Aircraft Crash Research Articles

Long-range underwater acoustic detection of aircraft surface impacts—The influence of acoustic propagation conditions and impact parameters

The 2019 crash of an F35 fighter aircraft off the east coast of Japan was detected at a range of approximately 3000 km by a hydroacoustic station of the Comprehensive Nuclear Test Ban Treaty Organisation’s International Monitoring System. In this paper we compare the acoustic propagation conditions relating to that detection to those relating to the crash of Malaysian Airlines flight MH370 in the Indian Ocean in 2014 with a view to reassessing the likelihood that acoustic signals detected on a similar hydroacoustic station could have been related to the loss of MH370. Possible differences in source levels due to different assumptions about impact parameters are also considered. Despite several extensive searches, the location of the wreckage of MH370 remains unknown.

Model, analyse and prevent fatal aircraft manoeuvres

On 24 June 1994 at Fairchild Air Force Base, during practice for an air show, a low-flying B-52H aircraft banked its wings vertically and crashed. Emphasizing the activity of modeling drag and gravity, these notes examine the possibility of recovery with several models. First, with algebra, historical data lead to a model where in a free fall near Earth's surface, the distance fallen is proportional to time squared. Calculus then gives an ordinary differential equation to model free fall near Earth's surface. Second, with calculus, historical data lead to various models of drag on objects moving through air. Third, combining models of drag and gravity with Newton's Laws of Motion leads to ordinary differential equations that model free fall in air. Fourth, predictions from such models with ordinary differential equations are consistent with the aircraft crash. Further models examine the possibility of increasing engine thrust to regain the vertical component of lift. All models fit in a first course in differential equations, without requiring any computational machinery. However, numerical experiments show how uninformed use of professional software can produce rounding errors to cause the modelled aircraft to plunge to the bottom of the deepest oceans and shoot up into space.

Aircraft overrun warning systems capabilities and disadvantages

Currently, attention of the aviation community and authorities is being increasingly focused on flight safety in the landing phase. It is accounted for the increased frequency of incidents in the final phase of flight and significant threats associated with the consequences of these events. The statistics of aviation accidents reveals that from 1959 to 2019, 55% of aircraft crashes in the world occurred in the phases of landing and takeoff. The given crashes resulted in 51% of all fatalities on board aircraft. In most cases, causes of these aviation accidents are involved with some kind of human error. Off-design conditions at an aerodrome also have a significant adverse effect on the aviation accident potential and severity. The increasing intensity of flights, airspace congestion, strict ATC-imposed restrictions, the necessity to perform a variety of procedures and general flight crew stress in conjunction with dynamically changing external conditions can disorient a flight crew and lead to a landing with a flight envelope overrange. The search for a solution in terms of preventing aircraft overruns is actively being conducted both by aviation authorities and aircraft manufacturers and operators. Within the framework of this review, the major external and operational factors, affecting the dynamics and the nature of the aircraft roll via the runway, are analyzed, including the context of several accidents that have occurred in recent years. In addition, the article emphasizes the methods to prevent and anticipate aircraft overruns based on the principles of active protection. In particular, the article examines the main operation aspects of onboard avionics systems installed on Boeing and Airbus aircraft and highlights the focus areas of their upgrading. Special attention is paid to the influence of the pilot and the possibility of taking his actions into account to predict an outcome of landing.

Implications of pilot reliability on the probability of unmanned aircraft crashes

This paper presents the issue of human reliability in the perspective of the safety of missions carried out by unmanned aerial vehicles, known as drones. The ever-increasing range of applications and widespread access to drones generates the risk of collisions, which greatly affects the safety of people, the environment and infrastructure elements. The aim of this study was to determine reliability for two variants of operations scenarios for different levels of pilot experience and to compare them. The analysis of pilot reliability, carried out using the HEART method, indicated that there are a number of factors that determine the level of pilot reliability affecting the probability of a collision occurring.

DESIGN AND MODELLING OF GROUND PROXIMITY WARNING SYSTEM (GPWS) FOR TRAINING AID

Controlled flight into terrain (CFIT) is the most common type of aircraft crashes in the world of aviation today. Following the sheer volume of terrain collisions, there was an introduction of CFIT classification to enable the grouping into one category of all crashes involving aircrafts colliding with terrains. To avert CFIT accidents, the Ground Proximity Warning System (GPWS) was introduced onboard the aircraft for the flight crew to be aware of the moment the aircraft is approaching a ground terrain via automatic and very distinct acoustic warning. This paper presents a digital display ground proximity warning system as a teaching aid with audio prompt using ultrasonic sensor to produce forward distance from aircraft to obstacle ahead, height, inclination of aircraft in relation to its terrain beneath the aircraft and a digital computer interface for instrument visualization for better performance using graphic user interface (GUI) thereby enabling clearer understanding on GPWS. The Arduino IDE using Arduino sketch and C language were used on the Arduino Uno. The aircraft was integrated with different electronic modules which includes Arduino single board, Ultrasonic sensor, accelerometer and transceiver module, and all these uses the Arduino to read the signal from the sensor, processes and transmit to the base station wirelessly via radio frequency. Simulation results indicates that the responses of the models are a replica of the actual aircraft operations.

Why Are Flight Psychologists Important to Flight Safety?

The developments in aircraft technologies both in our country and around the world cause a serious increase in both the aircraft fleets and ticket sales, as well as the number of airline companies, their employees and passengers. These developments in the aviation industry necessitate flight safety and highlight the importance of the human factor (flight crew) by reducing the causality of technical factors in ensuring safety. Studies within this scope show that the main causal factor (65-70%) in aircraft crashes is the flight crew. There are many factors such as physiological, psychological, personal and psychosocial at the basis of the unsuccessful performance of the flight crew. However, the number of studies in the literature that draw attention to the psychological elements of the flight crew is very few. In fact, it is known that the psychological well-being of the flight crew is important for the success of the flight operations, but the airline companies do not have any evaluation obligation regarding this. On the contrary, some negative consequences may be encountered due to the freedom in this matter. In particular, the fact that human factor causation is at a much higher level than previously thought in plane crashes increases the importance of flight psychologists for airline companies today. Therefore, in this study, it is aimed to reveal the importance of flight psychologists on flight safety in civil aviation. In this context, interviews were held with the flight crews of two airlines (private-public). The findings show that flight psychologists are important and necessary in airline companies in order to be able to perform safe flights with healthier flight crews.

Global damage evaluation of a dry storage structure subjected to postulated aircraft crashes

This paper describes an assessment of vulnerability to global damage of a dry storage structure subjected to postulated commercial aircraft crashes. The vulnerability from plausible collisions of an aircraft is expressed by failed volume fraction in distribution curves obtained from an integrated deterministic and probabilistic approach. Nonlinear dynamic analyses are performed using smoothed particle hydrodynamics and finite element method to simulate the aircraft impact and the subsequent reinforced concrete damage. The response surface method, polynomial regressions and Monte Carlo simulation are employed for the probabilistic assessment. Failure probabilities of damage for three predefined response modes are estimated at side and upper impact locations. Resultant probabilities under these scenarios were relatively high and, thus, global resistance of the structure to withstand aircraft crashes is generally low. The outcomes of this study can be incorporated into quantitative evaluation within a probabilistic risk assessment framework and associated with further numerical analysis methodologies.

MODELING AND COMPUTER IMPLEMENTATION OF A SPLINE FROM CLOTHOID SEGMENTS

When designing the contours of machines and units that operate in a moving environment, an important role is played by ensuring a smooth change in curvature. The law of curvature change is very important in this case, because the curvature break along the surface inherits the turbulent stall of the flow of the moving medium, which increases the resistance of the unit to the moving medium. An increase in resistance to a moving medium leads to a decrease in the speed of movement. And when used in aircraft construction, the disruption of a moving medium can lead to a peak and an aircraft crash. The integral curve of the “clothoid” is known. Its peculiarity lies in the fact that along the curve its curvature changes according to the linear law. Therefore, the use of this curve to construct a surface can provide a linear law of change in curvature along the surface. The paper considers the construction of a spline consisting of clothoid segments, which provides a linear closed curvature change along the entire spline curve. The specified spline is advantageous to use in the design of surfaces of machines and assemblies, working in a moving environment (surfaces of aircraft, cars, ships), in which it is important to specify the law of curvature variation along the surface. The law of curvature change is very important in this case, because the curvature break along the surface inherits the turbulent stall of the flow of the moving medium, hich increases the resistance of the unit to the moving medium. An increase in resistance to a moving medium leads to a decrease in the speed of movement. And when used in aircraft construction, the disruption of a moving medium can lead to a peak and an aircraft crash. The papers [1,2,3] consider various variants of surface portions, but none of them provides a linear law of curvature variation. Key words: curvature, spline of clothoid segments, “clothoid” curve.

Shock vibration and damage responses of nuclear island subjected to an aircraft crash

Although more attention has been given towards the analysis of large commercial aircraft impacts since the September 11 attacks, little work has been done on the vibration response of internal structures and equipment of nuclear power plants (NPPs) during an impact. With a focus on new NPPs, this paper develops a remeshing algorithm for contact surfaces, which utilizes the advantages of scaled boundary finite element (SBFE) polyhedral elements to fully realize the potential of Octree and structured grid discretization methods. The vibration response of nuclear island internal structures is examined. The influence of the interaction between the foundation and the structure on the overall dynamic response is analyzed. Meanwhile, different ranges of foundation size are investigated for balance between computational efficiency and accuracy. The vibration propagation mechanism is found by studying the influence of different artificial boundary types and damping conditions of foundation. The results show that the interaction has a significant influence on the vibration response, and that a foundation size of 1B (height of the steel containment vessel) on all sides provides the optimal balance between computational and accuracy requirements. Furthermore, the damping ratio of the foundation plays a key role in vibration propagation. Finally, the combined bonding method is highly flexible, and allows cross-scale integration of different mesh sizes.

Influence of bending pre-load on the tensile response of the lumbar spine

Previous full body cadaver testing has shown that both obliquely oriented seats in survivable aircraft crashes and far-side oblique crashes in vehicles present distinctive occupant kinematics that are not yet well understood. Knowledge surrounding how these loading scenarios affect the lumbar spine is particularly lacking as there exists minimal research concerning oblique loading. The current study was created to evaluate a novel experimental method through comparison with existing literature, and to examine the impact of a static bending pre-load (posture) on the load–displacement response for the whole lumbar spine loaded in non-destructive axial distraction. T12-S1 lumbar spines were tested in tension to 4 mm of displacement while positioned in one of three pre-load postures. These postures were: the spine’s natural, unloaded curvature (neutral), flexed forward (flexed), and combined flexion and lateral bending (oblique). Deviations from a neutral spine position were shown to significantly increase peak loads and tensile stiffness. The presence of a flexion pre-load caused statistically significant increases in tensile stiffness, tensile force, and bending moments. The addition of a lateral bending pre-load to an already flexed spine did not significantly alter the tensile response. However, the flexion moment response was significantly affected by the additional postural pre-load. This work indicates that the initial conditions of distraction loading significantly affect lumbar spine load response. Therefore, future testing that seeks to emulate crash dynamics of obliquely seated occupants must account for multi-axis loading.

МАТЕМАТИЧНЕ МОДЕЛЮВАННЯ ТА МЕТОДИ ПІДБОРУ СКЛАДУ ПОРИСТОГО ЦЕМЕНТОБЕТОНУ

Introduction. The construction and operation of airfield elements such as runways, taxiways, and parking places that meet the requirements of regulations and modern methods of road works are significant in the system of aviation security in modern conditions. In order to ensure safe conditions for landing aircraft on the runway during downpours and heavy rains, porous cement concrete should be used as the surface source, which will further reduce hydroplaning. Research problem. Due to a large number of aircraft crashes and their rolling outside the runway, which is associated with the frequent failure of the coating to perform drainage because of unfavorable weather conditions (including thunderstorms, showers, and snowfalls), there is the need to improve the existing structures of airfield pavements or to develop new technologies to improve the drainage of pavement and, accordingly, the safety of takeoff and landing of aircraft on the runway. The use of modern airfield pavement structures made of porous cement concrete with drainage properties is one of the ways to solve this problem. The purpose of the study. The research aims to prove that the use of porous cement concrete in mathematical modeling of porous cement concrete composition and improvement of airfield structure will guarantee safe conditions for takeoff and landing and taxiing of aircraft on the runway. Materials and methods. During the research, the analysis of monographs, normative documentation, methodical instructions and recommendations was made. These documents establish requirements concerning the selection of materials for porous cement concrete structure, its use in the construction of elements of an airfield, and their exploitation. Results. The feasibility of using different methods of design and selection of the design and selection of porous cement concrete is proved. Conclusion. The revision and analysis of the literature showed that in order to obtain products and structures with specified properties the most appropriate approach is the use of several methods simultaneously to project and select components for the composition of porous cement concrete. The benefits of the simultaneous use of several methods such as the reduction of information processing time, the improvement of mixture quality, the flexibility of the model to adjustment, the simplification of analysis, and the comparison of indicators of mathematical modeling and laboratory tests were highlighted.

Public relations strategy in rebuilding Airline Company reputation following aircraft crash

The issue discussed in this study is rebuilding Lion Air's reputation tarnished by aircraft accidents. This study aims to identify public relations strategies pursued by case study of Lion Air, Indonesia, to rebuild its reputation following air accidents it has been involved. The research method employed in this study is the qualitative method using single case studies on Lion Air Company. Data is collected through observation, interviews, and a review of news articles in the media. The output of the research takes the form of corporate strategies that are aimed at rebuilding the company's reputation using stakeholder approaches, including (1) alignment of internal perceptions within the organization; (2) "communication holding,"; (3) centralization of information issuance; (4) appointment of partners as "communicators"; (5) use of humanitarian approaches. The conclusion drawn from the research is that public relations strategies through a stakeholder approach would provide a basis for Lion Air's management to exercise control over information that brings positive value. The result also shapes stakeholders' perceptions to align with the company's expectation in restoring its reputation.

Development of an Evaluation Methodology for Loss of Large Area induced from Extreme Events with malicious origin

Event of loss of large area (LOLA) induced from extreme external event at multi-units nuclear installation has been emerged a new challenges in the realm of nuclear safety and regulation after Fukushima Dai-Ichi accident. The relevant information and experience on evaluation methodology and regulatory requirements are rarely available and negative to share due to the security sensitivity. Most of countries has been prepared their own regulatory requirements and methodologies to evaluate impact of LOLA at nuclear power plant. In Korea, newly amended the Nuclear Safety Acts requires to assess LOLA in terms of EDMG (Extended Damage Mitigation Guideline). Korea Institute of Nuclear Safety (KINS) has performed a pilot research project to develop the methodology and regulatory review guidance on LOLA at multi-units nuclear power plant since 2014. Through this research, we proposed a methodology to identify the strategies for preventive and mitigation of the consequences of LOLA utilizing PSA techniques or its results. The proposed methodology is comprised of 8 steps including policy consideration, threat evaluation, identification of damage path sets, SSCs capacity evaluation and identification of mitigation measures and strategies. The consequence of LOLA due to malevolent aircraft crash may significantly susceptible with analysis assumptions including type of aircraft, amount of residual fuel, and hittable angle and so on, which cannot be shared overtly. This paper introduces a evaluation methodology for LOLA using PSA technique and its results. Also we provide a case study to evaluate hittable access angle using flight simulator for two types of aircrafts and to identify potential path sets leading to core damage by affected SSCs within damaged area.

CFD Impingement Flow Study on Temperature Profile of Concave Plate

All the aircraft are equipped with an anti-icing system to prevent ice accretion on the body of the aircraft. The anti-icing system is important because ice accretion degrades the performance of the aircraft and may cause aircraft crashes. Piccolo tube Anti-icing system uses the impingement hot air and creates hotspot on nacelle lip-skin and edges of wings. The temperature distribution caused by the impingement of hot air must be studied to get a better design of the anti-icing system. The skin geometry shape affects hot airflow behavior in the impingement vicinity, hence influences temperature distribution on wing skin and nacelle lip-skin. Thus, the CFD simulation of the hot air impingement air various concave curvature radius was conducted by using ANSYS Fluent 19.2. The result shows the temperature contour has been plotted from the software. Correlation between Nusselt number on impingement point and Reynolds number was successfully done as the validation. Increasing the Reynolds number increases the dimensionless temperature of the concave plate. Temperature is 0.147125 has been recorded as the highest dimensionless temperature under the set of an air temperature of 43°C, Reynolds number of 4070, and 300mm curvature radius. Besides that, increases in heat dissipation decrease the dimensionless temperature of the plate with the curvature radius also decreases. The dimensionless temperature increases from 0.138747 to 0.142316 when the curvature radius increases from 150mm to 300mm.

Fault Detection in Three-Phase Transmission Line by Using IoT

Abstract: The electrical energy device is cut up into many special sections. One in all is the transmission mechanism, wherein Power is transmitted from producing stations and substations through transmission strains to customers. Both strategies Should numerous kinds of malfunctions are generally stated as a "Fault" Fault is described as a number of unwanted however Unavoidable incidents can temporarily disturb the strong circumstance of the power system that occurs while the insulation of the System fails at any factor. Furthermore, if a carrying out object comes in contact with a bare power conductor, a quick circuit, or Fault. The causes of faults are, lighting stroke, human error, wind damage, timber falling or wines plants throughout transmission Strains, aircraft crash on the transmission line, birds shorting traces, or vandalism. At some point in this study, the causes and consequences of faults Within the overhead transmission strains have been the maximum target of the research. A variety of the numerous reasons for faults and some Detection strategies are going to be mentioned. Those faults cause goodsized damage to the power system equipment. In India It's ordinary, the faults might be LG (Line to ground), LL (Line to Line), or 3L (3 lines) inside the availability structures and those faults in 3 phase delivery can affect the strength plant. Keywords: Three-phase Fault, Node MCU, Transmission line, Line to Lind fault, Line to Ground Fault, IoT based.

Determining the Relationship between Aircraft Crashes and Stock and Firm Values: An Analytical Study on Airline Carrier and Aircraft Manufacturing Companies

Çalışmanın amacı, havayolu sektöründeki uçak kazaları ile ticari havayolu taşıyıcı şirketleri ve ticari uçak üreticisi şirketlerin hisse senedi fiyatları arasında bir ilişkinin olup olmadığının belirlenmesidir. Dünyada havayolu sektöründe yer alan havayolu taşıyıcı şirketleri ve büyük uçak üreticisi iki şirketin 2013-2020 yıllarında yaptıkları toplam 38 adet uçak kazası sonrasındaki ilk gün ve takip eden haftanın günlerindeki anormal getirileri ile kümülatif anormal getirileri analiz edildiğinde; uçak kazalarının bazılarında kazadan sonraki ilk ve takip eden 7 gün içinde gerek havayolu taşımacı şirketlerinin gerekse uçak üreticisi şirketlerin hisse senetlerinin değerlerinde genel olarak düşüş yaşanırken, bazı uçak kazalarından sonraki günlerde hisse senetleri değerlerinde değişim olmadığı veya artış yaşanmadığı görülmüştür.

Two-dimensional response of a floating ice plate to a line load moving at variable speed

We significantly extend the results of Miles & Sneyd (J. Fluid Mech., vol. 497, 2003, pp. 435–439) for an accelerating line load on a floating ice plate in their simple linear mathematical model by proceeding to numerical calculations for the response due to a decelerating load. Our results show: (i) how the deflections produced by an impulsively started steadily moving line load begin to develop and eventually approach the well-known steady load-speed-dependent quasi-static and wave-like forms, including above the shallow water gravity wave speed where the shadow zone evolves; (ii) the singularity in the deflection predicted in the simple linear model when the load moves steadily is indeed avoided by a uniformly accelerating load, where the magnitude of the deflection continually increases and its maximum lags a little further behind as the load moves through the critical speed and beyond; (iii) there is also no singularity in the deflection due to a uniformly decelerating load, but whereas the response from a subcritical starting speed is preserved and travels with the load, the magnitude of the deflection may become quite large near a load starting from supercritical speed and approaching rest, which is attributed to constructive interference (reinforcement) as erstwhile trailing, predominantly gravity, waves catch up with the load. While this reinforcement poses no risk to Hercules transport aircraft landing on the thick sea ice at McMurdo Sound, it can account for the reported rapid sinking of the detached cockpit shortly after it came to rest in the 1974 Lockheed Electra aircraft crash in the Canadian Arctic.

An Agent Based Model for Developing Air Traffic Management Software

The Air Traffic Management system is a complex issue that faces factors such as Aircraft Crash Prevention, air traffic controllers pressure, unpredictable weather conditions, flight emergency situations, airplane hijacking, and the need for autonomy on the fly. agent-based software engineering is a new aspect in software engineering that can provide autonomy. agent-based systems have some properties such: cooperation of agents with each other in order to meet their goals, autonomy in function, learning and Reliability that can be used for air traffic management systems. In this paper, we first study the agent-based software engineering and its methodologies, and then design a agent-based software model for air traffic management. The proposed model has five modules .this model is designed for aircraft ,air traffic control and navigations aids factors based on the Belief-Desire-Intention (BDI) architecture. The agent-based system was designed using the agent-tool under the multi-agent system engineering (MaSE) methodology, which was eventually developed by the agent-ATC toolkit. In this model, we consider agents for special occasions such as emergency flights’ and hijacking airplanes in airport air traffic management areas which is why the accuracy of the work increased. It also made the flight’s sequence arrangement in take-off and landing faster, which indicates a relative improvement in the parameters of the air traffic management

A proposed approach for the evaluation of consequences of a large aircraft crash accident at an RBMK type reactor site during decommissioning

Nuclear power plants with RBMK reactors were designed in late sixties - early seventies and were built entirely in the European part of the Russian Federation, the Lithuanian Republic and the Ukrainian Republic. The plants in the Lithuanian and the Ukrainian Republics are in various stages of decommissioning. As currently planned, the most of RBMK reactors still operating in the Russian Federation will end their operation in this decade.The reactor building, spent nuclear fuel and radioactive waste storage facilities, built at the time of construction of RBMK plants are not specially designed to withstand the direct impact of an aircraft crash. There were no such regulatory requirements at the time the plants were designed and, no such requirements were introduced by regulatory bodies later on. But for now, in the aftermath of the September 11, 2001 terrorist attack on the United States, the event of an aircraft crash on a nuclear facility can no longer be considered as extremely unlikely.This paper considers the state of a nuclear power plant with the RBMK type reactor(s) during certain decommissioning and dismantling stages and discusses the approach for the evaluation of radiological consequences to the public in the event of a large aircraft crash on potentially hazardous objects of the plant. The damage to spent nuclear storage facilities, the reactor graphite stack and storage facilities for the combustible waste may cause a significant release of radionuclides to the environment. Key components of the approach include the evaluation of a structural damage to the facilities, the evaluation of a fire propagation and impact, the evaluation of a spent nuclear fuel cooling capability in storage pools, the evaluation of an airborne radionuclide release, the evaluation of a radionuclide dispersion in the environment and the evaluation of the public exposure. A set of widely used software and methods for the performance of the specific tasks is discussed. The paper also describes how the proposed approach was applied for the evaluation of radiological consequences from a Boeing 767-400 type aircraft crash at the Ignalina NPP site where a plant with two RBMK-1500 type reactors is decommissioned.The paper does not address modern radioactive waste and spent nuclear fuel management and storage facilities that might be built at RBMK sites as well. As a rule, assessment and mitigation of an aircraft crash accident consequences is an integral part of design of these new facilities.

Effect of design strength parameters of conventional two-way singly reinforced concrete slab under concentric impact loading

Damage evaluation and performance enhancement of the structures due to ever-rising malicious sporadic explosions, accidental detonations, vehicular collisions, aircraft crashing, falling construction equipment, and rock/boulder impact from landslips are of considerable concern and thus generate sufficient interest to structural engineers and researchers. In general, the mode of damage to a structure and its degree depends upon which element(s) of the structure is subjected to such impulsive loadings, damage resistance, and energy transferred to the element(s). For a deeper understanding of the failure mode and impact resistance, analysis of the structural elements under impulsive loadings (blast and impact) with varying design parameters seems necessary. The present work undertakes a numerical study to investigate the dynamic behavior of 1000 mm × 1000 mm × 75 mm two-way square singly reinforced concrete slab subjected to drop-weight impact loading at its centroid using a finite element method based commercial dynamic computer code, ABAQUS/Explicit version 6.15. The impact load is applied via a hard steel cone frustum-headed drop weight with a flat impacting face of mass 105 kg having a free-fall from a height of 2500 mm with an impacting velocity of 7.0 m/sec. Two well-known material models namely; Concrete Damage Plasticity (CDP) and Johnson-Cook (J-C) for concrete and steel, respectively, with strain rate effects have been considered. The numerical model of the slab is validated with the impact test results/observations in the open literature. Analyses have been extended to investigate the influence on the impact resistance of the slab by varying slab thickness and concrete strength without altering cover to the concrete, quantity and yield strength of the flexural steel reinforcement on the impact resistance of the slab. The slab is not provided with shear reinforcement. Three different concrete strengths (30, 40, and 50 MPa) for four slab thicknesses (75, 100, 125, and 150 mm) are considered for the parametric investigation. Results have been compared and discussed with regards to peak displacement and impact resistance of the slab.