航空发动机虚拟自学习控制方法研究

随着人工智能技术的发展，智能航空发动机逐渐成为当今航空领域研究的热点。传统的航空发动机控制对发动机模型的依赖性过强，而基于发动机气热动力学公式的机理建模会引入较大的建模误差，给控制器设计带来困难。对此，提出一种基于强化学习的航空发动机控制虚拟自学习方法，首先利用航空发动机的试验数据通过LSTM 神经网络建立虚拟学习环境，然后采用深度强化学习TD3 算法，在虚拟环境中训练智能控制器，最后采用JT9D 发动机模型验证智能控制器的性能。结果表明：相比于传统PID 控制，智能控制器产生的超调量更小，调节时间更短。     

氢化物—原子吸收光谱法测定人发中硒的研究

介绍用ＷＨＧ—１０２Ａ型流动注入氢化物发生器与ＷＦＸ—１Ｅ２型原子吸收分光光度计配合，测定人发中硒（Ｓｅ）。硒的吸收信号为平台吸收曲线，比用吸收峰所获得的数据更稳定可靠     

力限振动试验技术理论基础研究

为了深入理解双控方程,由运载火箭有限元模型的多自由度子结构方法,导出缩聚在星/箭连接界面处的全箭动力学方程,定义相应参数后,导出星/箭耦合中的双控方程,给出界面加速度、有源机械系统的自由加速度、界面力、紧固力、源阻抗和负载阻抗表达式,从而加深了对星/箭耦合双控方程的理解,进而促进力限试验技术研究.同时,从多自由度模型简...     

A100钢表面粗糙度与HVOF碳化钨涂层结合强度

采用超音速火焰喷涂方法在AerMet100钢(A100钢)基体上制备了WC10Co4Cr涂层,研究了不同喷砂条件对AerMet100钢表面粗糙度变化及对涂层与基体结合强度的影响.之后将涂层使用化学方法退除,观察涂层制备对AerMet100钢基体表面状态的影响,分析了粗糙度与涂层结合强度之间的关系.结果表明:AerMet100钢基体不同吹砂工艺产生的表面粗糙度 S_a=0.994~4.983 μm时,超音速火焰喷涂WC10Co4Cr涂层的结合强度均不低于72 MPa.喷涂涂层过程对基体表面状态没有较大影响:基体粗糙度 S_a<2 μm时,喷涂后,基体表面的粗糙度略有降低;基体粗糙度 S_a>3 μm时,喷涂后,基体粗糙度略有升高.超音速火焰喷涂的碳化钨钴涂层与AerMet100钢基体的结合同时存在物理与机械力结合,以前者为主要结合力.     

Numerical Study of Parachute-Payload Land Site Distribution with Randomize Wind Gust Model

A parachute-payload model with randomize wind gust is developed to study the landing accuracy of the parachute decelerator system,which can be exactly described by the landing site distribution.The research focuses on the steady descent phase of the parachute descent process,so the parachute and the payload suspension formulation during the phase are mainly discussed.In addition,since the wind effects have a significant impact on the land site distribution of the passive decelerator system and it is difficult to obtain the exact wind profile in practice,major features of parachute-payload system are studied via the randomized wind gust formulation.As the randomized wind gust formulation is adopted,the wind effect can be considered without the exact wind gust profile and the parachute aerodynamic simulation can be fulfilled with uncertainties.Finally,the model is validated and discussed,and the parachute land site distributions with different wind randomize profiles are presented for comparison.The results show that when parachute is less stable,the land site tends to have a larger variance.     

Carrier phase prediction method for GNSS precise positioning in challenging environment

Since the signals of global navigation satellite system (GNSS) are blocked frequently in challenging environments, the discontinuous carrier phases seriously affect the application of GNSS precise positioning. To improve the carrier phase continuity, this paper proposes a carrier phase prediction method based on carrier open-loop tracking. In the open-loop tracking mode, the carrier numerically controlled oscillator (NCO) is controlled by the predicted Doppler, but not by the loop filter output. To improve the phase prediction effective time, accurate receiver clock drift estimation is studied in the prediction method. The phase prediction performance is tested on GNSS software receiver. In the phase prediction effective time tests, open-loop processes were set for the tested channel. The test results show that, when some satellite signals are blocked in 15?s, the probability of carrier phase error less than quarter cycles is more than 94%. In the real time kinematic (RTK) positioning tests, some satellite signals are blocked in 10–15?s repeatedly. The test results show that, the carrier phase continuity is basically not affected by the signal interruption, and the RTK can almost keep continuous centimeter-level positioning accuracy without re-fixing the integer ambiguity.     

A drilling tool design and in situ identification of planetary regolith mechanical parameters

The physical and mechanical properties as well as the heat flux of regolith are critical evidence in the study of planetary origin and evolution. Moreover, the mechanical properties of planetary regolith have great value for guiding future human planetary activities. For planetary subsurface exploration, an inchworm boring robot (IBR) has been proposed to penetrate the regolith, and the mechanical properties of the regolith are expected to be simultaneously investigated during the penetration process using the drilling tool on the IBR. This paper provides a preliminary study of an in situ method for measuring planetary regolith mechanical parameters using a drilling tool on a test bed. A conical-screw drilling tool was designed, and its drilling load characteristics were experimentally analyzed. Based on the drilling tool-regolith interaction model, two identification methods for determining the planetary regolith bearing and shearing parameters are proposed. The bearing and shearing parameters of lunar regolith simulant were successfully determined according to the pressure-sinkage tests and shear tests conducted on the test bed. The effects of the operating parameters on the identification results were also analyzed. The results indicate a feasible scheme for future planetary subsurface exploration.     

Effects of in-track maneuver on Sun illumination conditions of near-circular low Earth orbits

By developing approximate analytical models considering the J₂ perturbation, the effects of an in-track maneuver on the orbital Sun illumination conditions of near-circular low Earth orbits are analyzed. First, two approximate models for the variations in orbital sunshine angles are developed, one for variations at a given time and the other for variations at a given argument of latitude. Next, two approximate models for variations in orbital arc in Earth shadow are developed, one considers the small eccentricity and the other uses the zero eccentricity. Finally, the developed approximate models are applied to analyzing the Sun illumination conditions of a typical in-track maneuver mission on a near-circular low Earth orbit. From the results obtained, three major conclusions can be drawn. First, the variations in orbital sunshine angles at a given time may reach tens of degrees when the drifting time reaches hundreds of orbital periods, and the approximate model for that situation cannot effectively approach the numerical results. Second, the variations in orbital sunshine angles for any given argument of latitude are only a couple of degrees even when the drifting time reaches 500 orbital periods, and the approximation model developed can effectively approach the numerical results. Third, for variations in orbital arc in Earth shadow, the approximate model considering the small eccentricity has simple expressions and can effectively approach the numerical results; in contrast, the approximate model using the zero eccentricity has relatively worse precision.