THRUST-AMPLITUDE CONTINUATION DESIGN APPROACH FOR SOLVING SPACECRAFT OPTIMAL CONTROLLED FLY-AROUND TRAJECTORY

针对航天器燃料最优可变周期绕飞轨迹的求解问题, 提出了一种以推力幅值为延拓参数的延拓方法. 问题求解从最为简单的双脉冲绕飞轨迹出发, 首先利用有限推力替代脉冲推力, 设定推力序列为“开— 关— 开”,然后逐步减小推力幅值, 最终得到最小推力绕飞轨迹; 此后, 再逐步增加推力幅值, 结合主矢量曲线判断最优推力开关序列, 将最小推力解延拓至有限推力以及脉冲推力燃料最优解. 该方法通过对推力幅值的延拓, 实现了有限推力bang-bang 控制与脉冲推力燃料最优绕飞轨迹优化问题的一并求解, 同时避免了最优控制问题中协态变量的随机猜测. 慢速与快速绕飞算例的优化结果验证了所提出方法的有效性.     

航天器最优受控绕飞轨迹推力幅值延拓设计方法

针对航天器燃料最优可变周期绕飞轨迹的求解问题, 提出了一种以推力幅值为延拓参数的延拓方法. 问题求解从最为简单的双脉冲绕飞轨迹出发, 首先利用有限推力替代脉冲推力, 设定推力序列为“开— 关— 开”,然后逐步减小推力幅值, 最终得到最小推力绕飞轨迹; 此后, 再逐步增加推力幅值, 结合主矢量曲线判断最优推力开关序列, 将最小推力解延拓至有限推力以及脉冲推力燃料最优解. 该方法通过对推力幅值的延拓, 实现了有限推力bang-bang 控制与脉冲推力燃料最优绕飞轨迹优化问题的一并求解, 同时避免了最优控制问题中协态变量的随机猜测. 慢速与快速绕飞算例的优化结果验证了所提出方法的有效性.      

抗滑桩设计推力计算方法研究

滑坡推力是抗滑桩设计推力的重要依据,工程中通常使用剩余推力法来计算滑坡推力。为了比较准确合理地计算出抗滑桩的设计推力,提出了在剩余推力法基础上的一种新的抗滑桩设计推力取值方法。分析极限平衡状态下和工程安全要求下各条块的剩余下滑力,选择合理的桩位,使得抗滑桩位于滑坡体的抗滑段;然后调整桩后滑体的剩余下滑力,其调整量一方面保证桩前桩后滑体满足工程安全要求,另一方面则作为抗滑桩设计推力的修正依据,其过程由程序实现。通过实例证明了该方法的合理性。同时对今后抗滑桩设计推力的合理取值提供了参考作用。     

A simplified method for the estimation of soil thrust exerted by a tracked vehicle

A simplified method for estimating the soil thrust exerted by a tracked vehicle is proposed. The relationship between the soil shear torque curve (shear torque-deformation curve) obtained from ring shear test and the thrust curve (soil thrust-slip ratio curve) of a tracked vehicle is analyzed and it is shown that there is a transformation law between these curves. A simplified analytical method for estimating the soil thrust exerted by a tracked vehicle is developed by using the above-mentioned transformation law. Soil thrust can be estimated by using the soil shear torque curve, shear ring and vehicle parameters. It is experimentally confirmed that the soil thrust can be easily estimated by using the proposed method.     

推力电磁轴承的电磁场分析

利用有限元法对推力电磁轴承的磁场分布进行了分析计算,并通过对某一实际电磁轴承的推力轴承磁场分布及漏磁的分析计算,得出了推力轴承和推力盘之间的气隙及推力轴承和转子之间的气隙之比的最佳设计值,所得结果可作为推力电磁轴承实际设计的准则     

Rotation of the thrust vector of a two-dimensional nozzle by means of displacing the critical surface

The method of thrust vector deflection by means of displacing the critical surface of a nozzle is numerically and experimentally investigated. The displacement is realized at the expense of extending rotatable walls, or deflectors, into the flow; in this case, one of the edges of the critical surface is displaced from the throat onto the deflector surface. Two nozzle configurations, with short and long deflectors, are studied. The thrust vector deflection angles and the nozzle thrust coefficients are determined in the thrust vector deflection regime. For the configuration with long deflectors the angle of rotation of the thrust vector amounts to 30° and is determined by the effect of jet ejection toward the opposite wall, similar with the Coanda effect.     

Static thrust recovery of PAR craft on solid surfaces

Power-Augmented-Ram Vehicles belong to a new class of ground-effect machines with hybrid support. Recovered static thrust and static lift on solid surfaces are important amphibious characteristics of this craft. Experimental data for the static thrust recovery and the transition to a hovering mode are obtained in the tests with a vehicle model on two types of ground surface and with variable engine thrust and flap trailing-edge gap. The uphill surface and increased mass of the model demonstrate reductions in thrust recovery. A comparison with a two-dimensional potential-flow theory is presented. The static thrust accumulation, identified in the pre-hovering regime of a model on solid surface, does not significantly benefit the low-speed forward motion.     

Evaluation of thrust measurement techniques for dielectric barrier discharge actuators

Despite its popularity in the recent literature, plasma actuators lack a consistent study to identify limitations, and remedy thereof, of various thrust measurement techniques. This paper focuses on comparing two different experimental techniques commonly used to measure the global, plasma-induced thrust. A force balance is used to make a direct measurement of the thrust produced, which is then compared with a control volume analysis on data obtained through particle image velocimetry. The local velocity measured by particle image velocimetry is also validated with a fine-tip pressure probe. For the direct thrust measurements, the effect of varying the actuator plate length upon which the induced flow acts is investigated. The results from these tests show that the length of the actuator plate is most influential at higher voltages with the measured thrust increasing as much as 20?% for a six times reduction in the length of the plate. For the indirect thrust measurement, the influence of the control volume size is analyzed. When the two methods are compared against each other, good agreement is found when the control volume size has a sufficient downstream extent. Also, the discharge length is optically measured using visible light emission. A linear correlation is found between the discharge length and the thrust measurements for the actuator configurations studied. Finally, the energy conversion efficiency curve for a representative actuator is also presented.     

涡轮膨胀机止推轴承－转子系统的振动分析

为了确保涡轮膨胀机止推轴承在受到瞬时冲击时不致发生损坏事故，研究了止推轴承－转子系统的轴向瞬态过程，计算了止推轴承的线性油膜刚度系数和阻尼系数，并对线性和非线性两种情况下的轴向瞬态响应作了分析与比较，为止推轴承；转子系统的可靠性评估提供了科学依据。     

柔性双尾鳍效率的测量和优化

建立了仿生拍动推进推力和效率的测量平台,通过电机的转动扭矩、转动角速度及推进力计算得到仿生推进系统的推进效率.对本课题组研制的组合仿生无人水下航行器中柔性双尾鳍模型进行了测量与分析,结果表明柔性尾鳍推进时小摆幅摆动运动效率要高于大摆幅运动;双尾鳍推进方式在小摆幅模式下无论在推进力还是在效率方面都要优于单尾鳍.最后根据模型实验数据,优化了双尾鳍推进的运动参数,并用于优化UUV性能.     

Investigation of the soil thrust interference effect for tracked unmanned ground vehicles (UGVs) using model track tests

The traction force of a tracked unmanned ground vehicle (UGV) depends on the soil thrust generated by the shearing action on the soil-track interface. In the development of soil thrust, because the continuous-track system consists of a number of single-track systems connected to each other, interference occurs between the adjacent single-track systems through the surrounding soil. Thus, the total soil thrust of the continuous-track system is not equal to the sum of the soil thrust of each single-track system, and the interference effect needs to be carefully considered. In this study, model track tests were conducted on model single-, double-, and triple-track systems according to relative density of soil and shape ratio (i.e., the length of the track plate to grouser depth). The test results indicated that the interference effect reduced soil thrust due to the overlapping shear zones between adjoining single-track systems. The loss of soil thrust increased as the relative density of the soil increased and the shape ratio decreased. Based on these findings, a soil thrust multiplier that can be utilized to assess the soil thrust of a continuous-track system was developed.     

Analysis of the aerodynamic interaction between two plunging plates in tandem at low Reynolds number for maximum propulsive efficiency

The thrust generated by two heaving plates in tandem is analyzed computationally by solving the Navier–Stokes equations for an incompressible and two-dimensional flow at low Reynolds numbers. We consider with detail two particular sets of configurations of interest in forward flight in a wide range of heaving amplitudes and frequencies: a plunging leading plate with the trailing plate at rest, and the two plates heaving with the same frequency and amplitude, but varying the phase difference. In almost all cases the thrust efficiency of the leading plate is augmented in relation to a single plate heaving with the same frequency and amplitude. In the first configuration with a trailing plate at rest, we characterize the range of nondimensional heaving frequencies and amplitudes of the leading plate for which the stationary trailing plate contributes positively to the global thrust. The maximum global thrust efficiency of this configuration, reached for an advance ratio slightly less than unity and a reduced frequency close to 5, is about the same as the maximum efficiency for an isolated plate, reached for slightly smaller frequencies. But for low frequencies the tandem configuration with the trailing plate at rest is more thrust efficient than the isolated plate. We also characterize the nondimensional frequency and amplitude regions for which the flow becomes chaotic. In the second configuration, the maximum of the total thrust efficiency is reached for a phase lag of 180° (counterstroking), particularly for an advance ratio unity and a reduced frequency 4.4. It is almost the same as the maximum thrust efficiency in the other configuration with the trailing plate at rest and that of a single plate. We discuss the flow structures and the aerodynamic interaction between plates responsible for the optimal thrust configuration in both cases.     

Thrust generation and wake structure of wiggling hydrofoil

Marine animals and micro-machines often use wiggling motion to generate thrust. The wiggling motion can be modeled by a progressive wave where its wavelength describes the flexibility of wiggling animals. In the present study, an immersed boundary method is used to simulate the flows around the wiggling hydrofoil NACA 65-010 at low Reynolds numbers. One can find from the numerical simulations that the thrust generation is largely determined by the wavelength. The thrust coefficients decrease with the increasing wavelength while the propulsive efficiency reaches a maximum at a certain wavelength due to the viscous effects. The thrust generation is associated with two different flow patterns in the wake： the well-known reversed Karman vortex streets and the vortex dipoles. Both are jet-type flows where the thrust coefficients associated with the reversed Karman vortex streets are larger than the ones associated with the vortex diploes.     

两串列扑翼的相位差对平均推力影响机理的实验研究

在一个低雷诺数的循环水洞中,实验研究了前后翅翼之间的相位差对两串列扑翼平均推力的影响.利用一个三分量的Kistler 压力传感器来测量扑翼的瞬时力;利用一个数字粒子测速仪系统(TSI DPIV) 来测量扑翼的前缘涡以及其周围的流场. 当相位差从0° 增加到360°,前翅的平均推力随着相位差正弦变化;前翅平均推力的增加是由于后翅的前缘涡和滞止区域增加了前翅的有效攻角. 后翅平均推力曲线有一个明显的V 字形低谷.低谷处较小的平均推力是由于前翅的脱落涡抑制了后翅前缘涡的形成并且减小了其有效攻角.当间距为0.5倍弦长相位差约为290°时,前后翅翼平均推力系数的合值能达到最大值0.667,明显大于两倍的单翼平均推力系数(2×0.255).      

提高高马赫数超燃冲压发动机推力的理论方法

斜爆轰发动机和激波诱导燃烧冲压发动机在高马赫数吸气式发动机中具有重要应用前景,但是斜爆轰发动机是否具有足够大的净推力,还是一个未知的问题,因此需要对高马赫数冲压发动机的推进性能以及提高推力的方法进行理论研究.本文主要分为3部分.第1部分理论研究了超燃冲压发动机中的爆燃波和爆轰波的传播特性.保证发动机稳定燃烧是提高推力的...     

推力轴承各耦合动特性系数对转子横向振动状态的贡献

系统地研究了推力轴承各耦合动特性系数对转子横向振动状态的贡献。计算结果表明，推力轴承对转子横向振动状态的影响主要由推力盘摆动而产生的耦合动特性系数所决定，而由平动所产生的耦合动特性系数对转子振动状态影响的贡献很小，可以忽略。     

Experimental study of extreme thrust on a tidal stream rotor due to turbulent flow and with opposing waves

Time-varying thrust has been measured on a rotor in shallow turbulent flow at laboratory scale. The onset flow has a turbulence intensity of 12% at mid depth and a longitudinal turbulence length scale of half the depth, about 5 times the vertical scale, typical of shallow flows. The rotor is designed to have thrust and power coefficient variations with tip speed ratio close to that of a full-scale turbine. Three extreme probability distributions give similar thrust exceedance values with the Type 1 Pareto in mid range which gives 1:100, 1:1000 and 1:10 000 exceedance thrust forces of 1.38, 1.5 and 1.59 times the mean value. With opposing waves superimposed the extreme thrust distribution has a very similar distribution to the turbulent flow only. Exceedance forces are predicted by superposition of a drag force with drag coefficient of 2.0 based on the wave particle velocity only and with an unchanged mean thrust coefficient of 0.89. These values are relevant for the design of support structures for marine turbines.     

Profiling the Supersonic Part of a Plug Nozzle with a Nonuniform Transonic Flow

The effect of transonic flow nonuniformity on the profiling of optimal plug nozzles is studied in the inviscid gas approximation. Sonic and supersonic regions providing maximum thrust for given nozzle dimensions and a given outer pressure are designed for given subsonic contours and calculated nonuniform transonic flows. As in the case of uniform flow on a cylindrical sonic surface, the initial regions of the designed contours satisfy the condition that in these regions the flow Mach number is unity or near-unity. In all the examples calculated, the optimal plug nozzles produce a greater thrust than the optimal axisymmetric and annular nozzles with a near-axial flow for the same lengths and the same gas flow rates through the nozzle. It is established that contouring without regard for transonic flow nonuniformity can result in considerable thrust losses. However, these losses are due only to a decrease in the flow rate, while the specific thrust may even increase slightly.     

Thrust of a contracting nozzle

A study is made of the influence of the nonuniformity of the parameters due to the two-dimensional nature of the flow on the specific thrust of a contracting nozzle. It is shown that for continuous flow of an ideal (inviscid and nonheat-conducting) gas the specific thrust in the supercritical regimes exceeds the value determined using the one-dimensional theory for the same stagnation parameters of the gas; in the subcritical regimes the specific thrust of the contracting nozzle is equal to the value found from the one—dimensional approximation.     

Influence of dimple geometry and micro-roughness orientation on performance of textured hybrid thrust pad bearing

The present study deals with numerical simulation of textured hybrid thrust pad bearing. Influence of providing micro-dimples of different cross-sectional shapes on the bearing surface has been theoretically investigated on the performance of thrust pad bearing. Reynolds equation has been solved using mass-conserving algorithm based on Jakobsson–Floberg–Olsson cavitation boundary conditions. A parametric study is carried out to optimize dimple shapes from the viewpoint of load carrying capacity of bearings. The textured bearing surface is noticed to be beneficial in reducing the frictional power losses. Providing half-section dimples (second half in the direction of runner rotation) towards the leading edge of thrust pad, enhance the load carrying capacity and fluid film stiffness coefficient of bearings. Micro-roughness in a textured surface having transverse orientation is seen to improve the dynamic characteristics of hybrid thrust pad bearings.