In order to cope with the challenges brought by the rapid growth of air traffic, effectively reduce aircraft flight delays, increase airspace capacity and operational efficiency, and reduce the workload of pilots of single pilot operations (SPO) mode aircraft. This paper proposes a spatiotemporal weighted pattern mining algorithm, which can effectively identify the aircraft combination with short distances and large flight delay in the airspace. The algorithm first mines the aircraft combination that meets the maximum spatial distance constraint in the airspace according to the spatial position relationship, and then uses the current delay time of the aircraft as the weight information of the aircraft, and then mines the aircraft combination that meets the distance constraint and the weight constraint at the same time, so as to provide help for the ground controller to make decisions and reduce the flight delay time of the aircraft in the airspace, and improve the operational efficiency of airspace. The experimental results show that the algorithm can accurately mine the aircraft combinations that meet both the maximum spatial distance constraint and the minimum weight constraint, effectively reduce the flight delay of single pilot operations mode aircraft in the flight, reduce airspace congestion, improve the airspace capacity and operation efficiency, and reduce the workload of pilots.
KEYWORDS: Intelligence systems, Artificial intelligence, Space operations, Evolutionary algorithms, Detection and tracking algorithms, Control systems, Clouds, Data processing, Strategic intelligence
To cope with the challenges brought by the rapid development of system intelligence, the variety of mission system pattern, the complexity of mission system environment, the constantly changing of the situation, an Automation, Autonomy and Artificial intelligence (3A) mission system for multi-domain joint operation is proposed, and it’s modeling and analysis are carried out. First, this paper introduced the development trend of mission system for multidomain operation. On this basis, the concept of 3A system and the levels about intelligence have been proposed. Finally, the effectiveness of 3A-based mission system organization is illustrated by modeling and analysis of a typical aerial combat assumption scenario.
Recently, active constrained layer damping (ACLD) has been widely used in vibration control and noise reduction. A
typical ACLD structure usually consists of three layers: the piezoelectric constraining layer, the viscoelastic damping
layer, and the host structure. In present study, the assumed modes method (AMM) is used for vibration modeling of
ACLD beams based on the Mead-Markus's sandwich theory. However, two cases called "case A" and "case B" arise
from the different choice of modes. The former chooses modes for three displacements including the axial displacement
of the active constraining layer, the axial displacement of the host beam, and the flexural displacement of the whole
structure, while the later selects modes for the axial and flexural displacements of the host beam. Detailed comparisons
are made on natural frequencies and modal loss factors with the results in the reference. It seems that for the same
number of modes, case A and B have similar precision on the 1st natural frequency and modal loss factor, yet case B
requires considerably less CPU time.
KEYWORDS: Finite element methods, Matrices, Differential equations, Spectral models, Chemical elements, Control systems, Gadolinium, Dynamical systems, Beam controllers, Feedback control
As we all know, the damping layer in the structures treated with active constrained layer damping (ACLD) is much softer
than the other layers. So thickness deformation in the damping layer may occur under flexural loads, which may
consequently change the dynamic characteristic and affect active control efforts. Thus, a new model for ACLD structures
is built with consideration of the thickness deformation as well as the shear deformation in the damping layer. Both the
differential equations and the boundary conditions are derived for the ACLD beams. The novel spectral finite element
method (SFEM) is used to model the ACLD structure in the frequency domain. And a special method called
"frequency-time conversion" is firstly proposed, which uses the eigenvalues and the eigenvectors to reconstruct the
control equation in the time domain. Then the linear quadratic regulator with a prescribed degree of stability based on
output feedback is used, which optimizes control energy and guarantees big damping simultaneously. And some
comparisons are made between the new model and the conventional Mead-Markus model.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.