摘要：【中文】本发明公开了一种大位阻烷基取代亚膦酸二酯的制备方法，本发明使用三氟甲磺酸三甲基硅酯为催化剂，实现大位阻醇类与亚磷酸三酯的直接反应制备已知方法很难合成的大位阻烷基取代亚膦酸二酯类化合物的新方法。因此，本方法可以说是对阿尔布佐夫方法合成大位阻烷基取代亚膦酸二酯类化合物的突破，由于本方法还适用于一般的伯醇原料，因此是一种具有高普适性的改进阿尔布佐夫方法。具体地，本方法使用稳定低毒的大位阻醇类为原料，反应条件简单、易于操作、无需溶剂，催化剂不含过渡金属，产物无过渡金属残留隐患，副产物为小分子的醇类如乙醇，几乎无毒性，因此是一种大位阻烷基取代亚膦酸二酯的绿色合成方法，具有很好研究价值和合成应用前景。 【EN】The invention discloses a preparation method of a large steric hindrance alkyl substituted phosphonite diester, which uses trimethyl silane trifluoromethanesulfonate as a catalyst to realize a new method for preparing a large steric hindrance alkyl substituted phosphonite diester compound which is difficult to synthesize by the known method through direct reaction of large steric hindrance alcohols and phosphite triesters. Therefore, the method is a breakthrough for synthesizing the alkyl substituted diphosphonite diester compound with large steric hindrance by the Albuzov method, and is an improved Albuzov method with high universality because the method is also suitable for general primary alcohol raw materials. In particular, the method uses stable and low-toxicity alcohols with large steric hindrance as raw materials, has simple reaction conditions, easy operation and no need of solvents, the catalyst does not contain transition metals, the product has no hidden danger of residual transition metals, and the byproducts are alcohols with small molecules such as ethanol and have no toxicity, so the method is a green synthesis method of alkyl substituted phosphonite with large steric hindrance, and has good research value and synthesis application prospect.

摘要：【中文】本发明公开了一种通电线圈辅助膜分离的机载制氮装置及其应用方法，属于航空系统技术领域，能够实现富氮气体的高浓度连续输出，具有维护简单，可靠性好，分离效率高的优点。本发明将通电线圈磁致分离与传统的膜分离技术相结合，在经典中空纤维膜装置外壳加上缠绕的线圈，缠绕方式为沿着进气方向轴向不断减少线圈圈数，在通电之后，中空纤维膜的空气在通电线圈产生的磁场作用下进行了预分离，此时，经过磁场不断预分离的空气，在通过中空纤维膜内部时，由于氧氮的磁化率不同，氧气和氮气在通电螺线管中进行了预分离，提高了进入中空纤维膜装置中的氮气浓度，通电线圈和中空纤维膜分离装置的协同工作，实现氮气的高浓度输出。 【EN】The invention discloses an airborne nitrogen production device with an electrified coil for assisting membrane separation and an application method thereof, belongs to the technical field of aviation systems, can realize high-concentration continuous output of nitrogen-rich gas, and has the advantages of simple maintenance, good reliability and high separation efficiency. The invention combines the magnetic separation of an electrified coil with the traditional membrane separation technology, a winding coil is added on the shell of a classical hollow fiber membrane device, the winding mode is that the number of coil turns is continuously reduced along the axial direction of an air inlet direction, after the hollow fiber membrane device is electrified, the air of the hollow fiber membrane is pre-separated under the action of a magnetic field generated by the electrified coil, at the moment, the air is pre-separated continuously through the magnetic field, when the air passes through the inside of the hollow fiber membrane, oxygen and nitrogen are pre-separated in the electrified solenoid due to different oxygen and nitrogen magnetic susceptibility, the concentration of nitrogen entering the hollow fiber membrane device is improved, and the high-concentration output of the nitrogen is realized through the cooperative work of the electrified coil and the hollow fiber membrane separation device.

摘要：【中文】本发明公开了一种引用飞机燃油机翼自动防除冰装置及其工作方法，装置包含包括油箱、燃油泵、流量阀、电加热层、控制器、结冰探测器、温度传感器和液位计。本发明利用航空燃油在地面吸收大量的热量，在飞行过程中通过循环泵把温度较高的燃油输送到飞机机翼的内蒙皮与外蒙皮之间的隔层进行充分的热交换，保持机翼表面温度高于冰点，防止机翼结冰。同时在飞机燃油温度降低到一定值或油箱燃油量过低时直接加热机翼外蒙皮，以防燃油温度过低后除冰装置失去效能。本发明机翼除冰装置除冰效率高，并且能量来自于占飞机比重较高的燃油吸收的显热，从而有效地降低了防除冰装置的能耗。 【EN】The invention discloses an automatic anti-icing and deicing device for fuel wings of a quoted aircraft and a working method thereof. The aircraft fuel oil absorbs a large amount of heat on the ground, and the fuel oil with higher temperature is conveyed to the interlayer between the inner skin and the outer skin of the aircraft wing by the circulating pump to carry out sufficient heat exchange in the flying process, so that the surface temperature of the wing is kept higher than the freezing point, and the wing is prevented from being frozen. And meanwhile, when the fuel temperature of the airplane is reduced to a certain value or the fuel quantity of a fuel tank is too low, the outer skin of the wing is directly heated, so that the deicing device is prevented from losing effectiveness after the fuel temperature is too low. The wing deicing device has high deicing efficiency, and the energy comes from the sensible heat absorbed by fuel oil which occupies higher proportion of the airplane, so that the energy consumption of the deicing device is effectively reduced.

摘要：【中文】本发明公开了一种飞机燃油管路压力脉动系统及其工作方法，该飞机燃油管路压力脉动系统采用开式循环方式，测控装置采集燃油管路压力与温度，自动控制电机转速以调节流量，控制燃油管道试验段前后端比例减压阀门开启大小与速度，测试燃油管路压力脉动；燃油管道系统设有溢流阀、蓄能器及散热器来保证系统运行的可靠性与稳定性。通过本发明使得飞机燃油管路压力脉动系统启动速度快、测试精度高，安全性好，能够自动采集及控制系统运行，适合研究燃油系统导致压力增大或波动的部件或系统失效机理，考虑可能导致其最大可能压力的部件或系统失效及可能存在的压力脉动，为典型静承压件燃油系统管路最大可能压力的确定提供支撑。 【EN】The invention discloses an aircraft fuel pipeline pressure pulsation system and a working method thereof, wherein the aircraft fuel pipeline pressure pulsation system adopts an open cycle mode, a measurement and control device collects the pressure and the temperature of a fuel pipeline, automatically controls the rotating speed of a motor to adjust the flow, controls the opening size and the opening speed of a proportional pressure reduction valve at the front end and the rear end of a fuel pipeline test section, and tests the pressure pulsation of the fuel pipeline; the fuel pipeline system is provided with an overflow valve, an energy accumulator and a radiator to ensure the reliability and stability of the system operation. The invention has the advantages of high starting speed, high testing precision and good safety of the aircraft fuel pipeline pressure pulsation system, can automatically acquire and control the system operation, is suitable for researching the failure mechanism of a part or a system of the fuel system causing pressure increase or fluctuation, considers the failure of the part or the system possibly causing the maximum possible pressure of the part or the system and the possible pressure pulsation, and provides support for determining the maximum possible pressure of the typical static pressure-bearing part fuel system pipeline.

摘要：【中文】本发明公开了一种基于生物除氧的飞机油箱惰化装置，包括生物除氧惰化子系统、微生物营养液供应子系统和测控子系统。本发明把酵母类等微生物运用于机载惰化系统消耗氧气来降低油箱中的氧含量，同时微生物生长代谢过程中也会产生大量的二氧化碳，把油箱上部的蒸汽混合物通过风机并调节温度后通入生物除氧器，处理后的气体过滤干燥后再通入油箱上部对其冲洗来达到惰化的目的；生物除氧器温度控制在酵母类等微生物快速生长和繁殖最适宜的环境下，并通过供液泵供应微生物营养液，保证微生物能够消耗有机物快速除氧。本装置通过氧浓度传感器和温度传感器来控制系统工作，具有无飞机燃油代偿损失，结构简单，无环境污染等优点。 【EN】The invention discloses an aircraft fuel tank inerting device based on biological oxygen removal, which comprises a biological oxygen removal inerting subsystem, a microbial nutrient solution supply subsystem and a measurement and control subsystem. The invention applies microorganisms such as yeast and the like to an onboard inerting system to consume oxygen to reduce the oxygen content in an oil tank, simultaneously generates a large amount of carbon dioxide in the microbial growth and metabolism process, leads a steam mixture at the upper part of the oil tank into a biological deaerator after passing through a fan and regulating the temperature, and leads the treated gas into the upper part of the oil tank to flush the treated gas to achieve the aim of inerting; the temperature of the biological deaerator is controlled in an environment which is most suitable for the rapid growth and reproduction of microorganisms such as yeast and the like, and microbial nutrient solution is supplied through a liquid supply pump, so that the microorganisms can consume organic matters to rapidly deaerate. The device controls the system to work through the oxygen concentration sensor and the temperature sensor, and has the advantages of no aircraft fuel compensation loss, simple structure, no environmental pollution and the like.