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检索条件"机构=Aviation Key Laboratory Science and Technology on Life-Support Technology"

共 139 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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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 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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Comparison of impulse noise energy distribution from two generations of parachute gun 2

Comparison of impulse noise energy distribution from two gen...

引用

2023 2nd International Conference on Acoustics, Fluid Mechanics and Engineering, AFME 2023

作者： Li, Jun Xie, Wujun Li, Hui Huang, Guangjun Key Laboratory of Science and Technology on Life-support Technology AVIC Aerospace Life-support Industries Ltd Hubei Xiangyang441100 China

The rocket ejection seat is an advanced life-saving device for fighter pilots. However, it can also produce damaging impulse noise during ejection, which could compromise the pilot's hearing health, and the manufacturer must assess the noise damage. This study uses Variational Mode Decomposition (VMD) and Hilbert-Huang transform (HHT) to analyze energy-instantaneous distribution over time and frequency-instantaneous and energy contribution of different modes of impulse noise generated by the parachute gun in two generations of rocket ejection seats. The results demonstrate considerable disparities in the energy distribution of impulse noise generated by the parachute gun in the new generation seat compared to the old generation seat. The new generation seat has higher overall energy, more concentrated action time, and a higher energy contribution in the 1-10 kHz frequency range. These findings provide valuable data for the design of the new generation of noise protection equipment for pilots. © Published under licence by IOP Publishing Ltd.

关键词： Mathematical transformations

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Performance of Hearing Protectors in Ejection Seat Parachute Gun Firing 6th

Performance of Hearing Protectors in Ejection Seat Parachute...

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6th China Aeronautical science and technology Conference, CASTC 2023

作者： Xie, Wujun Min, Liwu Li, Jun Li, Hui Key Laboratory of Science and Technology on Life-Support Technology AVIC Aerospace Life-Support Industries Ltd. Hubei Xiangyang China

ISBN: (纸本)9789819988600

During ejection rescue, the parachute gun attached to a rocket-assisted ejection seat generates jet noise that may damage a pilot’s sensitive auditory organs;hence the effectiveness of hearing protectors, primarily a helmet and earmuffs, is evaluated. A parachute gun firing experiment is designed, and overpressure data with and without protection are measured simultaneously during firing using piezoelectric pressure sensors inside and outside dummy ears. A comparative study of the measured data is conducted using time domain analysis and wavelet transformation methods, and the results show that the jet noise generated by a parachute gun firing is a broadband signal, consisting of shock waves and impulse noise;different from the attenuation characteristics in the continuous noise environment, in the jet noise environment, the effect of hearing protectors is significant for extenuating the high-frequency components that are prone to injury, but not significant for extenuating the low-frequency components. © 2024, Chinese Society of Aeronautics and Astronautics.

关键词： Time domain analysis

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Evaluation of Long-Duration Fatigue Alleviation Effect of a Rocket Ejection Seat Installed at a 35° Angle Based on Heart Rate Variability 15

Evaluation of Long-Duration Fatigue Alleviation Effect of a ...

引用

15th Asia Conference on Mechanical and Aerospace Engineering, ACMAE 2024

作者： Li, Hui Li, Jun Key Laboratory of Science and Technology on Life-support Technology AVIC Aerospace Life-support Industries Ltd. No.1 AVIC Avenue Hubei Xiangyang China

ISBN: (纸本)9781643685892

Fatigue significantly impacts modern flight safety, leading to decreased pilot performance, judgment errors, flight illusions, and potentially severe accidents. Rocket ejection seat for emergency escape with additional 35° mounting angle design. To verify the fatigue improvement effect of this design for long-duration flights, a simulated long-duration flight test was conducted. The trial uses wearable wireless physiological monitoring equipment to collect ECG from trainees. Short-term heart rate variability (HRV) indicators reflecting fatigue state were selected from the time-domain, frequency-domain, and nonlinear characteristics of valid samples. Paired sample test results showed significant changes in short-term HRV indicators before and after resting with the rocket ejection seat installed at a 35° angle, indicating reduced sympathetic activity and increased parasympathetic activity, thus alleviating fatigue. © 2025 The Authors.

关键词： Heart

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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...

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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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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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Time-Frequency Characteristics of Parachute Gun Shockwave Based on VMD-HT 8

Time-Frequency Characteristics of Parachute Gun Shockwave Ba...

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8th International Conference on Communication, Image and Signal Processing, CCISP 2023

作者： Li, Jun Xie, Wujun Li, Hui Fang, Liyi AVIC Aerospace Life-support Industries LTD Key Laboratory of Science and Technology on Life-support Technology Xiangyang Hubei China

ISBN: (纸本)9798350305838

During the ejection process of the fighter pilot, the parachute is shot out by the life-saving seat gun, which generates a shockwave that endangers human safety. In order to accurately and stably extract the time-frequency distribution characteristics, the shockwave signal is obtained through parachute gun shooting experiments, and features of the shockwave signal is extracted by using Variational mode decomposition and Hilbert transform methods (VMD-HT). VMD is a high sampling rate shockwave signal decomposition technique, which is suitable for analysing unsteady airborne parachute gun shooting shockwave signals. The HT method is used to accurately extract the relationship between time, instantaneous frequency and energy for the decomposed signal, and to obtain the marginal spectra. The analytic results show that the shockwave signal lasting 3ms has a significant energy concentration in the low frequency band of 0∽1kHz, which is important for the better protection of pilots. © 2023 IEEE.

关键词： Variational mode decomposition

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