 Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 124 journals)
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- Numerical Investigations of Bump Effects on the Performance of
Double-Ended Airfoils and ABC Rotors-
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Abstract: Abstract Numerical simulations based on RANS have been performed to investigate the aerodynamic characteristics of the double-ended airfoil deformed by local bumps on its lower surface, both in airfoil and coaxial rotor environments. The two-dimensional results show that the bump can reduce the magnitude of negative lift but increase the drag at large negative AoAs and high Mach numbers, and can increase the stability of the airfoil at positive AoAs in forward flow and at large negative AoAs in reverse flow. A bump has a more significant effect on airfoil performance if it is closer to the leading edge and has a larger area. A coaxial rotor with different double-ended airfoils deformed by bumps located inboard was predicted under a 0.5 advance ratio with a lift-offset of 0.3. Bumps under such flight conditions influence the root region on the advancing side more than on the retreating side. The root region at 14 ~ 33% span produces about 6% of the total thrust, so bump’s effects on the whole performance are insignificant. Through the flow details around inboard sections, it suggests that bumps have the potential to improve ABC rotor performance, and flight conditions and blade geometry should be considered in conjunction with the application of bumps for effectiveness. Although the double-ended airfoil only covers the blade range of 0.14 ~ 0.33R, the total rotor thrust is slightly increased by adding bumps, and a higher bump has a greater influence.
PubDate: 2023-12-02
- Improvement of Satellite System Integration Process Based on Dummy Panel
Method-
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Abstract: Abstract This paper discusses the process improvement of a satellite system integration based on the dummy panel method. The system integration procedures using a traditional sequential flight model (FM) panel and the proposed dummy panel are modeled using a design structure matrix (DSM). A discrete event simulation using the DSM is developed to assess the two different integration and test strategies. The proposed DSM-based modeling and simulation enable clear work policies, effective input data gathering, and probabilistic results. The approach also offers decision-making and risk management guidelines, including a cost–duration trade-off study that considers real-world scenarios and their potential impact on the schedule and cost. The effectiveness of the proposed approach is demonstrated through a case study on an actual space system project.
PubDate: 2023-11-27
- Level and Program Analytics of MUM-T System
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Abstract: Abstract This study establishes the concept and classification system of MUM-T for the operation and development of AI-based complex combat systems. We analyze the core aspects of this system: autonomy, interoperability, and program level. AI MUM-T can improve the survivability of manned systems, expand their operational range, and increase combat effectiveness. We analyze technical challenges and program levels using data from the USA and UK, which are building the AI MUM-T integrated combat system. Currently, MUM-T is at the level of complex operation of a manned platform and an unmanned aerial vehicle platform. In the mid to long term, interoperable communication between heterogeneous platforms such as unmanned ground vehicles, unmanned surface vehicles, and unmanned underwater vehicles is possible. Depending on the level of development of the common architecture and standard protocols for interoperability between AI MUM-T systems, MUM-T can evolve from the “1 to N” concept to various combinations of operating concepts from “N to N.” The difference of this study from existing studies is that the core technologies of the fourth industrial revolution, such as AI, autonomy, and data interoperability, are reflected in the MUM-T system. In addition, an AI-enabled autonomous MUM-T operation and facility classification system was established by reflecting AI and autonomy in the existing unmanned system taxonomy, and the level and program were analyzed taking this into consideration.
PubDate: 2023-11-23
- Research of the Influence of Single-Flow and Dual-Flow Patterns on Fuel
Tank Washing Inerting Process-
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Abstract: Abstract The purpose of this study is that safety issues of modern aircraft always attract extensive attention worldwide. The combustion and explosion of fuel tank system is one of the main causes of aircraft accident. This paper builds a general mathematical model for a multi-compartment fuel tank and provides the initial conditions for a solution using the Runge–Kutta method according to mass conservation, the equation of nitrogen–oxygen dissolution and evolution, and the equation of gas flowing through the orifice. Nitrogen-enriched air (NEA) flow is usually used to decrease the oxygen concentration inside fuel tank to keep it below the oxygen concentration required to support combustion. With a four-compartment fuel tank as the research objective and adopting a domestic separation membrane to generate NEA, single-flow and dual-flow patterns are designed, respectively. Also, a washing inerting simulation is performed and the variation in the average oxygen concentration in the fuel tank and each compartment with the flight envelope is analyzed. The research results indicate that these two patterns can both meet the requirement that the average oxygen concentration of the upper ullage in the fuel tank should be lower than 12%. Although the single-flow pattern is simpler than the dual-flow pattern, it cannot avoid external air entering the fuel tank, which will cause the oxygen concentration in some compartments to be higher than 12% during the diving phase, while the dual-flow pattern can guarantee that the oxygen concentration of compartments does not exceed the limits during the entire flight. With the comparison between single-flow and dual-flow patterns, this study may provide some reference for the further design and study of washing inerting process for fuel inerting system.
PubDate: 2023-11-23
- Fixed-Time Adaptive Cooperative Dynamic Surface Control of Non-strict
Feedback Multi-agent Systems with Unmodeled Dynamics-
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Abstract: Abstract This paper deals with the fixed-time consensus tracking problem for a class of non-strict feedback multi-agent systems (MASs) with quantized input, full-state constraints, unmodeled dynamics and dynamic disturbances under a directed graph topology. A distributed adaptive dynamic surface control strategy is proposed on the basis of hysteresis quantizer. This strategy is a consensus tracking method that combines adaptive neural network control and fixed-time command filter backstepping. The non-strict feedback systems with full-state constraints can be converted into unconstrained systems by introducing a logarithmic nonlinear mapping. Radial basis function neural networks are utilized to approximate unknown nonlinear continuous functions. Unmodeled dynamics are handled by introducing a dynamical signal. In addition, the errors generated by the fixed-time filter are eliminated using the error compensation signals. The designed controller in this paper avoids the problems of “singularity” and “complexity explosion” under the traditional backstepping design framework, and the design introduces a hysteresis quantizer that can effectively conserve network resources. Results reveal that the consensus tracking error of MASs can converge to a small neighborhood of the origin in fixed time and all signals and states in the closed-loop systems are bounded based on the Lyapunov stability theorem and graph theory. The effectiveness of the method is verified by two simulation examples.
PubDate: 2023-11-23
- Simulation and Experimental Research on Shape Adjustment of Membrane
Reflector Antenna (MRA) Combined with Electrostatic Forces and Boundary
Cable Forces-
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Abstract: Abstract The membrane reflector antenna (MRA) possesses significant advantages, such as being light in weight and having a large storage ratio. As a result, it is considered one of the critical forms of space-borne antennas. However, the MRA faces a challenge in that it is easily impacted by thermal loads in space, and there is a lack of effective shape adjustment means. To address this issue, a bidirectional adjustment method has been proposed utilizing electrostatic forces and boundary cable forces. Firstly, the mechanical analysis model of the MRA, including the cable-membrane-truss structure, is constructed based on the energy variation principle. Then the calculation formula of electrostatic forces has been deduced considering the change in the distance between the membrane reflector surface and the membrane control surface. The update process of electrostatic forces has also been presented. Finally, an optimization model of the shape adjustment of the MRA has been established, with electrode voltages and boundary cable forces as design variables and the surface accuracy of the membrane reflector as the optimization goal. Simulation examples have been conducted under three types of temperature loads, and a 10:1 scaled experimental prototype has been used to verify the effectiveness of the shape adjustment method.
PubDate: 2023-11-20
- Wind Turbine Simulations Using CPU/GPU Heterogeneous Computing
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Abstract: Abstract In this study, a heterogeneous solution framework using both CPUs and GPUs was used to numerically simulate flow over the National Renewable Energy Laboratory (NREL) Phase IV horizontal-axis wind turbine. An in-house line-based unstructured flow solver implemented on CPUs was coupled to an in-house structured solver implemented on GPUs via a lightweight Python-based framework within an overset mesh system. First, computations were conducted for an isolated rotor at three different wind speeds of 7 m/s, 10 m/s, and 20 m/s, and subsequently full wind turbine simulations that included the nacelle and the tower. The entire system was used to understand the blade–tower interference on both upwind and downwind configurations, and the predictions were compared with the experimental data in terms of blade airloads. The effects of the laminar–turbulent transition were also investigated on a blade using the two-equation transition model coupled with Spalart–Allmaras turbulence model, whose inclusion resulted in a more accurate torque prediction. The downwind tower interaction was much more severe than the upwind interaction on the blade owing to its blade–wake interaction. Finally, a normal wind profile model was used to simulate the freestream wind shear during the wind turbine operation in an atmospheric boundary layer. Even a small variation in the wind speed resulted in a high level of unsteadiness in the blade airloads, which could generate vibratory loads on the wind turbine.
PubDate: 2023-11-15
- Fractional-Order Nonsingular Terminal Sliding Mode Control of a
Cable-Driven Aerial Manipulator Based on RBF Neural Network-
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Abstract: Abstract High-performance control of aerial manipulators with active interactive operation under lumped disturbance is challenging. In this article, a robust control scheme is developed for the precise and anti-disturbance motion control of a novel cable-driven aerial manipulator. The fractional-order nonsingular terminal sliding mode control in the control structure guarantees tracking accuracy and avoids singular issues. At the same time, the radial basis function (RBF) neural network is adopted to approximate and compensate for the lumped disturbance to improve the tracking accuracy and robustness of the system. Besides, the chattering phenomenon of the sliding mode control is weakened thanks to the fractional calculus and the replacement of the sign function by a novel power function. Finally, several comparative simulation cases are conducted, and the effectiveness and superiorities of the proposed control strategy are demonstrated.
PubDate: 2023-11-13
- Three-Dimensional Cooperative Guidance Law Against Maneuvering Target with
Time-Varying Communication Delays-
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Abstract: Abstract This paper presents a novel three-dimensional time-space cooperative guidance law against maneuvering target despite the presence of time-varying communication delays between missiles. The guidance law is divided into two parts. In the first part, a consensus protocol is designed for a multi-agent system consisting of a virtual leader and multiple followers. The objective is to tackle the problem of consensus convergence among the agents with communication delays. Additionally, the relationship between the upper bound of delays and the controller parameters is established. Based on the consensus protocol and a prescribed-time slide mode control method, the guidance law in the line-of-sight (LOS) direction is designed to ensure that the missiles attack the target simultaneously. In the second part, the multi-missile surrounding attack is achieved by designing different desired LOS azimuth and elevation angles for each missile. A guidance law in the normal LOS direction is designed based on the prescribed-time slide mode control method to ensure that the LOS angle converges to the desired values. To estimate the disturbances caused by the unknown and unpredictable acceleration of the maneuvering target in the LOS and normal LOS directions, fixed-time disturbance observers are designed. The stability analysis of the cooperative guidance law is provided in the appendix section. To demonstrate the effectiveness and superiority of the proposed cooperative guidance law, comparative simulations are performed.
PubDate: 2023-11-13
- A Robust Subpixel-Level Celestial Edge Localization Algorithm for Optical
Navigation-
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Abstract: Abstract The precise localization of celestial edges is crucial for autonomous navigation in deep space. This study proposes a high-precision subpixel-level edge localization method based on coarse and fine detection techniques for interplanetary optical navigation systems. First, pixel-level detection is improved by integrating the 8-neighborhood edge gradient and subdividing the edge width into a single pixel. Second, an accurate subpixel detection method using Zernike moments with the ramp edge model is advanced after analyzing the celestial object’s light intensity distribution and edge intensity. Third, the Otsu algorithm is integrated into the Zernike moments’ method, effectively improving the efficiency of the threshold selection. Finally, experiments conducted on simulated and real images, in comparison with three representative algorithms, show that the proposed algorithm can accurately estimate subpixel edges of celestial bodies while maintaining good robustness.
PubDate: 2023-11-11
- Froude Similarity and Flying Qualities Assessment in the Design of a
Low-Speed BWB UAV-
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Abstract: Abstract In the development of a blended wing body (BWB) planform for low-speed unmanned aerial vehicles (UAV), the present design approach relies on rather cost-effective fidelity tools in aerodynamic modeling and testing. This enables efficient analysis management of the huge parametric studies from airfoil to wing definitions, and proves thereby to be appropriate for conceptual design. Here, emphasis is put on the dynamic stability analysis and flight quality criteria assessment as early design tasks. This turned out to be a challenging task in the conceptual design, since there are no established standards criteria for small to medium scales UAVs. However, design criteria are often derived from the existing larger manned aircraft test data and adjusted for these UAVs. In the present work, on the one hand, it is first shown how existing criteria on short period and phugoid frequencies and damping can be applied to UAVs as inherent longitudinal stability characteristics. On the other hand, the control anticipation parameter (CAP) criterion is used to assess the inherent maneuverability. To overcome the lack of precise subsonic BWB data, adjustment of these criteria through Froude scaling and parameters tuning are used for the definition of the upscaled reference aircraft as a candidate for CAP criterion assessment. The proposed procedure is built on existing class I light aircraft data. It is thus shown how mass-based scaling provides a more realistic approach compared to other scaling techniques. Consequently, the flight quality level evaluated for the virtually upscaled aircraft is then assigned to the designed mini UAVs. It is then believed that the suggested study based on Froude similarity for predicting flight quality in the early design phase contributes to more efficient conceptual design.
PubDate: 2023-11-06
- Routing Prediction Strategy for UAV Swarm Network Using Pigeon-Inspired
Optimization-Based Neural Network-
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Abstract: Abstract A routing prediction strategy via a pigeon-inspired optimization (PIO)-based neural network (NN) is designed for UAV swarm networks with highly dynamic topology. The proposed strategy can predict the performance of the neighboring nodes as the next hop. For more precise prediction and less computational complexity, the states of the UAV swarm motion and the network are considered as the prior information, and the PIO-based NN framework is established. Based on the system model, PIO is applied to find the optimal weight matrices of the NN-based routing prediction model. The matrix of the hop count index function is calculated using this prediction model. The proposed strategy can directly determine the next hop based on the prediction results or can be combined with other routing methods to maintain a balance between the stability and the shortest path. Numerical simulations are conducted to demonstrate the effectiveness of the proposed strategy.
PubDate: 2023-11-01
- Study on Energy Balance at the Operating Points of Staged Combustion Cycle
LRE-
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Abstract: Abstract In the present research, liquid rocket engine (LRE) balancing was performed at the design and the off-design points to confirm the characteristics for a 9-tonf staged combustion cycle LRE whose propellant consists of LOx/kerosene. When an LRE is designed, basic specifications, such as combustion pressure and O/F ratio, are predetermined and the corresponding balancing values are decided. Nevertheless, an engine may run over a nominal point in actual operation. Thrust control valve (THCV) and O/F ratio control valve (OFCV) are activated to adjust the engine status in real operation whenever an engine runs out of the design point. The engine power balancing requires thermophysical properties of the LOx and the kerosene for the combustion process and those were adopted from the CEA, which is an open-source code written by NASA. Also, MATLAB was employed and symbolic generation and numeric calculation was proposed to help set up the governing system and to reduce computational load. The off-design points were suggested to be set at ± 7%, ± 5%, ± 3% variance range from the nominal combustion pressure and the O/F ratio. It has been derived from the results that the required power of the pump was greatest at OD3 while least at OD1. If the combustion pressure is higher than DP, the THCV pressure difference should be set lower than DP. If the O/F ratio is higher than DP, the OFCV pressure difference should be set higher than DP. When the combustion pressure is over 100 bar, the TIT is over 700 K. It should be taken carefully in this section for turbine safety.
PubDate: 2023-11-01
- Review on Metrics and Prediction Methods of Civil Aviation Noise
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Abstract: Abstract Civil aviation noise is one of the main factors hindering the growth of the civil aviation industry. With the increase in global air traffic demand, the problem of aviation noise pollution will become more and more serious. It is of great significance to carry out research in aviation noise. First, by summarizing the characteristics of aviation noise metrics, this paper divides them into three categories: single event noise metrics, cumulative exposure metrics, and daily metrics. Representative metrics of each category are selected for explanation and in-depth analysis. Second, according to the principles of aviation noise prediction models, this paper classifies these existing models into three categories: best practice models, scientific models, and machine learning models. Relevant academic research results are summarized. The best practice model regards the aircraft as noise point source, and its specialty is to predict noise under complex air traffic conditions. The scientific model considers the noise from the level of aircraft components and reflects the underlying physical effects. Based on data, the machine learning model uses algorithms to mine the hidden relationship between various factors and noise to achieve the purpose of noise prediction. Then, this paper introduces two kinds of aviation noise simulation software based on the best practice and scientific models, and lists their access addresses. Finally, challenges and prospects are presented from three aspects: metrics, prediction models and simulation software.
PubDate: 2023-11-01
- Effects of Cesium Salts on the Electrical Conductivity of the Weakly
Ionized Gas in a Hypersonic MHD Channel-
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Abstract: Abstract To adequately utilize the high enthalpy of the weakly ionized gas and improve the performance of the magnetohydrodynamic generator (MHDG) in a hypersonic channel, cesium salts are homogeneously injected into the gas at the entrance of the MHD channel for elevating the gas electrical conductivity. The finite rate chemical dynamics and multi-species electrical conductivity model for seven-species (N2, O2, N, O, NO, NO+, e−) were adopted to simulate the electrical conductivity of the weakly ionized gas under different magnetic fields. The results demonstrate that the electrical conductivity of the weakly ionized gas with cesium salts is significantly higher than that without cesium salts due to two positive contributions of cesium salts, one is that a portion cesium atom ionize much more electrons, and the second is that cesium salts reduce the activation energy of \(N + O \leftrightarrow NO + e -\) by 3.5 times, which accelerates the production rate of electrons. The electrical conductivity of the gas with cesium salts is decreased monotonically along the flow direction, which is contrary to the trend of that without cesium salts. The variation of the collision frequency plays a crucial role in the electrical conductivity of the gas without cesium salts, nevertheless, this effect is marginal on the gas with cesium salts. The magnetic fields have negative impacts on the electrical conductivity of the gas with/without cesium salts. Additionally, the MHDG power generation efficiency is augmented with B for the gas with cesium salts, whereas the trend is reversed for that without cesium salts.
PubDate: 2023-11-01
- Active Debris Removal Simulations Using Spider-Web Space-Nets for KITSAT-1
Satellite-
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Abstract: Abstract This paper conducts capture simulations using space-nets based on the spider-web structure for Korea’s first satellite, KITSAT-1 to investigate the capture performance of the spider-web space-net. A nonlinear structural dynamics analysis code, ABAQUS, is used in the simulation study. Explicit scheme is applied to represent the nonlinearity and geometrical large deformation behaviors of the space-net. The capture performance of two types of space-net is investigated when changing the design parameters of the space-net from the baseline model. The numerical results show that the spider-web space-net has a better capture performance than the square space-net, and the possibility of the space-net as a means of capturing KITSAT-1 is investigated.
PubDate: 2023-11-01
- Vibration Energy Transfer Characteristics of Panels with Multiple Coupling
Forms in Satellites-
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Abstract: Abstract Micro-vibrations on-board a satellite have degrading effects on the performance of certain payloads like observation cameras. There are numerous sources and extremely complicated transfer paths for micro-vibration in satellites. The vibration energy transfer characteristics of panels with multiple coupling forms in satellites were analyzed, which can guide the vibration isolation measures of satellites. First, the satellite was divided into honeycomb panel subsystems with multiple coupling forms. In the next phase, based on the energy finite element analysis (EFEA), the energy finite element equation of the honeycomb subsystem and the connection matrix at the coupling boundary was established to determine the energy distribution and energy flow characteristics of the multiform coupled honeycomb panels under different excitation frequencies. Finally, the finite difference approximation based on the response obtained from the measurement point array was employed to obtain the energy density. By comparing the results of the experiment and EFEA simulation under different frequency excitations, the average error of the energy density was less than 4 dB, which proved the accuracy of EFEA in the transfer characteristics analysis of the vibration energy of the satellite. The experiment method of vibration transfer based on the finite difference approximation can directly obtain the energy density of the structure.
PubDate: 2023-11-01
- International Civil Aviation Organization (ICAO) Based Noise Exposure
Levels at Kuwait International Airport (KIA): Assessment and Mitigation
Strategies-
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Abstract: Abstract The article presented data analysis to address the challenge of reducing noise occurrence in the case of neighbourhoods that are close to the airport. A data analytic approach to this challenge is novel and makes contributions in the aspect of future aerospace sciences. This paper studied the noise exposure level of Kuwait International Airport (KIA) using a mathematical model from the International Civil Aviation Organization (ICAO) and actual data records for the year 2018. Then it specified if the noise restrictions have been fully applied by the airport authority, knowing that these restrictions have been evolved by the International Civil Aviation Organization (ICAO). Moreover, since noise charges have been introduced at numerous airports worldwide, an optimal noise charge policy was determined, taking into consideration meeting the ICAO’s Policies on Charges for Airports and Air Navigation Services. Applying noise charges policy means that if the noise levels produced by aircrafts at the airport at given times specially at night exceeds standard levels identified by ICAO, then a financial penalty will be charged on the airlines companies contributing the most to such high noise levels. Such fine will encourage the airlines companies to reduce their flight frequencies and hence enhance the overall airport environment by reducing the noise levels. Eventually, this research mainly focused on noise level reduction in Kuwait International Airport (KIA) using two methods. First, ensuring adherence to ICAO restrictions and secondly, applying noise charges policy. To better clarify, this paer focused on both folds as follows: to evaluate if the use of noise cancellation fine yields good outcomes as regards noise reduction in the airport environment and to ensure adherence to ICAO restrictions.
PubDate: 2023-11-01
- Correction to: Experimental Investigation on Liquid Breakup and Injection
Characteristics of a Rotary Slinger Atomizer-
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PubDate: 2023-09-20
- Correction: Selected Papers from the 13th Asian Computational Fluid
Dynamics Conference (ACFD 2022) (Jeju, Republic of Korea, Oct.
16th–19th, 2022)-
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PubDate: 2023-09-15
DOI: 10.1007/s42405-023-00665-6
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