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2012 Vol. 38, No. 7

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Flow separation control on control surface by blowing from leading edge of control surface
Deng Xueying, Wu Peng, Wang Yankui
2012, (7): 853-856.
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The wind tunnel experimental research on the flow separation control of control surface by blowing from leading edge of control was performed in D4 wind tunnel at Beihang University, in order to reduce the blowing air consumption. Blowing position was set at the separation point. The evolvement courses of flow field with the increasing of blowing momentum coeffecient was revealed by using particle image velocimetry(PIV) technique. The suction peak of control surface is increased as a result of ejector action which is caused by blowing, it is the main mechnisim of lift enhancement of leading edge blowing. The experiment results also indicate that not only the lift of control surface is enhanced, but also the drag is reduced.
Attachment saddle point topology and transformation of 3-D separation in juncture flow
Zhang Hua, Hu Bo, Muhammad Yamin Younis, Wang Hong
2012, (7): 857-861.
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An experimental investigation of laminar boundary layer 3-D steady separation vortex flow upstream of junctures had been conducted to verify the existence of attachment saddle point topology and to study the transformation of the flow topology. The laser light sheet of 2-D particle image velocimetry(PIV) system was set on the symmetry plane of junctures formed by different shape models mounted on a fixed length flat plate. A micro lens was used to take the local flow topology around the singular point. The results confirmed the existence of attachment saddle point structure under certain flow parameters in different shape of junctures. There is transformation between attachment saddle point topology and classical separation saddle point topology as Reynolds number increase or model bluntness changes. An analysis of relation between attachment saddle point topology and Lighthill-s classical steady 3-D separation mode is presented to show that Lighthill-s classical separation mode is applicable for attachment saddle point topology.
Investigation on non-linear characteristic of pitching moment of joined wing configuration aircraft
Wang Yankui, Shan Jixiang, Tian Wei, Deng Xueying
2012, (7): 862-866.
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The joined wing configuration is one of the best configurations for the next transonic aircraft due to the advantage in the drag and lift characteristic, but the pitching moment changes non-linearly with the attack angle increasing in some condition. To solve the problem, the investigations of flow mechanism over jointed wing configuration were conducted by computational flow method and the aerodynamic characteristic for all parts were also analyzed to combined with the flows interaction between the fore-wing and after-wing and the section aerodynamic force distribution in the wing, under the condition of Ma=0.75. The results show that the lack of aerodynamic efficiency of after-wing is caused by the influence of the separation flow over the fore-wing and the pitching moment of the aircraft will increase nonlinearly with the attack angle.
Trim induced drag analysis and optimization of elastic twin-tailboom aircraft
Wang Libo, Yang Chao, Wu Zhigang
2012, (7): 867-872.
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Based on the energy method, the trim equations of flexible aircraft considering static aeroelasticity are derived. The idea of using static vortex lattice method combined with Trefftz plane theory and empirical formula to solve the induced drag and trim drag of flexible aircraft in trimmed level flight was proposed. The method of reducing total induced drag through optimization of the wing geometric twist angle was introduced. An UAV with twin tailbooms was analyzed. The result shows that the longitudinal bending stiffness has large effects on the total induced drag of the aircraft in such configuration, and it also affects the profile drag of the elevator deflexion and the total drag of the aircraft remarkably. Results of the optimization indicate that appropriate optimization of the geometric twist can make the whole span-wise lift distribution more close to the ellipse one, which will reduce the total induced drag effectively and other drag components positively.
Vortex interaction mechanism over close-coupled canard configuration
Liu Peiqing, Wang Yaping, Liu Jie, Qu Qiulin
2012, (7): 873-876,881.
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Numerical investigation on the vortical structure was carried out on a simplified close-coupled canard configuration with a 50° swept delta wing and a 50° swept delta canard at various angle of attack (AOA) by solving Reynolds averaged Navier-Stokes(N-S) equations at 2.4×105 Reynolds number. The vortex evolution was analyzed by comparison with wind tunnel force measurement and water tunnel dye visualization. The dominant interaction mechanism was figured out in three AOA regions which were classified by the canard effect. Although the vortical flowfield are complex, the vortex interaction effect could be cataloged into three mechanism named induction, convolution and burst. The analysis indicates that the canard vortex would perform a favorable impact on the main wing vortex especially at the medium and high AOA region, where the convolution effect is dominant and the lift is enhanced most significantly.
Hypersonic boundary layer transition prediction based on laminar fluctuation energy transport equation
Song Bo, Lee Chunhian
2012, (7): 877-881.
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The transition of boundary layer flows has crucial effects on aerodynamic and heat performances of hypersonic vehicles. The fluctuation energy transport equation based on Favr average was solved in conjunction with the Favr averaged Navier-Stokes equations to predict the onset of the boundary layer transition. By comparing with the available experimental data, numerical results demonstrate that larger unit Reynolds number produces earlier transition, and the angle of attack delays transition on the windward surface, while promotes it on the leeward surface.
Characteristics of temperature oscillation inthermocapillary convection in rectangular pool
Zhu Peng, Duan Li, Kang Qi
2012, (7): 882-885.
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Experimental and numerical results on characteristics of temperature oscillation in a rectangular pool of silicone oil were presented. A thermocapillary-convection controlling system was established in laboratory to study the critical condition and characteristics of temperature oscillation. The applied temperature gradient along the fluid-gas interface drived shear flow along the free surface from hot to cold and a back flow in the underlying layer. When the temperature gradient increases to a critical value, the original steady flow will become unstable to oscillatory flow. And with the deeply increasement of the temperature gradient, the flow will finally transit to the state of chaos. A temperature measurement system, which consists of thermocouple, nano-voltmeter and data-acquiring computer, was used to record the temperature of the liquid dynamically. Critical conditions for different experimental parameters were obtained, and its relationship with Prandtl number and Bond number was discussed in details. In addition, thermocapillary convection in microgravity was simulated; Sloshing of free surface was observed, which is thought to be produced by the interaction between deformation of free surface and flow field.
Numerical investigation on separation control for flow over a bump with synthetic jet
Chen Zhanjun, Ba Yulong, Wang Jinjun
2012, (7): 886-890.
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Numerical simulation on the separation flow control over a bump was carried out with synthetic jet actuator before the separation point. The Reynolds averaged Navier-Stocks equations were solved by FLUENT® 6.3. The mechanism of synthetic jet actuator flow separation control was discussed by analyzing the friction coefficient, the vortex structure separated from the bump and the flow field near the actuator orifice. When the synthetic jet actuator was turned on, the length of the recirculation region can be reduced, and the separation of flow was locked by synthetic jet, so the frequency of separation was equal to the frequency of synthetic jet. For the fixed actuating frequency, the larger the blowing momentum coefficients of the synthetic jet,the shorter the separation region downstream of the bump. When the maximum blowing momentum coefficient is 0.369 1%, the length of separation region can be reduced by 11%.
Nature of vortex bifurcation and cascade in isotropic turbulence
Ran Zheng
2012, (7): 891-894,952.
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The central problem of fully developed turbulence is understanding the energy cascading process and multiscale interaction. Update, there is no deductive theory which leads to a full physical understanding or mathematical formulation. The definition, development,challenge and the corresponding status of turbulence cascade were briefly reviewed. The limitation of present methods were emphasized. Based on the Karman-Howarth equation in 3D incompressible fluid, a new isotropic turbulence scale evolution equation and its related theory progress, the existence of nonlinear dynamic system measured by turbulence Taylor microscale was proven. The present results indicate that the energy cascading process has remarkable similarities with the determinisitic construction rules of the logistic map. The cascade appears as an infinite sequence of period-doubling vortex bifurcations.
Numerical simulation of a new-style 2D thrust vectoring nozzle
Xiao Zhongyun, Jiang Xiong, Chen Zuobin, Liu Gang
2012, (7): 895-899.
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To exclude the inefficiency of existing fluidic thrust vectoring techniques, a new-style nozzle using ejecting mixing effects was proposed, which produced thrust vectoring by making use of the tendency of a fluid jet to be attracted to a nearby surface. The vectoring angles were manually controlled by producing different pressure gradients within the collar, where pumping effects were adjusted by flux limitation. A two dimensional nozzle was designed referring to the current idea. Thrust vectoring control was testified by numerical simulation. The maximum vector angle by flux limitation was 13.3 degree, which can be increased to 20 degree by additional steady jet. The fluidic mechanism of jet vectoring was investigated by numerical simulation, thrust loss and efficiency of the nozzle were discussed, which serves to further experimental study.
Two-phase flow numerical simulation and particle impingement heating prediction in SRM nozzle
Su Penghui, Ai Bangcheng, Pan Honglu
2012, (7): 900-904,909.
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The aluminum oxide particle laden two-phase flow is an important characteristic of the solid rocket motor (SRM) nozzle flow field. Numerical investigations were conducted to understand the two-phase flow field and the surface heat increment caused by particle impingement in SRM nozzle. The Eulerian Navier-Stokes equations for the gas-phase flow were solved by finite volume method. The particle source in cell (PSIC) two-phase coupling regime based on Lagrangian particle tracking scheme and the particle-wall rebounding model based on experimental data were applied in the computations. The influences of aluminum oxide particle size on the particle trajectories and the surface heat increment distribution were studied and investigated. The results show that in the nozzle expansion section, the particle free zone increases as the particle diameter increases; the peak value of nozzle surface heat increment rises up as the particle diameter increases; the surface heat increment occurs completely in the nozzle convergent section.
Application of detached-eddy simulation based on Spalart-Allmaras turbulence model
Chen Jiangtao, Zhang Peihong, Zhou Naichun, Deng Youqi
2012, (7): 905-909.
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The numerical simulation of the high Reynolds number, massively separated flows such as flow over the circular cylinder and supersonic base flow were performed with detached-eddy simulation based on Spalart-Allmaras turbulence model. The inviscid flux was obtained with 2nd order upwind scheme and 2nd order implicit dual time method was used for accurate time marching. Detached eddy simulation presented more resolved three dimensional turbulent vortex structures compared with corresponding RANS(Reynolds-averaged Navier-Stokes) method. The resolution of main turbulent structures in wake region and prediction of mean pressure distribution show agreement with experiments.
Calculation of steady and unsteady aerodynamic characteristics for ballonets
Song Shuheng, Chen Dehua, Liu Xiaobo
2012, (7): 910-914.
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For ballonets with various shapes at 0~20 km, the incompressible Navier-Stokes(N-S) equations were solved by artificial compressibility approach, and steady and unsteady flow fields around ballonets at five different altitudes were numerically simulated. The ballonet aerodynamic force and the complex flow separation at leeward region with changes of altitude and its shape for the steady condition were simulated. The results show that the complex spatial flow separation exists at leeward region when the ballonet thickness rate increases gradually. The unsteady flow field numerical simulation at translational or pitching motion conditions was performed successfully by applying dual-time method and dynamic grid technology. The effects of translational direction and velocity on ballonet unsteady characteristics were investigated. The variations of aerodynamic force and flow field during the translational process were obtained. For the pitching motion, the ballonet aerodynamic force and flow field at various pitching speeds and maximum angles were achieved. The calculation results show that the ballonet unsteady motion has evident effects on its flow field and aerodynamic force.
New method to evaluate crew workload and application
Wang Lijing, Xiang Wei, He Xueli, Li Runshan
2012, (7): 915-919,940.
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Crew workload assessment is an important index of airworthiness certification.Wokload assessment is required by both CFR-25.1523 of federal aviation administration(FAA) airworthiness certification and CCAR-25.1523 of Chinese airworthiness certification. The basic frame of evaluation index system was established by studying airworthiness certification, crew operation manual of Boeing 737 and Airbus 320, other correlated references and interviewing with pilots. The crew workload comprehensive evaluation index system was established by consultation with Delphi method, and index weight coefficients questionnaire with order relation analysis method. The crew workload of Boeing 737 and Airbus 320 was evaluated with fuzzy comprehensive evaluation method based on the built evaluation index. The result shows that this index is reasonable and practicable. The evaluation index system and evaluation results can provide design reference on crew workload for C919.
Compressive behaviour of composite cylindrical shell with open hole
Yan Chongnian, Fan Zhou, Cheng Xiaoquan, Li Zhengneng
2012, (7): 920-924.
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The compressive behavior of one-third composite cylindrical shell with opening reinforcement was studied under a compress load. The reinforced specimen was tested and failed in buckling at 65.922 kN near the open hole. A finite element model was established in ABAQUS to investigate the buckling behavior of the composite cylindrical shell. The computational results and experimental results of buckling failure mode and buckling load were compared to verify the validity of the finite element model. The results show that as opening area increases, the buckling load of the shell without reinforcement does not decrease progressively. However, in a certain range of opening area, the structure gets maximum and minimum buckling load values. While in the case of reinforcement, with the opening area being constant, the buckling load is in direct proportion with opening height, and is in inverse proportion with opening width. To considering design and workmanship, opening height should be increased.
Aerodynamics of hovering true hoverflies
Mou Xiaolei, Sun Mao
2012, (7): 925-930.
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The aerodynamic force production of true hoverfly which can hover with an inclined stroke plane (body being approximately horizontal) was investigated, using the method of numerically solving the Navier-Stokes equation. The power requirement was computed using the aerodynamic moment and the inertia of the wing. The aerodynamic force production and power requirement were compared with that of the normal hovering whose stroke plane was horizontal. The main results are as following. The major part of the weight-supporting vertical force is produced in the downstroke and it is contributed by both the lift and the drag of the wing, unlike the normal-hovering case in which the lift principle is mainly used to produce the weight supporting force. The mass specific power is 31.71 W穔g-1 that is similar to the normal hovering case. Because of the body being horizontal, immediate forward acceleration and roll maneuvering can be made, but no more power is needed.
Progressive damage analysis method and experimental investigation of composite end frame structure
Yang Lei, Yan Ying, Yan Wei, Wang Lipeng
2012, (7): 931-935.
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Aiming at the upper and lower end frames of the grid stiffened composite cylinder, the tensile tests of three kinds of end frame segment models with different sizes and stacking sequence were conducted. Thus the damage forms and ultimate load of the end frames were gained. The progressive damage analysis based on various strength theories was conducted by finite element method, and the results of different theories were compared. Based on Zinoviev strength theory, by expanding its failure criterion and stiffness degradation scheme to three-dimensional format, and introducing Hashin criterion to estimate the damage modes, the modified Zinoviev theory was developed. The proposed method was used to carry out damage evolution analysis and strength prediction of the end frame model. The results of numerical simulation show good agreement with test results.
Numerical simulation of shear band in amorphous alloy with initially random material imperfections
Yi Min, Shen Zhigang, Guo Yaofeng
2012, (7): 936-940.
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Based on the free volume theory, a constitutive model of amorphous alloy with free volume as an internal variable was developed to be implemented in the finite element simulation by ABAQUS UMAT subroutine. The initial free volume was taken as the variable of material imperfections. And the initial random material imperfections were defined through extracting random numbers and matching them with element numbering by a FORTRAN program. A plane strain model was utilized to simulate the formation and propagation of shear band in amorphous alloy with initial random material imperfections. It was found that local increase in free volume could induce localized deformation and the subsequent formation of shear band. The nucleation, formation and propagation of shear band could relax the strain and free volume in its surroundings. The simulation could capture the main feature of shear band in amorphous alloy.The results coincide with the experimental observation and the predictions of free volume theory.
Simulation of ice effects on aircraft controllability
Xu Zhongda, Su Yuan, Cao Yihua
2012, (7): 941-946.
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The aircraft icing parameter was used to describe the ice effects on the aircraft. A nonlinear six degree-of-freedom computational flight dynamics model was built. The aircraft icing parameter was taken into the flight dynamics model to build up a time-varying simulation model. On this basis, two autopilot modes, namely, the altitude hold mode and roll attitude hold mode were designed. Furthermore, the simulation model was verified by comparing to the flight test data. Eventually, simulations of both open loop and autopilot mode were taken under certain fight condition and icing environment. The results of simulations show that icing has several adverse effects on the controllability of aircraft, including trimming characteristics, response characteristics, and the autopilot performance.
Hygrothermal properties simulation and damage analysis of T300/QY8911 undirectional laminates
Qi Zhongxin, Yan Ying, Liu Yujia, He Mingze
2012, (7): 947-952.
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Flexural properties of T300/QY8911 undirectional laminates were tested under different hygrothermal conditions. Finite element models of composite undirectional laminates under hygrothermal conditions were built. The flexural properties of T300/QY8911 undirectional laminates tested in experimentation were simulated. Plus, a damage evolution simulation module of composite was developed. The integrated damage evolution process of T300/QY8911 undirectional laminates under hygrothermal conditions was simulated. Results show that, the flexural modulus of T300/QY8911 undirectional laminates remains unchanged under different hygrothermal conditions, but the flexural strength changes greatly with conditions. For flexural modulus, the error between simulation values and test results is less than 6%, and for flexural strength, it is less than 2%. The finite element models can predict flexural properties of composite undirectional laminates under different hygrothermal conditions relative exactly.
Alternating lower-upper splitting iterative method and its application in CFD
Xiang Qian, Wu Songping, Xu Yue
2012, (7): 953-956.
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Small time step is used to ensure convergence in the time-dependent method in computational fluid dynamics(CFD). An improved iteration method termed as the alternating lower-upper splitting (ALUS) iterative method was proposed to address the problem, in which the coefficient matrix was split into a lower and an upper triangular matrix. In each inner step, only two triangular matrices were solved by Thom asalgorithm, therefore the ALUS method is simple. Theorems were listed to ensure the ALUS method convergence.A linear equation problem and flow around the cylinder were used to illustrate the characteristic of the ALUS method.Theoretical analysis and numerical results both demonstrate the new method performs well for positive definite matrices. Withless amount of computational work, the CPU time can be greatlydiminished. Thus the new ALUS method is efficient and robust and it is applicable in CFD numerical simulation.
Study and verification on similarity theory for propellers of stratospheric airships
Liu Peiqing, Ma Lichuan, Duan Zhongzhe, Ma Rong
2012, (7): 957-961.
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According to similarity theory of propellers, equal Reynolds number and equal advanced ratio similarity was selected as a group of similarity criterion combination. The effect of different density on the propeller similarity criterion was investigated by using numerical simulation. The chosen similarity criterion and correctness of applicability were verified. The relevant test results obtained by using the ground wind tunnel test on the scaled propeller model and the numerical simulation results of the stratosphere propellers were compared and analyzed. The results show that the nondimensional aerodynamic character curves of propellers at different altitudes are nearly agreement with each other. And the experimental results in ground wind tunnel is corresponding to the results of numerical simulations. It means that the air density influences little of propeller similarity parameters. So that, the scaled model experiment of propeller for stratospheric airships in ground wind tunnel is feasible according to equal Reynolds number and advanced ratio similarity, and provides reference basis for the wind tunnel test of propellers in stratosphere.
Variable-fidelity optimization applied to wing-body configuration
Zhou Ting, Wu Zongcheng, Chen Zemin, Zhu Ziqiang
2012, (7): 962-965.
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Based on the trust region method, a variable-fidelity optimization method is developed to effectively manage and utilize low-fidelity models and high-fidelity models. The low-fidelity model was employed to build an approximation model in optimization process, while the high-fidelity model was used to correct the optimization approximation model and make the optimization results converged to high-fidelity model optimization results. The viscous and inviscid iteration of full-potential method and boundary layer method was chosen as the low-fidelity model and the multi-grid Navier-Stokes method was utilized as the high-fidelity model to optimize the wing-body configuration. The optimization results show that the method has not only high efficiency, but also good accuracy, therefore, is of practical meaning.
Derivative artificial compression method of conservation laws
Dong Haitao, Liu Fujun, Han Chong
2012, (7): 966-970.
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Applying high resolution difference schemes on the derivative equations of conservation laws could overcome the shortcoming of accuracy decay at extreme points that has plagued almost all high resolution schemes. Similar to Harten-s artificial compression method, the new method is called derivative artificial compression method, which has high resolution, low dissipation and low diffusion properties, and could enhance the resolution(of numerical solution) both at discontinuities and at extreme points. Numerical experiments are implemented on a single conservation law with initial values of discontinuities and extremes, and on one dimensional shock tube problem. The resolution problem of discontinuities and extremes is compared with Harten-s TVD scheme, artificial compression method and derivative artificial compression method.
Coaxial helicopter model identification based on differential evolution algorithm and accuracy analysis
Liu Peng, Meng Zhijun, Wu Zhe
2012, (7): 971-975.
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The coaxial helicopter exists intense aerodynamic interaction between the upper and lower rotor, and it is difficult to establish the accurate dynamic model for flight control systems using the theory analysis and wind tunnel experiment. Frequency sweep flight experiment data was used to extract the non-parametric frequency responses that fully characterizes the coupled helicopter dynamics. A nonlinear search based on differential evolution algorithm for a linear state-space model which matches the frequency-response data set was conducted. Parameter insensitivity and Cramer-Rao bound analysis results have low values, indicating very good reliability of the identified model. The accuracy of the identified model is verified by comparing the model-predicted responses with the responses collected during flight experiments, and the model can be used for flight quality analysis and flight control system design.
Boundary element solution method of free vibration of Timoshenko beam
Jin Jing, Xing Yufeng
2012, (7): 976-980.
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The fundamental solution for free vibration of Timoshenko beam was derived using the Fourier transform. Weighted residual method was adapted to deduce the boundary integral formulation from the control differential equations, from which and using boundary conditions one could find the frequency equation which could be solved through algebraic eigenvalue method and influence coefficient method. For any boundary condition, natural frequencies via boundary element method (BEM) for uniform 1D structure are exact, which is validated via the case of rod. The frequencies by BEM of Timoshenko beam were compared with those of finite element method(FEM) and the exact ones.
Analysis of gravity-assist mechanism based on three-dimension elliptic restricted three-body model
Jia Jianhua, Wang Qi
2012, (7): 981-986.
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A three-dimension elliptic restricted three-body model for the gravity-assist technology in interplanetary exploration was developed based on the planar elliptic restricted three-body model by introducing two extra parameters. By using integrated backward and integrated forward method, the energies and angular momentums of the spacecraft before and after the gravity-assist were obtained. Thus, the orbits can be divided into sixteen different types. The influences of the two extra parameters on the orbit of spacecraft were discussed and the variation laws were summarized. With the Earth-Moon system as an example, the selection region of gravity-assist parameters that can achieve escape and captive was calculated. In addition, the gravity-assist parameters were optimized.

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