Multi-dimensional vibration control method for the model of strut tail-supported aircraft

Patent metadata

Field	Value
Publication number	US-10969298-B2
Application number	US-201916761778-A
Country	US
Kind code	B2
Filing date	Sep 20, 2019
Priority date	Dec 18, 2018
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

A multi-dimensional vibration control method based on piezoelectric ceramic actuator applied to wind tunnel test of aircraft model. The pitch and yaw acceleration sensors arranged on the center of mass of the aircraft model are used to measure the two components of the main vibration acceleration of the aircraft model, and the main vibration vector of the aircraft model is obtained and the real-time vibration plane of the strut is determined. Inertia is introduced to solve the dynamic bending moment on the active section of the multi-dimensional vibration damper, and then the stress distribution on the active section is obtained. The multi-dimensional active vibration control system is adopted to improve the stability and reliability of the active vibration control system of wind tunnel model, extend the service life of piezoelectric ceramic actuator, and ensure the quality of wind tunnel test data and the safety of wind tunnel test.

First claim

The invention claimed is:

1. A multi-dimensional vibration control method for a strut tail-supported aircraft model, wherein the method is through the arrangement in the aircraft model on the center of mass of pitch and yaw acceleration sensor measuring aircraft model, the main vibration acceleration of two component, calculate a main vibration vector and determine a strut real-time aircraft model plane, introduction of inertial force to solve a multidimensional active vibration damper on an active section by dynamic bending moment, and then obtain an initiative stress distribution on the active section, through the real-time vibration plane space position relation of multidimensional vibration damper to participate in the work of piezoelectric ceramic actuator serial number; a vibration control force is calculated in real time according to the stress on the active section of a piezoelectric ceramic actuator, and then the dynamic bending moment is generated in the process of a reverse bending moment resisting the vibration of the aircraft model; the multi-dimensional vibration active control system based on the piezoelectric ceramic actuator is adopted to control the multi-dimensional vibration; the specific steps are as follows:
step 1: establish an absolute coordinate system of the aircraft model support system
the absolute coordinate system OXYZ (E) is established on an aircraft tail strut ( 4 ), and the coordinate origin is established in the equilibrium position at the intersection of the active section (F) and the axis of the aircraft tail strut ( 4 ), which is defined as O; the direction of the X axis coincides with the balance position of the axis of the aircraft tail strut ( 4 ) and points to the aircraft model ( 5 ),the direction of the Y axis is that the intersection of the active section (F) and the pitching plane points upward; the Z axis is determined by the right manipulation; a vibration measurement coordinate system O A X A Y A Z A (A) is established on the aircraft model ( 5 ), whose origin is established at the intersection of the centroid of the aircraft model ( 5 ) and the X axis of the absolute coordinate system OXYZ (E), which is defined as that the direction of the O A ;

X A coordinate axis coincides with the X axis of the absolute coordinate system OXYZ (E), the Y A coordinate axis and the Y axis of the absolute coordinate system OXYZ (E) point upward, and the Z A coordinate axis is determined by right manipulation;
step 2: obtain the components of the main vibration acceleration in the pitch plane and yaw plane in real time
using a pitching accelerometer ( 6 ) and a yaw accelerometer ( 7 ) at the centroid of the aircraft model ( 5 ) to measure the acceleration of the main vibration in the pitch plane and yaw plane perpendicular to each other, the acceleration of the main vibration is fed back to a real-time controller ( 8 ) controlled by an upper computer ( 9 ), and a plurality of acceleration sampling values of the pitch plane and the yaw plane are collected in each vibration control cycle, the acceleration components of the main vibration acceleration in the pitch direction and yaw direction in a vibration control cycle are calculated by formulas (1) and (2) respectively:

a
pith

⁡

(
t
)

=

∑

i
=
1

N

⁢

a
pithi

N

(
1
)

a

y
⁢
a
⁢
w

⁡

(
t
)

=

∑

i
=
1

N

⁢

a
yawi

N

(
2
)

among them, the acceleration component of the a pith (t) main vibration acceleration in the pitch direction, the acceleration component of the a yaw (t) main vibration acceleration in the yaw direction, a pithi (t) , a yawi (t) is the acceleration sampling value of the aircraft model ( 5 ) in the pitching plane and the yaw plane at the i sampling time, and N is the number of acceleration sampling values in each vibration control cycle, wherein i=1,2. . . N;
step 3: solve the main vibration acceleration vector in real time
the main vibration acceleration is obtained by combining the acceleration components in the pitching direction and yaw direction; the main vibration acceleration consists of magnitude and direction; the main vibration acceleration vector is constructed by solving the magnitude and direction of the main vibration acceleration vector in each vibration control cycle in real time by using formulas (3) and (4):



a
⁡

(
t
)



=

a
pith
2

+

a
yaw
2

(
3
)

∠
⁢

Assignees

• Univ Dalian Tech

Inventors

• Liu Wei
• Zhou Mengde
• Liang Bing
• Tang Linlin
• Yao Zhuang
• Wen Zhengquan
• Zhang Yang
• Si Likun
• Jia Zhenyuan

Classifications

• G01P15/02

  by making use of inertia forces {using solid seismic masses}(G01P15/14 takes precedence) · CPC title

• G01M9/04 Primary

  Details · CPC title

• G01M9/062

  Wind tunnel balances; Holding devices combined with measuring arrangements · CPC title

• G01M7/00

  Vibration-testing of structures; Shock-testing of structures (G01M9/00 takes precedence) · CPC title

• G01M9/08 Primary

  Aerodynamic models · CPC title