阅读说明：本技术 一种用于倾转旋翼飞机的螺旋桨 (Propeller for tilt rotor aircraft ) 是由 闫文辉 赵磊 闫文静 彭腾飞 吴鹏 穆杰 于 2020-05-20 设计创作，主要内容包括：本公开涉及一种用于倾转旋翼飞机的螺旋桨,包括桨叶、桨毂,所述桨叶通过转轴与所述桨毂固定连接,所述转轴可相对于所述桨毂转动,所述桨毂内设置有扭转调节机构,所述扭转调节机构可调节控制所述转轴转动,进而带动所述桨叶转动。使得倾转旋翼飞机具备良好的综合气动性能,保证倾斜旋翼/螺旋桨在悬停和巡航两个状态下都能够达到良好的气动效率,两种状态都合理高效地工作。(The utility model relates to a screw for rotor aircraft verts, including paddle, propeller hub, the paddle through the pivot with propeller hub fixed connection, the pivot can for the propeller hub rotates, be provided with torsion adjusting mechanism in the propeller hub, torsion adjusting mechanism adjustable control the pivot rotates, and then drives the paddle rotates. Make the rotor aircraft that verts possess good comprehensive aerodynamic performance, guarantee that tilt rotor/screw can both reach good aerodynamic efficiency under hovering and cruising two states, two kinds of states work rationally high-efficiently all.)

1. A propeller for a tiltrotor aircraft, comprising a blade (1), a hub (2), characterized in that: the paddle (1) is fixedly connected with the propeller hub (2) through a rotating shaft (3), the rotating shaft (3) can rotate relative to the propeller hub (2), a torsion adjusting mechanism (12) is arranged in the propeller hub (2), and the torsion adjusting mechanism (12) can adjust and control the rotating shaft (3) to rotate so as to drive the paddle (1) to rotate.

2. A rotor for a tiltrotor aircraft according to claim 1, wherein: the torsion adjusting mechanism (12) comprises a rocker arm (4), a retainer (5) and a driving mechanism (6), one end of the rocker arm (4) is fixedly connected with the rotating shaft (3), the other end of the rocker arm (4) is provided with a follow-up column (7), the retainer (5) is provided with a clamping groove (8), the follow-up column (7) is located in the clamping groove (8), the retainer (5) is fixedly connected with the driving mechanism (6), the retainer (5) can be driven to do telescopic motion by the telescopic motion of the driving mechanism (6), the rocker arm (4) can be driven to do swing motion by the telescopic motion of the retainer (5) through the clamping groove (8) and the follow-up column (7), and then the rotation of the paddle (1) is adjusted and controlled.

3. A rotor for a tiltrotor aircraft according to claim 2, wherein: the driving mechanism (6) is an actuator.

4. A rotor for a tiltrotor aircraft according to claim 2, wherein: the servo column (7) is sleeved with a copper sliding sleeve (9), the copper sliding sleeve (9) and the servo column (7) can rotate relatively, the copper sliding sleeve (9) is located in the clamping groove (8) and matched with the clamping groove, and the copper sliding sleeve (9) can slide within the length range of the clamping groove (8).

5. A rotor for a tiltrotor aircraft according to any one of claims 1 to 4, wherein: the blade comprises a blade body (1) and is characterized in that the root of the upper surface of the blade body (1) is provided with a gas blowing hole (10), the blade body further comprises a gas blowing device, the gas blowing device is connected with a gas blowing pipe, the gas blowing pipe is aligned to the gas blowing hole (10), and gas flow blown out by the gas blowing device is blown out from the gas blowing hole (10) through the gas blowing pipe.

6. A rotor for a tiltrotor aircraft according to claim 5, wherein: the air blowing holes (10) are uniformly distributed at the root position of the upper surface of the blade (1).

7. A rotor for a tiltrotor aircraft according to claim 5, wherein: the automatic air blowing device is characterized in that a baffle is arranged in the paddle (1), the baffle is connected with an automatic control mechanism, and the automatic control mechanism can control the baffle to act, so that the air blowing holes (10) are opened or closed by the baffle.

Technical Field

The present disclosure relates to tiltrotor aircraft technology, and more particularly, to a propeller for a tiltrotor aircraft.

Background

Tiltrotor aircraft have both high-speed cruise capabilities not available with conventional helicopters and vertical take-off and landing and hover capabilities not available with fixed-wing aircraft, and these unique capabilities all benefit from their unique tiltrotor/propeller configurations. The operating state of a particular tiltrotor aircraft can be described as: when the tilt rotor aircraft is in a hovering state, the axis of the tilt rotor/propeller is vertical to the aircraft body, the propeller acts as a rotor of a common helicopter, and the propeller in the hovering state provides lift force to overcome the gravity of the aircraft, so that the aircraft can hover in the air or move in the vertical direction; when the tilt rotor aircraft is in a cruising state, the propeller tilts forwards to play a role of the propeller of the fixed-wing aircraft. At this time, the propeller only provides resistance against the high-speed forward flight of the aircraft, and the lift is mainly provided by the wings of the fixed wings.

The speed of the airflow flowing into the surface of the propeller plate in the hovering state is far less than the speed of the airflow flowing into the surface of the propeller plate in the high-speed cruising state. It can be seen from an analysis that the twist angle of the propeller blades for the hovering condition of the aircraft is small as shown in fig. 1, while the twist angle of the propeller blades for the high-speed cruise condition is large as shown in fig. 2. Therefore, the fixed-state propeller blades cannot guarantee that the tilt rotor aircraft can achieve good aerodynamic efficiency under two working conditions. The propeller designed in the flow state under the cruising working condition has good state and high propulsion efficiency under the cruising working condition, but under the hovering working condition, the root airflow attack angle is too large due to the large torsion of the blades, and serious separation flow can be generated on the suction surface of the root blades to form an airflow separation area, as shown in fig. 3.

Therefore, in order to make the rotor aircraft that verts possess good comprehensive aerodynamic performance, guarantee that tilt rotor/screw can both reach good aerodynamic efficiency under hovering and cruising two states, two states all work rationally high-efficiently, this application provides a screw for rotor aircraft that verts.

Disclosure of Invention

To address at least one of the above technical problems, the present disclosure provides a propeller for a tiltrotor aircraft.

The technical scheme adopted by the invention is as follows:

the utility model provides a screw for verting rotor aircraft, includes paddle, propeller hub, the paddle through the pivot with propeller hub fixed connection, the pivot can for the propeller hub rotates, be provided with torsion adjusting mechanism in the propeller hub, torsion adjusting mechanism adjustable control the pivot is rotated, and then drives the paddle rotates.

Furthermore, the torsion adjusting mechanism comprises a rocker arm, a retainer and a driving mechanism, one end of the rocker arm is fixedly connected with the rotating shaft, the other end of the rocker arm is provided with a follow-up column, the retainer is provided with a clamping groove, the follow-up column is positioned in the clamping groove, the retainer is fixedly connected with the driving mechanism, the retainer can be driven by the driving mechanism to do telescopic motion through the telescopic motion, the rocker arm can be driven by the retainer to do swing motion through the clamping groove and the follow-up column, and the rotation of the paddle is adjusted and controlled.

Further, the drive mechanism is an actuator.

Furthermore, the servo column is sleeved with a copper sliding sleeve, the copper sliding sleeve and the servo column can rotate relatively, the copper sliding sleeve is located in the clamping groove and matched with the clamping groove, and the copper sliding sleeve can slide within the length range of the clamping groove.

Furthermore, the root of the upper surface of the blade is provided with an air blowing hole, the blade further comprises an air blowing device, the air blowing device is connected with an air blowing pipe, the air blowing pipe is aligned to the air blowing hole, and air flow blown by the air blowing device is blown out from the air blowing hole through the air blowing pipe.

Furthermore, the air blowing holes are uniformly distributed at the root position of the upper surface of the blade.

Furthermore, a baffle is arranged in the blade and is connected with an automatic control mechanism, and the automatic control mechanism can control the baffle to act, so that the opening or closing of the blowing hole by the baffle is realized.

In conclusion, the scheme of the invention enables the tilt rotor aircraft to have good comprehensive aerodynamic performance, ensures that the tilt rotor/propeller can achieve good aerodynamic efficiency in the hovering state and the cruising state, and works reasonably and efficiently in the two states; when the tilt rotor aircraft is in a high-speed cruising state, the propeller can work ideally without adjusting the twisting angle of the blades or blowing operation at the blowing holes of the blades, and the propelling efficiency is very high; when the aircraft is in a hovering state, the torsion angle of the control blade is adjusted through the torsion adjusting mechanism, meanwhile, the air blowing device can be started, the separation area of the suction surface at the root of the blade is blown away by air flow blown out of the air blowing hole, the flowing state at the root of the propeller is improved, the hovering efficiency of the propeller is improved, the lift force load capacity of the propeller is increased, and the flight quality of the tilt rotor aircraft is improved.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.

FIG. 1 is a schematic view of a small twist angle of a blade in a hovering state of a propeller;

FIG. 2 is a schematic view of the large twist angle of the blades in the cruise condition of the propeller;

FIG. 3 is a schematic view of blade root flow heavy separation;

FIG. 4 is a schematic view of blade root flow separation improvement;

FIG. 5 is a schematic view of a twist adjustment mechanism in cooperation with a blade according to the present application;

FIG. 6 is a schematic view of the blade, hub, shaft, twist adjustment mechanism, blow hole assembly of the present application.

The labels in the figure are: the device comprises a propeller 1, a propeller hub 2, a rotating shaft 3, a rocker arm 4, a retainer 5, a driving mechanism 6, a servo column 7, a clamping groove 8, a copper sliding sleeve 9, an air blowing hole 10, an air flow separation area 11 and a torsion adjusting mechanism 12.

Detailed Description

The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.