Nose Cone Research Articles

Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets

Due to sever aerodynamic heating, the protection of forebody of scramjet is crucial for hypersonic flight. In present work, a new cooling system is proposed and investigated for the protection of nose cone at hypersonic flight. Computational fluid dynamic is used for the simulation of the lateral and axial coolant jet released from the spike at high-velocity condition. The primary goal is to find optimum jet location for efficient cooling of nose and spike assembly. Influence of two coolant jets (Carbon dioxide and Helium) on the mechanism of cooling system are fully investigated. For simulation, RANS equations are coupled with species transport equation and SST turbulence model. Two different jet configurations (axial disk positions) are investigated to obtain efficient condition for protection of nose cone at hypersonic flight. Our results indicate that the presence of the spike on the nose cone decreases pressure up to 33% on the main body and the shifts the maximum pressure to higher angles because of the deflection of the air stream. Maximum pressure drops about 50% by injection of the coolant disk jet (C2) at angle of 55 deg.

Design and Construction of a High-Powered Rocket with a Camera Placed in the Nosecone

The goal of this project was to successfully launch a high-powered rocket with a camera inside of the nose cone and to get more experience using cameras in rockets. The first step of making the camera rocket was cutting out the bottom of the nose cone and inserting a sled with a camera in it into the nose cone and drilling a hole for the camera to see. The rocket we chose was a "Hi-Tech" rocket. This is a very simple and durable high-powered rocket kit and was easy to modify. Once we had built the rocket, we were ready to do a test flight. On March 29, 2023, we launched the rocket with camera in the nose cone on the University farm. The rocket was launched on a G-80, which is a common motor to use with Hi-Tech. The launch went well. The flight was straight and stable, and the parachute ejected well, even if a little late. The camera also worked well. We got great video, and the camera did not shift at all. We had a simple GPS tracker in the payload section of the Hi-Tech that allowed us to easily find the rocket when it landed. Overall, It was a successful flight, and a successful project. We have all gained valuable experience from this, and hope to put it to good use on bigger and better projects in the future.

Study on thermal protection characteristics of non-enclosed thermal cloak

The aerodynamic heat of hypersonic vehicle nose cone can reach MWm<sup>-2</sup> magnitude during flight, which could be transferred to the interior of hypersonic vehicle in the form of conduction and radiation. High efficient thermal insulation material is significant to keep internal electronic components working safely. Thermal metamaterials can regulate the macroscopic heat flow path, which have been developing rapidly and have a wide application prospect in the field of thermal protection. In this paper, a non-enclosed theoretical thermal cloak is designed to guide heat flow around hypersonic vehicle nose cone by using the transformation multithermotics, which can control thermal conduction and radiation simultaneously. A multi-layer structure is designed as cloak's simplified approximation due to the anisotropic parameters. Based on the software COMSOL, the thermal protection characteristics and heat transfer mechanism of the cloak and multi-layer structure are studied numerically. The results show that heat can flow around the object in the form of conduction and radiation in both theoretical thermal cloak and multi-layer structure, so the heat transferred to the inner area is decreased. Compared with the thermal insulation material, the heating rate of the protected area slows down, and the temperature at the front of the hypersonic vehicle nose cone is significantly reduced. However, the improvement of the thermal protection performance of cloak and multi-layer structures requires that the solid and radiative thermal conductivities of the material be lower than those of the original thermal insulation materials. To solve this problem, a non-enclosed theoretical extrapolation thermal cloak is further proposed. The solid and radiative thermal conductivities of extrapolation thermal cloak are non-singular, which could be higher than those of the original thermal insulation materials. Numerical simulation results show that the extrapolation thermal cloak can guide heat flow around object, so the thermal protection capability is improved significantly. Compared with the thermal insulation materials, the temperature of the front of the hypersonic vehicle nose cone is reduced by 100 K, and the temperature of the inner central zone of the hypersonic vehicle nose cone is reduced by 10 K. The non-enclosed extrapolation thermal cloak provides a new approach for thermal protection and is suitable for complex target areas, showing great application potential in thermal protection.

Vibration Analysis of Composite Laminated and Sandwich Conical Shell Structures: Numerical and Experimental Investigation

The use of composite conical shell structures across the globe in various applications concentrates on nose cones and incredibly complex vehicle components in the aerospace and automotive industries. This work investigates the free vibration analysis of laminated conical shell (LCS) and sandwich conical shell (SCS) structures with various foam cores. The sandwich construction is fabricated using the hand layup technique. The vibration characteristics of the fabricated LCS and SCS specimens are validated with the Finite element software (ANSYS). Very minimal variation was observed between the experimental and numerical simulations. The various parametric analyses were also studied for the LCS and SCS with length, ply orientation, and boundary conditions. Further, for SCS, vibration behaviors across multiple core materials and core thickness were also investigated.

Thermal Protection Mechanism of a Novel Adjustable Non-Ablative Thermal Protection System for Hypersonic Vehicles

In order to improve the thermal protection performance of the active thermal protection system (TPS) based on the spike and jet, an adjustable non-ablative thermal protection system, of which the spike can be rotated in the direction of the free stream, is proposed in this paper. The thermal protection mechanism and the optimal installation angle are analyzed by adopting the numerical method. The results show that the angle of attack has great influence on the peak heat flux of hypersonic vehicles, the dangerous point is on the windward side of the vehicles at the non-zero angle of attack. With the increase in angle of attack, the heat flux of the windward side of the vehicles rises rapidly, leading to the decrease in the global thermal protection efficiency. The adjustable non-ablative TPS in this paper greatly reduces the aeroheating of the windward side through the installation angle between the spike and nose cone, thus improving the global thermal protection efficiency. The optimal installation angle can be obtained by numerical or experimental methods in engineering design, and the difference between the angle of attack and the optimal installation angle is about 2.4° for the proposed model. Therefore, the installation angle can be automatically adjusted based on the angle of attack to achieve the highest thermal protection efficiency.

Comparative Study on Nose Cones with respect to Angle of Attack using CFD

A nose cone is the conically shaped forward most section of a rocket, guided missile or aircraft, designed to modulate oncoming airflow behaviours and minimize drag. In this paper, the authors analysed by means of a computational procedure the influence of varying the angle of attack for shapes of rocket nose cones in each of them, with this analysed and calculated the values of the, coefficient of lift and the coefficient of drag generated by our nose cones having as a working parameter in subsonic medium ranging from a Mach 0.03 to approximately 0.50, considering standard conditions for temperature and pressure. Drag and Lift both are aerodynamic forces which need to be calculated for cones. Objects with every kind of shapes experience a significant magnitude of Cl and Cd from airflow with the use of the ANSYS platform based on the CFD Fluent method it was possible to measure behaviour in the 3 shapes of cones and thus analyse the different contours. We showed the variation of pressure and velocity with their graphs. The scope of this paper is to simulate the different nose cones with different angle of attack for taking out the best result and comparing which one cone is best for which angle of attack.

Impact of therapeutic plasma exchange on amyloid plaque load and vascular health in APP/PS1 mice

AbstractBackgroundTherapeutic plasma exchange (TPE) has been shown to be a beneficial treatment for Alzheimer’s disease (AD) to both humans and mice; however, little is known about TPEs impact on preserving vascular function. Since AD pathology is usually associated with vascular dysfunction, the current study investigates the therapeutic potential of TPE on preserving vascular reactivity in young APPswe/PS1dE9 AD mouse model.MethodBi‐monthly TPE began at 6‐months of age (mo) in the treatment APP/PS1 group (n = 6), exchanging 300‐400 µL of plasma from a 2‐3 mo donor, wild‐type (WT) mouse. The control groups, APP/PS1 (n = 6) and WT group (n = 5), received no treatment. All mice were implanted with a 5mm cranial window and head‐fixed conditioned for awake optical imaging. Wide‐field optical imaging (WFOI) at 620nm light was used to assess vascular function. To this end, changes in optical imaging signal sensitive to blood oxygenation (OIS‐BOLD) produced by a 90‐sec hypercapnic stimulus (10% CO2 in air) delivered by nose cone. Peak changes from baseline OIS‐BOLD were measured (Fig. 1). Images of cortical amyloid plaques were obtained monthly using fluorescence microscopy 6‐24 hrs after Methoxy‐X04 administration (1 mg/kg, IP; Fig. 2). To account for between mouse variability in plaque accumulation, plaque data were normalized to their value immediately prior to their treatment (i.e., 6 mo data). An analysis of covariance was used to assess statics for vascular reactivity and plaque load.ResultTPE shows a trend towards reduced cortical plaque load in 8‐12 mo treated APP/PS1 mice (Fig. 2; p = 0.1658 ± 0.023). Vascular reactivity values measured by OIS‐BOLD also show a trend towards improved vascular function although our treated group measurements did not sample older ages (Fig. 3; F(2,134) = 2.08,p = 0.124).ConclusionOur findings showed that there is a trend to a decrease cortical amyloid plaque load in young‐middle aged AD mice treated with TPE, as well as a trend for improved vascular function. Further studies on old‐aged mice will provide additional information about the effects of TPE on AD and vascular function.

Numerical study of lateral coolant jet on heat reduction over nose cone with double-aerodome at hypersonic flow

One of the main challenges in designing a supersonic forebody is thermal protection. The application of the mechanical spike mounted at the nose considerably decreases the heat load on the main body. In this investigation, the hybrid technique of mechanical spike and coolant injection are examined to reduce the thermal load on the nose cone in the supersonic air stream. A three-dimensional model of a double aerodisked spike with different cooling systems is provided to find the efficient cooling injection system for reducing the heat load on the nose cone. Computational studies have been done on investigating a cooling mechanism in the proposed injection systems. This study has tried to present valuable information on flow features and shock interaction nearby the nose. The influence of different coolant gas on the thermal performance of the proposed configurations is comprehensively explained. Our results indicate that the cooling performance of single carbon dioxide is 85% more than helium jet in lateral injection. According to our findings, the cooling performance of lateral multi-jets is 90% more than opposing ones.

Abstract 120: Impact Of Mask Application On Aerosol Generation During Chest Compression And Defibrillation In A Swine Cardiac Arrest Model

Introduction: We previously demonstrated that defibrillation followed by chest compression generates more aerosols than chest compression or no-flow state alone. However, the best strategies to prevent aerosol spread during cardiac arrest (CA) resuscitation remain unknown. We hypothesized that mask applications could reduce aerosol spread during chest compressions and defibrillation in a swine CA model. Methods: To simulate witnessed CA with bystander-initiated CPR, 24 female non-intubated swine (43.8 [2.7] kg) underwent 4 minutes of untreated ventricular fibrillation CA followed by 10 two-minute cycles of mechanical chest compression and defibrillation without ventilation. The animals were randomized to receive no mask, cloth mask, surgical mask, N95 mask, or a sealed nose cone over their snouts during resuscitation (n=5/group except nose cone n=4). The diameter (0.3 - 10 μm) and quantity of particles generated during 45-second intervals of no-flow, chest compression, and after each defibrillation were measured 2 inches anterior to the snout. Results: There were no significant differences between total particles generated during chest compression after defibrillation in unmasked versus masked animals regardless of the mask type, while the nose cone significantly reduced total particles. These findings were consistent across all 10 defibrillations (Fig. 1a) and all particle sizes (Fig. 1b). Furthermore, the minimal pre- and post-defibrillation particles detected outside of the nose cone indicated that the ineffectiveness of masks in preventing aerosol spread during CA resuscitation was likely due to their inadequate fit (Fig. 1c). Conclusion: Mask application did not reduce aerosol spread during defibrillation followed by chest compression in a swine CA model. Our data indicate that mask fit is a critical parameter for reducing aerosol transport and do not support mask application on CA victims during bystander-initiated CPR.

Theoretical studies on the nature and conditions of interaction of heel and peripheral nose cones of offset roller cone bits with a bottom hole

An offset of roller cone rotation centerlines is used to increase the mechanical penetration rate while drilling in soft rocks. This enables increasing the area of a cutting structure teeth contact with a bottom hole. The analysis of offset cone drill bit (cutting structure) teeth wear showed that particularly significant wear is characteristic of the transition zone from the heel cone to the nose cone; which leads to significant reduction in the mechanical rate of penetration and a rapid decrease in the hole diameter. The purpose of this paper is to conduct a theoretical research on the nature and conditions of interaction between heel and peripheral nose cones of offset roller cone bits with a bottom hole; which is aimed at improving the efficiency of rock cutting by offset roller cone bits. To achieve the purpose; the authors analyzed data on the nature and causes of wear of existing offset roller cone bit cutting structure (teeth); developed a mathematical model in a cylindrical coordinate system allowing to determine the location and geometric parameters of the gage cone contact area with the hole wall for different roller cone bits sizes; developed a computer solid model for checking the adequacy of the mathematical model by comparing these two models; prepared recommendations for further improvement of the design of existing offset roller cone bit cutting structure (teeth). The research was carried out by the method of mathematical simulation of geometric figures and bodies corresponding to roller cones and a hole. The research has revealed that significant adjustments need to be made to the geometry of the roller cone teeth (currently being patented). This would allow decreasing the areas of cone heel blunting by 15–20 % as well as providing more prolonged contact of base and gage cones with bottom hole and wall surfaces. This allows to reduce wear of teeth in the transition zone of the generatrix from the peripheral nose cone to the gage (heel) cone of the roller cone and to maintain the required specific pressure on the cut rock for a longer period of time and; as a result; to increase both the mechanical penetration rate and the service life of the drilling tools.

Experimental study of bluntness effects on hypersonic boundary-layer transition over a slender cone using surface mounted pressure sensors

In this work, we studied the bluntness effect on the hypersonic boundary-layer transition over a slender cone at Mach 6 with interchangeable tips in a noisy Ludwieg tube tunnel before the so-called “transition reversal” phenomenon occurs. The evolution of instability waves is characterized using surface flush-mounted pressure sensors deployed along the streamwise direction within unit Reynolds number from 4E+ 6/m ≤ Reunit ≤ 10E+ 6/m, and the bluntness of the cone nose ranges from 0.1 mm to 5 mm. Power spectral density (PSD) of pressure fluctuation indicates that small nose bluntness (ReR ≤ 2000) has little influence on the evolution of instability waves along the hypersonic boundary-layer, whereas with a moderate nose size (2000 ≤ ReR ≤ 5000), the hypersonic boundary layer transition is delayed monotonically as the nose radius increases before the boundary-layer turns into fully laminar without instability waves. The delaying effect can be attributed to the increased entropy-layer swallowing distance with a large tip radius. Instability wave characterization reveals that the second mode instability wave plays a dominant role before the transition reversal happens. The quadratic phase locking of second mode instabilities can be identified by bispectral analysis, and it attenuates as the nose tip radius increases.

Experimental study on the flow field and aeroheating characteristics induced by a combinational aerospike and multi-jet scheme in large angle of attack

In the current study, a novel combination of the aerospike and multi-counterflowing-jet scheme is proposed for drag and heat reduction in high speed flight. The flow field and aeroheating characteristics in condition of large angle of attack are quantitatively investigated in a shock tunnel. The instantaneous flow field structure and aeroheating distribution are acquired using high-speed schlieren technique and heat flux sensors. The experimental results reveal that the counterflowing jets can push the leading bow shock wave off the model and form a pair of detached bow shock waves. The detached bow shock waves propagate at a constant velocity of about 49.8m/s and stop to oscillate ahead of the aerospike. The stagnation region between the detached bow shock wave and interface notably intensifies the local aeroheating within it. When it moves away, the local aeroheating is significantly alleviated accordingly. As the counterflowing jets start issuing, a high heat flux region yields near the nozzle and moves upstream. In case of jets not strong enough to push the stagnation region far away from the aerospike, the local aeroheating would be intensified instead of reduced. After the detached bow shock waves stop propagating upstream, the thermal load on the windward part of the blunt nose cone is reduced by more than 98%. Basing on the variation regulation and final position of the high heat flux region, it is suggested to rearrange the jet nozzle along the stagnation ling to alleviate the aeroheating more effectively.

Influence of coolant multi-jets on heat reduction of nose cone with blunt spike at hypersonic flow

The importance of the cooling system for the design of the forebody of high-speed vehicles is significant due to severe aerodynamic heating at hypersonic flight. In the present study, injection of multi and single-coolant jets on the thermal performance of forebody design of nose cone with the cut spike is thoroughly investigated at hypersonic flow. A three-dimensional model of the blunt cone is presented for computational investigations of proposed jet and spike configurations. Injection of two coolant gasses (Helium and carbon dioxide) into the cooling system of the nose cone with a blunt spike is investigated. Three locations for both opposing and lateral jets are compared to find the efficient jet location. Our results indicate that a single lateral jet injected from the tip of the spike is more efficient for heat reduction. A comparison of the multiple injection system also shows that the heat reduction of the helium gas is about 15% more than CO2 jets.

An integrated unified elasto-viscoplastic fatigue and creep damage model with characterization method for structural analysis of nickel-based high-temperature structure

This paper proposes an integrated unified elasto-viscoplastic fatigue and creep damage model with modified hardening equations to simulate the elasto-viscoplasticity, primary-secondary and tertiary creep, relaxation, cyclic softening, temperature-dependency, and creep-fatigue interaction (CFI) damage. For this purpose, we integrate the creep damage and fatigue damage model into the viscoplasticity-damage model to predict tertiary creep and cyclic softening behavior caused by creep and fatigue damage modes. Interaction effects between each damage mode are considered by the creep-fatigue interaction (CFI) damage scheme. This paper also introduces a genetic algorithm-based integrated characterization method that can effectively optimize material input parameters of the unified elasto-viscoplastic-damage material model with limited experimental data. Implicit Euler's backward iteration scheme is adopted to improve the convergence and accuracy of solutions. The proposed material model is implemented in UMAT for finite element (FE) analysis of high-temperature structures under cyclic-dwell loading. Experimental data of tensile, dwell, creep, and cyclic loading at various temperatures are used to verify the model. Finally, full-scale turbine blade FE analysis is performed under anisothermal conditions. The proposed material modeling framework can also be utilized for other high-temperature structures, such as power plants, leading-edge nose cones, etc.

Development of Tail and Nose Cone for Underwater Vertical Profiler Using Fused Deposition Modelling Technology

Unmanned underwater vehicle (UUV) research is currently a prominent and quite well-known topic for researchers from various engineering disciplines. A wide number of applications for 3D printing technologies have been explored, including robotics, automotive components, food, healthcare, space, marine, etc. This paper introduces the implementation of additive manufacturing technology (3D printing) into marine applications. The use of various 3D printing processes to create complex, cost-effective profiles have recently gained popularity to test the durability of newly designed products. The subsequent sections will explain the development of 3D printed nose and tail cones for the Underwater vehicles which will be used for underwater exploration. The development process is divided into the design of nose and tail cones using Solidworks, a 3D design software, flow analysis for the estimation and reduction of drag, operational depth of 3D printed parts using FEA software ANSYS, and prototyping using fused deposition modelling technology. The developed tail and nose cone were implemented into the vertical profiler and tested at the NITK swimming pool and successfully profiled the vertical column of the pool.

Experimental Investigation of Laminated Metal Matrix Composite Used in Drone Frame

Abstract: In this project design, fabrication, and analysis of sheet laminated Metal Matrix Composites will be carried out. It will be very useful for Aircraft Nose Cone, drone frames, and other surface materials of aircraft. The model of laminated metal matrix composite is designed using Catia V5 and also material to be applied to the body. Imported Geometry from Catia V5 to ANSYS will be analyzed by applying material properties and loads under different conditions. Based on ANSYS results the laminated metal matrix composite will experiment with. In that I take there are three types of Combinations of Laminated Metal Matrix Composites 1) Top and Bottom Aluminum Plate between Carbon fiber (aluminum top 1mm bottom 1mm +carbon 0.5 mm= 2.5mm thickness), 2) Top, Bottom, and Middle Aluminum in between Carbon fiber (aluminum (1+1+1)3mm + carbon 1mm= 4mm thickness), and 3) Top and Bottom Carbon and Middle Aluminum (Carbon (0.5+0.5) 1mm +aluminum 1mm =2mm thickness) which means 25%, 33%, and 50 % of carbon reinforced into aluminum metal.

Heat Flux on a Hypersonic Cone with a Highly Swept Fin

A detailed comparison between computations and experiments is given for Mach 6 flow over a straight cone with a highly swept fin. Five cases are simulated that vary the cone nose radius, fin thickness, fin sweep angle, and freestream unit Reynolds number. Experimental data are available for four cases. Surface heat flux comparisons between steady, laminar simulations and experimental measurements are made on the surface of the cone and fin. Uncertainty for both computations and experiments is estimated. Three cases are identified as transitional or turbulent, while one case is identified as laminar. Estimates of transition location are derived from experimental heat transfer and measurements of surface pressure fluctuations over a range of unit Reynolds numbers. The effect of geometric parameters is deduced. Further investigation into geometric changes demonstrates the sensitivity of the finned cone flowfield (e.g., vortex location and strength) to the shape of the fin–cone junction. Additionally, simulations demonstrate that the flow on the fin and cone is largely unaffected by truncating the fin. Changes in the flowfield remain localized to the fin truncation.

Analytical Study of the Penetration of Long Rod Projectiles with Conical and Blunt Nose in Normal and Oblique Ceramic Targets

The Mechanics of penetration investigate the interactions between projectiles and targets. The Mechanics of penetration were initially developed with military motives and were used in the design and manufacture of durable military vehicles, warships, protective vests, bulletproof panels, satellite protective equipment, nuclear reactor protection used. In this paper, the penetration of cylindrical and conical-nosed long rods projectiles in normal and the diagonally ceramic target is studied by analytically and numerical methods; And the Interface defeat e phenomenon, in which the projectile is eroded so that the material in the target surface is radial and outward flow. A comparison was also made between the oblique and normal penetration of long rods cylindrical and conical-nosed projectiles, which illustrates the importance of collision angles. The analytical relations related to the reduction of velocity and erosion of the projectile mass were investigated concerning the extraction time and kinetic energy loss of the projectile. Transition from the interface defeat phase to the penetration phase is also described in detail, and the variation of the critical speed suffering from the change in the angle of impact has been investigated. Each of the results of the analytical work and numerical simulations has been evaluated by experimental work carried out in previous studies and the comparison of the results shows the acceptable accuracy for the obtained relationships.

Numerical study of freestream turbulence effects on the nose cones in supersonic flow

PurposeThis paper aims to numerically investigate the influence of shock wave and freestream turbulence interaction on the parabolic and spherically blunted nose cones at supersonic speed.Design/methodology/approachUsing density-based solver, the three-dimensional steady-state simulation is carried out. The working fluid is calorically perfect that obeys ideal gas law and the no-slip boundary conditionis given to the surface of the nose cone. Pressure far-field boundary condition is imposed at the boundary of the computational domain by giving freestream Mach number, freestream static pressure and temperature.FindingsThe growth rate of the boundary layer is faster on the spherically blunted nose cone, hence, the overall drag force is higher than the parabolic nose cone. Temperature at the edge of the boundary layer is increased due to the early ampli-fication of instabilities by the upstream disturbance. In this sense, the effects of freestream turbulence depend on its level, freestream conditions, strength and type of shock wave and zone of influence.Research limitations/implicationsSimulations are carried out for the flow Mach number 2.0 at zero angles of attack for the freestream conditions of the flow at an altitude of 10,000 m.Practical implicationsThe phenomenon of shock wave–turbulence interaction occurs in flow regimes from transonic to hypersonic speeds and finds a wide range of applications, especially in the design of aircraft and missiles configurations.Originality/valueThe phenomenon of compression wave and freestream turbulence interaction around the commonly used nose cones in the case of aircraft, missiles, etc., is investigated. The performance characteristics such as aerodynamic drag, boundary layer dynamics and the nature of flow around the different nose cones at zero angle of attack are illustrated.

Particle tracer analysis for PIV experiments in a closed loop transonic wind tunnel

A performance study of several tracer particles for PIV has been conducted. The study included particle response time analysis of an oblique shock wave generated by a conical nose of a store model in a closed loop transonic wind tunnel, and in-situ measurements of the particle size distribution in a low-speed wind tunnel facility. From the oblique shock wave analysis, the estimated particle response time for different smoke materials and generator settings was of the order of 1.4 - 2.2 μs and the effective particle size was 0.58 - 0.85 μm, which was much larger than the measured geometric mean particle size. This larger size was mainly attributed to the correlation bias towards larger particles in PIV measurements. The effective particle size from the particle response time analysis accounts for the holistic performance of the PIV system. Additionally, particle response analysis was performed on ambient water droplets resident in the tunnel. The estimated particle response time for the water droplets was in the order of 3.4 μs and the effective particle size was 0.97 μm, revealing inferior performance compared to the smoke particles.