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Journal articles on the topic 'Nosecone'

Author: Grafiati
Published: 2 June 2025
Last updated: 31 July 2025

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1

Fernandes, C. D., B. H. Coutinho, B. F. Borges, et al. "EXPERIMENTAL AND NUMERICAL EVALUATION OF AN IN-FLIGHT ANGLE OF ATTACK MEASUREMENT SYSTEM FOR HIGH POWER MODEL ROCKETS." Revista de Engenharia Térmica 21, no. 4 (2023): 27. http://dx.doi.org/10.5380/reterm.v21i4.89676.

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The angle of attack (α) affects the drag, flight path, and flight stability during rocket ascent. This work proposes an in-flight α measurement system based on pressure measurements at the surface of the nosecone for low apogee rockets. An electronic micro differential pressure transducer was selected to measure the pressure difference between selected points in the rocket’s nosecone. Wind tunnel tests were performed to correlate the α with the sensor output at low Mach numbers (Ma ≃ 0.08). The experimental results were further used as a reference for the construction of CFD models of the exte
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2

IJRAME, Journal. "Vibration Control on a Thin Walled Aerospace Nosecone with Preload." International Journal of Research in Aeronautical and Mechanical Engineering 13, no. 5 (2025): 46–59. https://doi.org/10.5281/zenodo.15564396.

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This project explores the vibrational behavior (natural frequencies) of thin-walled aerospace structures, with a focus on optimizing nosecone design. It aims to enhance structural stability and reduce the risk of vibration induced failures, which are critical concerns in aerospace applications. The study begins with a detailed literature review and a careful selection of aerospace-grade materials, including composites and alloys known for their superior structural properties. Key geometrical parameters of the nosecone are optimized to improve performance. Using Design Modeler in ANSYS, a detai
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3

Oktay, Tugrul, Metin Uzun, and Ozturk Ozdemir Kanat. "Maximum lift/drag ratio improvement of TUAVs via small aerodynamic modifications." Aircraft Engineering and Aerospace Technology 90, no. 9 (2018): 1438–44. http://dx.doi.org/10.1108/aeat-07-2017-0175.

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Purpose The purpose of this study is to increase maximum lift/drag ratio (Emax) of tactical unmanned aerial vehicles (TUAVs) via applying novel small aerodynamic modifications. Design methodology/approach A TUAV is manufactured in Erciyes University, Faculty of Aeronautics and Astronautics, Model Aircraft Laboratory. It has both passive and active morphing capabilities. Its nosecone and tailcone shapes are redesigned to improve Emax. Moreover, active flow control is also built on its wing for improving Emax. Findings Using these novel small aerodynamic modifications, considerable improvement o
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4

Wasilczuk, Filip, Marcin Kurowski, and Paweł Flaszyński. "Test Section Design for Measuring the Drag Coefficient of a Suborbital Rocket Model at Ma 2.45." Transactions on Aerospace Research 2024, no. 3 (2024): 86–100. http://dx.doi.org/10.2478/tar-2024-0018.

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ABSTRACT This study investigates the drag coefficient of three models of suborbital rockets with different nosecones. A test section allowing for force measurement of a 1:50 scale rocket model was designed with the aid of numerical simulations. The velocity obtained in the wind tunnel corresponds with a Mach number of 2.45. RANS simulations were used in verifying operating parameters, as well as testing the support configurations for connecting the model with the bottom wall of the tunnel section. Pressure distribution measurements on the top and bottom walls of the wind tunnel matched simulat
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5

Huebner, Lawrence D., James L. Pittman, and Arthur D. Dilley. "Hypersonic parabolized Navier-Stokes code validation on a sharp nosecone." Journal of Aircraft 26, no. 7 (1989): 650–56. http://dx.doi.org/10.2514/3.45816.

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6

Baogang, Geng, Zhang Yongdong, Meng Xiaojun, et al. "Dynamics Analysis of Mooring Near Space Airship with Nosecone Constraint." MATEC Web of Conferences 288 (2019): 02005. http://dx.doi.org/10.1051/matecconf/201928802005.

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The near space airships usually have a large volume. when the airship leave the boathouse, it is influenced by the near surface wind significantly, and the attitude of the airship will change, and the risk of the experiment will be increase. In this paper, the dynamics method is used to analyse the force in the mooring rope and the attitude of the airship with nosecone constraint. The kinetic equation is established. A typical near space airship is choose as an example. The Runge- Kutta method is used to solve the dynamic equation. According to calculation result, the change law of the force i
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7

Widyastuti, Widyastuti, Ruri Agung Wahyuono, Rindang Fajarin, et al. "Low Reflection-Loss Thermal Barrier Coating on Hastelloy C276 for Radio Control Rocket Tip Nosecone Using Yttria-Stabilized Zirconia (YSZ) at Extreme Temperature." Solid State Phenomena 354 (December 20, 2023): 49–60. http://dx.doi.org/10.4028/p-fngyk1.

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The nosecone tip during the launch process becomes the first part that experiences friction against the atmosphere so that heat is generated, which continues to increase over time. Therefore, the nosecone tip material must have high-temperature resistance, and the materials used must not interfere with the avionics and telemetry systems of the rocket. When the sounding rocket orbits at an altitude of 200-300 Km, the atmospheric environmental conditions also fluctuate, so the nose cone tip must also be able to adapt to this condition. The end of the nose cone must be protected with a high heat-
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8

Suguta, Masahiko, Akihiko Nakano, Yoichi Hoshino, Tomoyuki Tomita, Akira Hasegawa, and Masahiko Kurabayashi. "Intracoronary separation of a nosecone: An unusual complication of directional atherectomy." Catheterization and Cardiovascular Interventions 54, no. 4 (2001): 526–30. http://dx.doi.org/10.1002/ccd.1326.

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9

Wu, Yifei, Zhengping Zou, Chao Fu, and Weihao Zhang. "NUMERICAL STUDY OF POROUS BLUNT NOSECONE TRANSPIRATION COOLING UNDER SUPERSONIC INCOMING FLOW." Journal of Porous Media 20, no. 7 (2017): 607–18. http://dx.doi.org/10.1615/jpormedia.v20.i7.30.

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10

Fincke, J. R., J. B. Workman, G. A. Kryala, et al. "Close-in nosecone configuration and blast damage in point backlight x-ray radiography." Review of Scientific Instruments 75, no. 10 (2004): 3966–68. http://dx.doi.org/10.1063/1.1789254.

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11

MAEDA, Takao, Yasunari KAMADA, Kenta ADACHI, and Jun SUZUKI. "OS2-11 Performance improvement of micro wind turbine with a combination of nosecone and diffuser casing." Proceedings of the National Symposium on Power and Energy Systems 2007.12 (2007): 157–60. http://dx.doi.org/10.1299/jsmepes.2007.12.157.

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12

Pradyumna Rangnath Surwase. "Optimizing Obscurity: Advancing Stealth Capabilities and Performance of BWB Fighter with Symmetric Supercritical Airfoils." Acceleron Aerospace Journal 3, no. 2 (2024): 464–73. http://dx.doi.org/10.61359/11.2106-2443.

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The F-22 Raptor is widely recognized as the most dominant aircraft on the battlefield due to its unparalleled stealth characteristics. However, in terms of overall performance, it is not the best. The current article proposes the design of a next-generation blended wing body (BWB) aircraft. A key motivation for using a symmetrical supercritical airfoil is the research gap identified in the literature. This design also incorporates novel approaches such as short take-off and landing capabilities and a dual combustor engine, which are expected to significantly enhance performance characteristics
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13

Chowdhury, Soumyadeep, Sayantan Das, and Udaya Kumar. "Possibility of Lightning Strike to Surface-Mounted Antennas on Aircraft." Amrit Research Journal 4, no. 2 (2024): 11–17. http://dx.doi.org/10.3126/arj.v4i2.65538.

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Lightning is considered a significant electromagnetic hazard for airplanes. One of the initial stages in developing lightning protection systems for airplane involves determining potential areas where lightning may strike and attach to the airplane. The most common mode of attachment to the airplane, known as the airplane-initiated mode, is caused by airplane-initiated bipolar leaders. Previous research has indicated that airplane components, such as the nosecone, wingtips, and stabilizer tips, play a crucial role in the commencement of connecting leaders. Apart from these, other extremities f
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14

FUKIBA, Katsuyoshi, Nobuyuki TSUBOI, and Hiroaki KOBAYASHI. "Numerical Study on Flow Angles and Mach Number Measurement Using the Surface Pressure of a Supersonic Aircraft with Nosecone." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 58, no. 676 (2010): 130–37. http://dx.doi.org/10.2322/jjsass.58.130.

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15

Das, Sayantan, and Udaya Kumar. "Modeling of Bi-Polar Leader Inception and Propagation from Flying Aircraft Prior to a Lightning Strike." Atmosphere 13, no. 6 (2022): 943. http://dx.doi.org/10.3390/atmos13060943.

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Lightning is one of the major environmental threats to aircraft. The lightning strikes during flying are mostly attributed to aircraft-triggered lightning. The first step toward designing suitable protective measures against lightning is identifying the attachment locations. For this purpose, oversimplified approaches are currently employed, which do not represent the associated discharge phenomena. Therefore, in this work, a suitable model is developed for simulating the inception and propagation of bi-polar leader discharge from the aircraft. Modeling of leader discharges requires field comp
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16

Wu, Han, Chuntai Zheng, Peng Zhou, et al. "The multi-functional rotor aerodynamic and aeroacoustic test platform at HKUST." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 2 (2021): 4410–17. http://dx.doi.org/10.3397/in-2021-2695.

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This paper describes the multi-functional rotor noise and aerodynamics test platform at the Hong Kong University of Science and Technology (HKUST). To investigate the noise characteristics of propellers with aerodynamic flows, the test rig is installed in the 2.5×2 (m) low-speed and low-noise wind tunnel in the Aerodynamic and Acoustic Facility (AAF) at HKUST. The wind tunnel can facilitate flow from 0 to 40 m/s. The test rig is assembled in a turntable on the ceiling of the tunnel wall, which enables the testing range of pitch angle can vary from 0° (axial flow) to 90° (parallel flow), with a
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17

Cadamuro, Riccardo, Maria Teresa Cazzola, Nicolò Lontani, and Carlo E. D. Riboldi. "A Static Stability Analysis Method for Passively Stabilized Sounding Rockets." Aerospace 11, no. 3 (2024): 242. http://dx.doi.org/10.3390/aerospace11030242.

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Sounding rockets constitute a class of rocket with a generally simple layout, being composed of a cylindrical center-body, a nosecone, a number of fins placed symmetrically around the longitudinal axis (usually three or four), and possibly a boat-tail. This type of flying craft is typically not actively controlled; instead, a passive stabilization effect is obtained through suitable positioning and sizing of the fins. Therefore, in the context of dynamic performance analysis, the margin of static stability is an index of primary interest. However, the classical approach to static stability ana
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18

Lakshminarayan, Raghuram, Paul M. Scott, and Rakesh Kapur. "Aortic Zone 0 Stenting in the Presence of a Metallic Aortic Valve: A Novel Technique of Loop Wire with a Trimmed Nosecone." European Journal of Vascular and Endovascular Surgery 62, no. 3 (2021): 499. http://dx.doi.org/10.1016/j.ejvs.2021.05.018.

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19

Uldahl, Kristine B., Signe B. Jensen, Yuvaraj Bhoobalan-Chitty, Laura Martínez-Álvarez, Pavlos Papathanasiou, and Xu Peng. "Life Cycle Characterization of Sulfolobus Monocaudavirus 1, an Extremophilic Spindle-Shaped Virus with Extracellular Tail Development." Journal of Virology 90, no. 12 (2016): 5693–99. http://dx.doi.org/10.1128/jvi.00075-16.

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ABSTRACTWe provide here, for the first time, insights into the initial infection stages of a large spindle-shaped archaeal virus and explore the following life cycle events. Our observations suggest thatSulfolobusmonocaudavirus 1 (SMV1) exhibits a high adsorption rate and that virions adsorb to the host cells via three distinct attachment modes: nosecone association, body association, and body/tail association. In the body/tail association mode, the entire virion, including the tail(s), aligns to the host cell surface and the main body is greatly flattened, suggesting a possible fusion entry m
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20

A Whitmore, Stephen, and Zheng Qi C Case. "Comparing a 3-d printed hemispherical-head and Rankine-body probe shapes for very low speed flush air data system (FADS) measurements." Aeronautics and Aerospace Open Access Journal 7, no. 2 (2023): 71–85. http://dx.doi.org/10.15406/aaoaj.2023.07.00173.

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This study investigates the feasibility of using Flush Air Data Sensing (FADS) System technology for air data measurements at the very low-airspeeds, where many Unmanned Aerial Vehicles (UAVs) operate. FADS is a non-intrusive alternative to pitot probes, where the vehicle nosecone, wing leading edge, or other aerodynamic surfaces are configured with multiple pressure-ports distributed along the windward face. Although FADS technology has been used for a variety of high-speed aircraft, FADS has never been applied to very low-airspeed flight regimes. This study reports on wind tunnel tests of tw
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21

"Integra CEM Nosecone." Biomedical Safety & Standards 43, no. 10 (2013): 79–80. http://dx.doi.org/10.1097/01.bmsas.0000430709.56699.94.

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22

Gedlu, Solomon. "Design and Analysis of 3/4 Power Series Rocket Nosecone." August 11, 2020. https://doi.org/10.19070/2470-4415-2000028.

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Drag is defined as the force that opposes forward motion through the atmosphere and is parallel to the direction of the free stream velocity of the airflow, this paper included within different types of drag forces some of them are experienced in rocket nosecone like form drag and skin friction drag also supersonic rocket experience additional drag is called wave drag, finally reach on the conclusion that the length of nosecone 3.02976830 meter and total drag force experienced on nosecone 44,987.43173 kg m/sec2 .
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23

"Integra CUSA Excel CEM Nosecone." Biomedical Safety & Standards 44, no. 8 (2014): 61–62. http://dx.doi.org/10.1097/01.bmsas.0000446421.31707.73.

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24

Li, Songqi, Wenyan Li, and Lawrence Ukeiley. "Time-resolved Velocity Estimation from Inflow Pressure Measurements in a Subsonic Jet Using Machine-Learning Methods." 14th International Symposium on Particle Image Velocimetry 1, no. 1 (2021). http://dx.doi.org/10.18409/ispiv.v1i1.73.

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The goal of this study is to estimate aspects of the time-resolved (TR) velocity field that is associated with pressure fluctuations measured in a subsonic jet using machine learning (ML) approaches. The experiments were conducted in the Anechoic Jet Test Facility at the University of Florida using a round converging nozzle operated at at a Mach number of 0.3 and ReD = 3.8 × 105. Planar PIV was utilized to record nonTR, 2D velocity snapshots on the streamwise plane. A B&K 4138 1/8” microphone and a GRAS 46DD 1/8” microphone were employed to measure inflow pressure fluctuations synchronousl
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25

Pasquetti, Leonardo, Edoardo Pasqui, Giuseppe Galzerano, Bruno Gargiulo, Cecilia Molino, and Gianmarco de Donato. "Protected retrieval of a detached iliac branch device nosecone." Journal of Vascular Surgery Cases, Innovations and Techniques, May 2025, 101835. https://doi.org/10.1016/j.jvscit.2025.101835.

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26

Solomon, Gedlu. "Design and Analysis of 3/4 Power Series Rocket Nosecone." International Journal of Aeronautical Science & Aerospace Research, August 11, 2020, 230–34. http://dx.doi.org/10.19070/2470-4415-2000028.

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27

Ibraheem, Muhammad, Awais Ahmad Khan, Muhammad Kamran Saleem, Mujtaba Rashid, and Muhammad Subhan Tariq. "Machine Learning Methods for Design and Analysis of a Rocket Nosecone." International Journal of Aeronautical and Space Sciences, June 11, 2025. https://doi.org/10.1007/s42405-025-00983-x.

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28

Fox, Gideon, Adam Vincent, Quinton Shepard, Dayne Locke, null null, and null null. "Design and Construction of a High-Powered Rocket with a Camera Placed in the Nosecone." John Heinrichs Scholarly & Creative Activities Day, 2023. http://dx.doi.org/10.58809/rmop8052.

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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 r
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29

Wang, Xiaoyin, Christian Cheung, Natasha Goyal, et al. "Abstract 4134277: Impairment of Vascular Endothelial Function by Inhalation of Smoke or Aerosol from Tobacco and Marijuana Products is Dependent on Vagus Nerve Input from the Airway." Circulation 150, Suppl_1 (2024). http://dx.doi.org/10.1161/circ.150.suppl_1.4134277.

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Background: Smoke or vaporizer aerosol from different tobacco or marijuana products can cause vascular endothelial dysfunction in humans and rodents. Mechanisms of acute smoke-induced endothelial dysfunction are complex and remain ambiguous. We reported that endothelial functional impairment by tobacco smoke is dependent on intact vagus nerves, leading us to hypothesize that endothelial function impaired by smoke/aerosol from tobacco or marijuana relies on vagal input from the airway. Methods: We used Sprague-Dawley rats at 10-12 weeks of age (n=8/group; 4M+4F). Rats were anesthetized by ketam
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