Computation of the pressure on the surface of a fuselage with a wing in an ideal fluid

The flows around complex three-dimensional bodies by an ideal fluid are computed by methods [1–3] using approximation of the surface by a set of plane elements. A layer of surface singularities, whose intensity is found by solving a system of linear algebraic equations of very high order, is distributed continuously over each element. Evaluation of the system coefficients and its solution require significant machine time expenditures on powerful electronic computers. If in the method of [2] the total system of equations is separated successfully into several subsystems by simplifications and an approximate solution of the problem is obtained more rapidly than by the method in [1], then the same author practically used the method in [1] to design specific fuselages in [3]. A method [4] developed for a fuselage is expanded in this paper to design a wing-fuselage combination. This method turns out to be less tedious, without being inferior in accuracy, by being different from the method in [1] in the means of solving the fundamental integral equation.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 3, pp. 110–115, May–June, 1977.     

转子内含激波跨声速全三元流动各类杂交命题统一的变域变分理论:(Ⅰ)势流

本文将文[1,16]所提出的各类杂交气动命题统一的变域变分原理推广到全三元亚跨声速流动,并顾及了叶面及内外壁上的抽(喷)气分布,应用变域变分工具成功地处理了全部未知边界与间断面(例如激波、自由尾涡面),将几乎全部界面条件都转化成自然条件。本文理论为叶片的气动设计与改型提供了一系列新途径,为有限元法及其它变分直接解法奠定了新的理论基础,同时也是叶片最优设计理论[6]的一个重要组成部分。     

Development and commissioning of a transmission grating spectrometer on the National Ignition Facility

The design and calibration of a soft X-ray transmission grating imaging spectrometer for the National Ignition Facility (NIF) [1] has been discussed elsewhere [2] and will be summarised here for ease. This work primarily discusses the supporting modelling and analysis techniques associated with the transmission grating spectrometer (TGS) and provides further analysis of the dedicated qualification shot on the NIF. Comparisons are made between: the CASSANDRA [3] opacity tables (used within the radiation-hydrodynamics code NYM [4]); the opacity derived from FLYCHK [5]; and the obtained spectrum using different analysis methods. Consideration is also given to the spectral resolution [6] of the diagnostic, the design aims of the diagnostic and limitations in the utilised codes.     

Asymptotic analysis of transonic flows

In this paper we derive the equations of the second and third approximations for the stream function of two-dimensional and axisymmetric potential transonic flow of an inviscid gas and find their particular solutions corresponding to certain transonic flows.A similar study concerning the second approximation of subsonic and supersonic flow was made by Van Dyke [1] and Hayes [2]. The second approximation for the velocity potential of transonic flow has been examined in detail by Hayes [3]. Euvrard [4, 5] has investigated the asymptotic behavior of transonic flow far from a body, while Fal'kovich, Chernov, and Gorskii [6] have studied the flow in a nozzle throat.The transonic asymptotic analysis for the stream function is presented in this paper.     

Application of the modified method of multiple scales to solving the problem of a thin clamped circular plate of a very large deflection

In this paper,asymptotic behaviour of the solution to the problem of a thin clamped circular plate under uniform normal pressure at very large deflection is restudied by means of the modified method of multiple scales given in[1?].The result presented herein is in good agreement with the one obtained by professor Chien Wei-zang who first proposed the method of composite expansions to solve this problem in[3].However,by contrast,the advantage of the modified method of multiple scales it seems to be relatively simpler than the method used in[3].It is also shown that the restriction of the method of paper[1-2]pointed out in paper[4]is not essential,and several computation errors in[3]are corrected as well.     

Infinitely many solutions for double hamonic perturbed problem

ＩＮＦＩＮＩＴＥＬＹＭＡＮＹＳＯＬＵＴＩＯＮＳＦＯＲＤＯＵＢＬＥＨＡＭＯＮＩＣＰＥＲＴＵＲＢＥＤＰＲＯＢＬＥＭＤａｉＱｉｕｙｉ（戴求亿）（ＸｉａｎｇｔａｎＭｉｎｉｎｇＩｎｓｔｉｔｕｔｅ,Ｘｉａｎｇｔａｎ４１１２０１．Ｏ．Ｒ．Ｃｈｉｎａ）（Ｒｅｃｃｉｖ...     

耦合热弹性问题的分区变分原理及其广义变分原理

本文在文献[1]和[2]的基础上建立并论证了耦合热弹性问题的分区变分原理及其分区广义变分原理     

Instability of solution for a class of the third order nonlinear differential equation

ＩＮＳＴＡＢＩＬＩＴＹＯＦＳＯＬＵＴＩＯＮＦＯＲＡＣＬＡＳＳＯＦＴＨＥＴＨＩＲＤＯＲＤＥＲＮＯＮＬＩＮＥＡＲＤＩＦＦＥＲＥＮＴＩＡＬＥＱＵＡＴＩＯＮＬｕＤｅｙｕａｎ卢德渊（ＲｅｃｅｉｖｅｄＮｏｖ１０１９９４ＣｏｍｍｕｎｉｃａｔｅｄｂｙＺｈａｎｇＳｈｉ...     

Investigation of the shape of the transverse contour of a conical three-dimensional body of minimal drag moving in rarefied gas

The shape of bodies of minimal drag moving in rarefied gas in the entire range of flight heights is investigated at present on the basis of the use of local interaction models [1]. Corresponding theoretical investigations have been published in [2, 3] for the case of bodies of rotation and in [4] for three-dimensional winged bodies, and detailed numerical investigations have been carried out in [2, 5–7]. In the present paper, an analytic investigation is carried out for the purpose of determining the optimal shape of three-dimensional bodies with minimal drag in an intermediate region of flight heights in rarefied gas.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 5, pp. 112–117, September–October, 1986.     

Comment on “Precise Control for vibration of rigid-flexible mechanical arm”

The results presented in a paper by Zichen et al. [1] has some flaws. The idea in [1] is to combine assumed modes method using an integration method with optimal control adaptive law for a spatial rigid-flexible mechanical arm as an underactuated mechanical systems (UMS). The nonlinear dynamic equation formulation from reference [6] is incorrectly used in [1]. Furthermore, the control law approach in [1] was to achieve a similar result for a UMS rigid manipulator as the one published by Spong [2] and a proper citation must have been credited.