Total Impulse Research Articles

The Demands of a Women's College Soccer Season.

The purpose of this study was to use GPS, accelerometers, and session rating of perceived exertion (sRPE) to examine the demands of a Division II women’s soccer team. Data was collected on 25 collegiate Division II women’s soccer players over an entire regular season (17 matches and 24 practices). ZephyrTM BioHarnesses (BHs) were used to collect tri-axial acceleration information and GPS derived variables for all matches and practices. Acceleration data was used to calculate Impulse Load, a measure of mechanical load that includes only locomotor related accelerations. GPS was used to quantify total distance and distance in six speed zones. Internal Training Loads were assessed via sRPE. Mean Impulse Load, total distance, and sRPE during match play was 20,120 ± 8609 N·s, 5.48 ± 2.35 km, and 892.50 ± 358.50, respectively. Mean Impulse Load, total distance, and sRPE during practice was 12,410 ± 4067 N·s, 2.95 ± 0.95 km, and 143.30 ± 123.50, respectively. Several very large to nearly perfect correlations were found between Impulse Load and total distance (r = 0.95; p < 0.001), Impulse Load and sRPE (r = 0.84; p < 0.001), and total distance and sRPE (r = 0.82; p < 0.001). This study details the mechanical demands of Division II women’s soccer match play. This study also demonstrates that Impulse Load is a good indicator of total distance.

Effect of tendon vibration during wide-pulse neuromuscular electrical stimulation (NMES) on muscle force production in people with spinal cord injury (SCI)

BackgroundNeuromuscular electrical stimulation (NMES) is commonly used in skeletal muscles in people with spinal cord injury (SCI) with the aim of increasing muscle recruitment and thus muscle force production. NMES has been conventionally used in clinical practice as functional electrical stimulation (FES), using low levels of evoked force that cannot optimally stimulate muscular strength and mass improvements, and thus trigger musculoskeletal changes in paralysed muscles. The use of high intensity intermittent NMES training using wide-pulse width and moderate-intensity as a strength training tool could be a promising method to increase muscle force production in people with SCI. However, this type of protocol has not been clinically adopted because it may generate rapid muscle fatigue and thus prevent the performance of repeated high-intensity muscular contractions in paralysed muscles. Moreover, superimposing patellar tendon vibration onto the wide-pulse width NMES has been shown to elicit further increases in impulse or, at least, reduce the rate of fatigue in repeated contractions in able-bodied populations, but there is a lack of evidence to support this argument in people with SCI.MethodsNine people with SCI received two NMES protocols with and without superimposing patellar tendon vibration on different days (i.e. STIM and STIM+vib), which consisted of repeated 30 Hz trains of 58 wide-pulse width (1000 μs) symmetric biphasic pulses (0.033-s inter-pulse interval; 2 s stimulation train; 2-s inter-train interval) being delivered to the dominant quadriceps femoris. Starting torque was 20% of maximal doublet-twitch torque and stimulations continued until torque declined to 50% of the starting torque. Total knee extensor impulse was calculated as the primary outcome variable.ResultsTotal knee extensor impulse increased in four subjects when patellar tendon vibration was imposed (59.2 ± 15.8%) but decreased in five subjects (− 31.3 ± 25.7%). However, there were no statistically significant differences between these sub-groups or between conditions when the data were pooled.ConclusionsBased on the present results there is insufficient evidence to conclude that patellar tendon vibration provides a clear benefit to muscle force production or delays muscle fatigue during wide-pulse width, moderate-intensity NMES in people with SCI.Trial registrationACTRN12618000022268. Date: 11/01/2018. Retrospectively registered.

The kinematic genesis of vortex formation due to finite rotation of a plate in still fluid

We present a combined experimental and numerical study of an idealized model of the propulsive stroke of the turning manoeuvre in fish. Specifically, we use the framework of Lagrangian coherent structures (LCSs) to describe the kinematics of the flow that results from a thin plate performing a large angle rotation about its tip in still fluid. Temporally and spatially well-resolved velocity fields are obtained using a two-dimensional, incompressible finite-volume solver, and are validated by comparisons with experimentally measured velocity fields and alternate numerical simulations. We then implement the recently proposed variational theory of LCSs to extract the hyperbolic and elliptic LCSs in the numerically generated velocity fields. Detailed LCS analysis is performed for a plate motion profile described by$\dot{\unicode[STIX]{x1D703}}(t)=\unicode[STIX]{x1D6FA}_{max}\sin ^{2}(\unicode[STIX]{x1D714}t)$during$0\leqslant t\leqslant t_{o}$and zero otherwise. The stopping time$t_{o}$is given by$t_{o}=\unicode[STIX]{x03C0}/\unicode[STIX]{x1D714}=10~\text{s}$, the value of$\unicode[STIX]{x1D6FA}_{max}$chosen to give a stopping angle of$\unicode[STIX]{x1D703}_{max}=90^{\circ }$, resulting in a Reynolds number$Re=c^{2}\unicode[STIX]{x1D6FA}_{max}/\unicode[STIX]{x1D708}=785.4$, where$c$is the plate chord length and$\unicode[STIX]{x1D708}=10^{-6}~\text{m}^{2}~\text{s}^{-1}$the kinematic viscosity of water. The flow comprises a starting and a stopping vortex, resulting in a pair of oppositely signed vortices of unequal strengths that move away from the plate in a direction closely aligned with the final plate orientation at$t/t_{o}\approx 2$. The hyperbolic LCSs are shown to encompass the fluid material that is advected away from the plate for$t&gt;t_{o}$, henceforth referred to as the advected bulk. The starting and stopping vortices, identified using elliptic LCSs and hence more objective than Eulerian vortex detection methods, constitute only around two thirds of the advected bulk area. The advected bulk is traced back to$t=0$to identify five distinct lobes of fluid that eventually form the advected bulk, and hence map the long-term fate of various regions in the fluid at$t=0$. The five different lobes of fluid are then shown to be delineated by repelling LCS boundaries at$t=0$. The linear momentum of the advected bulk region is shown to account for approximately half of the total impulse experienced by the plate in the direction of its final orientation, thus establishing its dynamical significance. We provide direct experimental evidence for the kinematic relevance of hyperbolic and elliptic LCSs using novel dye visualization experiments, and also show that attracting hyperbolic LCSs provide objective characterization of the spiral structures often observed in vortical flows. We conclude by showing that qualitatively similar LCSs persist for several other plate motion profiles and stopping angles as well.

Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster

Liquid propellants are fast becoming attractive for pulsed plasma thrusters due to their high efficiency and low contamination issues. However, the complete plasma interaction and acceleration processes are still not very clear. Present paper develops a multi-layer numerical model for liquid propellant PPTs (pulsed plasma thrusters). The model is based on a quasi-steady flow assumption. The model proposes a possible acceleration mechanism for liquid-fed pulsed plasma thrusters and accurately predicts the propellant utilization capabilities and estimations for the fraction of propellant gas that is completely ionized and accelerated to high exit velocities. Validation of the numerical model and the assumptions on which the model is based on is achieved by comparing the experimental results and the simulation results for two different liquid-fed thrusters developed at the University of Tokyo. Simulation results shows that up-to 50 % of liquid propellant injected is completely ionized and accelerated to high exit velocities (&gt;50 Km/s), whereas, neutral gas contribute to only 7 % of the total specific impulse and accelerated to low exit velocity (&lt;4 Km/s). The model shows an accuracy up-to 92 % . Optimization methods are briefly discussed to ensure efficient propellant utilization and performance. The model acts as a tool to understand the background physics and to optimize the performance for liquid-fed PPTs.

Experimental investigation of solid rocket motors for small sounding rockets

Experimentation and research of solid rocket motors are important subjects for aerospace engineering students. However, many institutes in Thailand rarely include experiments on solid rocket motors in research projects of aerospace engineering students, mainly because of the complexity of mixing the explosive propellants. This paper focuses on the design and construction of a solid rocket motor for total impulse in the class I-J that can be utilised as a small sounding rocket by researchers in the near future. Initially, the test stands intended for measuring the pressure in the combustion chamber and the thrust of the solid rocket motor were designed and constructed. The basic design of the propellant configuration was evaluated. Several formulas and ratios of solid propellants were compared for achieving the maximum thrust. The convenience of manufacturing and casting of the fabricated solid rocket motors were a critical consideration. The motor structural analysis such as the combustion chamber wall thickness was also discussed. Several types of nozzles were compared and evaluated for ensuring the maximum thrust of the solid rocket motors during the experiments. The theory of heat transfer analysis in the combustion chamber was discussed and compared with the experimental data.

Research and Development of Electrothermal Pulsed Plasma Thruster Systems Onboard the Osaka Institute of Technology 2nd PROITERES Nano-Satellite

The Project of Osaka Institute of Technology Electric-Rocket-Engine onboard Small Space Ship (PROITERES) was started at Osaka Institute of Technology in 2007. After successfully launching the 1st PROITERES nano-satellite, the 2nd PROITERES nano-satellite with electrothermal Pulsed Plasma Thrusters (PPTs) has been developed since 2010. The main mission is powered flight with very long distance, i.e. changing more than 10km in altitude on near-earth orbits by high-power PPTs. In this research, a 30W-class PPT system was developed. The PPT achieved the maximum impulse bit of 2.47mNs, specific impulse of 342s and total impulse of 90.1Ns with repetitive 72,000 shots. Repetitive 100,000 shots could be also carried out using a newly developed Power Processing Unit (PPU). Furthermore, a long-time operation system with a Multi-Discharge-Room type PPT (MDR-PPT) head was developed. In the present paper, we explain development status of EM-PPT system including MDR-PPT, PPU, and capacitor.

Leg amputation side determines performance in curve sprinting: a case study on a Paralympic medalist

The lower limb kinetics of curve sprinting in amputees are not well described in the literature, particularly with respect to the effect of the side of amputation. This is an issue due to the importance of the knowledge for prosthetic design and classification of athletes. Thus, the aim of this study was to investigate the influence of side of amputation on curve sprinting performance in athletes with a unilateral leg amputation. A three-dimensional motion analysis system (Vicon), four force plates (Kistler) and a modified mathematical human model (ALASKA) were used to compare clockwise and counter clockwise curve sprinting lower limb kinematics and kinetics of a Paralympic medalist with a left-sided knee exarticular amputation. Results reveal that vertical ground reaction force application and total vertical impulse were lower when the affected limb was at the inside of the curve. The unaffected limb showed joint mechanics different to those established for non-amputee athletes and might contribute better to propulsion when being the inside limb. Curve sprinting biomechanics and the ability to attain high radial velocities are directly dependent on the side of amputation relative to the curve direction in a unilateral amputee athlete of highest performance level.

Influence of debris flow solid fraction on rigid barrier impact

The dynamics of debris flows are fundamentally governed by the interaction between the solid and fluid phases. However, current approaches used to estimate impact load treat debris flow as an equivalent fluid without considering solid–fluid interaction separately from other factors. In this study, a series of centrifuge tests was carried out to investigate the influence of interaction between solid and fluid phases on single-surge debris flow impact on a rigid barrier. The effect of solid–fluid interaction was studied by varying the solid fraction of the flows. A model rigid barrier was instrumented to capture induced bending moment and impact pressure. Test results demonstrate that the transition from a pile-up mechanism to a run-up mechanism is governed by the solid fraction and thus the grain contact stresses. The rigid barrier design for the impact with a pile-up mechanism is mainly dominated by the static load. Contrary to the hydrodynamic approach, which assumes that the frontal impact is the most critical, the frontal impact of a run-up mechanism contributes less than 25% of the total force impulse. The consideration of static loading leads to the development of a new impact model with a triangular distribution of the impact pressure.

Three-dimensional steep wave impact on a vertical plate with an open rectangular section

The present study treats the three-dimensional hydrodynamic slamming problem on a vertical plate subjected to the impact of a steep wave moving towards the plate with a constant velocity. The problem is complicated significantly by assuming that there is a rectangular opening on the plate which allows a discharge of the liquid. The analysis is conducted analytically assuming linear potential theory. The examined configuration determines two boundary value problems with mixed conditions which fully are taken into account. The mathematical process assimilates the plate with a degenerate elliptical cylinder allowing the employment of elliptical harmonics that ensure the satisfaction of the free-surface boundary condition of the front face of the steep wave, away from the plate. This assumption leads to an additional boundary value problem with mixed conditions in the vertical direction. The associated problem involves triple trigonometrical series and it is solved through a transformation into integral equations. To tackle the boundary value problem in the vertical direction a perturbation technique is employed. Extensive numerical calculations are presented as regards the variation of the velocity potential on the plate at the instant of the impact which reveals the influence of the opening. The theory is extended to the computation of the total impulse exerted on the plate using pressure-impulse theory.

Design of high efficiency and high thrust grid system for ion thruster

Ion thruster is the most efficient population system of satellite to control its orbits in deep space. Total efficiency, thrust, and specific impulse are the key characterization parameters of an ion thruster which define its performance. At present, total efficiency is limited within the range of 36–68%. In this paper, a new grid design is discussed to increase the total efficiency and thrust of ion thruster wherein screen grid has chamfered edges. The ion beam dynamics were simulated in OPERA14.0-3D. The simulated result is shown to have increased thrust and total efficiency from 0.196–0.364 mN and 41.29–74.66%, respectively.

Inverse Estimation of Local Slamming Loads on a Jacket Structure

Slamming loads from plunging breaking waves feature a high impulsive force and a very short duration. It is difficult to measure these loads directly in experiments due to the dynamics of the structures. In this study, inverse approaches are investigated to estimate the local slamming loads on a jacket structure using hammer test and wave test data from a model scale experiment. First, a state-of-the-art approach is considered. It uses two deconvolution techniques to first determine the impulse response functions and then to reconstruct the wave impact forces. Second, an easier applicable approach is proposed. It uses linear regression with the ordinary least square technique for the force estimation. The results calculated with these two approaches are highly identical. The linear regression approach can be extended to account for the loads transferred among different locations. This leads to lower and theoretically more accurate estimation of the loads compared to the previous two approaches. For the investigated case, the total impulse due to the wave is 22% lower. The estimated forces by the extended approach have a resolution at the millisecond level, which provides detailed information on the shape of the forces. The approach is an important tool for statistical investigations into the local slamming forces, and further on for the development of a reliable engineering model of the forces.

Three-Dimensional Printing of “Green” Fuels for Low-Cost Small Spacecraft Propulsion Systems

This paper details the advantages of employing modern additive manufacturing methods to fabricate hybrid rocket fuels for intrinsically safe and green small spacecraft propulsion systems. Using additive manufacturing overcomes multiple issues frequently associated with hybrid propulsion, including poor volumetric efficiency, system ignitability, and low fuel regression rates. When certain three-dimensionally printed thermoplastics are subjected to a high-voltage low-wattage charge, electrostatic arcing along the surface pyrolizes a small amount of material that, with the introduction of an oxidizer, “seeds” combustion and produces immediate and reliable ignition. Thermoplastic fuel grains can be printed with port shapes that enhance burn properties and increase volumetric efficiencies. Embedded helical fuel ports significantly increase regression rates. The presented test results from several prototype systems using gaseous oxygen and printed acrylonitrile butadiene styrene demonstrate the various advantages of additive manufacturing, including low-power ignition, regression rate enhancement, and system scalability. The test results from both ambient and vacuum tests of a 25 N flight-weight small spacecraft thruster are presented. Multiple burn tests allowed statistical characterization of ignition timing and burn-to-burn thrust, as well as total impulse consistency. The test results demonstrating specific impulse values exceeding 295 s are presented. When fully developed, this propulsion technology has the potential for “drop-in” replacement of many hydrazine-based propulsion applications.

An impulse based model for spherical particle collisions with sliding and rolling

Particle impact behavior description is significant for dense multiphase flow simulation and particle deposition prediction. The paper presents a novel impulse based particle collision model considering sliding and rolling. The collision model includes three components, normal, tangential and adhesion model. Normal collision model is established to predict the normal coefficient of restitution (COR), contact area, total normal impulse etc., by dividing the collision process into three compression stages (elastic, elastic-plastic and fully plastic stages), and an elastic recovery stage. The tangential and angular velocities are calculated based on the normal impulse and the determination of sliding or rolling contact. It is verified that the direction of tangential relative velocity remains the same during the whole collision process, with the assumption that the deformation of the particles does not affect the tangential forces. The adhesion loss is only activated in the recovery stage using Dunn's model, which describes the adhesion force as an idealized line force acting on the contact radius. Several cases are tested to verify the proposed model, including low velocity normal impact of particle and wall, oblique impact of particle and wall with or without spin, sphere moving on a flat plate under gravity, and particle-particle collision. The results show that the proposed model is able to predict the experimental measurements with good accuracy and captures the essential physics of particle-particle and particle-wall impacts.

Semi‐Closed Investigations of New Aluminized Thermobaric and Enhanced Blast Composites

AbstractThe investigations of new aluminum‐enriched RDX‐based composites belonging to the thermobaric and enhanced blast explosive formulations were undertaken. In a semi‐closed bunker, the blast wave and the thermal characteristics of pressed and layered charges made from the composites are determined. The study includes the blast wave history registrations as well as the determination of the overpressure peaks and the specific impulses of the incident blast wave. The total impulses have been estimated for a period of 60 ms. Since the composites are supposed to be volumetric, the explosion light outputs and the fireball temperatures were also investigated. The results obtained for the composite charges were compared with the blast performances and fireball temperatures of TNT and phlegmatized RDX charges of the same mass. Also differences between the pressed and the layered composite charges prepared from the same composites were observed and explained. The effect of the aluminum particle size was checked. Discussion of the results and conclusions about the aluminum combustions during the explosions of such charges were presented.

Relationships among the Tethered 3-min All-Out Test, MAOD and Swimming Performance

To allow the use of the 3-min all-out parameters for anaerobic evaluation, the aim of the present study was to test its relationships to maximal accumulated oxygen deficit (MAOD) and short/middle distance performances. 9 swimmers (age 19±1 years, height 176.7±6.1 cm and body mass 68.7±6.1 kg) underwent a 3-min all-out test and MAOD procedures (10 submaximal efforts and one exhaustive effort at maximal force attained during a graded exercise test); both were applied using tethered swimming conditions. Short/middle free-swimming performances were assessed at 50, 100 and 200 m distances. Only the peak force (PF) attained during 3-min all-out test exhibited a direct relationship to MAOD (r=0.77; p=0.02). Mean force, mean force until 150 s and total impulse, which were obtained during the 3-min all-out test, exhibited inverse relationship to short/middle performances (r>-0.79; p<0.02). However, no relationship was observed between PF and performances. In addition, MAOD exhibited an inverse relationships to all performances (r>-0.72; p<0.04). Thus, the present study demonstrated that only PF can be used to evaluate the anaerobic metabolism and most of the 3-min all-out test parameters are dependent on force maintenance capacity, which is also important in short/middle performance.

Effect of tendon vibration during wide-pulse neuromuscular electrical stimulation (NMES) on the decline and recovery of muscle force

BackgroundNeuromuscular electrical stimulation (NMES) is commonly used to activate skeletal muscles and reverse muscle atrophy in clinical populations. Clinical recommendations for NMES suggest the use of short pulse widths (100–200 μs) and low-to-moderate pulse frequencies (30–50 Hz). However, this type of NMES causes rapid muscle fatigue due to the (non-physiological) high stimulation intensities and non-orderly recruitment of motor units. The use of both wide pulse widths (1000 μs) and tendon vibration might optimize motor unit activation through spinal reflex pathways and thus delay the onset of muscle fatigue, increasing muscle force and mass. Thus, the objective of this study was to examine the acute effects of patellar tendon vibration superimposed onto wide-pulse width (1000 μs) knee extensor electrical stimulation (NMES, 30 Hz) on peak muscle force, total impulse before “muscle fatigue”, and the post-exercise recovery of muscle function.MethodsTendon vibration (Vib), NMES (STIM) or NMES superimposed onto vibration (STIM + Vib) were applied in separate sessions to 16 healthy adults. Total torque-time integral (TTI), maximal voluntary contraction torque (MVIC) and indirect measures of muscle damage were tested before, immediately after, 1 h and 48 h after each stimulus.ResultsTTI increased (145.0 ± 127.7%) in STIM only for “positive responders” to the tendon vibration (8/16 subjects), but decreased in “negative responders” (−43.5 ± 25.7%). MVIC (−8.7%) and rectus femoris electromyography (RF EMG) (−16.7%) decreased after STIM (group effect) for at least 1 h, but not after STIM + Vib. No changes were detected in indirect markers of muscle damage in any condition.ConclusionsTendon vibration superimposed onto wide-pulse width NMES increased TTI only in 8 of 16 subjects, but reduced voluntary force loss (fatigue) ubiquitously. Negative responders to tendon vibration may derive greater benefit from wide-pulse width NMES alone.

Inline screw feeding vacuum arc thruster.

A new type of micropropulsion device for nanosatellite applications is presented-the inline-screw-feeding vacuum-arc thruster (ISF-VAT). This thruster couples a conventional "triggerless" ignition geometry with a feeding mechanism that maintains a steady state discharge performance. The feeding mechanism implements a screw action on a central cathode rod. At a predetermined rate, a complete and uniform erosion of the cathodes tip is obtained as well as "healing" of the insulator coating. The inline feeding of the cathode forces the arc to emerge on the tip of the cathode, flush with the exit plane of the anode. This enables the plasma plume to efficiently accelerate away from the thruster, eliminating the need for an additional ion acceleration stage. The ISF-VAT feeding mechanism is computer controlled and offers reliable operation of the thruster over a large number of pulses. Characterization of the ISF-VAT performance is presented, conducted on an experimental prototype in the Aerospace Plasma Laboratory, Technion. Measurement results of the mass flow rate, electrical parameters of the discharge, and thrust are presented. Using a Ti cathode at a discharge power of 3 W, a mass flow rate of ≈1.8×10-9 kg/s and a thrust level ≈ 7 μN were measured. More than 106 pulses were demonstrated in a single run, accumulating a total impulse of 0.2 Ns. The thruster prototype dimensions are 15 × 15 × 65 mm3 and are ≈ 60 g in mass.

Cycle optimization of the staged combustion rocket engines

PurposeThe purpose of this paper is to introduce new and modified “staged combustion” cycles in the form of engineering algorithm as a possible propulsion contender for future aerospace vehicle to achieve the highest possible “total impulse” to “mass” of propulsion system.Design/methodology/approachIn this regard, the mathematical cycle model is formed to calculate the engine’s parameters. In addition, flow conditions (pressure, temperature, flow rate, etc). in the chamber, nozzle and turbopump are assessed based on the results of turbo machinery power balance and initial data such as thrust, propellant mixture ratio and specifications. The developed code has been written in the modern, object-oriented C++ programming language.FindingsThe results of the developed code are compared with the Russian RD180 engine which demonstrates the superiority and capability of new “thermodynamic diagrams”.Research limitations/implicationsThis algorithm is under constraint to control the critical variation of combustion pressure, turbine rpm, pump cavitation and turbine temperature. It is imperative to emphasize that this paper is limited to “oxidizer-rich staged combustion” engines with “single pre-burner”.Originality/valueThis study sheds light on using fuel booster turbopump and the second-stage fuel pump to moderate the effect of cavitation on pumps which reduces tank pressure and, as a consequence, decreases the propulsion system weight.

Guidance and Attitude Control of Unstable Rigid Bodies With Single-Use Thrusters

In this paper, we introduce a novel computationally efficient and practical algorithm for robust guidance and attitude control of unstable rigid bodies using the discrete fixed-magnitude, fixed-duration actuation representative of single-use thrusters. New guidance and attitude continuous control laws are developed based on the nonlinear rigid-body motion model, where the objective is to intercept a target and maintain the near zero angle of attack. A methodology is then introduced to adapt the continuous control system to discrete impulsive forces with constant magnitude and duration. An actuation management scheme is presented based on the equivalence of the total impulse of the continuous control law and thruster force. Realistic time delays and noise distributions are included in a sensor fusion algorithm based on the extended Kalman filter. Simultaneous control for course corrections to ensure the target interception and stabilization of the vehicle attitude is presented through Monte Carlo simulations with various uniformly distributed direction and velocity errors.

Close-Range Blast Effects on Small Square Clamped Plates Made from Aluminum 6061-T6

The main objective of this paper is to describe the methodology followed to verify and validate (V&V) a finite element model developed to simulate a spherical air blast on a square aluminum (Al) 6061-T6 plate. In order to have confidence in the material model and properties, the first part of this paper provides a brief review of the Defence Research and Development Canada split Hopkinson pressure bar (SHPB) facility and presents the tests performed on Al 6061-T6 specimens at different strain rates. The obtained high strain rate compression tests combined to the available published data in the literature allowed us to calibrate the parameters of the Johnson–Cook constitutive material model of the Al 6061-T6. Finite element simulations of an axisymmetric two-dimensional model were then performed to reproduce the SHPB experiments and thus validated the material properties obtained previously. The second part of this paper describes the finite element model developed to simulate the effects of a spherical close-range air blast on a predefined square target. For V&V purpose, the simulations results were compared to a wide range of experiments where the mass of the explosive was varied between 15 and 220 g and the target plate had three different thickness’ either 1.524 mm (0.06 in), 2.286 mm (0.09 in) and 3.048 mm (0.12 in). As well, the stand-off distance between the center of the C-4 explosive and the surface of the plate was varied between 10, 20 and 30 cm. Finally, the permanent midpoint deflection and the total impulse obtained numerically were compared to the experimental results and have shown good agreement in general. The methodology followed in this study required a great effort from the experimental and numerical sides but at the end, provided a set of Johnson–Cook material parameters for Al 6061-T6 and a blast loading model that can be further used to reproduce accurately the deformation of various structures made from this material.