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Coaxial rigid rotor pneumatic elastic response method

A kind of aeroelasticity and rotor technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems without theoretical research and experimental verification

Inactive Publication Date: 2015-01-28
CHINA HELICOPTER RES & DEV INST
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

[0005] Domestic research on coaxial rigid rotor helicopters has just started, and there is no substantial theoretical research and experimental verification on the analysis methods of its flight trim and aeroelastic response.

Method used

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  • Coaxial rigid rotor pneumatic elastic response method
  • Coaxial rigid rotor pneumatic elastic response method
  • Coaxial rigid rotor pneumatic elastic response method

Examples

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specific Embodiment

[0092] Specific embodiment: take the XH-59A coaxial twin-rotor helicopter of Sikorsky Corporation of the United States as an example, and its relevant parameters are shown in Table 2. In the helicopter mode (without auxiliary propulsion device), the total weight of the whole machine is 5400Kg, the sea level is 300 meters, the pitch angle of the fuselage is 0°, the control angle is 40° in advance, and the rotor speed is 340rpm. Using the CFD / CSD loosely coupled aeroelastic response analysis method proposed by this method, including the whole machine trim calculation, the steady-state response and aerodynamic load of the rotor blade under different forward flight speeds and lateral lift offset (LOS) are analyzed. Simulation analysis. Specific steps are as follows:

[0093] Table 2XH-59A Helicopter Parameters

[0094] parameters

value

gross weight

5400kg

main rotor radius

5.49m

100% rotor speed

345rpm

Rotor pitch

0.75m

...

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Abstract

The invention provides a coaxial rigid rotor coupling pneumatic elastic response analysis method, and belongs to a helicopter kinetic analysis technology. The method is characterized in that according to the operation and control characteristics of a coaxial rigid rotor helicopter, a balance equation optimization solution method is built, and an optimization solution is found according to the given target and constraint conditions. According to the characteristic of complicated coaxial rigid rotor flow field environment, a rotor flow field is calculated by using a computational fluid dynamic method based on an Euler / N-S equation; and then, the coupling pneumatic elastic response is calculated by using a computational fluid dynamic / computational structural dynamic loose coupling analysis method. The coaxial rigid rotor coupling pneumatic elastic analysis method has the advantage that when the analysis method is used, balance operation and control parameters, blade response, rotor loads and the like of the coaxial rigid rotor helicopter can be calculated. The method has good analysis precision and engineering applicability; the relying of the development process on the test can be reduced; and the design period and the development cost can be greatly reduced.

Description

technical field [0001] The invention belongs to the helicopter dynamics analysis technology, and relates to an aeroelastic response analysis method for a coaxial rigid rotor helicopter. Background technique [0002] The coaxial rigid rotor helicopter is a new type of high-speed helicopter, and its rotor system includes a pair of coaxial, reverse, rigid hingeless rotors. It retains the most important features of conventional configuration helicopters - hovering and low-speed efficiency. When flying forward at a high speed, the lift is mainly generated by the forward blades of the two rotors, and the backward blades are unloaded, thereby avoiding the speed and load factor limitations caused by the backward blade stall, and using the up, The reverse force on the forward side of the lower counter-rotating rotor balances the torque of the hub to achieve lateral and roll trimming. The coaxial rigid rotor helicopter can significantly improve the forward flight speed and rotor eff...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 陈全龙朱艳
Owner CHINA HELICOPTER RES & DEV INST
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