more.

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