Reconstructing schlieren images of flow fields using wall pressure measurements is widely regarded as an effective technique for monitoring the state of flow fields in scramjet engines. However, this reconstruction process can be significantly affected by wave system changes resulting from flow field oscillations and boundary layer interference. To tackle this issue, we introduce a dual-branch network

By implementing dual synthetic jets (DSJ) control on a slender delta wing, the leading-edge vortex (LEV) is effectively managed, resulting in substantial modifications to the flow field structure on the upper surface. The co-rotating acceleration generated by the DSJ significantly retracts the LEV and reduces its rotational radius. This process also leads to a significant optimization of the flow topology

Unmanned aerial vehicles (UAVs) are increasingly employed in various fields owing to their mobility and cost-effectiveness. High-precision applications, such as communications, remote sensing, formation flight, and cooperative localization, require accurate onboard frequency standards and reliable time–frequency synchronization. Conventional approaches utilizing temperature-compensated or oven-controlled

This paper presents the application and assessment of a recently introduced boundary integral formulation for solving wave equations in domains bounded by porous or solid surfaces undergoing large deformations. Specifically, it is applied to predict acoustic waves generated by large-amplitude pulsations of a sphere immersed in an unbounded, quiescent, inviscid perfect gas. Fluid perturbations are expressed

Hypersonic inlet is exposed to severe aerodynamic force/heat loads, the impacts caused by the Fluid-Thermal-Structure Interaction (FTSI) are crucial. This paper proposes a three-dimensional FTSI framework and studies the FTSI effects of inlet. Subsequently, the mechanism of FTSI is elaborated, and the scale effect on hypersonic inlet is analyzed. Research shows that the traditional design of thermal-protection

The primary aim of this study is to investigate the buzz phenomenon and its onset mechanism in a supersonic air inlet by analyzing wind tunnel test data. The inlet under examination is an axisymmetric and mixed-compression inlet designed for a Mach number of 2. To examine the effects of boundary layer suction on changing the mechanism and characteristics of the buzz phenomenon, applying the slot and

Advancements in space technology have increased the demand for large-aperture space antennas essential for mobile communication and earth observation missions. To address these requirements, this study introduces a novel deployable antenna consisting of a deployable truss and a cable-net reflector. The primary novelty is the double-ring deployable truss, which integrates scissor mechanisms and telescopic

Based on the dual attention mechanism, the paper proposes a new hybrid algorithm of TCN-iTransformer for aircraft aerodynamic parameter estimation. This algorithm adopts a new iTransformer architecture, which applies Self-Attention and Feed-Forward Neural Network (FFNN) in inverted dimensions, and enhances the feature extraction by the prepositive placing an improved Temporal Convolutional Network

The liquid break-up in supersonic crossflow is primarily encountered in scramjet engines. An angled liquid jet injector can be considered an effective way to enhance liquid breakup and atomization, which is particularly convenient to implement and requires no additional work. The process of liquid fuel breakup, atomization and mixing of fuel involves multiple complex phenomena that are closely interconnected

Air mobility enabled by multirotor aircraft is an emerging transportation mode with wide real-world applications. Maximum range and flight duration are critical aspects of the performance, governed by the vehicle energy efficiency. This paper studies the energy-optimal planning of the multirotor, which aims at finding the optimal ordering of waypoints with the minimum energy consumption for missions

The flow field in a multistage compressor is complex and the loss evolution mechanism of each stage requires further study. A subsonic three-stage compressor designed by the authors’ team was used as the research object. The applicability of the total pressure loss weighting analysis method based on a vortex structure in a stage environment was discussed, and then, the operability of a dissipation

Sandwich structure with corrugated core configuration is amicable for Integrated Thermal Protection System (ITPS) panels of Reusable Launch Vehicles (RLVs), since it can provide sufficient stiffness, strength and thermal insulation. These panels can experience spatial and temporal variation of temperature resulting in vehicle location dependent transient stresses. Thus, spatially optimized design of

The maneuverability of high-speed aircrafts in flight needs to be improved. However, conventional control methods for rudder deflection have disadvantages such as poor control effect and low control efficiency. In this paper, the ability of using high energy jet arrays to change the structure of the rudder plate flow field and enhance the control efficiency of the rudder is numerically simulated and

This paper studies the autonomous maneuver decision-making problems of unmanned combat aerial vehicles (UCAVs) engaged in one-to-one within visual range (WVR) air combat. Based on expert experience, we construct a relative situation-based air combat maneuver decision tree to generate expert databases. A generative adversarial imitation learning (GAIL) based decision-making method is developed for UCAVs

The laminar–turbulent transition has an important effect on the near-field flows past high-lift devices, but its effects on the far-field noise are not fully clear. To explore the influence of the transition on both flows and noise, the improved delayed detached eddy simulation (IDDES) method based on the k-ω-γ transition model (Tr-IDDES) is applied to simulate the flows past a finite-span wing with

Conventional ground track-based constellation designs focus on the distribution of ascending and descending nodes, addressing only the relative spacing of ground tracks. This study for the first time introduces an analytic constellation design framework that allocates ground track configurations by examining the distribution of independent intersection points, pioneering a comprehensive analysis of

Driven by the limitations of current turbulence models in predicting Shock Wave Boundary Layer Interference (SWBLI) flows with high accuracy, this study introduces an enhanced Bayesian Neural Network (RBNN)-assisted optimization framework designed to rapidly and accurately identify SST turbulence model parameters. To explore various SWBLI conditions under different shock intensities, a compressed corner

This paper presents an attitude control system for an Earth-pointing satellite, applicable to both circular and elliptical orbits. Two actuator configurations are proposed in this work: one utilizing two reaction wheels, three magnetorquers, and three pairs of Coulomb shells, and a reduced configuration with a single reaction wheel alongside the same set of magnetorquers and Coulomb shells. The magnetorquers

The article presents the analysis of pitching moment in a drone propeller. This aspect of blade design process is not frequently considered, as variable pitch propellers (VPPs) aren’t usually implemented in small-size aerial vehicles due to their mass and reliability issues. The research shows a potential for addressing these issues for both active- and passive VPP systems by pivot point displacement

Fast-moving technologies have enabled many new applications of Unmanned Aerial Systems for military and commercial purposes. This technological advancement has opened an incredible number of new opportunities for UAVs to be used in addressing a variety of societal challenges. Despite the considerable investments and operational success, the non-conventional UAV control surfaces design has not been

On-orbit servicing and active debris removal of non-cooperative spacecrafts rely on autonomous navigation systems, particularly visual navigation, to perform orbiting and approach maneuvers around the target. Robust pose estimation is a critical technology of visual autonomous navigation, providing position and orientation measurements for navigation filters. Learning-based monocular vision methods

The growing number of Geosynchronous Earth Orbit (GEO) objects necessitates efficient multi-sensor tasking methods to maintain a space object catalog (SOC) for accurate orbital state estimation and collision risk assessment. While sensor tasking methods based on probabilistic Random Finite Set (RFS) theory have recently gained attention, effectively capturing epistemic uncertainty arising from incomplete

Three-dimensional reconstruction of space non-cooperative targets is a crucial prerequisite for on-orbit servicing. Compared to image sensors, LiDAR can perform more accurate distance measurements in space, but the point cloud of LiDAR is sparse and lacks texture. This could lead to the failure of point cloud registration under large viewpoint differences. In this paper, we propose an image-guided

The rocket sled is an experimental ground-based device for hypersonic vehicles, which uses rocket boosters with strong thrust to obtain the aerodynamic characteristics of the load. In order to accurately predict the heat flux of the rocket sled at Mach 8–10, a geometrically similar blunt body configuration was analyzed in this study. Computational fluid dynamics (CFD) simulations were utilized to investigate

This study conducted a series of anti-icing experiments in a large-scale 3 m × 2 m icing wind tunnel, employing a full-scale two-dimensional nacelle model equipped with an original piccolo tube, an optimized piccolo tube, and three distinct enhanced heat transfer nacelle skins featuring surface structures integrated into the internal wall. Through these experiments, comprehensive relationship curves

Traditional integrated navigation algorithms for guided projectiles face significant roll error resulting from poor MEMS IMU accuracy and limited observability of roll angles during in-flight alignment. This article introduces a Lie groups-based Kalman filter (LG-KF) SINS/GNSS algorithm in the launch-centered earth-fixed (LCEF) frame to enhance navigation convergence and accuracy under conditions of

This study investigates the complex multi-scale and nonlinear flow phenomena of reusable rockets during vertical recovery under high subsonic inflow conditions. It focuses on the effects of angle of attack, inflow Mach number, and retro-propulsion jet interference on the aerodynamic characteristics of the rocket airframe. Proper orthogonal decomposition (POD) and dynamic mode decomposition (DMD) methods

The fuel types for the continuous rotating detonation ramjet engine (CRDRE) include gas, liquid, and solid. When the fuel types are different, the suitable range of flight Mach number for CRDRE varies. To determine the suitable range of flight Mach number for CRDRE with different types of fuels, a theoretical model of CRDRE with different types of fuels is established and validated by numerical simulations

This work focuses on the wave propagation in graphene platelets (GPLs) reinforced piezoelectric polymer composite plates. The GPL volume fractions in the multilayered structure vary step-wisely to emulate a functionally graded profile. The governing equations for the piezoelectric composite plate are obtained using the Reissner-Mindlin theory in conjunction with the Hamilton’s principle. A polynomial

The environment of beyond-visual-range (BVR) air combat is complex and dynamic, making traditional decision-making methods insufficient for modern combat scenarios. This paper first analyzes the confrontation process in BVR air combat and develops a corresponding decision-making model for air combat. To address the challenge of coupling maneuver and missile launch decisions, we propose a hybrid bifurcation

Based on the results of photometric simulation, the long-term optical observation data of NORAD 41586 is analyzed in this work. We find that the trend of the actual measured light curves on certain nights do not match the synthetic light curves under the nominal mode. The nights on which the peak occurred in the actual measured light curves did not coincide with the period of seasonal glint. We eliminate

The development of efficient solar aircraft necessitates advanced thermal management and energy utilization. Carbon nanotubes in single-walled (SWCNTs) and multi-walled (MWCNTs) form offer promising solutions due to their exceptional thermal and electrical properties. The stability and performance of CNT-based nanofluids, particularly in dynamic flight conditions are crucial. Factors such as solar

This work develops a novel design method for generating hypersonic inlets based on random non-uniform inflow (NUF) distribution. Basic flowfields for the inlets are established using the multi-objective particle swarm optimization algorithm, with the objective of simultaneously maximizing mass capturing ratio and minimizing energy loss. The non-uniform inlet (NUI) is then designed by adopting the classical

Solving compressible flows is of great significance in aerospace, but achieving high precision and high efficiency remains a challenging issue. In order to address this problem, we propose novel deep operator neural networks for solving compressible flows (CF-DeepONet) based on deep learning, comprising a trunk network and multiple branch networks. The trunk network extracts spatiotemporal features

To explore the feasibility of using liquid aviation kerosene in an advanced vortex combustor, a comprehensive numerical simulation is conducted to investigate the effects of blockage ratio, fuel injection position, and fuel/air jet momentum flux ratio on the flow and combustion characteristics in this study. The results indicate that as the blockage ratio increases, the vortex structures within the

Hybrid electric power system based on turboshaft engines (HEPS-TE) emerges as a practical solution for powering the land and air vehicles (LAVs), which are capable of operating both on land and in the air. The coordinated control strategy is crucial for achieving coordinated operation of the components of HEPS-TE, based on the optimal reference commands from the upper-level energy management strategy

In this paper, the dynamic behavior of a stochastic delay rotor-seal system with fractional damping is investigated. Firstly, the stochastic delay differential equation (SDDE) of the rotor-seal system with the fractional Muszynska seal force model is constructed. Then, the SDDE is reduced to one-dimensional Itoˆ average differential equation by the central manifold method and stochastic average method

To reduce the axial length and weight of the compression system in variable cycle engine (VCE), this study proposes a novel front/rear fan (FRFan) configuration. The design eliminates the variable inlet guide vane of the rear fan and replaces the front fan stator with variable camber stator (VCS), which adopts the same adjustment mechanism as the variable camber guide vane. In this configuration, the

This study presents tunable diode laser absorption spectroscopy techniques for simultaneous measurement of pressure, temperature, and velocity of supersonic flows. A triangular laser beam path is proposed to facilitate single-side installation of the tunable diode laser absorption spectroscopy system, velocity measurement in the passage with parallel side walls, and signal amplification by enhancing

This work outlines the design, commissioning, and successful implementation of the supercritical ethylene injector piston (SCIPi) in the T4 hypersonic shock tunnel facility at The University of Queensland. Short duration test facilities, such as T4, present significant challenges for delivering stable fuel plenum conditions to models due to short test times and the rapid firing sequence of the facility

Bird strikes with aircraft have been increasing, leading to higher safety risks for passengers and crew, and rising costs for airlines. This problem is expected to worsen with the advent of Advanced Air Mobility aircraft operating in low-altitude airspace, where the risk of bird strikes is the highest. Although extensive research has been conducted to investigate this issue, there remains a need for

This paper investigates the attitude control problem for quadrotor unmanned aerial vehicles under full-state constraints and unknown initial conditions, with a focus on both matched and unmatched uncertainty-disturbance models and particular attention to physical and virtual input saturations. Using the barrier Lyapunov function theory, an initial condition-free robust backstepping scheme is developed

In order to address the significant damage caused by interstage leakage flow to the compressor cascade performance and the flow field structure, an interstage seal air-entraining jet structure is designed to weaken the deteriorating effect of interstage leakage in this study. The effects of different jet positions, heights, and widths on the performance are researched. The findings indicate that the

To mitigate the negative impacts of streamwise vortex-shock train coupling interference and enhance the flow field quality, direct-connected wind tunnel experiments were conducted on the concave channel at incoming Mach numbers of 2.10 and 2.85. These experiments investigated the control effects of micro-vortex generators (MVGs) with different heights on the coupled flow field. The results indicate

Aircraft automatic landing control technology faces several challenges, including the complexity of nonlinear dynamic modeling, inadequate response to external environmental disturbances (such as wind speed), the difficulty of multivariable control, and the difficulty of meeting high-precision control requirements. To address these issues, this paper proposes an automatic landing control system based

We present an Interior-Point optimization framework for aerodynamic shape optimization, integrating the high-fidelity SU2 suite with IPOPT to handle high-dimensional, nonlinear design problems. The framework is evaluated using two standardized test cases from the AIAA Aerodynamic Design Optimization Discussion Group. The study systematically examines barrier parameter update strategies, including Mehrotra

Multi-fidelity surrogate models are of particular interest in aerospace applications, as they combine the computational efficiency of low-fidelity simulations with the accuracy of high-fidelity models. This methodology, often implemented via data fusion, aims to reduce the cost of data generation while preserving predictive accuracy. Despite the widespread use of traditional machine learning techniques

Flow control for lifting surfaces at high angle of attack is essential to increase the lift coefficient. Inspired by covert feathers of birds, a passive rotatable flap is added to the suction surface of an aerofoil to analyze its effectiveness and flow control mechanism from the perspective of fluid structure interaction. The lift coefficients of the aerofoil are measured by a balance, increasing near

Unmanned aerial systems (UAS), an integral part of the advanced air mobility (AAM) vision, are capable of performing a wide spectrum of tasks in urban environments. The societal integration of UAS is a pivotal challenge, as these systems must operate harmoniously within the constraints imposed by regulations and societal concerns. In complex urban space, safety has been a perennial obstacle to the

The study of the Two-Body and Circular Restricted Three-Body Problems in the field of aerospace engineering and sciences is deeply important because they help describe the motion of both celestial and artificial satellites. With the growing demand for satellites and satellite formation flying, fast and efficient control of these systems is becoming ever more important. Global linearization of these

Hybrid VTOL UAVs combine the configuration advantages of fixed-wing UAVs and rotary-wing UAVs, offering great environmental adaptability and improved forward flight efficiency, but they also impose more stringent demands on UAVs' safety attitude control, particularly during the transition mode. To address this issue, this paper proposes an adaptive safety attitude control strategy for a hybrid VTOL

To fill the gap in experimental research on adaptive stability enhancement casing treatment in stabilization of the counter-rotating axial compressor (CRAC), this paper takes a two-stage CRAC as the research object, and conducts a discrete distributed self-recirculating casing treatment (SRCT) stability augmentation experiment. The stabilization improvement approach previously proposed, cross-stage

Aluminum-water (Al-H2O) propellant is a solid propulsion that offers the advantages of cost-effectiveness and minimal signal feature. Nonetheless, prevailing formulations of Al-H2O propellants result in 70–80 % combustion residue, presenting a potential hazard in terms of nozzle blockage and specific impulse. In this study, oxidants were introduced into an Al–H₂O propellant to establish a methodology

Reliability assessment of aerospace structures is crucial for ensuring operational safety and preventing catastrophic failures. However, conventional reliability methods face significant challenges in adapting to diverse scenarios and capturing complex failure mechanisms under extreme conditions. To address the dual challenges of single-model dependency and modeling inaccuracy in such scenarios, the

With the advancement of aerospace technology, inflatable wings (renowned for their lightweight design and rapid deployment capabilities) have emerged as a promising solution for unmanned aerial vehicle rapid-response missions and extreme lightweight requirements. However, their reliability and safety under extreme conditions or sudden loads remain significant challenges, particularly due to limited

Establishing a precise intake pressure environment in the aeropropulsion systems test facility (ASTF) is critical for evaluating aeroengines' flight characteristics. The model-partial and robust active disturbance rejection control (ADRC), that is extended state observer (ESO)-based controller, has become a favorable solution to the complex intake pressure control system. The parameter b0, as the estimated

This study presents an intelligent control strategy for mitigating vibrations induced by external shocks on sandwich doubly curved panels with a Triply Periodic Minimal Surface (TPMS) core and piezoelectric face sheets. The sandwich panel system, equipped with piezoelectric materials as both sensor and actuator layers, is subject to external excitations, including airflow pressure and mechanical shocks

Progressive dynamic crushing remains a significant focus in contemporary research aimed at developing and optimizing energy-absorbing structures. This study investigates thin-walled passive energy absorbers featuring multi-level crush initiators in the form of spherical embossments. The experimental setup involved aluminum columns subjected to an impact energy of 1700 J. These columns were designed

This paper proposes an effective emission control strategy for an aero-engine using nonlinear dual-estimators, which aims to address challenges arising from state and parameter uncertainties. Transient air-fuel ratio (AFR) regulation issues, primarily caused by the wall-wetting and manifold-filling phenomena, are mitigated by a novel approach leveraging dual nonlinear estimators: (i) an extended Kalman