红外辐射测量系统内部杂散辐射建模与仿真

杂散辐射是影响光学系统性能的重要因素,对于红外光学系统,除了外部杂散辐射,还须考虑系统自身结构产生的内部杂散辐射。为提高红外辐射计内部杂散辐射分析的精度,建立了 1种基于复合蒙特卡洛法的内部杂散辐射数学模型。首先,将红外辐射计的内部杂散辐射源根据位置分为 2部分:遮光罩入瞳处的热辐射和辐射计内部光学元件、机械部分所发出的热辐射。对于遮光罩入瞳处和辐射计内部光机元件发出的杂散辐射,分别采用正向蒙特卡洛法和反向蒙特卡洛法进行追踪,得到探测器接收面入瞳处的杂散辐射辐照度分布,进而分析不同位置的发射源对接收面入瞳处的杂散辐射贡献。最后,与直接模拟仿真结果进行对比。实验结果表明,在追迹光线数相等的情况下,该方法的精度更高。仿真结果体现了红外辐射计各部分杂散辐射对探测器入瞳面接收到的杂散辐射造成的影响,对后期开展内部杂散辐射抑制提供了方向。     

基于输入电流连续型开关升压变换器的永磁同步电机预测电流控制方法的研究

针对传统永磁同步电机(PMSM)驱动系统存在的问题,应用一种连续型开关升压逆变器,通过应用预测控制方法提高PMSM控制性能。拓扑电路在逆变电路和输入直流电源之间加入一个开关升压电路,以达到提高系统电压增益和消除死区的目的,同时可使系统具有更高的可靠性。此外,采用预测电流控制(PCC)方法对PMSM进行控制,与传统的矢量控制技术相比,PCC具有更快的动态响应,并减少了电流脉动。最终,通过试验验证了基于开关升压变换器的PMSM PCC的可行性。     

激光参数对光船性能影响分析

采用三温度11组元热化学非平衡空气模型计算了激光能量在等离子体中的沉积过程,并在激光脉冲作用结束8 μs后采用平衡空气模型,完成激光推进光船工作过程的数值模拟,研究了不同入射激光能量和脉冲宽度对光船推进性能的影响。结果表明:当脉冲宽度相同时,入射激光能量越大,所得冲量耦合系数越大;当入射激光脉冲能量相同时,脉冲宽度越小,所得冲量耦合系数越大。将计算所得冲量耦合系数与Schall实验所得结果进行比较,结果非常吻合。     

Limitations of radiometer performance in spherically invariantnoise

The radiometer is a common method for detection of unknown signals in noise. Most analyses of radiometer performance are based on assumptions of stationary Gaussian noise with known marginal statistics. In this note, we use a spherically invariant noise model to derive simple expressions for radiometer performance degradation in noise variance uncertainty. Numerical examples are provided to show that channel uncertainty imposes a substantial penalty in detection performance     

基于微波辐射测量的电波折射修正技术

针对电波折射修正精度直接影响无线电系统的探测和定位精度这一问题,提出了利用微波辐射计反演大气折射率剖面进行电波折射修正的解决方法,并引入RBF（Radial Basis Function,径向基）神经网络算法反演大气折射率.在青岛市气象局架设MP-3000A型多通道微波辐射计,开展了长达1个月的与探空数据的联合观测比对实验,对输出的大气折射率剖面进行了详细的分析.实验结果表明：RBF神经网络算法与MP-3000A自带的神经网络算法相比,反演大气折射率剖面的精度提高了30％以上,同时,电波折射修正的精度也得以提高.因此,利用微波辐射计反演大气折射率剖面进行电波折射修正方法可行.     

Observations of Irradiance Variations

Since November 1978 a complete set of total solar irradiance (TSI) measurements from space is available, yielding a time series of 21 years. From measurements made by different space radiometers (HF on NIMBUS-7, ACRIM I on SMM, ACRIM II on UARS and VIRGO on SOHO) a composite record of TSI can be compiled. The corrections which are needed for each radiometer, mainly to compensate for degradation, but also for operational influences are described. ACRIM I (1980–1989) and ACRIM II (1992–1995) are taken as reference because their degradation was monitored by inflight comparisons with spare radiometers; since 1996 VIRGO is used as reference. The scale of ACRIM II is adjusted to ACRIM I by comparison with NIMBUS-7 and ERBE. The reliability of this adjustment depends strongly on the stability of the HF and ERBE radiometer during the period of the gap between the ACRIMs which is discussed in detail together with an assessment of the overall precision of the composite.     

Absolute Radiometer for the Flow Field of a Hypervelocity Projectile

As part of a hypervelocity instrumentation development program, it was desirable to include a radiometer system for measuring absolute radiation from projectile flow fields. A system employing a photomultiplier tube was designed, and laboratory and range experiments were conducted to investigate its performance characteristics. The laboratory experiments show that the linearity, saturation, and noise characteristics are suitable for this measurement; the system bandwidth is adequate to allow low frequency calibrations to be applied to high frequency measurements; and a derived expression for radiometer sensitivity variation as a function of photomultiplier supply voltage is reasonably correct. The results of the range experiments imply that the system response is sufficient to reproduce accurately input pulses as narrow as one microsecond and that a particular analytical technique for calculating the form of the radiative input to the radiometer from the projectile stagnation region is valid. Principles involved in the design of photomultiplier radiometer circuits of this type are discussed in detail.     

A Microwave Feedback Radiometer

Two versions of a microwave feedback radiometer have been built and tested. One used an electromechanical feedback system; the other, an all-electronic system. The response of the servo loops proved to be fast enough and linear enough for almost any radiometer application. The rms noise fluctuation was the same as that of a Dicke radiometer. Stability was excellent even under adverse environmental conditions.     

Radio Interferometry of Random Terrestrial Backgrounds

When relative motion exists between the antenna of a microwave radiometer and a random background, the variance of the radiometer output can, in many cases, be primarily determined by the spatial variance of the background. The result is a decrease in signal-to-noise ratio for small target detection. In this paper an interferometer is examined as a potential means of suppressing this background variance until the limiting variance imposed by the receiver is more nearly realized. A bivariate normal distribution in conjunction with three different correlation functions is assumed for the background apparent temperature field. The elements of the interferometer are assumed to possess a very narrow "pencil" power pattern. With relative motion between antenna and background, the audio power density spectrum at the output of the interferometer is exanmned. The background variance suppression achieved by an interferometer is shown to be a function of element spacing, wavelength, correlation distance for the background, range to the background, and form of the correlation function of the background. The result is that a radiometer may be designed which is receiver-limited rather than background-limited.     

Radar: The Cassini Titan Radar Mapper

The Cassini RADAR instrument is a multimode 13.8 GHz multiple-beam sensor that can operate as a synthetic-aperture radar (SAR) imager, altimeter, scatterometer, and radiometer. The principal objective of the RADAR is to map the surface of Titan. This will be done in the imaging, scatterometer, and radiometer modes. The RADAR altimeter data will provide information on relative elevations in selected areas. Surfaces of the Saturn’s icy satellites will be explored utilizing the RADAR radiometer and scatterometer modes. Saturn’s atmosphere and rings will be probed in the radiometer mode only. The instrument is a joint development by JPL/NASA and ASI. The RADAR design features significant autonomy and data compression capabilities. It is expected that the instrument will detect surfaces with backscatter coefficient as low as −40 dB.RADAR Team LeaderThis revised version was published online in July 2005 with a corrected cover date.     

Scanning Spaceborne Synthetic Aperture Radar with Integrated Radiometer

Spaceborne synthetic aperture radar systems are severely constrained to a narrow swath by ambiguity limitations. Here a vertically scanned-beam synthetic aperture system (SCANSAR) is proposed as a solution to this problem. The potential length of synthetic aperture must be shared between beam positions, so the along-track resolution is poorer; a direct tradeoff exists between resolution and swath width. The length of the real aperture is independently traded against the number of scanning positions. Design curves and equations are presented for spaceborne SCANSARs for altitudes between 400 and 1400 km and inner angles of incidence between 20° and 40°. When the real antenna is approximately square, it may also be used for a microwave radiometer. The combined radiometer and synthetic-aperture (RADISAR) should be useful for those applications where the poorer resolution of the radiometer is useful for some purposes, but the finer resolution of the radar is needed for others.     

Experimental Evaluation of Passive Microwave Velocity/Altitude Sensing

Experiments were conducted to determine the feasibility of using a passive microwave sensor of velocity/altitude ratio (V/H) as the basis for an aircraft navigation system. This sensor, combined with a radar altimeter, yields the velocity information needed for navigation. Airborne measurements were made with a two-beam X-band radiometer in a C-47 test aircraft. Radiometer signals and auxiliary information were recorded on magnetic tape. Ground-based data processing provided a comparison of radiometer-derived V/H measurements with those derived from independent sensors. Good results (fluctuating errors comparable to experimental uncertainties) were obtained over green farmland, urban areas, rice paddies, and certain desert areas; marginal results were obtained over other deserts and winter farmland. It was concluded that a microwave V/H sensor is feasible as the basis for a navigation system at low altitude over favorable terrains.     

面向风险均衡的AFDX虚拟链路路径寻优算法

为确保综合模块化航空电子系统的安全性需求能够在全双工交换式以太网中得到一致性保证,提出了一种面向风险均衡的路径规化（RBPP）算法,以满足各航电功能间的安全隔离要求,同时分散风险,避免局部物理链路的风险集中,提高系统安全性。以民机失效状态类别划分为基础,建立了航电功能、分区、端系统、虚拟链路（VL）风险模型;RBPP以均衡各物理链路风险为目标,同时综合考虑网络实时性、链路负载能力等因素,采用粒子群算法进行优化目标求解。利用仿真优化方法对RBPP算法进行了实现,在典型工业航空电子全双工交换式以太网（AFDX）网络架构及A380AFDX网络架构下进行仿真分析,结果显示多播VL的简化处理的会使网络风险增加;在1 000条VL配置下与负载均衡（LB）算法和最短路径（SP）算法进行了分析对比,结果显示RBPP算法在满足各航电功能间的隔离需求的同时,链路风险均衡能力在两种网络拓扑下分别比负载均衡算法提高了10.7%和23.4%,比最短路径算法分别提高了35.4%和47.9%。     

Potential starter/generator technology for future aerospaceapplication

This paper presents a search and comparative review of the literature available on variable speed constant frequency (VSCF) technologies. In particular, most of the progress made in the past ten years, using power electronics and electric machines for VSCF systems is reported. Two VSCF systems, based on induction and switched reluctance machine technologies, are presented. The research on the singly- and doubly-fed induction machines has focused on VSCF for wind power generation; whereas, that on switched reluctance machines has been directly studied as a VSCF technology in aircraft system. Results obtained so far favor the switched reluctance machine over the induction machine. Based on the foregoing comparative review, it is recommended that the induction machine be fully investigated as a VSCF drive in aircraft system. The findings should then be compared with the counterpart SRM system. Issues of comparison may include fault tolerance and redundancy, power density, torque requirements, overload ratings, temperature range and cooling, efficiency and stability over expected operating speed range     

Potential starter/generator technologies for future aerospaceapplications

This paper presents a search and comparative review of the literature available on variable speed constant frequency (VSCF) technologies. In particular, most of the progress made in the past ten years, using power electronics and electric machines for VSCF systems, is reported. Two VSCF systems, based on induction and switched reluctance machine technologies are presented. The research on the singly- and doubly-fed induction machines has focused on VSCF for wind power generation, whereas that on switched reluctance machines has been directly studied as a VSCF technology in aircraft systems. Results obtained so far favor the switched reluctance machine over the induction machine. Based on the foregoing comparative review, it is recommended that the induction machine be fully investigated as a VSCF drive for aircraft systems. The findings should then be compared with the counterpart SRM system. Issues of comparison may include fault tolerance and redundancy, power density, torque requirements, overload ratings, temperature range and cooling, efficiency and stability over expected operating speed range     

Cyclic code shift keying: a low probability of intercept communication technique

A low probability of intercept (LPI), or low probability of detection (LPD) communication technique known as cyclic code shift keying (CCSK) is described. We discuss the basic concepts of CCSK and describe a system based on the use of random or pseudorandom codes for biphase modulation. We use simulation to show that the bit error rate (BER) for CCSK can be closely estimated by using existing equations that apply to M-ary orthogonal signaling (MOS). Also, we show that significantly fewer computations are required for CCSK than for MOS when the number of bits per symbol is the same. We show that using biphase modulation results in waveforms that have a large time-bandwidth product and very low input signal-to-noise ratio (SNR) and thus inherently have an LPI by a radiometer. We evaluate detection by a radiometer and show that LPI can be achieved by using codes of lengths greater than about 2/sup 12/ (i.e., by transmitting more than about 12 bits per symbol). Results illustrate the effect that the CCSK symbol length and error probability, and the radiometer integration time and probability of false alarm (PFA), have on detection by a radiometer. We describe a variation of CCSK called truncated CCSK (TCCSK). In this system, the code of length 2/sup k/ is cyclically shifted, then truncated and transmitted. Although shortened, the truncated code still represents k bits of information, thus leading to an increased data rate. We evaluate radiometer detection of TCCSK and it is shown that the probability of detection is increased compared with the detection of CCSK.     

Frequency-hopping signal detection using partial band coverage

The performance of a channelized radiometer in detecting a frequency-hopping signal is analyzed for a variable number of parallel radiometers not necessarily covering the entire hopping band. The full band may not be covered because of an attempt to avoid interfering signals, limited radiometer resources, lack of knowledge of the band frequency location, or combinations of these factors. The analysis provides for calculation of the value of the signal-to-noise ratio (SNR) required to achieve a given probability of detection for a specified false-alarm rate, assuming an observation interval equivalent to N hops using either a fixed or a moving observation window. The dependence of the probability of detection on a misalignment of the detector observation intervals with the hop transitions is also analyzed. Numerical results are presented and discussed. Applied to a typical slow-hopping VHF radio, the results imply that a 150-hop transmission can be detected by a channelized radiometer covering half the hopping band when the SNR is about 2 dB     

变体无人机动力学模型及切换控制研究

针对能够在飞行过程中进行结构变形的变体无人机,考虑由变形引起的气动力与力矩,惯性力与力矩的非线性变化,建立其在质点系假设条件下的多体动力学模型。根据切换系统理论,将变体无人机视为一类线性切换系统,选择设计点,采用极点配置方法针对各设计点处的线性子系统设计控制器,再制定以变形量为决策变量的控制切换方案,构成切换控制系统。通过建立公共Lyapunov函数,推导了能够保证闭环切换系统在结构变形过程中一致有界的充分条件。以变体无人机Fire-Bee为例,验证了方案的有效性,仿真结果表明闭环系统无论在固定结构下还是变形过程中都具有良好的动态特性。     

铝合金薄板中裂纹的电磁热效应局部跨越止裂

 讨论了电磁热裂纹止裂时脉冲放电瞬间的电流、温度和热应力的耦合关系。通过自制的 ZL-1型强脉冲放电止裂装置进行了模拟实验研究;理论分析中采用了复变函数的研究方法给出了跨越止裂后裂纹尖端附近的温度值和热应力值;通过热 -电耦合和热 -机械耦合 2个过程对脉冲放电瞬间的电流 -温度 -热应力的演变进行了数值模拟,数值模拟的结果与理论分析和实验研究有较好的吻合。三方面的研究结果均表明 :通过电磁热效应局部跨越止裂可以使铝合金薄板中裂纹在裂纹尖端处很小的范围内熔化形成微小焊口,减小了裂纹尖端的应力集中,并在裂尖处形成压应力区,从而遏制了裂纹的扩展。该方法可应用于飞机机翼疲劳裂纹的止裂中。     

Effects of yaw-roll coupling ratio on the lateral-directional departure prediction and restraint

The experimental data obtained from yaw-roll coupled wind tunnel tests are used for lateral-directional departure prediction, by linearizing the_b model to extract nominal dynamic derivatives at each coupling ratio.The prediction results are compared with those of the existing engineering methods which are based on the conventional aerodynamic derivatives.The comparison shows that the yaw-roll coupling ratio has a great influence on the departure susceptibility.The departure resistance will loss in partial region of the coupling ratio when the angle of attack is higher than a critical value.According to the stable and unstable regions of coupling ratio, a two-segment stability augmentation system with two different feedback gain matrices is obtained by pole-placement method.The two-segment stability augmentation system is used in the simulations of straight and level flight, steady turn, spin recovery and Herbst maneuver.The simulation results are also compared with the applications of a fixed-gain stability augmentation system designed by the conventional aerodynamic derivatives.When the yaw-roll coupling effects are fully considered, the two-segment stability augmentation system is more effective for departure restraint and can provide a better flying quality with less control energy.