Fuel-optimal trajectories of aeroassisted orbital transfer withplane change

The fuel-optimal control problem arising in noncoplanar orbital transfer employing aeroassist technology is addressed. The mission involves the transfer from high Earth orbit to low Earth orbit with plane change. The complete maneuver consists of a deorbit impulse to inject a vehicle from a circular orbit to an elliptic orbit for atmospheric entry, a boost impulse at the exit from the atmosphere for the vehicle to attain a desired orbital altitude, and a reorbit impulse to circularize the path of the vehicle. In order to minimize the total fuel consumption, a performance index is chosen as the sum of the deorbit, boost, and reorbit impulses. The application of optimization principles leads to a nonlinear, two-point, boundary value problem, which is solved by a multiple shooting method     

A Study of Pilot Reaction Capability to Sound Stimulus

An experiment is described which was used to evaluate a typical pilot's ability to activate a switch in response to a sound stimulus. Regularly spaced voice countdown, irregular voice countdown, initiation of a tone, and termination of a tone were each used as the stimulus. The individual under test was given a task similar to that involved in maintaining accurate flight conditions to occupy his attention. The regular voice countdown is shown to be least accurate in defining the switching time, providing a mean delay of approximately -0.09 second (actually a stimulus anticipation) and a standard deviation of a bit more than 0.2 second. In each of the other cases, a mean delay of approximately 0.25 second and a standard deviation of approximately 0.09 second were obtained. This compares favorably with previous experimental results.     

Determination of a suitable set of loss models for centrifugal compressor performance prediction

Performance prediction in preliminary design stages of several turbomachinery components is a critical task in order to bring the design processes of these devices to a successful conclusion.In this paper,a review and analysis of the major loss mechanisms and loss models,used to determine the efficiency of a single stage centrifugal compressor,and a subsequent examination to determine an appropriate loss correlation set for estimating the isentropic efficiency in preliminary design stages of centrifugal compressors,were developed.Several semi-empirical correlations,commonly used to predict the efficiency of centrifugal compressors,were implemented in FORTRAN code and then were compared with experimental results in order to establish a loss correlation set to determine,with good approximation,the isentropic efficiency of single stage compressor.The aim of this study is to provide a suitable loss correlation set for determining the isentropic efficiency of a single stage centrifugal compressor,because,with a large amount of loss mechanisms and correlations available in the literature,it is difficult to ascertain how many and which correlations to employ for the correct prediction of the efficiency in the preliminary stage design of a centrifugal compressor.As a result of this study,a set of correlations composed by nine loss mechanisms for single stage centrifugal compressors,conformed by a rotor and a diffuser,are specified.     

风险投资过程代理风险控制模型研究

风险投资过程中,由于信息不对称所造成的代理风险是导致投资高风险的一个重要因素。因而,如何有效地控制风险投资过程中的代理风险,是确保投资成功的重要环节。对投资机构与风险企业之间关系进行了模型化,比较系统、全面地研究了投资过程中所面临的逆向选择和道德风险问题。通过模型化研究从理论上分析产生这两类代理风险的原因,并在此基础上探讨了如何规避和降低这类风险的方案和措施。     

滑流层对轴对称外压式进气道稳定性的影响

本文论述了在来流M1.72条件下,一个可变中心锥外压式进气道,强度为5～11％的六种滑流层在各种位置上进入唇口时对进气道稳定性的影响。 试验证明,强度低于10％的滑流层在唇口附近进入该轴对称进气道,并没有引起进气外罩内侧的附面层分离 强度直至11％的滑流层可以在进口处任意位置上进入该进气道,而不产生喘振。文献表明,强度仅为6～7％的滑流层就可以导致二元进气道的喘振,从而显示了轮对称进气道对滑流层进入所引起的喘振有较强的抵抗能力。     

Bayesian Quickest Signal Detection in a Discrete-Time Observation

This paper deals with the problem of quickest detection of a signal in discrete-time observations where the noise is not necessarily additive. By introducing a new cost function, penalizing the decision delay, in addition to penalizing wrong decisions as in the classical case, a global risk function is derived for use in a Bayesian framework. The minimization of the average risk leads to the optimum Bayesian decision regions, giving the structure of the optimum receiver. Some simplifications for elementary costs and some applications are investigated. The optimum receiver is shown to be a parallel bank of classical optimum filters, each one matched to a particular delay of the signal to be detected. Our approach is shown to apply to the detection of certain changes in a stochastic process.     

止裂孔尺寸对止裂效果影响的研究

当航空器结构在航线使用过程中出现疲劳裂纹损伤时,通常在裂纹尖端打止裂孔进行临时性修理。通过理论分析和计算及试验分析,研究了止裂孔尺寸对止裂效果的影响。结果表明,当航空器结构出现疲劳裂纹损伤时,采用5.57～7.14mm直径的止裂孔进行止裂修理,止裂效果较好;当止裂孔直径为6.35mm时,止裂效果最好。     

Optimum FFT-based frequency acquisition with application toCOSPAS-SARSAT

In the case of a single sinusoid or multiple well-separated sinusoids, a coarse estimator consisting of a windowed Fourier transform followed by a fine estimator which is an interpolator is a good approximation to an optimal frequency acquisition and measurement algorithm. The design tradeoffs are described. It is shown that for the fine-frequency estimator a good method is to fit a Gaussian function to the fast-Fourier-transform (FFT) peak and its two neighbors. This method achieves a frequency standard deviation and a bias in the order of only a few percent of a bin. In the case of short-time stationarity, for a moderate number of averages and for an adaptive threshold detector, only between 0.5 and 1 dB is lost when averaging is traded off for FFT length, in contrast to the asymptotic result of 1.5 dB. The COSPAS-SARSAT satellite system for emergency detection and localization is used to illustrate the concepts. The algorithm is analyzed theoretically, and good agreement is found with test results     

Dynamics and de-spin control of massive target by single tethered space tug

This paper investigates the dynamics and de-spin control of a massive target by a single tethered space tug in the post-capture phase. The dynamic model of the tethered system is derived and simplified to a dimensionless form. Further, a decoupled PD controller is proposed, and the local stability of the controller is analyzed by linearization technique. Parametric studies of the dynamics and de-spin control of a massive target are conducted to characterize the dynamic process of de-spin with the proposed control law. It is shown that the massive target can be de-span by a single and small space tug with limited thrust within finite time. The thrust tangent with the tether de-spins the target while the thrust normal to the tether prevents the tether from winding up the target. The tether length has a positive contribution to the de-spin of a target. The longer tether leads to a faster de-spin process.     

A scaling procedure for measuring thermal structural vibration generated by wall pressure fluctuation

This paper attempts to develop a scaling procedure to measure structural vibration caused simultaneously by wall pressure fluctuations and the thermal load of hypersonic flow by a wind tunnel test. However, simulating the effect of thermal load is difficult with a scaled model in a wind tunnel due to the nonlinear effect of thermal load on a structure. In this work, the temperature variation of a structure is proposed to indicate the nonlinear effect of the thermal load,which provides a means to simulate both the thermal load and wall pressure fluctuations of a hypersonic Turbulent Boundary Layer(TBL) in a wind tunnel test. To validate the scaling procedure,both numerical computations and measurements are performed in this work. Theoretical results show that the scaling procedure can also be adapted to the buckling temperature of a structure even though the scaling procedure is derived from a reference temperature below the critical temperature of the structure. For the measurement, wall pressure fluctuations and thermal environment are simulated by creating hypersonic flow in a wind tunnel. Some encouraging results demonstrate the effectiveness of the scaling procedure for assessing structural vibration generated by hypersonic flow. The scaling procedure developed in this study will provide theoretical support to develop a new measurement technology to evaluate vibration of aircraft due to hypersonic flow.     

机载电子系统设备的智能故障诊断系统设计

探讨了动态机载电子设备智能故障诊断系统建设的主要问题,设计了基于现代无线通信网络的智能故障预测诊断系统的总体结构及解决方案,对其中的关键技术进行了论述,尤其是无线通信协议、机载电子设备的故障预测模型及智能故障诊断专家系统等,为该系统后期研发奠定了基础.     

Controlled experiments from the space shuttle

A study has been carried out to identify the controlled space physics and plasma physics experiments that can be performed from the space shuttle on sortie missions of 7 to 30-day duration. An experiment facility of this type appears to be well-matched to the sortie missions capability, and a technically feasible laboratory can provide a base for an extensive and significant research program to be carried out during the 1980–1990 time period. The laboratory, known as PPEPL, consists of a 33-ft pallet of instruments connected to a 25-ft pressurized control module. Two deployable 50-m booms, two subsatellites, a high power transmitter, a multipurpose high-power accelerator array, a set of deployable canisters for releases, and a gimbaled platform for pointing instruments are the primary systems mounted on the pallet.     

Predicting the visibility of LEO satellites

We present a simple algorithm to determine the visibility-time function of a circular low Earth orbit (LEO) satellite at a terminal on the Earth's surface. The simplicity of the algorithm is based on approximating the ground trace of the satellite (which is not a great circle due to Earth's rotation) during a time interval of the order of in-view period, by a great-circle are. This enables us to use spherical geometry to compute the location and time epoch of the observation of the closest approach of the satellite's ground trace to the terminal. This is also the epoch of the observation of the maximum elevation angle from the terminal to the satellite. Applying a result derived relating the maximum elevation angle to the in-view period, we obtain the visibility-time function of the satellite at the terminal. Numerical results illustrate the accuracy of the algorithm for a wide range of LEO orbit altitudes     

Streamwise vortex generation by the rod

The technology development related to aerodynamics is leading to ever increasing loads of wings, airfoils and turbine and compressor blades. The increase in aerodynamic forces is often leading to flow separation and depreciation of the aerodynamic performance of flying objects or propulsion systems. Flow control methods are required to avoid these negative effects. In the recent two decades the flow control by means of air-jet vortex generators has been also intensively investigated. In this method a streamwise vortex is introduced by an oblique jet. The necessity to supply air by a pipe system may be considered a disadvantage. In order to eliminate this feature, it has been proposed to put out a rod instead of a jet. It has been shown that the application of a rod can introduce the same effect as a jet, as long as the streamwise vortex generation is concerned and appropriate dimensions are used. The present paper focuses on the influence of rod vortex generators on a flow pattern downstream. The results presented here concern experimental and numerical investigations and provide guidelines for the design of a new flow control method dedicated mainly to external flows.     

Constant Voltage Digital Control of an AC Motor Positioning Servo

A theoretical approach is presented to digitally manipulating the drive frequency of an ac induction motor so as to allow the motor to be used in a closed loop positioning servo. Additionally, the basic power source can be a simple dc power supply such as a battery pack. A hardware demonstration of the loop is discussed which has achieved a convergence accuracy of a 0.3 mrad to a step input.     

A pilot-centered autoflight system concept

Ease of use has become a primary concern in avionics recently. Pilot training time represents a significant cost to aircraft operators, and the importance of human factors considerations in safety has been highlighted by the FAA, who notes that human error is a cause in roughly 70% of aircraft accidents. These concerns have led to a new focus on human-centered design, which seeks to define system functionality based on the user's perspective rather than that of the designer. We have used the principles of user-centered design to develop a new autoflight system concept that integrates the autopilot and flight management system functions into a single user interface that most pilots can learn to use within about fifteen minutes. This is in contrast to the weeks required to learn a typical flight management system     

Haptic based teleoperation with master-slave motion mapping and haptic rendering for space exploration

This paper presents a new solution to haptic based teleoperation to control a large-sized slave robot for space exploration, which includes two specially designed haptic joysticks, a hybrid master-slave motion mapping method, and a haptic feedback model rendering the operating resistance and the interactive feedback on the slave side. Two devices using the 3 R and DELTA mechanisms respectively are developed to be manipulated to control the position and orientation of a large-sized slave robot by using both of a user's two hands respectively. The hybrid motion mapping method combines rate control and variable scaled position mapping to realize accurate and efficient master-slave control. Haptic feedback for these two mapping modes is designed with emphasis on ergonomics to improve the immersion of haptic based teleoperation. A stiffness estimation method is used to calculate the contact stiffness on the slave side and play the contact force rendered by using a traditional spring-damping model to a user on the master side stably. Experiments by using virtual environments to simulate the slave side are conducted to validate the effectiveness and efficiency of the proposed solution.     

Detection of chi-square fluctuating targets in arbitrary clutter

In a recent paper, general expressions were derived for the density and cumulative probability functions of the amplitude of a linear matched-filter output given a nonfluctuating target in a clutter-limited environment. These expressions were based on the clutter amplitude density function. The results are extended to calculate the cumulative probability function of the output of a linear matched filter used to detect a chi-square fluctuating target in a clutter-limited environment. The resulting method is applied to a common radar clutter model, and experimental sonar data.     

MMAE-Based Control with Space-Time Point Process Observations

A multiple model adaptive estimator (MMAE) has been formulated to estimate the state of a dynamic system modeled by a linear stochastic differential equation, from which measurements, described as a noise-corrupted space-time point process functionally related to that state, are extracted. Assumed certainty equivalence is used to combine such an estimator with the LQ full-state feedback controller to synthesize a practical, implementable controller. Performance of the estimator and resultant controller characteristics are investigated via simulation as a function of approximation method used to limit the full-scale estimator to finite dimensionality and also as a function of important parameters defining the dynamics and observation processes.