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检索条件"机构=Aviation Key Laboratory ofScience and Technology on Life-support Technology"

共 55 条记录，以下是1-10 订阅

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Study on the Impact Characteristics of Modular Floating Airbags for life-Saving Platforms Entering Water 7th

Study on the Impact Characteristics of Modular Floating Airb...

引用

7th China Aeronautical Science and technology Conference, CASTC 2024

作者： Zhu, Yuanchun Sun, Libing Ren, Jian AVIC Aerospace Life-Support Industries Ltd. Xiangyang441000 China Key Laboratory of Aviation Science and Technology for Aviation Protection and Life-Saving Technology Xiangyang441000 China

ISBN: (纸本)9789819797738

The life-saving platform can provide remote life-saving materials and refuge facilities for victims who encounter sudden natural disasters and accidents within the delivery radius, and has the ability to improve the survival chances of victims. The rescue platform in this article is equipped with a modular floating airbag to provide the rescue platform with long-term floating capacity. In order to evaluate whether the connection belt and airbag pressure of the modular floating airbag and the selection of airbag material and connection belt material meet the requirements when the life-saving platform enters the water with different posture, three water entry posture were simulated and calculated. The simulation results show that the pressure of the connecting belt and the airbag of the water entry posture 2 is the most tested, and the design of the connecting belt and the airbag has a large safety space. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Disasters

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SIMULATION RESEARCH ON THE PERFORMANCE OF EJECTING INFLATION SYSTEM OF EMERGENCY EVACUATION SLIDE

SIMULATION RESEARCH ON THE PERFORMANCE OF EJECTING INFLATION...

引用

2024 CSAA/IET International Conference on Aircraft Utility Systems, AUS 2024

作者： Jin, Lou Liu, Qilong Wu, Liang Overall Technology R&D Department AVIC Aerospace Life-support Industries Ltd. Xianyang441000 China Emergencv Rescue Technology R&D Department AVIC Aerospace Life-support Industries Ltd. Xianyang441000 China Aviation Key Laboratory ofScience and Technology on Life-support Technology Xianyang441000 China

In this article, the CFD method is used to analyse the performance of the ejecting inflation system of the emergency evacuation slide. The simulation model is established according to the operating principle of the ejecting inflation system. Quantitative analysis of the applicability and accuracy of simulation models in the performance simulation of the ejecting inflation system is carried out, and the effects of different ejection pressures and ejection working fluid components on the system performance are simulated. The research results show that the Realizable k-e model has the smallest simulation deviation, and the ejection flow rate and ejection ratio are within 5% of the experimental value, which meets the requirements of engineering development;increasing ejection pressure is beneficial to increase the ejection flow rate and speed up the inflation of the slide, but the ejection ratio will decrease when the ejection pressure pass 3.75MPa, which is not conducive to reducing the weight of the system;increasing the N2 content in the ejection gas source is beneficial to increase the ejection ratio and reduce the weight of the system while ensuring the inflation performance. The research results of this article can provide a theoretical basis for the determination of the design index of the ejecting inflation system of the emergency evacuation slide. © The Institution of Engineering & technology 2024.

关键词： Ejectors (pumps)

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RESEARCH ON AIRSPEED CORRECTION technologyOFEJECTION SEAT BASED ON CFD 34th

RESEARCH ON AIRSPEED CORRECTION TECHNOLOGYOFEJECTION SEAT BA...

引用

34th Congress of the International Council of the Aeronautical Sciences, ICAS 2024

作者： Jin, Lou Feng, Guanghui Wu, Liang Aviation Key Laboratory of Science and Technology on Life-support Technology Xianyang441000 China Overall Technology R&D Department AVIC Aerospace Life-support Industries Ltd Xianyang441000 China

A certain ejection seat airspeed sensing system is located in the wake flow field of the seat, andtheperceived static pressure will produce a large error from the local standard static pressure, requiringaerodynamic corrections to the sensed static pressure to ensure the accuracy of the measured velocityandaltitude parameters. In this paper, a technique to correct the static pressure of ejection seats duringejectionfrom the cabin is proposed, which combines CFD simulation and successive iterative approximationalgorithm. CFD simulation method was used to simulate the dynamic flow field during the seat egressfromcabin, and the total and static pressure data measured by the pitot tube sensing systemat ejectionvelocitybelow 3 Ma were analyzed. The total and static pressure values at different ejection speeds werecalculatedwith the principle of "total pressure taking the maximum and static pressure taking the minimum", andtherelationship curves of the static pressure correction coefficient with ejection velocity were obtained. Asuccessive iterative approximation algorithm was used to correct the measured static pressure basedontherelationship between the static pressure correction coefficient and the ejection velocity (Mach number). Thecalculation results show that the maximum error of perceived total pressure and static pressuresimulationvalues with test values is 2.5% at different speeds, and the maximum error of felt static pressuresimulationis 1.9%. The CFD simulation accuracy is high, and the simulation results can be used as input foraerodynamic correction. When the ejection velocity is less than Mach 3, the static pressurecorrectioncoefficient decreases monotonically with the ejection velocity increasing, and the successiveiterativeapproximation calculation converges. The maximum error between the static pressure correctionvaluecalculated by the successive iterative approximation algorithm and the static pressure at the test siteis3.8%, and the maximum error betwe

关键词： Ejection seats

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Research on intelligent control technology for enhancing precision airdrop system autonomy 4

Research on intelligent control technology for enhancing pre...

引用

4th International Conference on Machine Learning and Computer Application, ICMLCA 2023

作者： Xu, Ronghua Yu, Gang Aerospace Life-Support Industries Ltd. Xiangyang China Aviation Key Laboratory of Science and Technology on Life-Support Technology Xiangyang China Hubei University of Arts and Science Xiangyang China

ISBN: (数字)9781510680265

ISBN: (纸本)9781510680258

The Precision Airdrop System (PADS) is widely used in the accurate recovery of spacecrafts and the precision delivery of supplies. The accuracy of control is the core of the PADS achieving the precision airdrop. To enhance control accuracy, an intelligent control technology for enhancing PADS autonomy based on simulation environment is developed. The dynamic model employed to calculate the PADS state is a 6-degree-of-freedom (6-DOF) model, and the reinforcement learning control training method is based on the A-C architecture. Through analysis of simulation results in both windless and windy environments, it is evident that the reinforcement learning control strategy based on the AC architecture outperforms the traditional PID strategy. The analysis highlights the challenges posed by wind in achieving precise control and presents an effective approach for enhancing PADS autonomy through intelligent control. © 2024 SPIE.

关键词： Intelligent control

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Research on Calculation Method of Drag Chute Opening Performance Based on Rocket Sled Platform 7th

Research on Calculation Method of Drag Chute Opening Perform...

引用

7th China Aeronautical Science and technology Conference, CASTC 2024

作者： Jin, Lou Cui, Dongyue Yang, Pin Yu, Yuanyuan Aviation Key Laboratory of Science and Technology on Life-Support Technology Xianyang China Overall Technology R&D Department AVIC Aerospace Life-Support Industries Ltd. Xianyang China Institute of Mechanical and Electrical System AVIC The First Aircraft Institute Xi’an China

ISBN: (纸本)9789819797738

This paper proposes a calculation method based on the rocket sled test method to quickly verify the performance of the main drag chute of aircraft. According to the working principle and folding process of the drag chute, combined with the pre-processing folding and calculation folding methods, the simulation folding process of the finite element model of the drag chute is designed, the finite element model of the rocket sled system was established. Then, the S-ALE fluid structure coupling algorithm was used to simulate and calculate the performance parameters of the rocket sled drag parachute system during the parachute deployment process, forming a simulation verification process for the parachute deployment performance of the drag chute. The calculation results show that the force on the rope of the drag chute during the operation process of the rocket sled drag parachute system shows a consistent trend over time, and the error generated by calculating the opening performance parameters of the rocket sled drag parachute system using the method proposed in this article are within 12%, which can meet the requirements of engineering use. The calculation method proposed in this article can to some extent replace the rocket sled test to verify the performance of the parachute. The calculation method proposed can quickly predict the performance of the drag chute instead of physical tests at the initial stage of development. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Parachutes

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Quantitative Analysis of Flow Resistance in the Ventilation Pipeline of Ejection Seats and Optimization Design of Flow Resistance Reduction 7th

Quantitative Analysis of Flow Resistance in the Ventilation ...

引用

7th China Aeronautical Science and technology Conference, CASTC 2024

作者： Jin, Lou Wu, Jing Chen, Yuxiang Cui, Dongyue Aviation Key Laboratory of Science and Technology on Life-Support Technology Xianyang China Overall Technology R&D Department AVIC Aerospace Life-Support Industries Ltd. Xianyang China Institute of Mechanical and Electrical System AVIC The First Aircraft Institute Xi’an China

ISBN: (纸本)9789819797707

During normal flight, the ejection seat ventilation system provides a dedicated gas transmission channel for electronic oxygen and anti load regulators. The flow resistance of the pipeline directly affects the ventilation and supply performance of the regulator and the anti load protection ability during mobile operations. This article adopts a combination of numerical simulation and experimental testing methods to quantitatively analyze the flow resistance of a certain type of ejection seat ventilation pipeline. Based on the principle of gas supply performance testing and numerical simulation methods, a research process is designed. The simulation accuracy of different simulation models under different ventilation flow rates is analyzed, and the ventilation pipeline is optimized based on the calculation formula of pipeline flow resistance theory and the analysis results of pipeline flow field. The research results indicate that among multiple turbulence models, the Realizable k-e model has the best accuracy in simulating pipeline flow resistance, with a maximum error of 14.2% and a minimum error of 1.3% under different flow conditions, both below 15%, meeting the requirements for engineering use;the vortices generated at the corners and variable diameter areas of the ventilation pipeline can lead to energy dissipation. Optimizing the transition corners and pipeline diameter of the bend can reduce the generation of vortices and reduce the system flow resistance to 17.9% of the original value;under the premise of constant pipeline flow rate, the flow resistance of ventilation pipelines is inversely proportional to the fifth power of pipeline diameter. When optimizing pipeline flow resistance design, emphasis should be placed on optimizing from the pipeline diameter. © Chinese Society of Aeronautics and Astronautics 2025.

关键词： Ejection seats

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NUMERICAL SIMULATION OF IMPACT OF EJECTION SEAT ROCKET MOTOR IGNITION SHOCK WAVES ON AIRCRAFT WINDSHIELD LOADING

NUMERICAL SIMULATION OF IMPACT OF EJECTION SEAT ROCKET MOTOR...

引用

2024 CSAA/IET International Conference on Aircraft Utility Systems, AUS 2024

作者： Wu, Liang Jin, Lou Xu, Hang Wu, Yibin Overall Technology R&D Department AVIC Aerospace Life-support Industries Ltd. Xianyang441000 China Aviation Key Laboratory of Science and Technology on Life-support Technology Xianyang441000 China Ejection Lifesaving Technology R&D Department AVIC Aerospace Life-support Industries Ltd. Xianyang441000 China

Aircraft windshield fragmentation during seat ejection can adversely affect crew ejection from the aircraft safety. In this paper, the shock wave loads caused by the firing of an ejection seat rocket motor were simulated numerically, and the numerical simulation flow was designed with the dynamic grid technique. The results show that the pressure peak of the inner surface monitoring point at the front end of the windshield is 9.4% lower compared with the test value at the same location when the rocket engine is firing at 0 km/h velocity ejection, which proves the numerical simulation method feasible. The effects of rocket pack ignition shock waves on the aircraft windshield can be divided into shock wave loading phase and quasistatic pressure loading phase. The former has a large peak load and a short duration, while the latter has a small peak load and a long *** corners within the cockpit, converging phenomena occur during shock wave propagation, and the area near the cabin inner wall at the front and sides of the aircraft's windshield is more heavily loaded and has a higher risk of damage than other areas. The moment of maximum windshield loading for each calculated state is the moment of the first load peak. Due to the high velocity airflow blowing effect, the maximum windshield loading at 1100 km/h ejects is close to the zero velocity ejection value, acting in the opposite direction. The zero velocity ejection and impact loads at 1100 km/h eject should be emphasized in the windshield strength analysis. © The Institution of Engineering & technology 2024.

关键词： Ejection seats

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Research on residual design of ignition circuit of ejection seat 24

Research on residual design of ignition circuit of ejection ...

引用

5th International Conference on Computer Information and Big Data Applications, CIBDA 2024

作者： Wang, Wensheng Wu, Shuanglong Li, Jin Jin, Liying Aviation Key Laboratory Science and Technology on Life-Support Technology Xiangyang Hubei441003 China Aerospace Life-Support Industries Ltd. Xiangyang Hubei441003 China Xiangyang Key Laboratory of Intelligent Manufacturing and Machine Vision Hubei University of Arts and Science Hubei Province Xiangyang441053 China

ISBN: (纸本)9798400718106

At present, the programmed ignition circuit is used in the ejection seat to stimulate the explosive materials. This paper analyzes the ignition circuit architecture of the parachute projectile fired by the electric detonator on the ejection seat, and puts forward two other feasible ignition schemes. Combined with the task reliability block diagram and model, the three schemes are respectively quantitatively calculated and qualitatively analyzed, thus the optimal fire scheme is determined. Then it provides a reference for the redundancy design of other parts of the ejection seat. © 2024 ACM.

关键词： Ejection seats

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Measuring Center of Gravity of Pilot Helmet Based on Binocular Vision 4

Measuring Center of Gravity of Pilot Helmet Based on Binocul...

引用

4th International Conference on Advances in Computer technology, Information Science and Communications, CTISC 2022

作者： Jun, Li Xie, Wujun Wan, Chuanqi Jia, Zixiao Yang, Junwei Avic Aerospace Life-Support Industries LTD. Aviation Key Laboratory of Science and Technology on Life-Support Technology Xiangyang China

ISBN: (数字)9781665458726

ISBN: (纸本)9781665458726

A variety of functions are integrated into the pilot helmet, making it an intelligent weapon platform for pilots to improve situational awareness and target attacks capabilities. However, the mass distribution of the helmet has also been changed, which has a negative impact on the pilot's health and safety. Accurate measurement of the Center of Gravity (CG) of pilot helmet is of great significance for the ergonomic design. Benefiting from the rapid development of 3D computer vision technology, a 3D coordinate of CG measurement scheme for pilot helmet based on binocular vision is proposed by adopting suspension method. The measuring equipment and program are introduced in detail, and the calculation model for the center of gravity is also established. The calibration results show that the proposed measurement scheme based on binocular vision is effective. © 2022 IEEE.

关键词： Binocular vision

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Simulation Study on the Influence of Engine Room Wake Field on the Perceived Total Pressure of Ejection Seat Pitot 6th

Simulation Study on the Influence of Engine Room Wake Field ...

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6th China Aeronautical Science and technology Conference, CASTC 2023

作者： Jin, Lou Cui, Dongyue Wang, Xun Wu, Yibin Overall Technology R&D Department AVIC Aerospace Life-Support Industries Ltd. Xianyang441000 China Aviation Key Laboratory of Science and Technology On Life-Support Technology Xianyang441000 China Institute of Mechanical and Electrical System AVIC The First Aircraft Institute Xi’an710000 China

ISBN: (纸本)9789819988662

An approach to simulate the total pressure of the pitot during ejection is proposed by combining the numerical simulation of seat motion trajectory and dynamic CFD technology in this paper. By establishing the simulation model of cabin, human-seat system and pitot, the seat motion parameters obtained from the simulation of the motion trajectory are used as input to write the UDF, the motion boundary of the human-seat system is specified, and the grid update during the movement of the seat is realized by dynamic grid method, and the influence of the wake field of the cabin on the total pressure of the pitot under different ejection states is analyzed. The simulation results show that due to the influence of the wake field of the cabin, the perceived total pressure of the pitot first increases and then decreases, peaks at about 0.08s after ejection starts, and is greater than the test total pressure in the subsequent 0.01s time range, and the maximum deviation reaches 14.65%. This peak can be reduced by filtering, reducing the deviation to less than 5%. The simulation model and algorithm are calibrated, and the deviation is less than 2%, which meets the engineering requirements, and the simulation results can provide a basis for the optimization of seat aerodynamic layout and program controller data processing strategy. © 2024, Chinese Society of Aeronautics and Astronautics.

关键词： cabin wake field dynamic CFD ejection seat pitot

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