RU2013157078A - METHOD FOR CONSTRUCTING AN OPTIMAL AERODYNAMIC SURFACE OF A HYPERSONIC AIRCRAFT - Google Patents
METHOD FOR CONSTRUCTING AN OPTIMAL AERODYNAMIC SURFACE OF A HYPERSONIC AIRCRAFT Download PDFInfo
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- RU2013157078A RU2013157078A RU2013157078/11A RU2013157078A RU2013157078A RU 2013157078 A RU2013157078 A RU 2013157078A RU 2013157078/11 A RU2013157078/11 A RU 2013157078/11A RU 2013157078 A RU2013157078 A RU 2013157078A RU 2013157078 A RU2013157078 A RU 2013157078A
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- ratio
- lift
- drag
- degrees
- coefficient
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
Способ построения оптимальной аэродинамической поверхности гиперзвукового летательного аппарата, включающий воздействие на его поверхность с использованием критерия оптимизации, отличающийся тем, что в качестве критерия оптимизации используют отношение степеней коэффициентов подъемной силы и силы лобового сопротивления, по которому формируют оптимальную поверхность летательного аппарата для решения задачи уклонения от столкновения, с использованием численных методов решения полных уравнений Навье-Стокса, для чего определяют рациональное расположение несущих поверхностей и форму носовой части аппарата с минимальными тепловыми нагрузками, гдеР - отношение степеней коэффициентов подъемной силы и силы лобового сопротивления, характеризующее показатель эффективности, полученный в результате численного решения дифференциальной игры качества,- коэффициент подъемной силы, определяемый как отношение подъемной силы к скоростному напору и характерной площади,- коэффициент силы лобового сопротивления, определяемый как отношение силы лобового сопротивления к скоростному напору и характерной площади.A method for constructing an optimal aerodynamic surface of a hypersonic aircraft, including impact on its surface using an optimization criterion, characterized in that the ratio of the degrees of lift and drag force coefficients is used as an optimization criterion, according to which the optimal aircraft surface is formed to solve the problem of avoiding collisions, using numerical methods for solving the complete Navier-Stokes equations, for which the rational arrangement of the bearing surfaces and the shape of the nose of the vehicle with minimal thermal loads are determined, where P is the ratio of the degrees of the lift and drag force coefficients, which characterizes the efficiency indicator obtained as a result of the numerical solutions of the differential game of quality, - coefficient of lift, defined as the ratio of lift to velocity head and characteristic area, - coefficient of drag force niya, defined as the ratio of the force of the frontal resistance to the velocity head and the characteristic area.
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RU2013157078/11A RU2558498C2 (en) | 2013-12-24 | 2013-12-24 | Construction of optimum airfoil for hypersonic aircraft |
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RU2013157078/11A RU2558498C2 (en) | 2013-12-24 | 2013-12-24 | Construction of optimum airfoil for hypersonic aircraft |
Publications (2)
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RU2013157078A true RU2013157078A (en) | 2015-06-27 |
RU2558498C2 RU2558498C2 (en) | 2015-08-10 |
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RU2013157078/11A RU2558498C2 (en) | 2013-12-24 | 2013-12-24 | Construction of optimum airfoil for hypersonic aircraft |
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Families Citing this family (2)
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RU2683017C1 (en) * | 2017-12-28 | 2019-03-25 | Акционерное общество "Корпорация "Тактическое ракетное вооружение" | Aircraft with the air-jet engine aerodynamic appearance determining method |
CN110589010B (en) * | 2019-09-09 | 2020-11-27 | 南京航空航天大学 | Hypersonic large-loading-space waverider design method |
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SU719916A1 (en) * | 1953-09-05 | 1980-03-05 | Ростовский государственный университет | Method of plotting regular curvilinear surfaces of puselage and other elements of aircraft |
US7979255B2 (en) * | 2007-03-16 | 2011-07-12 | Airbus Operations Sas | Method, system and computer program product for the optimization of power system architectures at the aircraft level during pre-design |
FR2944623B1 (en) * | 2009-04-21 | 2011-06-10 | Airbus France | METHOD AND TOOL FOR SIMULATING THE AERODYNAMIC BEHAVIOR OF AN AIRCRAFT IN FLIGHT IN THE NEIGHBORHOOD |
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RU2558498C2 (en) | 2015-08-10 |
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MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20151225 |