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Sensor layout method for hypersonic flight vehicle control surface structure distribution load identification

An aircraft rudder and hypersonic technology, applied in the aerospace field, can solve the problem of fewer sensor layouts, achieve the effect of avoiding clustered configurations and high solution efficiency

Active Publication Date: 2019-12-03
BEIHANG UNIV
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Problems solved by technology

However, there are relatively few studies on the optimization of sensor layout with the goal of structural dynamic load reconstruction

Method used

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  • Sensor layout method for hypersonic flight vehicle control surface structure distribution load identification

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Embodiment

[0056] The geometric dimensions of the aircraft selected in the present invention are based on the X51-A air-breathing hypersonic aircraft, and the finite element structure diagram of the plate structure simplified by means of equivalent mechanical properties of the control surface structure is as follows figure 2 As shown, a total of 3 partitions are used to encode the finite element nodes of the plate structure, and there are 660 nodes in total. The material parameters of the rudder surface are shown in Table 1, and the damping of each order is ignored.

[0057] Table 1

[0058]

[0059] It is assumed that the rudder surface structure is subjected to two kinds of loads, which are the linear distributed load acting on the leftmost boundary (load case 1) f(x,y,t)=5000te -2t cos(16πx) and surface distributed load acting on the entire rudder surface (load case 2) f(x,y,t)=50(-1-3x-3y+2x 2 +2y 2 +xy+4x 3 +4y 3 +2x 2 y+2xy 2 )[1-cos(30πt)], the real load on the rudder s...

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Abstract

The invention discloses a sensor layout method for hypersonic flight vehicle control surface structure distribution load identification. According to the method, the number and positions of sensors are taken as design variables, a comprehensive evaluation index is constructed based on a load identification robustness evaluation index representing the identification performance of the sensors and adistribution index reflecting the distribution performance of the sensors, and a sensor layout optimization model is established by taking the index as an optimization target. The method comprises the following steps: firstly, based on an interval process envelope method, establishing a dynamic distribution load identification model of an uncertain control surface structure, solving load identification parameters, and establishing a load identification robustness evaluation index; secondly, in order to eliminate redundant information in sensor configuration, establishing a distribution index;then, based on the two indexes, establishing a joint fitness function through a normalization and weight method; and finally, through an algorithm combining particle swarm optimization and sensor number updating, obtaining an optimal sensor layout of control surface structure distribution load identification.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a sensor layout method for identifying distributed loads on a rudder surface structure of a hypersonic vehicle. Background technique [0002] With the development of hypersonic vehicles in the direction of faster flight speed, longer flight distance, and stronger maneuverability, the load service environment they are facing is becoming more and more severe. The structural load design based on experience can no longer meet its higher structural reliability requirements. It is extremely difficult to directly measure the distributed dynamic load of the rudder surface structure of a hypersonic vehicle in a complex aerodynamic environment. It is urgent to accurately obtain the actual load of the structure and realize the structural load. The precise design of the distribution, and the load identification in the flight test is the main method to accurately obtain the actual load of ...

Claims

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Application Information

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IPC IPC(8): G06F17/50G06N3/00G06Q10/04G06Q10/06G06Q50/30
CPCG06Q10/04G06Q10/06393G06N3/006G06Q50/40Y02T90/00
Inventor 王磊刘亚儒刘易斯刘东亮
Owner BEIHANG UNIV
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