Shock protection of penetrator-based instrumentation via a sublimation approach

It is often necessary for space-borne instrumentation to cope with substantial levels of shock acceleration both in the initial launch phase, as well as during entry, descent and landing in the case of planetary exploration. Current plans for a new generation of penetrator-based space missions will subject the associated on-board instrumentation to far greater levels of shock, and ways must therefore be found to either ruggedize or else protect any sensitive components during the impact phase. In this paper, we present an innovative method of shock protection that is suited for use in a number of planetary environments, based upon the temporary encapsulation of said components within a waxy solid which may then be sublimated to return the instrument back to its normal operation. We have tested this method experimentally using micromachined silicon suspensions under applied shock loads of up to 15,000g, and found that these were able to survive without incurring damage. Furthermore, quality factor measurements undertaken on these suspensions indicate that their mechanical performance remains unaffected by the encapsulation and subsequent sublimation process.     

Acceleration of interplanetary pick-up ions and anomalous cosmic rays

It may not be doubted anymore that anomalous cosmic rays (ACRs) are produced in the heliosphere from interplanetary pick-up ions through their acceleration at the solar wind termination shock. However, there is no general agreement in the community of heliospheric researchers concerning the mechanism of injection of the pick-up ions into the shock acceleration. We discuss here three possible ways for pick-up ions to be involved into the acceleration process at the termination shock: (1) preacceleration of pick-up ions in the whole region from the Sun up to the termination shock by solar wind turbulences and interplanetary shock waves, (2) local preacceleration of pick-up ions in a vicinity of the termination shock by shock surfing, and (3) formation of high-velocity tails in pick-up ion spectra consisting of secondary pick-up ions which are produced in the supersonic solar wind due to ionization of energetic neutral atoms entering from the inner heliosheath.     

A first step towards proton flux forecasting

We present a preliminary version of a potential tool for real time proton flux prediction which provides proton flux profiles and cumulative fluence profiles at 0.5 and 2 MeV of solar energetic particle events, from their onset up to the arrival of the interplanetary shock at the spacecraft position (located at 1 or 0.4 AU). Based on the proton transportation model by Lario et al. [Lario, D., Sanahuja, B., Heras, A.M. Energetic particle events: efficiency of interplanetary shocks as 50 keV E < 100 MeV proton accelerators. Astrophys. J. 509, 415–434, 1998] and the magnetohydrodynamic shock propagation model of Wu et al. [Wu, S.T., Dryer, M., Han, S.M. Non-planar MHD model for solar flare-generated disturbances in the Heliospheric equatorial plane. Sol. Phys. 84, 395–418, 1983], we have generated a database containing “synthetic” profiles of the proton fluxes and cumulative fluences of 384 solar energetic particle events. We are currently validating the applicability of this code for space weather forecasting by comparing the resulting “synthetic” flux profiles with those of several real events.     

高焓激波风洞喷管流场非平衡特性研究

高焓激波风洞是开展高超声速流动研究的重要地面模拟设备,但其产生的高焓气流在喷管中的膨胀过程是一种典型的热化学非平衡流动,试验段特征参数通过直接实验测量难以完全确定。本文通过求解耦合双温度模型的轴对称Navier-Stokes方程,研究了高焓激波风洞中典型状态下气流的热化学非平衡流动特性,分析了焓值对非平衡特性的影响规律。结果表明,喷管出口自由流均匀区域达到出口截面直径的75%以上,能够为实验提供足够的空间;喷管出口自由流处于热化学非平衡状态,在喷管喉道后约1/5喷管长度处气流即已处于冻结流状态,组分浓度和振动温度随气流流动基本不变;焓值在8.4MJ/kg~19.5MJ/kg之间变化时,非平衡程度随着焓值的增加而增强,但是低焓值时非平衡程度的增强更加剧烈。     

Stationary flow fields prediction of variable physical domain based on proper orthogonal decomposition and kriging surrogate model

In this paper a new flow field prediction method which is independent of the governing equations, is developed to predict stationary flow fields of variable physical domain. Predicted flow fields come from linear superposition of selected basis modes generated by proper orthogonal decomposition(POD). Instead of traditional projection methods, kriging surrogate model is used to calculate the superposition coefficients through building approximate function relationships between profile geometry parameters of physical domain and these coefficients. In this context,the problem which troubles the traditional POD-projection method due to viscosity and compressibility has been avoided in the whole process. Moreover, there are no constraints for the inner product form, so two forms of simple ones are applied to improving computational efficiency and cope with variable physical domain problem. An iterative algorithm is developed to determine how many basis modes ranking front should be used in the prediction. Testing results prove the feasibility of this new method for subsonic flow field, but also prove that it is not proper for transonic flow field because of the poor predicted shock waves.     

二维喷管的初始流动

基于可压缩Navier-Stokes方程,采用大涡模拟方法与高精度混合WENO/TCD格式,对Ma=1.4的超声速平面射流初始流场进行了数值研究.数值结果清晰地描述了超声速平面射流初始流场的结构特征,包括主涡环与激波结构以及它们演变过程.因主涡环内存在涡导激波对,激波与涡相互作用加速射流剪切层失稳,使剪切层首次卷起形成小涡的位置出现在涡导激波对后,此与亚声速射流情况不同.小涡串卷起成后,相继与涡导激波对相互作用,使激波出现明显的变形并加速主涡环失稳.      

高超声速边界层转捩机理及应用的若干进展回顾

高超声速边界层转捩对飞行器的热传递、表面摩阻和流动分离等有重要影响,尤其是再入飞行器和吸气式巡航飞行器。然而,人们对边界层转捩机理中的很多问题认识还不清楚,或存在争议。本文从扰动波演化的角度回顾了高超声速边界层感受性、线性稳定性和非线性作用的国内若干研究进展,并以基于谐波共振的人工转捩技术为例示范了这些机理认识在转捩控制上的应用。扰动的产生和发展是认识边界层转捩机理的核心。通过研究扰动波来认识边界层转捩机理,开展应用创新研究对提升飞行器性能具有重要意义。     

Effect of blade tip winglet on the performance of a highly loaded transonic compressor rotor

The tip leakage flow has an important influence on the performance of transonic com-pressor. Blade tip winglet has been proved to be an effective method to control the tip leakage flow in compressor, while the physical mechanisms of blade tip winglet have been poorly understood. A numerical study for a highly loaded transonic compressor rotor has been conducted to understand the effect of varying the location of blade tip winglet on the performance of the rotor. Two kinds of tip winglet were designed and investigated. The effects of blade tip winglet on the compressor over-all performance, stability and tip flow structure were presented and discussed. It is found that the interaction of the tip winglet with the flow in the tip region is different when the winglet is located at suction-side or pressure-side of the blade tip. Results indicate that the suction-side winglet (SW) is ineffective to improve the performance of compressor rotor. In addition, a significant stall range extension equivalent to 33.74% with a very small penalty in efficiency can be obtained by the pressure-side winglet (PW). An attempt has been made to explain the fundamental mechanisms of blade tip winglet in detail.     

Experimental investigation of shock-buffet criteria on a pitching airfoil

An experimental investigation of the shock-buffet phenomenon subject to unsteady pitching supercritical airfoil around its quarter chord has been conducted in a transonic wind tunnel. The model was equipped with pressure taps connected to the fast response pressuretransducers. Measurements were conducted at different free-stream Mach number from 0.61 to0.76. The principle goal of this investigation was to experimentally discuss the shock-buffet criterion over a SC(2)-0410 supercritical pitching ...     

基于谐振舵面的跨声速抖振抑制探究

跨声速抖振引起的非定常脉动载荷会造成飞行器结构疲劳甚至引发飞行事故,所以跨声速抖振的控制研究逐渐成为航空领域的热点。采用基于Spalart-Allmaras(S-A)湍流模型的非定常雷诺平均方程开展了基于谐振舵面的跨声速抖振抑制研究。首先验证静止NACA0012翼型的抖振边界和频率特性,然后分别从舵偏平衡位置、舵偏幅值、频率以及相角等角度研究了谐振舵面的控制效果。舵偏平衡位置等效于减小了翼型的有效迎角;幅值和频率对抖振抑制效果影响较大,当舵面振荡频率与抖振频率接近时发生共振现象;相角对控制效果有一定影响,在270°相角附近,升力系数幅值减小了60%。在合适的舵偏幅值、频率以及相角组合下,谐振舵面有可能成为跨声速抖振的有效开环控制策略。