Aircraft Motion Research Articles

Importance of a Letter of Operational Coordination Agreement (Loca) Between Airnav and Police

Juwata Tarakan International Airport serves scheduled and unscheduled flights. The North Kalimantan Regional Police Helicopter is also an unscheduled flight that served by Juwata Tarakan International Airport, especially Perum LPPNPI Tarakan Branch. The police helicopter flies from MAPOLDA North Kalimantan located in Tanjung Selor to MAKOPOLAIRUD located in Tarakan and vice versa. The movement of the police helicopter can endanger the movement of aircraft traffic that is descent to circuit altitude to land at Juwata Tarakan International Airport and can interfere with aircraft that will take-off from Runway 24. The purpose of this research is to review the importance of making a Letter of Operational Coordination Agreement (LOCA) between Perum LPPNPI Tarakan Branch and the North Kalimantan Regional Police in order to create aviation safety and security, especially in Tarakan Airspace. The research method used is a descriptive qualitative approach with data collection techniques through observation. The results revealed that the North Kalimantan Regional Police helicopter flight path was very dangerous for VFR flights passing through the VFR corridor of Tarakan Airspace, causing potential hazards. To overcome and prevent the potential occurrence of these hazards, the need to make a Letter of Operational Coordination Agreement between Perum LPPNPI Tarakan Branch and the North Kalimantan Regional Police regarding flight procedures and safe routes to pass will ensure safety, security, efficiency, and regularity of flight traffic on Tarakan Airspace.

Dynamics simulation model for the analysis of aircraft movement characteristics on an aircraft carrier deck

Aircraft on an aircraft carrier deck are taxied or towed using a tractor. As these vehicles move within a limited area and are affected by the aircraft carrier motion, the possibility of aircraft movement in the entire space must be confirmed. The potential aircraft movements can be determined using simulations, wherein the movement characteristics of the aircraft must be analyzed by considering the movement of the carrier. Therefore, an aircraft dynamics simulation model considering the six-degrees-of-freedom movement of the platform is presented in this study to analyze the aircraft movement characteristics on the deck. The proposed model was verified using various reference data and models, and the simulation results of the multi-body dynamics analysis program DAFUL were employed to estimate the tire stiffness coefficient according to the slope. The proposed model facilitated the analysis of the movement characteristics of the aircraft by implementing driving simulations for various platform movements.

SYSTEM IDENTIFICATION OF AIRCRAFT LONGITUDINAL MOTION BY MEANS OF FLIGHT SIMULATOR DATA

In presented article, an exemplary problem of identifying parameters of an aircraft's motion within the vertical plane of symmetry is solved. The data was collected by FlightGear simulator for a Pilatus PC-9M aircraft flight case. After submitting a sequence of commands to pitch elevator and engine thrust, the simulator records five parameters of longitudinal motion at certain frequency. The collected data are further used to build a state-space model of the flight through least-squares estimation. The obtained numerical results are compared with the experimental ones and are overlaid graphically. Charts depicting elevator angle to trim are derived in addition. A source code developed in GNU Octave is applied with the help of which the problem was solved.

Modelling of Aircraft Delays in Akure Airport

As the economy of any nation grows, globally it also affect the rate of movement from one country to the other, whereby causing the increase in traffic and also delays in some facilities that should be accessed. Delay is a prominent event mostly experience at airport by both airlines and passengers. This study investigated if there are delays in Akure airport, secondary data were used for the study, data ranging from January 01, 2023 to March 31, 2023, the data were extracted from NCAA and FAAN records, nine hundred aircraft movement records combined for both arrival and departure were extracted respectively. Queue models were developed to ascertain the through situation of arriving aircraft traffic and departing aircraft. The result of the study reveal that there was no issue of delays for departing traffic in Akure Airport, Therefore, it can be concluded that the Akure Airport, is a transit or receiving airport with low aircraft traffic due to highly spaced headways and frequency of service in Akure airport, the study recommends that the state government should boost economic, commercial and tourism activities that will enhance air traffic so that the airport can have more patronage. It was also recommended that the state can float its own airline (carrier) so that the airport can become a hub for operations within a 24-hour period.

EVALUASI TEBAL PERKERASAN PADA RUNWAY BANDARA SYUKURAN AMINUDDIN AMIR LUWUK BERDASARKAN CUMULATIVE DAMAGE FAILURE

Air transportation is a mode of transportation still quite in demand, although recently there has been a decline in passengers. Syukur Aminuddin Amir Luwuk Airport belongs to the category of Class II Domestic Airport with airside facilities, a Runway with a size of 2,250 m x 45 m, a Taxiway 60 m x 18 m, and an Apron with a size of 315 x 15 m. The operation of several types of aircraft with a larger capacity occurs due to the increase in the number of passengers every year. An increase in the number of passengers will certainly have an impact on the number of aircraft movements, it is necessary to analyze how to determine the thickness of the runway pavement which is influenced by the type of aircraft that will operate based on the subgrade conditions that are there using the FAARFIELD method. The results of the evaluation on the thickness of the runway pavement which has a CBR value of 15%, with a pavement thickness of 215 mm for HMA Surface, 152 mm for Crushed Aggregate, and 200 mm for Uncrushed Aggregate with a service life of 20 years in 2040 it was found that the Subgrade CDF value was 0.00 and the HMA CDF of 0.86. The test results with FAARFIELD software change the pavement thickness for the base layer to 152 mm (minimum value) from the value of 100 mm. So planning the thickness of the pavement requires an additional layer of 52 mm.

Performance Improvement of Human Centrifuge Systems through Multi-Objective Configurational Design Optimisation

Human Centrifuge Systems (HCSs) are an effective training tool to improve the G-acceleration and Spatial Disorientation (SD) tolerance of aircrew. Though highly capable HCSs are available, their structure and performance are yet to be fully optimised to efficiently recreate the G-vectors produced using Aircraft Combat Manoeuvres (ACMs). To achieve this improvement, the relationship between configurational design and HCS performance should be profoundly investigated. This work proposes a framework for identifying the optimal configurational design of an active four Degree-of-Freedom (DoF) HCS. The relationship between configurational design parameters and objective criteria is established using inverse kinematics and dynamics. Then, a multi-objective evolutionary optimiser is used to identify the optimum arm length and seat position, minimising the Coriolis effect, relative acceleration ratio, and cost. The results of the work show that the applied optimisation step can significantly contribute to (1) efficiently replicating the aircraft motion, (2) minimising the detrimental effects generated during HCS motion, and (3) reducing the overall cost of the system. The applied methodology can be adapted to HCSs with different structures and DoFs.

ANALYSIS OF METHODOLOGICAL ERRORS OF THE AVIATION GRAVIMETRIC SYSTEM WITH A TRANSFORMATON GRAVIMETER

The equations of motion and a list of the main components of the AGS are given: gravimeter, stabilization system, system for determining navigation parameters, height meter, on-board digital computer. An analysis of methodological errors of the aviation gravimetric system with a transformer gravimeter was carried out, from which the accuracy requirements for the AGS components were formulated, provided that the accuracy of PST measurements is 1–2 mGal Analytical expressions were found and the coefficients of sensitivity of the total error of the AGS output signal to the measurement errors of the following aircraft movement parameters were calculated: speed, course, latitude, altitude, vertical speed, vertical acceleration, path for different flight modes. Therefore, the study of the sensitivity of the AGS to errors in the measurement of speed, latitude and course, depending on a number of parameters of the aircraft movement, showed that in the case of aviation gravimetric measurements along the Earth’s meridian, it is necessary to accurately determine the course, along the Earth’s parallel – to accurately measure the speed, in mid-latitudes – latitude . It is substantiated that the use of a new two-channel transformer gravimeter provides the necessary increase in the accuracy of AGS. Changes in the sensitivity of the error of the AGS output signal to speed measurement errors were studied depending on the latitude of the site at constant values of the course, as well as on the course of the aircraft at constant values of the latitude. It is shown that the sensitivity of the AGS to speed measurement errors is maximum for the east and west courses (22.6 mGl/m/s and – 6.5 mGl/m/s, respectively) at the location latitude j= 00; minimum for north and south courses and at j=900 regardless of the course (8.05 mGl/m/s). Permissible values of errors in determining the flight parameters of the aircraft were calculated: speed 0.05…0.15 m/s, heading 1.43…3 arcmin, latitude 0.5…1.5 arcmin. min., height 3.3…10 m, vertical speed (0.5…1).102 m/s, vertical acceleration (1…3).10-5 m/s2, path (1.5…4.5) m.

Analysis of the impact of trailing-edge wing flaps on the aerodynamic characteristics and performance of the Tecnam P-2008JC aircraft

The aim of the article was to analyse the impact of three selected types of trailing-edge flaps on the aerodynamic characteristics and performance of the Tecnam P-2008JC aircraft. The SOLIDWORKS software, together with the Flow Simulation module, was used to design the 3D model of the aircraft and to simulate the air flow. The article contains descriptions of issues related to the aerodynamics and dynamics of aircraft motion, calculations describing the procedure for designing and building a model of the tested aircraft in the SOLIDWORKS software, performing simulations using the Flow Simulation module and determining the aerodynamic characteristics of the aircraft with the flaps applied, determining the basic performance of the aircraft with extended flaps, and then comparing the determined performance with the in a configuration without flaps.

Entry Count vs Occupancy Count to assess sector capacity with Fast Time Simulation

An air traffic controller should manage aircraft movements per hour to ensure the safety and efficiency of the traffic system. This study proposed an innovative methodology to estimate the air traffic controllers’ workload through sector occupancy. Starting with a model for the workload of sector controllers designed by Eurocontrol for tower controllers, the authors defined a taskload model from real audio that occurred in an examined Terminal Control Area (TMA). Moreover, trombones have been implemented to sequence arrival flows in the simulated TMA. Therefore, an airside model has been reproduced using Fast Time Simulation software, and its capacity has been calculated in terms of occupancy due to approaching movements. The results permit to evaluate the impact of infrastructural and operative modifications on the sector capacity in terms of hourly entry count and occupancy. Total and maximum occupancy values have been deepened to identify the best predictive factor of controllers’ workload and to manage the airspace configuration.

Hybrid Adaptive Control for Tiltrotor Aircraft Flight Control Law Reconfiguration

Tiltrotor aircrafts have both fixed-wing control surfaces and helicopter rotors for attitude control. The redundancy of control surfaces provides the possibility for the control system to reconfigure the control law when actuator faults occur during flight. Possible actuator faults have been classified into two categories: predictable and unpredictable faults, and a different strategy has been adopted to deal with each kind of fault. Firstly, the predictable faults are handled by a multiple-model switching adaptive scheme. These kinds of faults are modeled, and their corresponding controllers are derived offline. Secondly, since the degree of drop in aerodynamic effectiveness cannot be predicted a priori, unpredictable faults are handled by a simple adaptive control scheme, to force the plant with faults to track the prescribed reference model. The presented methodology has been verified by nonlinear full-envelope flight simulation for both categories of actuator faults. The predictable fault is represented by the elevator floating. Elevator damage causing an aerodynamic effectiveness drop by 80% is chosen as the example of unpredictable fault. Both faults are simulated at the late stage of the tiltrotor conversion mode. Results show that the presented strategy of reconfiguration is able to detect the fault rapidly and stabilize the aircraft when a fault occurs, while the aircraft motion diverges without the reconfiguration scheme. The aircraft also presents a relatively good performance under controller reconfiguration with a well-tracked conversion path.

Determination of the influence of the shape of the nose fairing on the ballistic characteristics of a meteorological missile

Climate change currently stands as one of the key threats and challenges to humanity. Researching atmospheric parameters not only enables the analysis of current climatic variations but also facilitates forecasting future changes and predicting extreme abrupt climatic shifts, natural phenomena, and catastrophes. Meteorological rockets play a significant role in this research, bridging the gap between balloons and meteorological satellites. The main purpose of meteorological rockets is to study the upper layers of the atmosphere, collect information for weather forecasting, and similar rockets can also be used for X-ray and ultraviolet astronomy. Utilizing modern numerical simulation methods allows for swift and precise simulations of complex tasks. Designing rocket technology poses a complex challenge due to the intricate system of differential equations describing the aircraft's motion. Consequently, numerical modeling found extensive application in ballistic design. Through contemporary numerical modeling methods, the flight of a meteorological rocket was simulated, determining its key flight parameters. An analysis was conducted on the influence of three types of nose cone shapes on the rocket's energy-ballistic trajectory.

CONSTRUCTION PLANNING OF THE UPPER STRUCTURE OF THE PKP-PK BUILDING AT HUSEIN SASTRANEGARA AIRPORT BANDUNG

The PKP-PK building is one of the facilities located at an airport to visually monitor aircraft movements. In connection with this, at Husein Sastranegara Airport Bandung there is a PKP-PK building. In this study, it is intended to plan the PKP-PK building structure in accordance with SNI. so that in analyzing the structure, the SRPMK (Special Moment Bearing Frame System) method is used. In the calculation of the structure used SRPMK (Special Moment Bearing Frame System) and Strong Column Weak Beam which refers to SNI 1726: 2019 concerning earthquakes. In planning the building structure, SNI 2847: 2019 concerning reinforced concrete and SNI 1727: 2018 for loading are used. In this research, the SAP 2000 auxiliary program is used for 3D building modeling, PCAColumn for column interaction diagram calculation, and Autocad 2018 for reinforcement details. In the planning, 400/600mm main beam, with 5 D 19 flexural reinforcement at positive moment, at 7 D 19 flexural reinforcement at negative moment, 300/500mm sub-beam, with 3 D 16 flexural reinforcement at positive moment, at 5 D 16 flexural reinforcement at negative moment, 200/300 sub-beam with 3 D 13 flexural reinforcement at positive moment, at 5 D 13 flexural reinforcement at negative moment 600/600 column and 100 mm plate thickness and structural reinforcement details are included in the engineering drawings. In addition, the PKP-PK structural design control check based on SNI 1726: 2019 has met the requirements and fulfills the Strong Column Weak Beam concept and the cost required for the PKP-PK building construction planning is Rp1,324,860,000.00 (One Billion Three Hundred Twenty Four Million Eight Hundred Sixty Thousand Rupiah).

Improvement of methods of interception of enemy UAVs

The main result of this work is the creation of a methodology for determining the coordinates, velocities and trajectories of spatial movements of moving objects by means of kinematic design and the development of principle schemes for the optimal placement of radar search equipment for the successful detection of enemy UAVs. Its purpose is to increase the defense capability of military units, populated areas of Ukraine and their infrastructure by resisting attacks by attack and sabotage reconnaissance unmanned aerial vehicles (UAVs). The protection scheme is based on the determination of coordinates, movement speeds and trajectories of spatial movements of enemy aircraft by means of kinematic design. The established coordinates of enemy UAVs are reported to command posts equipped with liquidator drones (kamikaze) and small arms or to control points of anti-aircraft missile systems (SAMS), which eliminate these aircraft. The proposed improvement of the widespread method of radar search for moving objects is based on the introduction of additional search radar equipment and mathematical apparatus for precise calculations of coordinates and parameters of spatial movements of moving objects by means of kinematic design. Two paired radar search systems, equipped with modern high-speed computing equipment with appropriate software, are able to "screen out" false return electromagnetic signals. This makes it possible to clearly single out the wanted moving object and subsequently track its movement in space. Corresponding mathematical dependencies are proposed for calculating the distance of a moving object to radar stations, its coordinates in the introduced orthogonal coordinate system, speed and acceleration of movement, that is, instantaneous coordinates and parameters of spatial movements of moving objects. This makes it possible to increase the effectiveness of detecting enemy attack and sabotage-reconnaissance unmanned aerial vehicles, including Iranian-made drones of the Sahed-136 model.

Evaluation of Aircraft Emissions at Bucharest Henri Coanda Airport

This study presents the influence of aircraft movements on air quality by highlighting the contribution of landings and/or takeoffs at Henri Coanda Airport, Bucharest. An experimental campaign was carried out using a mobile laboratory equipped with reference instruments for the main air pollutants (NO-, NO2, NOx, SO2, CO, and O3) and a meteorological station to measure wind speed and direction, air temperature, pressure, and relative humidity at a height of 10 m above the ground. The mobile testing laboratory was located inside the airport near the passenger embarking area, and measurements were carried out for 7 days. Air sampling was carried out at a height of 3.5 m above the ground. Pollutant levels were continuously measured throughout the measurement period, with high-precision equipment and a 10-second interval. The results obtained showed an increase in pollutant concentrations during takeoffs and/or landings, providing an initial assessment of gaseous pollutant levels and hourly distribution. Airport authorities can use this assessment to balance aircraft and passenger movements to minimize human exposure to gaseous pollutants. Furthermore, this study used the Pearson correlation between each pollutant and meteorological parameters to establish the best conditions for passengers to be present on the airport premises. The results showed that wind speed and direction directly influence the distribution of gaseous pollutants, especially during landings and takeoffs.

Analisis Perencanaan Struktur Perkerasan Apron Pada Bandar Udara Internasional Sultan Hasanuddin Menggunakan Metode FAA

This study aims to determine and analyze thickness of apron pavement structure with Boeing 747-400 aircraft type at Sultan Hasanuddin International Airport using the Federal Aviation Adminstration method. This research is located at Sultan Hasanuddin International Airport Makassar. Data required includes secondary data in the form of aircraft movement traffic data from 2014 to 2018, apron layout and subgrade test California Bearing Ratio data as well as other data. The results of the planning analysis obtained the thickness of apron pavement structure with Boeing 747-400 aircraft type at Sultan Hasanuddin International Airport using the Federal Aviation Adminstration method, the thickness of subbase was 20 cm, base course (stabilized) was 15 cm and surface f’c 33,2 MPa was 41 cm

Assessment of the technical condition of the airport runway surface using an UAV

The technical condition of airport pavements not only has a significant impact on the performance of air operations in the ground movement area but also affects the comfort of aircraft movement on the airport pavement, which determines the safety of air operations. The requirements for airfield pavements are specified in defense standards, as well as in civil documents, e.g. (International Civil Aviation Organization), EASA (European Union Aviation Safety Agency), FAA (Federal Aviation Administration), where exploitation parameters in the field of airport pavement construction are defined. The article presents the methodology of the initial assessment of the technical condition of airport pavements in terms of existing damage, as well as anomalies of the existing gradeline, which may indicate inadequate evenness of the pavement. The assessment was made using an aerial photogrammetry kit and the test results were presented. This work focuses on the use of an aerial photogrammetry set, which made a flight over the runway of a military airport providing its full imaging.

An Approach to Robust Control of Aircraft Motion

The article deals with approaches to designing aircraft control systems based on the robust synthesis. The mathematical model of the aircraft control system both for deterministic and stochastic cases is considered. The Dryden filter models are represented. The state-space conception is applied. The concept of robust designing based on H-infinity synthesis, function of the mixed sensitivity, and loop shaping is represented. The features of Robust Control Toolbox necessary for automated designing of aircraft control systems are studied. The weighting transfer functions are proposed. Results of simulation of the synthesized robust control system are shown in the form of transient processes in lateral and longitudinal motions. The proposed approach is directed on providing the possibility of the aircraft to function in conditions of influence of disturbances. The possible applications of obtained results is control of aircraft motion in civil aviation.

CONTROL MODEL OF A GROUP OF MANEUVERABLE UNMANNED AERIAL VEHICLES TAKING INTO ACCOUNT THEIR FLIGHT SAFETY

The article deals with the urgent scientific problem of creating an algorithmic support for an automated situational control system for group maneuverable unmanned aerial vehicles, taking into account the possibility of improving their flight safety. To realize this possibility, the authors proposed a non-linear flight model of group formation. This is the basis for the synthesis of nonlinear control laws for these aircraft. The difference of the proposed approach is taking into account the influence of changes in the speed and direction of wind flows on the laws governing the movement of aircraft in a group. Promising areas of research are considered, namely: the application of the results obtained to justify the requirements for the design characteristics of control systems and their algorithmic support in terms of not only improving their flight safety in group formations, but also ensuring the specified performance indicators for a wide range of possible flight tasks by a group of maneuverable aircraft

Severity assessment of sudden plunging motion for jet transport aircraft in response to severe atmospheric turbulence

PurposeThe purpose of this paper is to present a comparative study of flight circumstances, dynamic stability characteristics and controllability for two transport aircraft in severe atmospheric turbulence at transonic cruise flight for the purpose to obtain the prevention concepts of injuries to passengers and crew members for pilot training in International Air Transport Association (IATA) – Loss of Control In-flight (LOC-I) program.Design/methodology/approachA twin-jet and a four-jet transport aircraft encountering severe atmospheric turbulence are the study cases for this paper. The nonlinear unsteady aerodynamic models are established through flight data mining and the fuzzy-logic modeling technique based on the flight data of flight data recorder. This method can be adopted to examine the influence of horizontal wind shear and crosswind on loss of control, dynamic stability characteristics and controllability for transport aircraft in different weights and different sizes in tracking aviation safety of existing different types of aircraft.FindingsThe horizontal wind shear or crosswind before the turbulence encounter will easily induce rolling motion and then initiate the sudden plunging motion during the turbulence encounter. The roll rate will increase the oscillatory rolling motion during plunging motion, if the rolling damping is insufficient. The drop-off altitude will be enlarged by the oscillatory rolling motion during the sudden plunging motion.Research limitations/implicationsA lack of the measurement data of vertical wind speed sensor on board to verify the estimated values of damping term is one of the research limitations for this study. The fact or condition of being severe in sudden plunging motion can be judged through the analysis of oscillatory derivatives with both dynamic stability and damping terms.Practical implicationsThe roll rate will increase the oscillatory rolling motion during plunging motion, if the rolling damping is insufficient. The drop-off altitude will be enlarged by the oscillatory rolling motion during the sudden plunging motion. The horizontal wind shear or crosswind before the turbulence encounter will easily induce rolling motion and then initiated the sudden plunging motion during the turbulence encounter. If the drift angle is large, to turn off the autopilot of yaw control first and stabilize the rudder by the pedal. When passing through the atmosphere turbulence area, the pilots do not need to amend the heading angle urgently.Social implicationsThe flight safety prevention in avoidance of injuries for passengers and cabin crews is essential for the airlines. The horizontal wind shear or crosswind before the turbulence encounter will easily induce rolling motion and then initiated the sudden plunging motion during the turbulence encounter.Originality/valueThe flight safety prevention in avoidance of injuries for passengers and cabin crews is essential. The present assessment method is an innovation to examine the loss of control problems of aviation safety and promote the understanding of aerodynamic responses of the jet transport aircraft. It is expected to provide a valuable lecture for the international training courses for IATA – LOC-I program after this paper is being published.

Predictor–Corrector Guidance for a Hypersonic Morphing Vehicle

In an effort to address the problem of hypersonic morphing vehicles reaching the target while avoiding no-fly zones, an improved predictor–corrector guidance method is proposed. Firstly, the aircraft motion model and the constraint model are established. Then, the basic algorithm is given. The Q-learning method is used to design the attack angle and sweep angle scheme to ensure that the aircraft can fly over low-altitude zones. The B-spline curve is used to determine the locations of flight path points, and the bank angle scheme is designed using the predictor–corrector method, so that the aircraft can avoid high-altitude zones. Next, the Monte Carlo reinforcement learning (MCRL) method is used to improve the predictor–corrector method and a Deep Neural Network (DNN) is used to fit the reward function. The planning method in this paper realizes the use of a variable sweep angle, while the improved method further improves the performance of the trajectory, including the attainment of greater final speed and a smaller turning angle. The simulation results verify the effectiveness of the proposed algorithm.