Relevant bibliographies by topics / Nosecone

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  1. Journal articles
  2. Conference papers
  3. Reports

Academic literature on the topic 'Nosecone'

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

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Journal articles on the topic "Nosecone"

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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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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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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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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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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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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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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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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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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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Conference papers on the topic "Nosecone"

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Mehmedagic, Igbal, and Siva Thangam. "Modeling and Simulation of Aerodynamic Nosecone Ablation." In ASME 2024 Heat Transfer Summer Conference collocated with the ASME 2024 Fluids Engineering Division Summer Meeting and the ASME 2024 18th International Conference on Energy Sustainability. American Society of Mechanical Engineers, 2024. http://dx.doi.org/10.1115/ht2024-122193.

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Abstract This work deals with the modeling and simulation of ablation in aerodynamic heating of a highspeed projectile. Generic projectiles with plastic hollow nosecones (for housing the radar system) in supersonic flight are considered for the purpose of developing efficient designs for high-speed projectiles. Computations are performed using the shear-stress transport (SST) k-omega model that is widely used for many aerodynamic applications. The time-averaged equations of motion and energy are solved using the modeled form of transport equations for the turbulence kinetic energy and specific
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Ranjan, Robin R., Devendra V. Parmar, Hardik K. Raipuria, and Pradeep B. Singh. "Innovative Nose Cone Design of Aircraft." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-50264.

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The term aerodynamic design means to have a drag reducing shape that cause to reduce the resistance offered by the fluid. Currently designs of the aircraft nosecone is simple rigid shaped Our concept is to have a type of inter-flight convertible nosecone, which can change its shape according with the physical condition of the environment, it means when the aircraft is to take-off, at that time it must have the most aerodynamic shape. And thus the shape of its nosecone should be sharp or may be pin pointed. And if the aircraft has to land back on the runway, it has to resist the air so that the
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3

Drenth, Aaron, and Michael L. Anderson. "Nosecone Design to Withstand Hypersonic Debris Impact." In AIAA SCITECH 2025 Forum. American Institute of Aeronautics and Astronautics, 2025. https://doi.org/10.2514/6.2025-1653.

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Ehler, Andrew, Christopher Hoppe, Hayden Kovarik, et al. "Design and Test of an Articulation Mechanism for a Morphing Missile Nosecone." In ASME 2020 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/smasis2020-2215.

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Abstract This paper covers the design and development of a mechanism to change the angle of an air-to-air missile nosecone relative to the missile body while in flight. A group of senior cadets at the United States Air Force Academy performed the work in fulfillment of requirements for their capstone design project. The Air Force Research Laboratory (AFRL) sponsored the project and provided a set of requirements to guide the design. These requirements include the challenge of torque transfer under significant loading in order to drive the nosecone to a new angle. The report will cover signific
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Bhattacharya, Maharshi, and Francisco Jung. "Multi-Mission Space Exploration Vehicle (MMSEV) Nosecone Design Optimization." In Congreso SIGraDi 2020. Editora Blucher, 2020. http://dx.doi.org/10.5151/sigradi2020-36.

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DESHPANDE, ARCHIT, NAVEEN VENUGOPAL, and HAMID DALIR. "Design and Analysis of an Optimized Formula 3 Nosecone Structure." In American Society for Composites 2019. DEStech Publications, Inc., 2019. http://dx.doi.org/10.12783/asc34/31257.

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Stewart, Ben, Russell Boyce, Andrew Neely, and Judy Odam. "CFD Analysis of Nosecone Geometries and a Generic 2D Scramjet." In AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-3339.

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Stephen, Eric J., Gregg Abate, Thomas E. McLaughlin, et al. "Investigation of Articulating Nosecone for Flight Control under Mach 2 Conditions." In 2018 Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3547.

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Sree, Narreddy Reddy Kavya, Ruban Raj Oyyappan Ganesan, Nelluri Sri Varun, et al. "Numerical analysis of aerodynamics charateristics of different nosecone shapes at supersonic speed." In PROCEEDINGS OF GLOBAL CONFERENCE ON AERONAUTICAL, AEROSPACE AND MECHANICAL SCIENCES. AIP Publishing, 2025. https://doi.org/10.1063/5.0261909.

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10

Bos, M., R. Nienkemper, and F. Meiboom. "Development of the Nosecone Separation System for the Ariane-5 Booster Recovery System." In 13th Aerodynamic Decelerator Systems Technology Conference. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1592.

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Reports on the topic "Nosecone"

1

PHENIX EXPERIMENT, E. OBRIEN, S. BOOSE, et al. TECHNICAL DESIGN REPORT FOR A NOSECONE CALORIMETER (NCC) FOR THE PHENIX EXPERIMENT. Office of Scientific and Technical Information (OSTI), 2007. http://dx.doi.org/10.2172/912838.

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