Summary In this paper, the adaptive back‐stepping controller is investigated for a class of strict‐feedback systems using command filter technique. Adaptive laws are designed updating parameters when both plant and actuator‐failure unknown. Furthermore, auxiliary dynamics developed to deal with input constraints. Closed‐loop stability asymptotic‐state tracking ensured. The method applied longitudinal generic hypersonic aircraft in presence actuator faults Based on parameter estimation,...

Background Plasma protein alterations may occur in patients with acute myocardial infarction (AMI). In this study, we investigated the plasma proteomics of first‐onset AMI to identify a novel diagnostic target for infarction. Methods Using case–control design, recruited 6 and age‐ sex‐matched healthy controls. Mass spectrometry was used analyze their proteomics. Additionally, enrolled 156 232 individuals validate differentially expressed proteins using ELISA. Results A total 58 were...

Sepsis is an inflammatory response caused by infection with pathogenic microorganisms. The body shock it called septic shock. In view of this, we aimed to identify potential diagnostic gene biomarkers the disease.Firstly, mRNAs expression data sets were retrieved and downloaded from GEO (Gene Expression Omnibus) database for differential analysis. Functional enrichment analysis was then used biological function DEmRNAs (differentially expressed mRNAs). Machine learning determine Thirdly,...

In this paper, a model reference adaptive control (MRAC) augmentation method of linear controller is proposed for air-breathing hypersonic vehicle (AHV) during inlet unstart. With the development flight technology, vehicles have been gradually moving to stage weaponization. During maneuvers, changes attitude, Mach number and back pressure can cause unstart phenomenon scramjet. Inlet causes significant in aerodynamics AHV, which may lead deterioration tracking performance or instability...

Aiming at the cooperative guidance problem of multi-hypersonic glide vehicles, a method based on parametric design and an analytical solution time-to-go is proposed. First, hypersonic reentry trajectory optimization was transformed into parameter problem. The parameters were optimized to determine angle attack profile time enter altitude velocity corridor. Then, using quasi-equilibrium condition, estimation form remaining flight analytically derived satisfy accurately constraint. Using...

The target-encirclement guidance problem for many-to-one missile-target engagement scenario is studied, where the missiles evenly distribute on a target-centered circle during homing guidance. proposed distributed law can achieve simultaneous attack of multiple in different line-of-sight directions. Firstly, decentralization protocols desired angles are constructed based information neighboring missiles. Secondly, biased proportional navigation that arbitrarily designate impact angle cited....

This paper presents a deep neural network-based online trajectory generation method for the aerodynamic characteristic description and terminal-area energy management of wave-rider aircrafts. First, flight dynamics equations in domain are linearized discretized to generate numerous aircraft samples with sequential convex optimization (SCO) methods. Then, an objective function is designed promote smoothness control variables improve similarity. Compared nonlinear programming (NLP), proposed...

The risk assessment of power network is beneficial to improve the reliability system. It only considers condition equipment itself in conventional methods, but lacks a consideration various influence factors network. A comprehensive method based on Equipment Condition and entropy proposed evaluate this paper. Firstly, model established, considering key including condition, structure, loads, natural weather etc. Then, AHP used determine subjective weight, while applied obtain objective...

A switch scheme of reaction-jet/aerodynamic multi-control missile using pose controlled pulse-engine is present. In order to increase response speed autopilot and reducing the coupling form Reaction-jet aerohelm, in last stage attacking aerodynamic controller disconnection used only. first part, model control system given; then, has been designed by variable structure control. Finally it proved simulation that this multiple can greatly enhance well robustness effect jet interaction.

The guidance accuracy of an infrared air-to-air missile is affected by various factors such as target maneuver, interference, and the natural environment. complicated confrontational environment posed maneuver decoy launch considered in this article. more practical adjoint analysis model for influence on established analyzing jamming process, motion characteristics, mechanism system point source decoy. By using method, barrel roll angular rate, numble simultaneous launch, ignition time,...

Hypersonic cruise missile always adopts the configuration of waverider body with restraint scramjet. As a result, lateral motion exhibits serious coupling, and controller design system cannot be conducted separately for yaw channel roll channel. A multiple input output optimal control method integrators is presented to combined hypersonic missile. model linearized as plant, which coupled by kinematics fin deflection between roll. In controller, are augmented, respectively, into loop angle...

Introduction: Septic shock, a severe manifestation of infection-induced systemic immune response, poses critical threat resulting in life-threatening multi-organ failure. Early diagnosis and intervention are imperative due to the potential for irreversible organ damage. However, specific sensitive detection tools septic shock still lacking. Methods: Gene expression files early were obtained from Expression Omnibus (GEO) database. CIBERSORT analysis was used evaluate cell infiltration. Genes...

Vertical launching technology can effectively improve the performance of antiaircraft missile, which reduce preparative time for missile to attack targets. The scheme vertical control system is present. autopilot has used angle pitch, yaw and roll as feedback signal. flight any direction from state by controlling Euler missile. model multiple controls aerodynamic actuator TVC (thrust vector control) given, then been designed using linear quadratic regulator (LQR) theory. Finally it proved...

The technology of Bank-to-Turn has been recognized as an attractive direction due to their significance for the control hypersonic glide vehicle. Strong coupling existing among pitch, yaw and roll channel was a great challenge banking turn, thus novel global sliding mode controller designed glider in this paper. Considering channels interference, we can use invariance principle motion realize decoupling control. system could eliminate stage reaching, which lead realization whole systematic...

A new assessment method based on the combination of factor analysis and probabilistic neural network (PNN) is proposed to meet research main equipment condition-based maintenance in power distribution ． As quantity parameters that represent state cable many，the multi-source information database established The missing for incomplete eliminated，and used calculate factors their scores, probability was evaluate operation status cable, then obtain a condition network．Simulation results show...

For hypersonic-vehicle fairing separation, the reliable separation of and rapid suppression disturbance are required in scenarios where there is high dynamic pressure abrupt changes aerodynamic shape aircraft as well overall parameters. A switching-based control method proposed this paper for interference aiming to ensure stability system cases controlled object. First, an unsteady-flow calculation adopted clarify characteristics model fairing-separation process established; then, two states...

Design of a robust controller for the longitudinal dynamics hypersonic aircraft by using parameter space method is present. The desirable poles are mapped to pole placement approach in this method. intersection common multiple mode system. This can meet need different phases aircraft. It has been proved simulation that highly performance precision and robustness disturbance caused separation, cowl open, fuel on off perturbation unknown dynamics.

An airbreathing hypersonic vehicle(AHV) generally adopts a scramjet engine as its propulsion, which needs strict conditions of flight dynamic pressure. A new pressure control system is presented, in the AHV autopilot directly uses to track command. Firstly, model established and state equations are given. Then, implemented using LQR optimal theory. The error augmented order add an integral with zero steady error. structure also obtained. simulation results show that has good performance for...

Remotely piloted unmanned combat aerial vehicle (UCAV) will be a prospective mode of air fight in the future, which can remove physical restraint pilot, maximize performance fighter and effectively reduce casualties. However, it has two difficulties this mode: (1) There is greater time delay network pilot-wireless sensor-UCAV, degrade piloting performance. (2) Designing universal predictive method very important to pilot different UCAVs remotely, even if model control augmentation system...

A strategy of intercepting the near-space hypersonic aircraft is proposed, which based on infrared window guidance, change guidance law from side constraint to fixed lead angle, sliding mode variable structure with prefix angle designed. First, setting up dynamic model for end interceptor direct force/aerodynamic control, deriving integrated mathematical interceptor’s longitudinal and control. Then, by using smooth Last, simulation results show that designed can achieve high precision...

The scramjet performance of air-breathing hypersonic vehicle is highly correlated with flight height, Mach and angle attack (AOA).The violent disturbance the AOA can cause engine power off.Consequently, maneuverability strictly limited in cruising period.A composite control system for an presented.The has a configuration tailcontrol rudders set deflectable wings installed nearby center gravity.During period, precision achieved by deflecting tail rudders, command maneuverable acceleration...