飞行器载GNSS接收机抗干扰试验布局设计方法

为了合理设计飞行器载GNSS接收机动态抗干扰试验布局,需要对目标航迹上的干扰信号辐射场分布特征和变化范围进行仿真。文中利用结合镜像原理和等效原理的角锥喇叭辐射场半解析计算方法,使得快速计算航迹上任一点的辐射场成为可能。在此基础上,结合抗干扰试验布局的一般性要求,对典型布局场景下的干扰信号辐射场分布特征进行了仿真和对比研究,给出了该类试验布局设计方法和规律,并提出验证了一种干扰瞄准偏离修正方法。

全数字飞行仿真平台的设计与实现

为便于对飞行器建模和控制等理论技术进行演示和验证,采用软件工程的概念设计并实现了一种通用的研究型可视化飞行仿真平台.首先,基于面向对象的思想设计了仿真平台的总体结构和各个主要功能模块,建立了飞行器运动/动力和飞行控制模块的数学模型,并为其设计了模式化的接口,使平台可适用于多飞行器多控制策略下的飞行仿真.为获得较高的仿真真实度,建立了风切变、紊流的飞行干扰模型.然后,在各模块设计的基础上,基于.Net框架和Direct3D绘图编程接口实现了飞行仿真平台.最后,在PID飞控规律下,通过跟踪矩形航迹进行仿真实验.结果表明,该平台具有良好的可操纵性和逼真度,实时输出的飞行参数较为准确、全面,符合预期.

Tom70 mediates activation of interferon regulatory factor 3 on mitochondria

Intracellular RNA viruses are sensed by receptors retinoic acid-inducible gene 1 （RIG-I）/melanoma differentiation-associated gene 5 （MDA5） that trigger the formation of MAVS signal complex on mitochondria. Consequently, this leads to the activation of TANK-binding kinase 1 （TBK1） and phosphorylation of interferon regulatory factor 3 （IRF3）, both of which constitutively associate with cytosolic chaperone Hsp90. It remains largely unknown how MAVS activates TBK1/IRF3. In this study, we identified translocases of outer membrane 70 （Tom70）, a mitochondrial import receptor, to interact with MAVS upon RNA virus infection. Ectopic expression or knockdown of Tom70 could enhance or impair IRF3-mediated gene expression, respectively. Mechanistically, the clamp domain （R192） of Tom70 interacts with the C-terminal motif （EEVD） of Hsp90, thus recruiting TBK1/IRF3 to mitochondria. Disruption of this interaction or mislocation of Tom70 sharply impairs activation of TBK1 and IRF3. Furthermore, host antiviral responses are significantly boosted or crippled in the presence or absence of Tom70. Collectively, our study characterizes Tom70 as a critical adaptor linking MAVS to TBK1/IRF3, revealing that mitochondrion is evolutionarily integrated with innate immunity.

Interference-Free Pilot Design and Channel Estimation Using ZCZ Sequences for MIMO-OFDM-Based C-V2X Communications

Cellular vehicle-to-everything(C-V2X) communications is regarded as a promising and feasible solution for 5G-enabled vehicular communications and networking. In this paper, we investigate the pilot design and channel estimation problem in MIMO-OFDM-based C-V2X systems with severe co-channel interference due to spectrum reusing among different V2X communication links. By using zero-correlation zone(ZCZ) sequences, we provide an interference-free pilot design scheme and a corresponding time-domain(TD) correlation-based channel estimation(TD-CCE) method. We employ the ZCZ sequences from the same family set to be designed as the TD pilot symbols and guarantee the pilot sequeneces for neighboring V2X communication links are code-division multiplexing(CDM). The co-channel pilot interference of the deisgned pilot symbols can be effectively eliminated by exploiting the provided TD-CCE method. Simulation results indicate that the accuracy of channel estimation can be effectively improved by the proposed scheme, whose performance is close to that of the non-interference situation.

Fast Secret Key Generation Based on Dynamic Private Pilot from Static Wireless Channels

In static or quasi-static wireless channel environments, secret key generation(SKG) based on wireless channels is vulnerable to active attacks due to the openness and invariance of public pilot, especially man-inthe-middle(MITM) attacks, where attacker acts as a transparent relay to manipulate channel measurements and derive the generated keys. In order to fight against this attack, a dynamic private pilot is designed, where both private pilot and secret key are derived from the characteristics of wireless channels and private to third party. In static or quasi-static environments, we use singular value decomposition techniques to reconstitute the wireless channels to improve the randomness of the wireless channels. Private pilot can encrypt and authenticate the wireless channels, which can make channel state information intercepted by MITM attacker reduced to zero and the SKG rate close to that without attacks. Results of analysis and simulation show the proposed SKG scheme can withdraw the MITM attacks.

Nonsingular Fast Terminal Sliding Mode Control Based on Nonlinear Disturbance Observer for a Quadrotor

Given external disturbances and system uncertainties,a nonsingular fast terminal sliding mode control(NFTSMC)method integrated a nonlinear disturbance observer(NDO)is put forward for quadrotor aircraft.First,a NDO is proposed to estimate the actual values of uncertainties and disturbances.Second,the NFTSM controller based on the reaching law is designed for the attitude subsystem(inner loop),and the control strategy can ensure Euler angles’fast convergence and stability of the attitude subsystem.Moreover,the NFTSMC strategy combined with backstepping is proposed for the position subsystem(outer loop),which can ensure subsystem tracking performance.Finally,comparative simulations show the trajectory tracking performance of the proposed method is superior to that of the traditional sliding mode control(SMC)and the SM integral backstepping control under uncertainties and disturbances.

卫星跟踪猎隼失联案例分析

猎隼(Falco cherrug)是迅速濒危中的物种。对近10年卫星跟踪的67只猎隼进行国籍、性别、信号时长、失联月份统计,分析其死亡原因、受威胁因素以及年返回率。就其中2016年来自俄罗斯和蒙古的10只猎隼进行更详细的死因分析,当发射器不再返回信息时,前往GPS最后位点,在一定区域内进行拉网式搜索,并分析周围的环境和动物痕迹,将找到的尸体进行解剖,查找死亡原因。结果显示,这67只猎隼中雌鸟有37只,占总数的55.2%,雄鸟有29只,另1只性别未知。其平均信号时长为(201±129.94)d(n=64),小于200 d的占60.9%,小于400 d的占92.2%。年返回率为31.4%;在秋季和初冬季(8～12月)失联的占67.2%。而2016年跟踪的10只猎隼中,获取4只失联猎隼的信息,1只在蒙古国被猎杀,1只死因不详,1只在中国因电击死亡,1只在中国因擦碰和饥饿死亡。卫星跟踪数据显示,猎隼的年返回率明显降低,表明猎隼的处境不容乐观,这引发了猛禽研究专家的担忧。

Analysis of residual gas disturbance on the inner satellite of Inner Formation Flying System

The Inner Formation Flying System （IFFS） consisting of an freely flying in the shield cavity can construct a pure gravity outer satellite and an inner satellite which is a sphere proof mass orbit to precisely detect the earth gravity field. The residual gas in the cavity is a significant disturbance source due to the temperature inhomogeneity and relative motion of the inner satellite. The expressions of the disturbance forces were derived based on the property of rarefied gas, including the radiometer effect and the damping force. According to the current design of IFFS, heat transfer analysis of the cavity and the inner satellite was carried out, and the surface temperature distribution of the cavity and the inner satellite was given. The relative motion of the inner satellite was obtained from the formation control simulation of IFFS. Then the residual gas disturbance was calculated. The disturbance acceleration acting on the inner satellite due to the radiometer effect was on the order of 10^-11 m s^-2 and the damping acceleration was on the order of 10^-15 m s^-2.