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Journal articles on the topic 'Atmospheric reentry'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 June 2025

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1

Costa, R. R., J. A. Silva, S. F. Wu, Q. P. Chu, and J. A. Mulder. "Atmospheric Reentry Modeling and Simulation." Journal of Spacecraft and Rockets 39, no. 4 (2002): 636–39. http://dx.doi.org/10.2514/2.3855.

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2

Yang, Chen, Ning Xianwen, and Su Sheng. "Analysis and Study of Heat Transfer Resistance Inside and Outside the Reentry Capsule." MATEC Web of Conferences 257 (2019): 01001. http://dx.doi.org/10.1051/matecconf/201925701001.

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According to the heat transfer characteristics inside and outside of the lunar-earth high-speed reentry capsule, a typical calculation model of heat conduction in external thermal protection system(TPS) coupled with internal radiation was established. The thermal properties of thermal resistance inside and outside the reentry capsule were analysed. The effects of thickness of the TPS, surface conditions and atmospheric pressures on the temperature were further explored. The results showed that atmosphere pressure was necessary to be controlled under 10Pa to ensure the safety temperature of the equipment and pipe. Based on the critical pressure, the configuration was optimized. The results provide detailed data for the system design of the lunar exploration, and also provide a reference for the thermal design of the atmospheric reentry spacecraft.
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3

Saldia, J. P., A. Cimino, W. Schulz, S. Elaskar, and A. Costa. "Atmospheric Reentry Dynamics of Conic Objects." Mathematical Problems in Engineering 2009 (2009): 1–14. http://dx.doi.org/10.1155/2009/859678.

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One of the key issues in a reentry risk analysis is the calculation of the aerodynamic coefficients. This paper presents a methodology to obtain these coefficients and couple it to a code that computes re-entry trajectories considering six degrees of freedom. To evaluate the different flight conditions encountered during the natural re-entry of conical objects, the Euler Equations for gasdynamics flows are used. A new scheme TVD (Total Variation Diminishing) is incorporated to a finite volume unstructured cell-centred formulation, for application to three-dimensional Euler flows. Finally, numerical results are obtained for a conical body at different attack angles and Mach. With these results, the calculation of the trajectories during atmospheric re-entry is completed.
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4

De Giorgis, Maurizio, Giorgio Borriello, Andrea Allasio, Raffaele Vavala, Thierry Leveugle, and Orazio Cosentino. "Atmospheric Reentry Demonstrator balloon flight test." Journal of Spacecraft and Rockets 36, no. 4 (1999): 507–10. http://dx.doi.org/10.2514/3.27192.

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5

Shoemaker, Michael A., Jozef C. van der Ha, and Kazuhisa Fujita. "Trajectory reconstruction of Hayabusa's atmospheric reentry." Acta Astronautica 71 (February 2012): 151–62. http://dx.doi.org/10.1016/j.actaastro.2011.08.006.

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6

Chander, Avinash, and Iyyanki Krishna. "Atmospheric Reentry Dispersion Correction Ascent Phase Guidance for a Generic Reentry Vehicle." Defence Science Journal 63, no. 3 (2013): 233–41. http://dx.doi.org/10.14429/dsj.63.3733.

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7

Mazaheri, Alireza. "High-Energy Atmospheric Reentry Test Aerothermodynamic Analysis." Journal of Spacecraft and Rockets 50, no. 2 (2013): 270–81. http://dx.doi.org/10.2514/1.a32407.

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8

Meyer, K. W., and C. C. Chao. "Atmospheric Reentry Disposal for Low-Altitude Spacecraft." Journal of Spacecraft and Rockets 37, no. 5 (2000): 670–74. http://dx.doi.org/10.2514/2.3616.

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9

Kirillovykh, V. A., and V. M. Nikolaev. "Atmospheric reentry: Flow regime and optical radiation." Fluid Dynamics 28, no. 5 (1994): 748–49. http://dx.doi.org/10.1007/bf01050065.

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10

Yurasov, Vasiliy S., Andrey I. Nazarenko, Kyle T. Alfriend, and Paul J. Cefola. "Reentry Time Prediction Using Atmospheric Density Corrections." Journal of Guidance, Control, and Dynamics 31, no. 2 (2008): 282–89. http://dx.doi.org/10.2514/1.26593.

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11

Rachman, Abdul, and Rhorom Priyatikanto. "BASIC LIFETIME MODEL FOR REENTRY TIME PREDICTION OF ARTIFICIAL SPACE OBJECTS." Jurnal Sains Dirgantara 15, no. 2 (2018): 107. http://dx.doi.org/10.30536/j.jsd.2018.v0.a2902.

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The identification of space debris and the prediction of its orbital lifetime are two important things in the initial mitigation processes of threat from falling debris. As a part of the development of related decision support system, this study focuses on developing a basic lifetime model of artificial space object based on a well-known theory and prediction scheme in the field of satellite reentry research. Current implemented model has not accounted atmospheric oblateness or other correcting factors, but it has a reasonably good performance in predicting reentry time of several objects with various initial eccentricities. Among 30 predictions conducted to 10 objects that reentered the atmosphere from 1970 to 2012, there are 13 calculations that yield prediction time with accuracy of < 30% relative to the actual reentry time. In addition, 11 calculations yields prediction time which were more accurate compared to the outputs from SatEvo software that is currently used in the decision support system on the falling debris operated by Space Science Center LAPAN. These results were considered satisfying and can be developed further by adopting the updated atmospheric model and by calculating other relevant correcting factors.
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12

Eggen, Njord, Tiago Soares, and Luisa Innocenti. "Containment methods for the atmospheric reentry of satellites." Journal of Space Safety Engineering 7, no. 3 (2020): 390–96. http://dx.doi.org/10.1016/j.jsse.2020.07.015.

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13

Komarevskiy, Nikolay, Valery Shklover, Leonid Braginsky, et al. "Design of Reflective, Photonic Shields for Atmospheric Reentry." Journal of Electromagnetic Analysis and Applications 03, no. 06 (2011): 228–37. http://dx.doi.org/10.4236/jemaa.2011.36037.

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14

Sim, Hyung-Seok, Kyu-Sung Choi, Jeong-Hwan Ko, and Eui-Seung Chung. "Development of Survivability Analysis Program for Atmospheric Reentry." Journal of the Korean Society for Aeronautical & Space Sciences 43, no. 2 (2015): 156–65. http://dx.doi.org/10.5139/jksas.2015.43.2.156.

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15

zur Nieden, P., and H. Olivier. "Determination of Atmospheric Densities from Reentry Flight Data." Journal of Spacecraft and Rockets 44, no. 2 (2007): 332–37. http://dx.doi.org/10.2514/1.19338.

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16

Jung, Minseok, Hisashi Kihara, Ken-ichi Abe, and Yusuke Takahashi. "Reentry blackout prediction for atmospheric reentry demonstrator mission considering uncertainty in chemical reaction rate model." Physics of Plasmas 25, no. 1 (2018): 013507. http://dx.doi.org/10.1063/1.5010713.

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17

Abbasi, Davood, and Mahdi Mortazavi. "A New Concept for Atmospheric Reentry Optimal Guidance: An Inverse Problem Inspired Approach." Mathematical Problems in Engineering 2013 (2013): 1–13. http://dx.doi.org/10.1155/2013/419409.

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This paper presents a new concept for atmospheric reentry online optimal guidance and control using a method called MARE G&C that exploits the different time scale featured by reentry dynamics. The new technique reaches a quasi-analytical solution and simplified computations, even considering both lift-to-drag ratio and aerodynamic roll as control variables; in addition, the paper offers a solution for the challenging path constraints issue, getting inspiration from the inverse problem methodology. The final resulting algorithm seems suitable for onboard predictive guidance, a new need for future space missions.
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18

Al-Zaidi, H. K., M. J. Al-Bermani, and A. M. Taleb. "Estimating the lifetime and Reentry of the Aluminum Space Debris of Sizes (1 and 10 cm) in LEO under Atmosphere Drag Effects." Journal of Kufa-Physics 12, no. 02 (2020): 66–75. http://dx.doi.org/10.31257/2018/jkp/2020/120207.

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This study attempts to address the lifetime and reentry of the space debris in low earth orbit LEO which extends from 200 to 1200 km. In this study a new Computer programs were designed to simulate the orbit dynamics of space debris lifetime and reentry under atmospheric drag force using Runge-Kutta Method to solve the differential equations of drag force. This model was adapted with the Drag Thermosphere Model (DTM78, 94), the Aluminum 2024 space debris in certain size (1&10 cm) were used in this study, which is frequently employed in the structure of spacecraft and aerospace designs. The selected atmospheric model for this investigation was the drag thermospheric models DTM78 and DTM94, because of this dependence on solar and geomagnetic activities. It was found that the lifetime of the space debris increases with increasing perigee altitudes. It was also found that the elliptical shape of the debris orbit would change gradually into a circular shape, then its kinetic energy would be transformed into heat and hence the debris might be destroyed in the dense atmosphere.
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19

Al-Zaidi, H. K., M. J. Al-Bermani, and A. M. Taleb. "Estimating the lifetime and Reentry of the Aluminum Space Debris of Sizes (1 and 10 cm) in LEO under Atmosphere Drag Effects." Journal of Kufa-Physics 12, no. 02 (2020): 66–75. http://dx.doi.org/10.31257/2018/jkp/2020/120207.

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This study attempts to address the lifetime and reentry of the space debris in low earth orbit LEO which extends from 200 to 1200 km. In this study a new Computer programs were designed to simulate the orbit dynamics of space debris lifetime and reentry under atmospheric drag force using Runge-Kutta Method to solve the differential equations of drag force. This model was adapted with the Drag Thermosphere Model (DTM78, 94), the Aluminum 2024 space debris in certain size (1&10 cm) were used in this study, which is frequently employed in the structure of spacecraft and aerospace designs. The selected atmospheric model for this investigation was the drag thermospheric models DTM78 and DTM94, because of this dependence on solar and geomagnetic activities. It was found that the lifetime of the space debris increases with increasing perigee altitudes. It was also found that the elliptical shape of the debris orbit would change gradually into a circular shape, then its kinetic energy would be transformed into heat and hence the debris might be destroyed in the dense atmosphere.
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20

Virgili, Josep, Peter C. E. Roberts, and Nathan C. Hara. "Atmospheric Interface Reentry Point Targeting Using Aerodynamic Drag Control." Journal of Guidance, Control, and Dynamics 38, no. 3 (2015): 403–13. http://dx.doi.org/10.2514/1.g000884.

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21

Morita, Yasuhiro, Jun'ichiro Kawaguchi, Yoshifumi Inatani, and Takashi Abe. "Demonstrator of atmospheric reentry system with hyperbolic velocity—DASH." Acta Astronautica 52, no. 1 (2003): 29–39. http://dx.doi.org/10.1016/s0094-5765(02)00119-4.

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22

Bikdash, Marwan, Ken Sartor, and Abdollah Homaifar. "Fuzzy guidance of the shuttle orbiter during atmospheric reentry." Control Engineering Practice 7, no. 3 (1999): 295–303. http://dx.doi.org/10.1016/s0967-0661(98)00188-9.

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23

MORINO, Yoshiki, and Toshinari YOSHINAKA. "F-1501 Research on Atmospheric Reentry Thermal Protection Structures." Proceedings of the JSME annual meeting IV.01.1 (2001): 315–16. http://dx.doi.org/10.1299/jsmemecjo.iv.01.1.0_315.

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24

Bogdan, DOBRESCU, BLIDERAN Radu, and CHELARU Adrian. "Parachute systems for the atmospheric reentry of launcher upper stages." INCAS BULLETIN 9, no. 1 (2017): 37–48. http://dx.doi.org/10.13111/2066-8201.2017.9.1.4.

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25

NAKAMURA, Toshiya, and Kenji FUJII. "3311 Probabilistic Transient Thermal Analysis of an Atmospheric Reentry Vehicle." Proceedings of the JSME annual meeting 2005.5 (2005): 349–50. http://dx.doi.org/10.1299/jsmemecjo.2005.5.0_349.

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26

DRAWIN, S. "ChemInform Abstract: Atmospheric Reentry: Degradation of Thermal Protection Shield Materials." ChemInform 24, no. 20 (2010): no. http://dx.doi.org/10.1002/chin.199320293.

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27

Falcoz, Alexandre, David Henry, and Ali Zolghadri. "Robust Fault Diagnosis for Atmospheric Reentry Vehicles: A Case Study." IEEE Transactions on Systems, Man, and Cybernetics - Part A: Systems and Humans 40, no. 5 (2010): 886–99. http://dx.doi.org/10.1109/tsmca.2010.2063022.

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28

Nakamura, Toshiya, and Kenji Fujii. "Probabilistic transient thermal analysis of an atmospheric reentry vehicle structure." Aerospace Science and Technology 10, no. 4 (2006): 346–54. http://dx.doi.org/10.1016/j.ast.2006.02.002.

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29

Bettinger, Robert A. "Atmospheric reentry hemisphere prediction for prograde orbits using logical disjunction." Advances in Space Research 67, no. 10 (2021): 3267–81. http://dx.doi.org/10.1016/j.asr.2021.01.056.

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30

Shi, Guoxiang, Ke Zhang, Pei Wang, and Zhiguo Han. "Algorithm of Reentry Guidance for Hypersonic Vehicle Based on Lateral Maneuverability Prediction." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 3 (2020): 523–32. http://dx.doi.org/10.1051/jnwpu/20203830523.

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Aiming at the problem that the traditional error corridor guidance method has poor adaptability in lateral guidance of predictor-corrector guidance, an algorithm of reentry guidance based on the vehicle lateral maneuverability prediction is proposed without increasing the calculation too much. The lateral component mean value of lift at reentry is calculated by using the bank angle magnitude function obtained from longitudinal guidance. According to the above-mentioned, a crossrange corridor with dynamic boundary constraint is designed to control bank angle reversal timing. Online parameters estimation is introduced to suppress the influence of the atmospheric density and aerodynamic parameters disturbance on the predictor model. The CAV-L, a kind of hypersonic vehicle, is used as an object to carry out reentry guidance simulation. The results show that the guidance algorithm can effectively guide vehicle to target for reentry missions of different range, the landing point error are small and the guidance effect is stable. The simulated results via Monte Carlo method verify that the guidance algorithm has a good adaptability and robustness to initial state deviations and process disturbances.
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31

Ledkova, T. A., and V. S. Aslanov. "Space Tethered System Control for Payload Delivery from a Circular Orbit." Mechanical Engineering and Computer Science, no. 11 (December 22, 2017): 1–16. http://dx.doi.org/10.24108/1117.0001323.

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The article deals with the transportation operation of a payload delivery from a circular orbit using a space-tethered system. The use of the tether allows transferring the payload capsule to the reentry orbit without using the jet fuel. The whole transport operation can be divided into three stages: braking for the payload exit from the original orbit, flight along the elliptical orbit to the boundary of the atmosphere, and reentry. For braking at the first stage, an extended tether is used. Its length varies according to the swing principle. This principle allows us to swing the space tethered system and use the relative speed of the tether return swing to reduce the absolute payload rate at the tether end.The objective of this work is to develop a technique for selecting the parameters of the tether length control law and the moment of the payload separation from the tether, which provides the payload capsule landing taking into account the allowable thermal and dynamic loads at the atmospheric stage of its motion.The paper considers a planar motion of a mechanical system consisting of a satellite, a weightless tether and a payload. Presents equations describing the payload motion at the stages of joint motion, free orbital flight, and reentry. Proposes a technique for selecting the parameters of the tether length control law. As a criterion of efficiency, a functional has been used, which takes into account the dynamic and thermal loads at the atmospheric stage of the payload motion. This functional can be constructed numerically, as a result of a series of numerical calculations, for a system with given mass and geometric parameters. A comparison of the reentry payload using the well-known dynamic law of the tether control and the law based on the swing principle was carried out within the framework of research activities. It was shown that in the problem of the payload delivery from a circular orbit, the swing principle is more effective than dynamic deployment. The optimum value of the control law parameter is at the border concerning the tether deployment speed.The obtained results can be used at the design stage of space transportation systems containing extended tethers.
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32

Keidar, Michael, Minkwan Kim, and Iain D. Boyd. "Electromagnetic Reduction of Plasma Density During Atmospheric Reentry and Hypersonic Flights." Journal of Spacecraft and Rockets 45, no. 3 (2008): 445–53. http://dx.doi.org/10.2514/1.32147.

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33

Savino, Raffaele, and Mario De Stefano Fumo. "Aerothermodynamic Study of Ultrahigh-Temperature Ceramic Winglet for Atmospheric Reentry Test." Journal of Thermophysics and Heat Transfer 22, no. 4 (2008): 669–76. http://dx.doi.org/10.2514/1.33296.

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34

Webb, Bruce A., and Richard W. Ziolkowski. "A Metamaterial-Inspired Approach to Mitigating Radio Frequency Blackout When a Plasma Forms Around a Reentry Vehicle." Photonics 7, no. 4 (2020): 88. http://dx.doi.org/10.3390/photonics7040088.

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Radio frequency (RF) blackout and attenuation have been observed during atmospheric reentry since the advent of space exploration. The effects range from severe attenuation to complete loss of communications and can last from 90 s to 10 min depending on the vehicle’s trajectory. This paper examines a way of using a metasurface to improve the performance of communications during reentry. The technique is viable at low plasma densities and matches a split-ring resonator (SRR)-based mu-negative (MNG) sheet to the epsilon-negative (ENG) plasma region. Considering the MNG metasurface as a window to the exterior of a reentry vehicle, its matched design yields high transmission of an electromagnetic plane wave through the resulting MNG-ENG metastructure into the region beyond it. A varactor-based SRR design facilitates tuning the MNG layer to ENG layers with different plasma densities. Both simple and Huygens dipole antennas beneath a matched metastructure are then employed to demonstrate the consequent realization of significant signal transmission through it into free space beyond the exterior ENG plasma layer.
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35

Boehrk, Hannah, Hendrik Weihs, and Henning Elsäßer. "Hot Structure Flight Data of a Faceted Atmospheric Reentry Thermal Protection System." International Journal of Aerospace Engineering 2019 (November 18, 2019): 1–16. http://dx.doi.org/10.1155/2019/9754739.

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The second sharp-edged flight experiment is a faceted suborbital reentry body that enables low-cost in-flight reentry research. Its faceted thermal protection system consisting of only flat radiation-cooled thermal protection panels is cost-efficient since it saves dies, manpower, and storage. The ceramic sharp leading edge has a 1 mm nose radius in order to achieve good aerodynamic behaviour of the vehicle. The maximum temperature measured during flight was 867°C just before transmission ended and was predicted with an accuracy of the order of 10%. The acreage thermal protection system is set up by 3 mm fiber-reinforced ceramic panels isolated by a 27 mm alumina felt from the substructure. The panel gaps are sealed by a ceramic seal. Part of the thermal protection system is an additional transpiration-cooling experiment in which nitrogen is exhausted through a permeable ceramic matrix composite to form a coolant film on the panel. The efficiencies at the maximum heat flux are 58% on the porous sample and 42% and 30% downstream of the sample in the wake. The transient load at each panel location is derived from the trajectory by oblique shock equations and subsequent use of a heat balance for both cooled and uncooled structures. The comparison to the heat balance HEATS reveals heat sinks in the attachment system while the concurrence with the measurement is good with only 8% deviation for the acreage thermal protection system. Aerodynamic control surfaces, i.e., canards, have been designed and made from a hybrid titanium and ceramic matrix composite structure.
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36

Joshi, Ojas, and Pénélope Leyland. "Implementation of Surface Radiation and Fluid-Structure Thermal Coupling in Atmospheric Reentry." International Journal of Aerospace Engineering 2012 (2012): 1–8. http://dx.doi.org/10.1155/2012/402653.

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During atmospheric reentry, radiative heating is one of the most important component of the total heat flux. In this paper, we investigate how the thermal radiation coming from the postshock region interacts with the spacecraft structure. A model that takes into account the radiation reflected by the surface is developed and implemented in a solid solver. A partitioned algorithm performs the coupling between the fluid and the solid thermal fields. Numerical simulation of a hollow cone head and a deployed flap region shows the effects of the radiative cooling and the significance of the surface radiation.
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37

Takahashi, Yusuke, Kazuhiko Yamada, and Takashi Abe. "Examination of Radio Frequency Blackout for an Inflatable Vehicle During Atmospheric Reentry." Journal of Spacecraft and Rockets 51, no. 2 (2014): 430–41. http://dx.doi.org/10.2514/1.a32539.

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38

Takahashi, Yusuke, Kazuhiko Yamada, and Takashi Abe. "Prediction Performance of Blackout and Plasma Attenuation in Atmospheric Reentry Demonstrator Mission." Journal of Spacecraft and Rockets 51, no. 6 (2014): 1954–64. http://dx.doi.org/10.2514/1.a32880.

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39

ENOKI, Naoya. "Mitigation of Radio Frequency Blackout during Atmospheric Reentry using Surface Catalytic Effect." Proceedings of the Fluids engineering conference 2018 (2018): OS9–14. http://dx.doi.org/10.1299/jsmefed.2018.os9-14.

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40

Joshi, Ashok, K. Sivan, and S. Savithri Amma. "Predictor-Corrector Reentry Guidance Algorithm with Path Constraints for Atmospheric Entry Vehicles." Journal of Guidance, Control, and Dynamics 30, no. 5 (2007): 1307–18. http://dx.doi.org/10.2514/1.26306.

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41

Rugescu, Radu Dan. "Reentry Design Solution for a Hypersonic Small Capsule." Applied Mechanics and Materials 332 (July 2013): 33–43. http://dx.doi.org/10.4028/www.scientific.net/amm.332.33.

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Restriction and selection criteria of inertial guidance sensors and system for a small recoverable capsule from onboard a hypersonic, atmospheric reentering rocket vehicle have attracted a specific research on the reentry design and challenges, with emphasize on the overall cost reduction and an optimal balance between the performances and costs under the given exploitation constraints. A simplified method for attitude control is derived that shows an easy accommodation in the capsule, given its high mass constraints, and convenient applicability for the class of small payloads under investigation. The palled experiments and investigating methodology is shown, as the result of the ORVEAL contract research team of ADDA-Association Dedicated to Development in Astronautics research organization, under the sponsorship of Romanian UEFISCDI authority for scientific research.
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42

Asl, Vahid Balouchestani, and Somayeh Davoudabadi Farahani. "Analyzing Reentry Vehicle Control Vane Effect on Stability of a Vehicle in the Atmospheric Outgoing Phase." Applied Mechanics and Materials 307 (February 2013): 227–30. http://dx.doi.org/10.4028/www.scientific.net/amm.307.227.

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In this paper, the effect of RV (Reentry Vehicle) control vane on stability of a launch vehicle in the atmospheric outgoing phase will be analyzed. Despite of necessity for stability or control purposes in atmospheric re-entry phase, the RV vane has adverse effects on the stability of the whole launch vehicle in the phase of atmospheric outgoing. For analyzing this, a pilot launch vehicle is selected, the geometry is modeled in GAMBIT, flight data is extracted and using FLUENT, the launch vehicle conditions is simulated and the stability results is extracted for analyzing that shows the adverse effects of RV control vane on whole launch vehicle stability. Finally, some suggestions are offered.
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43

Bendoukha, Sidi Ahmed, Kei-ichi Okuyama, and Bianca Szasz. "A STUDY OF RADIO FREQUENCY BLACKOUT FOR SPACE PROBE DURING ATMOSPHERIC REENTRY PHASE." International Journal of Research -GRANTHAALAYAH 5, no. 3 (2017): 1–15. http://dx.doi.org/10.29121/granthaalayah.v5.i3.2017.1750.

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During the re-entry flight, the radio signal will be interrupted, which is commonly referred to as the communications blackout. Once the plasma sheath forms in the stagnation region of a small space probe, the probe losses more than 70 percent of its downlink data. This shows that the attenuation of the radio signal is very high during the re-entry. When the probe enters the Earth’s atmosphere, the high velocity, high surface temperature and high plasma frequency cause a shock wave layer, which is the main cause of radio blackout. For other reason, the completely reflection of the electromagnetic wave at all communication lines. This study describes the theoretical and numerical study of radio communication during reentry. The paper defines an approach to end radio signal blackout occurring in the wake region and how to exactly solve the radio blackout problem using new methods as injection of coolants, the aerodynamic shaping reducing the concentration of electrons, using transceiver with high operating frequency or interaction of Static Magnetic Field (SMF). Data from OREX probe are used to prove the solution to the Radio Frequency (RF) blackout problem. The significance of the used SMF method is established by computing the reduction in plasma attenuation.
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44

Ogasawara, Toshio, Takuya Aoki, Mohamed Sayed Aly Hassan, Yosuke Mizokami, and Naoyuki Watanabe. "Ablation behavior of SiC fiber/carbon matrix composites under simulated atmospheric reentry conditions." Composites Part A: Applied Science and Manufacturing 42, no. 3 (2011): 221–28. http://dx.doi.org/10.1016/j.compositesa.2010.10.015.

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45

Al-Zaidi, H. K., M. J. Al-Bermani, and A. M. Taleb. "Reentry of Space Debris from Low Earth Orbit by Pulsed Nd:YAG Laser." Journal of Kufa-Physics 12, no. 02 (2020): 39–51. http://dx.doi.org/10.31257/2018/jkp/2020/120204.

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This research studies the orbital dynamics of space debris in near earth orbit. The orbital dynamics of space debris is closely examined in near earth orbit whereby (apogee altitude ha=1200 km and perigee altitude hp=200 km). In addition, the lifetime of the space debris is calculated using the influence of the friction force exerted on the atmospheric particles with debris dimensions measuring between (1 and 10 cm). In this study, the Drag Thermospheric Models (DTM78 and DTM94) are used because of their dependence on solar and geomagnetic activities, and pulsed lasers are utilized to interact with Aluminum 2024 particles which are frequently employed in the structure of spacecraft and aerospace designs. A numerical analysis program (NaP1) was built to calculate the lifetime of space debris and its time of return to the atmosphere. It is then integrated with a second numerical analysis program (NaP2) developed using the Lax-Wendroff finite difference method to simulate the laser material interaction model. A high power Nd:YAG laser was applied to produce shock wave pressure in target. The results show that the maximum peak pressure occurs at 50 µm depth then slowly decays, the peak pressure increases with the increase of the laser intensity, and the optimum value of the momentum coupling coefficient (Cm) for the aluminum debris of size range (1and10 cm) is 6.5 dyn.s/j.
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46

Al-Zaidi, H. K., M. J. Al-Bermani, and A. M. Taleb. "Reentry of Space Debris from Low Earth Orbit by Pulsed Nd:YAG Laser." Journal of Kufa-Physics 12, no. 02 (2020): 39–51. http://dx.doi.org/10.31257/2018/jkp/2020/120204.

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Abstract:
This research studies the orbital dynamics of space debris in near earth orbit. The orbital dynamics of space debris is closely examined in near earth orbit whereby (apogee altitude ha=1200 km and perigee altitude hp=200 km). In addition, the lifetime of the space debris is calculated using the influence of the friction force exerted on the atmospheric particles with debris dimensions measuring between (1 and 10 cm). In this study, the Drag Thermospheric Models (DTM78 and DTM94) are used because of their dependence on solar and geomagnetic activities, and pulsed lasers are utilized to interact with Aluminum 2024 particles which are frequently employed in the structure of spacecraft and aerospace designs. A numerical analysis program (NaP1) was built to calculate the lifetime of space debris and its time of return to the atmosphere. It is then integrated with a second numerical analysis program (NaP2) developed using the Lax-Wendroff finite difference method to simulate the laser material interaction model. A high power Nd:YAG laser was applied to produce shock wave pressure in target. The results show that the maximum peak pressure occurs at 50 µm depth then slowly decays, the peak pressure increases with the increase of the laser intensity, and the optimum value of the momentum coupling coefficient (Cm) for the aluminum debris of size range (1and10 cm) is 6.5 dyn.s/j.
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47

Allouche, R., R. Haoui, J. D. Parisse, and R. Renane. "Study of Thermo-Chemical Non-Equilibrium Phenomena behind Strong Shock Waves at Atmospheric Reentry." Advanced Materials Research 274 (July 2011): 13–22. http://dx.doi.org/10.4028/www.scientific.net/amr.274.13.

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This work consists of the numerical simulation of high enthalpy flows. The numerical model is governed by Euler equations and supplemented by the equations of the chemical kinetics modeling the phenomena of the chemical air components in a non-equilibrium state. The finite differences method is used for numerical simulations, the phenomena of a hypersonic flow one-dimensional reactive, non-viscous, chemical non-equilibrium is developed taking into account the physicochemical phenomena like the vibration, the dissociation of the diatomic molecules, the ionization of molecules and the formed atoms of chemical species to higher temperatures which appear behind a strong shock detached and evolve according to time in a relaxation range until to reach the equilibrium state. We are interesting in particular on the temperature effect in ionization of the atoms and the molecules.
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48

Takahashi, Yusuke, Reo Nakasato, and Nobuyuki Oshima. "Analysis of Radio Frequency Blackout for a Blunt-Body Capsule in Atmospheric Reentry Missions." Aerospace 3, no. 1 (2016): 2. http://dx.doi.org/10.3390/aerospace3010002.

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49

Annaloro, Julien, Stéphane Galera, Cédric Thiebaut, et al. "Aerothermodynamics modelling of complex shapes in the DEBRISK atmospheric reentry tool: Methodology and validation." Acta Astronautica 171 (June 2020): 388–402. http://dx.doi.org/10.1016/j.actaastro.2020.03.006.

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50

Hermant, Audrey. "Optimal control of the atmospheric reentry of a space shuttle by an homotopy method." Optimal Control Applications and Methods 32, no. 6 (2010): 627–46. http://dx.doi.org/10.1002/oca.961.

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