Take-off Aircraft Research Articles

Analisis Data Angin Permukaan di Bandara Udara Depati Amir Pangkalpinang Menggunakan Metode Windrose

Pangkalpinang is a city in the Bangka Belitung Islands that is close to the sea. This indicates that Pangkalpinang is influenced by land winds and sea breezes. The purpose of this study is to analyse the percentage of wind speed and maximum wind speed in Pangkalpinang City in each month. The data used were obtained from synoptic observations of the Depati Amir Class I Meteorological Station in Pangkalpinang from January to December from 2011 to 2020. The data obtained is processed using WRPLOT (Wind Rose Plots for Meteorological Data) software to determine the direction and magnitude of wind speed and produce wind pattern images in the form of wind rose diagrams. The results obtained show that the dominant wind blows from the Southeast (112 - 157°) with the highest wind speed of 1 - 4 knots with a percentage of 42.9%, while the maximum wind speed throughout 2011 - 2020 is 28 knots which occurred in the period January - December 2013. The results obtained show that the wind conditions at Depati Amir Airport Pangkalpinang are still safe for aircraft take-off and landing operations.

Comparison of Aerodynamics and Flight Performance of Fixed Wing Solar Powered Unmanned Aerial Vehicle When Separate Lift and Thrust Vertical Take-Off and Landing System is Installed

The objective of this research paper is to analyze the effects of installing a separate Lift and Thrust vertical takeoff system for fixed-wing solar powered UAVs in terms of flight performance changes. This research article uses a prototype aircraft in this study, which is a fixed-wing aircraft powered by an electrical system and equipped with a solar system. There are 2 types of designs, namely the type with installation and without installation of the Vertical Take-Off and Landing system which the vertical take-off and landing aircraft compared to the normal configuration will weigh 42.48% more and have a zero-lift drag coefficient of 67.1% more. The initial step involves creating an aircraft model in the XFLR5 software to assess the lift and drag coefficients and compare them with the wind tunnel test results. Subsequently, the software analysis findings are used to evaluate the flight performance of both aircraft configuration, as well as to identify the performance changes that occur when the VTOL system is installed. The outcomes align with expectations, installing a VTOL system leads to a significant reduce in flight performance, In particular, the Endurance and maximum range of vertical take-off aircraft are only 41.55% and 43.43% of normal aircraft and for solar-powered systems. The vertical takeoff has the Endurance and range is 31.46% and 32.06% of normal aircraft equipped with solar systems. which can be distinctly contrasted with the performance of aircraft in various aspects. However, these compromises are made in exchange for the capability to take off and land vertically.

Порівняння злітних характеристик двох типів крила для літака з можливістю короткого зльоту та посадки

The subject of study in this article is the effect of mechanization of the trailing edge of the wing, located along 95% of the wing console, on the lift coefficient, drag coefficient, and aerodynamic quality of the wing during takeoff operation for a wing with a high curvature profile. The purpose of this study was to determine the effectiveness of using a flap along 95% of the trailing edge of the wing console for profiles with high curvature during takeoff for aircraft with short takeoff and landing capabilities. Objectives: to set the geometric characteristics of the wing, create a mathematical model of the wing for two design cases, determine the control data for the calculation, and compare the data obtained. The method for determining the efficiency is to conduct an analysis by comparing the aerodynamic characteristics of wings with the same mechanization, namely, a single-slot Fowler flap, but the flap has a different length. In the first design case, roll control is performed using an aileron that reduces the length of the flap. In the second design case, the flap is placed along 95% of the trailing edge of the wing cantilever, and roll control is performed using interceptors. The study was conducted using the PANSYM software. A key factor is that during the calculation, the structural elements responsible for roll control are not used, i.e., they are in a non-deflected position. The influence of the screen effect is not considered. The calculation is performed at angles of attack from -5° to +15°, viscosity is considered, and the number of viscosity calculation operations is 8. Conclusions. This paper presents additional studies of the influence of the flap along 95% of the wing console edge on its aerodynamic characteristics. The scientific novelty is that the efficiency of using flaps along 95% of the trailing edge of the wing for aircraft with the possibility of short takeoff and landing in the takeoff flight mode has been proved. After comparing the obtained results of the calculation of the two mathematical models, the following conclusions were drawn: the increase in lift coefficient is 30%–50% and the increase in drag coefficient is 35%–45%, but this leads to a decrease in aerodynamic quality by 11%–21%. Thus, a significant increase in the lift coefficient makes it possible to reduce the required distance for takeoff, which is important for aircraft with the capability of short takeoff and landing.

Analysis of aerodynamic characteristics of aircraft during take-off and landing

Take-off and landing are the most critical phases of flight, as they require the pilot's utmost attention and skill. Through force analysis, we can determine the main factors that affect aircraft take-off and landing performance. By understanding these factors, we can improve the safety and efficiency of air travel. During take-off and landing, lift, weight, thrust, and drag work together to give rise to the aircraft's resultant motion and angle of attack. By analysing these forces, we can determine the aircraft's speed and altitude during these critical phases. Ground friction is a factor that is often neglected in theoretical analysis but has a significant effect on aircraft performance in reality. Friction between the wheels and the runway affects the braking of the aircraft after it begins to decelerate on the runway, making it essential for a secure landing. Accurately measuring the friction coefficient can help prevent accidents, particularly in severe weather conditions. Investigating these factors can aid in improving aircraft performance, achieving better energy efficiency, and meeting modern society's needs for safe and efficient air travel. By considering these factors, we can enhance the safety and efficiency of aircraft take-off and landing, ensuring a more reliable and enjoyable travel experience for all.

Research of test method for ski-jump takeoff which is based on BP neural network and multi-factor weight analysis

Ski-jump takeoff of carrier-based aircraft is a very risky subject. At present, the principle, characteristics and influencing factors of ski-jump takeoff are mainly studied at home and abroad, but there is no relevant research on how to carry out ski-jump takeoff test and related risk control. To ensure smooth and safe ski-jump takeoff testing, this paper first determines the influencing factors of ski-jump takeoff based on the dynamics model. Secondly, based on the BP neural network, the corresponding relationship between the influencing factors, the angle of attack and the lifting speed is established. Finally, the quantitative analysis conclusion of the influencing factors is obtained according to the multi-factor weight analysis method and put forward the design method takeoff under the combined conditions of “weight-center of gravity-inertia-configuration” and the test risk control measures, which provides methods and ideas for the safety of ski-jump takeoff test.

Safety analysis of catapult takeoff of carrier-based aircraft using System-Theoretic Process Analysis method

Catapult takeoff has become the main way for carrier-based aircraft to take off. However, as a complex process of multi-system coupling and multi-control actions link, it is an important task to ensure the safety of catapult takeoff. Therefore, this paper adopts the System-Theoretic Process Analysis (STPA) and establishes a model of catapult takeoff using the Systems Theoretic Accident Model and Process(STAMP) model. To carry out safety analysis, identify unsafe control actions and extract the causes of unsafe behavior, simulation analysis is also carried out for typical unsafe actions. The results show that using STPA to make safety analysis, combined with simulation, can comprehensively analyze and evaluate the safety of catapult takeoff, which helps identify the risk before the flight test and reduce the flight test risk.

Application of 3D acoustic scene analysis using sound arrival direction at Noi Bai International Airport in Vietnam

This paper discusses improvement of 3D acoustic scene analysis based on sound arrival direction for airport noise monitoring as well as illustrates a result of application using noise observations of unattended noise monitoring at four noise monitors installed near the both ends of two closed-parallel runways at Noi Bai International Airport in Vietnam. The static analysis method visualized the noise level distribution in the focused direction by varying the analysis time. Estimation of sound source movement trajectories not only for landing paths but also for takeoff paths was also realized. The result suggests that the proposed method is useful for identifying noise contributions of various sound sources including aircraft take-off and landing operations aircraft ground operation on the apron and taxiway.

Analysis of Catapult-Assisted Takeoff of Carrier-Based Aircraft Based on Finite Element Method and Multibody Dynamics Coupling Method

Catapult-assisted takeoff is the initiation of flight missions for carrier-based aircrafts. Ensuring the safety of aircrafts during catapult-assisted takeoff requires a thorough analysis of their motion characteristics. In this paper, a rigid–flexible coupling model using the Finite Element Method and Multibody Dynamics (FEM-MBD) approach is developed to simulate the aircraft catapult process. This model encompasses the aircraft frame, landing gear, carrier deck, and catapult launch system. Firstly, reasonable assumptions were made for the dynamic modeling of catapult-assisted takeoff. An enhanced plasticity algorithm that includes transverse shear effects was employed to simulate the tensioning and release processes of the holdback system. Additionally, the forces applied by the launch bar and holdback bar, nonlinear aerodynamics loads, shock absorbers, and tires were introduced. Finally, a comparative analysis was conducted to assess the influence of different launch bar angles and holdback bar fracture stain on the aircraft’s attitude and landing gear dynamics during the catapult process. The proposed rigid–flexible coupling dynamics model enables an effective analysis of the dynamic behavior throughout the entire catapult process, including both the holdback bar tensioning and release, takeoff taxing, and extension of the nose landing gear phases. The results show that higher launch bar angle increase the load and extension of the nose landing gear and cause pronounced fluctuations in the aircraft’s pitch attitude. Additionally, the holdback bar fracture strain has a significant impact on the pitch angle during the first second of the aircraft catapult process, with greater holdback bar fracture strain resulting in larger pitch angle variations.

Deformation Control of Subway Tunnels Undercrossing Airport Facilities: A Case Study of the Xinzheng Airport Rail Transit Hub Project

The rapid expansion of urban areas due to China’s booming economy has led to a conflict between people and vehicular traffic. Consequently, rail transit, represented by subways, has become the primary mode of transportation for residents. However, the influence of soil damage on tunnel deformation is often overlooked in research on the safety of soft soil tunneling, leading to discrepancies between the results predicted by models and the actual settlement of tunnels. In this study, soil investigation and mechanical strength testing were carried out to analyze the impact of aircraft takeoff and landing activities on the Xinzheng Airport facilities. Damage variables are introduced into the Drucker‒Prager ideal elastic‒plastic criterion, and a soft soil tunneling model with soil deformation is established to investigate the spatial and temporal effects of the shield-cutting force, moving aircraft load, and tunnel deformation. Based on the synchronous grouting technique, a mechanical load-bearing system consisting of a concrete runway, solidified grout, and high-strength segments is formed to ensure the safety of flight activities.

The performance and application of sweep wing aircraft

With the development of science and technology, more and more civil and military aircraft have adopted swept-back wing shapes. this paper explores the relationship between the angle of swept-wing and the lift, drag and lift-drag ratio of the aircraft, and expounds it in combination with the actual swept-wing aircraft, such as Boeing737 and MIG-23 to find the best sweep angle of the aircraft in the appropriate range and analyze the effect of swept wing angle on flight speed. This paper studies and analyzes the data through literature retrieval and data processing and cites data models from many academic journals. The experimental data are mainly derived from computational fluid dynamics and wind tunnel simulation. This paper finds that a wider sweep angle can result in better aerodynamic performance, suited for supersonic flight, while a smaller sweep angle can result in a better lift-drag ratio, it is suitable for takeoff and landing of aircraft and low-speed flight attitude.

Revolutionizing Aviation: Pressure Assisted Electromagnetic Braking System (PAEBS) for Sustainable Air Travel

Air transportation is integral to modern society, facilitating global connectivity and access to remote regions. Nevertheless, challenges such as runway length requirements, landing/take-off accidents, airport congestion, and fuel inefficiencies necessitate innovative solutions. This research paper introduces the Pressure Assisted Electromagnetic Braking System (PAEBS), a self-sustained braking and accelerating system designed to address these challenges and enhance air travel safety, accessibility, and sustainability. The integration of the PAEBS is a seamless process, necessitating no significant alterations to the existing hardware of commercial aircraft, as its operation occurs beneath the runway surface. This innovation has the remarkable capacity to reduce the required runway length for aircraft landing and take-off by up to half. Traditionally, a runway extends to approximately 3000 meters, but with the implementation of PAEBS, this length can be halved to a mere 1500 meters. Preliminary calculations indicate the potential for substantial fuel consumption reductions, ranging from 3% to 4.5% (Rowland, n.d.) [1], contingent upon the size of the airliner. The adoption of this system holds the promise of reducing worldwide commercial jet fuel consumption by a significant 9 billion litres annually (stat, n.d.) [2], which would result in substantial cost savings for airliners, estimated at approximately $4.2 billion per year.

Aerodynamic optimization of an adaptive flap for next-generation green aircraft

Adaptive, morphing flaps are taking ever-increasing attention in civil aviation thanks to the expected benefits this technology can bring at the aircraft level in terms of high-lift performance improvement and related fuel burnt reduction per flight. Relying upon morphing capabilities, it is possible to fix a unique setting for the flap and adapt the flap shape to match the aerodynamic requirements for take-off or landing. The proper morphed shapes can assure better high-lift performances than those achievable by referring to a conventional flap. Moreover, standing the unique flap setting for take-off and landing, a dramatic simplification of the flap deployment systems may be achieved. As a consequence of this simplification, the deployment system can be fully hosted in the wing, thus avoiding under-wing nacelles with significantly better aerodynamics and fuel consumption. The first step for a rational design of an adaptive flap consists in defining the target morphed shapes and the unique optimal flap setting in the take-off and landing phases. In this work, aerodynamic optimization analyses are carried out to determine the best flap setting and related morphed shapes in compliance with the take-off and landing requirements of a reference civil transport aircraft. Four different initial conditions are adopted to avoid the optimization falling into local optima, thus obtaining four groups of optimal candidate configurations. After comparing each candidate's performance through 2D and 3D simulations, the optimal configuration has been selected. 2D simulations show that the optimal configuration is characterized by a maximum lift increase of 31.92% in take-off and 9.04% in landing. According to 3D simulations, the rise in maximum lift equals 22.26% in take-off and 3.50% in landing. Numerical results are finally verified through wind tunnel tests, and the aerodynamic mechanism behind the obtained improvements is explained by carefully analyzing the flow field around the flap.

Contribution of jet flow noise sources to the far-field sound power

Jet noise is the dominant source of noise during aircraft takeoff. This study uses direct numerical simulation (DNS) data of subsonic jet flow obtained from computational fluid dynamics (CFD) simulations to perform acoustic analyses. The non-negative contribution technique (NNC) is employed to identify aeroacoustic sources of jet noise with the greatest contribution to far-field sound power. The NNC technique uses the Lighthill source distribution with an acoustic impedance matrix constructed from radiation kernels of the free-field Green’s function. The fast multipole method (FMM) is integrated with the NNC technique to reduce computational cost arising from decomposition of the acoustic impedance matrix as well as from the high number of CFD grids associated with the DNS data. The results showed that the dominant aeroacoustic sources are associated with the first component of the Lighthill tensor (T11) and are concentrated along the jet centerline, downstream of the nozzle exit.

New reference day atmosphere for analyses of quiet supersonic overflight

New reference day atmospheric conditions have been defined for future supersonic aircraft en route noise certification procedures. As field measurements are acquired, in a variety of atmospheric conditions, it is important to relate those measurements back to a common reference atmosphere to provide uniformity in method across applicants for noise certification. Because of the long propagation distances involved between the aircraft flight altitude and the ground, en route noise certification measurements can be substantially affected by the atmosphere. Properties, such as pressure, density, temperature, humidity, and winds, vary with altitude. Therefore, the definition of reference atmospheric profiles as a function of altitude are needed instead of the coarse layered atmosphere and homogeneous humidity used in subsonic aircraft landing and takeoff noise certification. Ground loudness levels from overflight of a quiet supersonic demonstrator concept, calculated with atmospheric data from sites across the world, were compared with the results from several candidate reference atmospheres to identify a reference that would minimize the required adjustment to certification test measurements. The existing ICAO 7488/3 profiles for temperature and pressure, combined with a modified ISO 5878 humidity profile, were found to offer the best results.

Vertical take-off and hover to cruise transition for a hybrid UAV using model predictive controller and MPC allocation

PurposeDual-thrust hybrid unmanned aerial vehicle (UAV) technology offers a highly robust and efficient system that incorporates the take-off and landing capabilities of rotary-wing aircraft with the endurance capacities of fixed-wing aircraft. The purpose of this study is to model and control a hybrid UAV in three distinct flight modes: rotary-wing, fixed-wing and over-actuated model.Design/methodology/approachModel predictive control (MPC) along with linear models are applied to design controllers for the rotary-wing or vertical take-off and transition to the fixed-wing flight. The MPC algorithm is implemented with two approaches, first in its usual form and then in a new form with the help of tracking error variables as state variables.FindingsBecause the tracking error variables are more compatible with the cost function used in MPC, the results improve significantly. This is especially important for a safe and stable transition from rotary-wing to fixed-wing flight, which should be done quickly. The authors also propose a control allocation strategy with MPC algorithm to exploit the thrust and control inputs of both rotary-wing and fixed-wing systems for the transition phase. As the control system is over-actuated, the proposed algorithm distributes the control signal among the actuators better than the MPC alone. The numerical results show that the flight trajectory is also improved.Originality/valueThe research background is reviewed in the introduction section. The other sections are originally developed in this paper to the best of the authors’ knowledge.

Characterization of Boeing 777 Nose Landing Gear to Better Withstand Rough Landing

An important role a landing gear plays is that it aids in the landing and takeoff of aircraft. The landing gear must be designed in such a way that it can take these stresses in static and dynamic situations. This is to accommodate both rough and smooth landings that result from various loads acting upon it, such as drag force, vertical load, and side load. In the aviation industry, landing gear stress is a key concern, and different research in this field has previously yielded excellent results. However, the time has come to raise the bar even higher. This report will focus on the optimization of the Boeing 777's nose landing gear to better withstand rough landings. During the timeframe of this research, SOLIDWORKS was utilized to model and analyze various components of the landing gear. The results summarize that a single material should be avoided throughout the components of the landing gear. Components such as pistons with a larger stress allocation should be made of titanium alloy, while components with a lesser stress allocation should be made from aluminum alloy.Abstract. An important role a landing gear plays is that it aids in the landing and takeoff of aircraft. The landing gear must be designed in such a way that it can take these stresses in static and dynamic situations. This is to accommodate both rough and smooth landings that result from various loads acting upon it, such as drag force, vertical load, and side load. In the aviation industry, landing gear stress is a key concern, and different research in this field has previously yielded excellent results. However, the time has come to raise the bar even higher. This article will focus on the improvement of the Boeing 777's nose landing gear to better withstand rough landings. During the timeframe of this research, motion study in SOLIDWORKS 2020 (Stand-alone license) was utilized to model and analyze various components of the landing gear. The results summarize that a single material should be avoided throughout the components of the landing gear. Components such as pistons with a larger stress allocation should be made of titanium alloy, while components with a lesser stress allocation should be made from aluminum alloy.

Field observations of aerosol particles in aircraft takeoff and taxiing plumes: A case study at Kobe Airport, Japan

Field observations of aerosol particles in aircraft takeoff and taxiing plumes: A case study at Kobe Airport, Japan

The Stability of Longitudinal Motion of Amphibious Aircraft During Takeoff

In this paper, the mathematical model of the takeoff of an amphibious aircraft was established. On this basis, the hydrodynamic coefficients in the pitch and heave motion equation were calculated using the strip theory. The stability criterion was used to analyze the longitudinal motion stability of the amphibious aircraft during takeoff, and three characteristic parameters of the general stability of longitudinal motion were obtained: natural period, half-decay period, and damping ratio. The result showed that the motion of amphibious aircraft was stable during takeoff.

Rapid and Accurate INS Transfer Alignment for Air Launched Tactical Missile Using Kalman Filter

An Inertial Navigation System (INS) independently measures the Position, Velocity, and Attitude (PVA) of thevehicle to navigate it towards the target. Since INS is a dead-reckoning system, it requires accurate initialization toprovide the navigation (PVA) solution. In the case of an air-launched tactical missile, the aircraft navigation system(Master INS) information is used to initialize accurately the missile INS (Slave INS). Rapid transfer alignment isneeded in today’s combat operation to converge slave INS initialization in the shortest possible time using aircraftnavigation information. The transfer alignment consists of first initializing the missile INS and establishing anavigation solution (PVA) using the missile IMU rates and accelerations, then a Kalman filter is used to, estimatethe errors between the Slave INS and Master INS. The proposed method’s simulation results show that a tacticalmissile INS can be aligned to an acceptable accuracy in a very short time based on the aircraft’s attitude information and with natural maneuvers experienced during aircraft take-off.

A Self-Attention Integrated Learning Model for Landing Gear Performance Prediction.

The landing gear structure suffers from large loads during aircraft takeoff and landing, and an accurate prediction of landing gear performance is beneficial to ensure flight safety. Nevertheless, the landing gear performance prediction method based on machine learning has a strong reliance on the dataset, in which the feature dimension and data distribution will have a great impact on the prediction accuracy. To address these issues, a novel MCA-MLPSA is developed. First, an MCA (multiple correlation analysis) method is proposed to select key features. Second, a heterogeneous multilearner integration framework is proposed, which makes use of different base learners. Third, an MLPSA (multilayer perceptron with self-attention) model is proposed to adaptively capture the data distribution and adjust the weights of each base learner. Finally, the excellent prediction performance of the proposed MCA-MLPSA is validated by a series of experiments on the landing gear data.