Parameter Optimization of Nose Landing Gear Considering Both Take-off and Landing Performance of Catapult Take-off Carrier-Based Aircraft

Optimization of the parameters of landing gear systems with double-stage air springs of catapult take-off carrier-based aircraft is here studied based on the mathematical equations of the classic dual mass spring-damper dynamic model.Certain standards for both take-off and landing performance are put forward.The contradictory factors between take-off and landing processes are analyzed.The optimization of oil in the pin area and the area near the rear oil hole is performed.Then these optimized parameters are used to assess the influence of the initial pressure of the low chamber,the ratio of the high chamber to the low chamber,and the tire inflation pressure on the performance of arresting landing and catapult take-off.The influences of these parameters on carrier-based aircraft and the aircraft-carrier on aircraft catapult take-off is also assessed.Based on the results of the simulation,respective take-off criteria must be drafted considering different types of aircraft and different take-off load cases,all of which must be matched to parameters relevant to catapult take-off.

Guidance and Control Techniques of Carrier-Based Aircraft for Automatic Carrier Landing

We summarize the guidance and control techniques of automatic carrier landing for carrier-based aircraft.First,we analyze the carrier landing operations of the manned fixed-wing aircraft,unmanned fixed-wing aircraft and helicopters.Second,we look into the navigation and guidance system and the flight control methods for current different aircraft.Finally,we draw several conclusions of the development prospects for aircraft carrier landing,including the precision landing control techniques,precision approach and landing guidance techniques,and adaptive,reconfigurable and intelligent flight control techniques.

Dynamics Analysis of Carrier-Based Aircraft with Off-Center Catapult Launch

In order to enhance the safety of the catapult launch of the carrier-based aircraft,the catapult launch multibody dynamic model is established aiming at the problem of off center catapult launch.The whole catapult process including four stages which are buffering,tensioning,releasing and taxiing is taken into consideration and the body dynamics of the off-center catapult during each stage is analyzed.The catapult launch dynamic differences between the conditions only considering taxiing and that considering four stages are compared,and the effects of the different initial off center distances considering four stages on the attitude,landing gear load and acceleration of the carrier based aircraft during catapult launch are discussed.The results show that only considering taxiing may underestimate the dynamics of the carrier-based aircraft substantially.When taking four stages into consideration,the initial off-center distance has small influence on the aircraft dynamic characteristics during buffering and tensioning but has larger influence on that during releasing and taxiing.The increase of the off-center distance will cause the enhancement of the aircraft rolling and yawing,which may lead to the load difference between the left and right landing gears and the increase of the aircraft lateral acceleration.The establishment and simulation of the catapult launch multi body dynamic model founded on buffering,tensioning,releasing and taxiing provide reference for the carrier-based aircraft design and analysis of the catapult launch dynamics.

Optimal Preview Control for Automatic Carrier Landing System of Carrier-Based Aircraft with Air Wake

Carrier-based aircraft carrier landing is a special kind of tracking control problem and not suitable for classical control methods,which may miss the desired performance or result in overdesign.Therefore,we present an optimal preview control for automatic carrier landing system(ACLS)by using state information of system,as well as future reference information,which can avoid the shortcomings of classical control methods.Since the flight performance of carrier-based aircraft is disturbed by air wake when the aircraft flies near the area of carrier stern,we design a disturbance rejection strategy to ensure that aircraft track the glide path with high precision and robustness.Further,carrier-based aircraft is a complex nonlinear system.However,the nonlinear model of carrier-based aircraft can be linearized at equilibrium landing state and decoupled into the longitudinal model and the lateral model.Therefore,an optimal preview control system is designed.The simulation results of a carrier-based aircraft show that the optimal preview control system can effectively suppress air wake.Tracking accuracy of optimal preview controller is higher than that of the proportional integral differential(PID)control system.

A bi-population immune algorithm for weapon transportation support scheduling problem with pickup and delivery on aircraft carrier deck

The weapon transportation support scheduling problem on aircraft carrier deck is the key to restricting the sortie rate and combat capability of carrier-based aircraft.This paper studies the problem and presents a novel solution architecture.Taking the interference of the carrier-based aircraft deck layout on the weapon transportation route and precedence constraint into consideration,a mixed integer formulation is established to minimize the total objective,which is constituted of makespan,load variance and accumulative transfer time of support unit.Solution approach is developed for the model.Firstly,based on modeling the carrier aircraft parked on deck as convex obstacles,the path library of weapon transportation is constructed through visibility graph and Warshall-Floyd methods.We then propose a bi-population immune algorithm in which a population-based forward/backward scheduling technique,local search schemes and a chaotic catastrophe operator are embedded.Besides,the randomkey solution representation and serial scheduling generation scheme are adopted to conveniently obtain a better solution.The Taguchi method is additionally employed to determine key parameters of the algorithm.Finally,on a set of generated realistic instances,we demonstrate that the proposed algorithm outperforms all compared algorithms designed for similar optimization problems and can significantly improve the efficiency,and that the established model and the bi-population immune algorithm can effectively respond to the weapon support requirements of carrier-based aircraft under different sortie missions.

抗阻训练对航母舰载机飞行学员颈部疼痛和颈部功能的影响

目的通过运动疗法和颈肌抗阻训练改善飞行员颈部功能,研究抗阻训练对舰母载机飞行学员颈部疼痛水平和表面肌电活动的影响。方法对航母舰载机飞行学员进行颈部疼痛干预实验,实验周期为3个月。纳入23~35岁的男性舰载机飞行学员,运动前进行健康筛查和风险评估,排除高风险人群。发放调查问卷,包括颈椎功能障碍指数表和中国体力活动调查表。进行颈肌功能测试,包括颈肌最大肌力、颈椎关节活动度和表面肌电。将实验对象随机分为两组,每组各8名。第一组为对照组,每天照常进行部队安排的训练;第二组为抗阻训练组,在照常进行部队安排训练的基础上使用自主研发的舰载机飞行员用颈椎病预防训练器,制订有针对性的训练方案。每周进行3次抗阻训练,每次训练时间为20 min,在干预实验结束时再次测试颈肌最大肌力、颈椎关节活动度和表面肌电值。将所有数据导入SPSS 22.0软件,结果采用平均值±标准差(x±s)表示,以P<0.05为差异具有统计学意义。结果(1)干预3个月后,抗阻训练对视觉疼痛模拟评分(VAS)的影响效果显著。(2)干预后受试者颈椎功能障碍指数(NDI)的自身前后测试结果表明,其颈椎功能障碍水平得到明显好转。(3)干预后,受试者自身关节活动度的组间对比结果显示,抗阻训练组受试者的前屈、后伸、左屈、右屈、左旋和右旋的自身变化差值比较,差异具有统计学意义(P<0.05)。(4)干预后,两组受试者的自身颈部肌力结果显示,抗阻训练组受试者的六个动作自身变化差值比较,差异无统计学意义(P>0.05)。(5)干预前后在前屈、后伸、左屈、右屈四个动作测试中抗阻训练组的均方根值(RMS)结果显示,左右胸锁乳突肌和左右侧斜方肌上束的差异均无统计学意义(P>0.05)。(6)干预前后在前屈、后伸、左屈、右屈四个动作测试中抗阻训练组的积分肌电值(iEMG)结果显示,左右胸锁乳突肌和左右侧斜方肌上束的差异均无统计学意义(P>0.05)。结论接受3个月抗阻训练可有效缓解舰载机飞行学员的颈部疼痛,改善颈椎功能障碍以及颈部被测四块肌肉深浅肌纤维的载荷,增强颈部肌肉力量、抗疲劳能力和颈部关节活动度,优化颈部深浅层肌肉的激活模式。

舰载机飞行员选拔用多色光脑电诱发闪光灯研制

目的:研制一种多色光脑电诱发闪光灯,以鉴定舰载机飞行员选拔中是否存在光敏感性癫痫者。方法:该闪光灯由灯体、控制盒、支架3个部分组成。灯体内设置4排LED,分别发出红、黄、绿、橙4种颜色光;控制盒盒体上有信号、灯、电源3个插口和1个颜色转换开关,控制电路板固定于控制盒内底部;支架为双关节臂折叠式设计。将普通光脑电诱发闪光灯与该闪光灯进行对比,验证该闪光灯诱发光敏感性癫痫的效果。结果:清醒闭目条件下,多色光脑电诱发闪光灯与普通光脑电诱发闪光灯诱发光敏感性癫痫的人数对比,差异无统计学意义(P>0.05)。结论:该闪光灯可弥补普通光脑电诱发闪光灯的不足,可用于舰载机飞行员的选拔。

“舰载飞行力学与控制”课程引入PBL教学法探讨

通过分析“舰载飞行力学与控制”课程的教学现状以及引入PBL教学法的必要性,以《机动飞行》章节的教学内容为例,给出了PBL教学法的实施过程;同时,针对教学过程中出现的问题,提出了相应的注意事项。实践表明,PBL教学法能够激发学生的学习兴趣,培养学生的自学能力,增强其团队协作精神,促进学生知识的掌握和运用,提高教学效率和教学质量,但是,PBL教学法对课程内容、师资力量和教学组织提出了更高的要求。因此,将PBL教学方法应用到“舰载飞行力学与控制”教学中是切实可行的。

轰炸机舱室颜色优选实验研究

目的 研究轰炸机飞行员对飞机舱室的颜色需求,提出基于视觉工效的颜色设计方案,为飞机舱室的内部装饰颜色设计提供依据.方法 试验对象为151 名轰炸机飞行员,平均年龄26-40 岁.要求飞行员对飞机舱壁及主要控制设备的备选颜色进行选择排列,并与其日常喜欢的颜色进行对比.结果 (1)飞行员对座舱舱壁装饰浅色系按适合程度由高到低的排序为:E,B,D、F,C,A,J、I,H,G,K,L;(2)飞行员对座舱控制设备装饰深色系适合程度由高到低的排序为:E',H'、F',A',C',B',D',G',I',J',K',L';(3)飞行员对深、浅两个色系各12 种颜色的选择度并不相同,且均具有统计学意义(P<0.001);(4)飞行员日常生活中喜欢的颜色对于本次选择结果的影响不显著(P>0.05).结论 (1)飞行员对于轰炸机内饰颜色的选择不受日常颜色偏好的影响;(2)浅色系中最适合用于轰炸机舱壁的颜色为E(FS36463)、B(FS36495),其次为D(FS36628)、F(FS36492);(3)深色系中最适合用于轰炸机控制设备的颜色为 E'(FS36173)、H'(FS36176),其次为 F'(FS36152)、A'(FS36118).

The effects of 12 weeks of functional strength training on muscle strength,volume and activity upon exposure to elevated Gz forces in high-performance aircraft personnel

Background:Technological advancements in modern military and acrobatic jet planes have resulted in extraordinary psychophysiological loads being exerted upon flying personnel,including inducing neck and back pain.The purpose of this study was to examine the effects of 12 weeks of functional strength training on 1)the volume and strength of the neck and shoulder muscles and 2)muscular activity upon exposure to helmets of different masses and elevated Gz forces in a long-arm centrifuge in high-performance aircraft personnel.Methods:Eighteen participants underwent 12 weeks of functional strength training(n=12)or the control protocol(n=6)without additional strength training.Pre-and post-intervention tests included evaluations of isometric strength of the head extensor muscles,flexion,and lateral flexion and rotation,as well as magnetic resonance imaging(MRI)to measure the volume of the m.sternocleidomastoideus,m.trapezius,and deep neck muscles.Furthermore,during a long-arm centrifuge(+1.4 and+3Gz)protocol,the muscular activity levels of the m.sternocleidomastoideus,m.trapezius and m.erector spinae muscles were assessed without a flight helmet,with a helmet,and with a helmet and night vision goggles.Each participant’s perception of muscular strain was noted immediately after the long-arm centrifuge protocol.Results:The maximal isometric strength in all exercises and muscle volumes increased in the training group but not the control group(P<0.05).Relative muscle activity(%MVC)with a helmet decreased after the intervention in the training but not the control group(P=0.01).Relative muscle activity while wearing a helmet and night vision goggles was higher after intervention in the control group than in the training group(P<0.01).The perceived muscular strain of the neck muscles induced by the long-arm centrifuge did not differ between the groups.Conclusions:Twelve weeks of functional strength training improves the maximal isometric strength and volume of neck and shoulder muscles and leads to lower relative muscle activation upon exposure to elevated Gz forces in a long-arm centrifuge.

Temporal Prediction of Aircraft Loss-of-Control: A Dynamic Optimization Approach

Loss of Control (LOC) is the primary factor responsible for the majority of fatal air accidents during past decade. LOC is characterized by the pilot’s inability to control the aircraft and is typically associated with unpredictable behavior, potentially leading to loss of the aircraft and life. In this work, the minimum time dynamic optimization problem to LOC is treated using Pontryagin’s Maximum Principle (PMP). The resulting two point boundary value problem is solved using stochastic shooting point methods via a differential evolution scheme (DE). The minimum time until LOC metric is computed for corresponding spatial control limits. Simulations are performed using a linearized longitudinal aircraft model to illustrate the concept.

舰载机飞行员自发性气胸的诱发因素分析及防护对策

随着我国海军航空母舰的入役,海军需要培养大批舰载机飞行员,探索舰载机飞行员的身体疾患与健康维护对于提高作业能力具有重要意义。自发性气胸在舰载机飞行员中较为罕见,但危害严重,一旦发生可严重威胁飞行安全。本文通过对美国海军舰载机飞行员发生的自发性气胸状况进行分析,探讨其诱发因素并提出防护对策,为我军舰载机飞行员的职业健康维护提供参考。

智能座舱辅助系统研究

从对飞行员知识掌握要求高、造成飞行员总体工作负荷增加、对飞行员空战辅助支持不足和人机交互信任存在矛盾冲突四个方面分析传统座舱设计存在的问题,研究美国“飞行员助手”系统(PA)、“旋翼机飞行员助手”系统(RPA),以及其他国家的智能座舱辅助系统发展情况。分析智能座舱辅助系统的应用前景和影响,根据国外发展应用情况及我国实际,针对发展应用智能座舱辅助系统、实现高效的辅助决策,提出启示建议。

基于视觉SLAM的飞机模拟座舱三维地图构建

针对飞机座舱副驾驶的研究需要,为使得机械臂能够在飞机座舱完成导航任务,旨在构建一个可用于机械臂导航的飞机模拟座舱三维地图。针对特征点分布情况对即时定位与地图构建(simultaneous localization and mapping,简称SLAM)的建图精度的影响,通过实验对比,验证了ORB-SLAM改进的ORB(oriented FAST and rotated BRIEF)特征检测算法相对于OpenCV库中SIFT,SURF和ORB算法检测提取的特征点分布更加均匀,更适用于SLAM。采用Kinect V2.0作为深度信息图像和彩色图像的数据采集设备,在飞机模拟座舱真实的环境下,结合ROS系统和ORBSLAM2系统框架,构建了飞机座舱内的三维稠密点云地图。针对点云地图存在数据大和难以实现导航等问题,采用了OctoMap数据模型,该数据模型能够压缩点云,调节分辨率和判断空间是否被占据,将点云地图转化为八叉树地图,最终获得数据小和适用于导航的三维八叉树地图。

一种优化的基于对流可分辨模式的飞机积冰潜势概率预报方法

本文对飞机积冰概率预报方法进行了优化,该算法主要基于对流可分辨率数值模式输出的温湿层结结构进行计算,可输出高时空分辨率,且符合中国积冰情况的积冰潜势。相较于原始算法,从云层判断、对流云积冰、隶属函数三方面进行了优化。首先,优化后算法采用了更切合中国积冰分布的隶属函数。其次,使用随高度变化而变化的相对湿度阈值来判断云层,可以有效减少低层云和高层云的空报、中层云的漏报。第三,增加对流云中积冰条件的预报,进一步提高积冰潜势算法的预报准确率。通过对近600份国内飞机积冰报告的系统性检验评估,结果表明优化后的潜势预报方法在高阈值与低阈值区间预报效果均优于原始预报方法及传统IC算法。通过2020年3月陕西中南部的三次飞机飞机积冰场外探测个例检验,不仅对积冰条件的有无预报准确,而且在积冰强度方面也符合实际观测结果。

Dynamics Model of Carrier-based Aircraft Landing Gears Landed on Dynamic Deck

In order to study the carrier-based aircraft landing laws landed on the carrier, the dynamics model of carrier-based aircraft landing gears landed on dynamic deck is built. In this model, the interactions of the carrier-based aircraft landing attitude and the damping force acting on landing gears are considered, and the influence of dynamic deck is introduced into the model through the deck normal vectors. The wheel-deck coordinate system is put forward to solve the complex simulation problem of force-onwheel which comes from the dynamic deck. At last, by simulation, it is demonstrated that the model can be applied to landing attitude when the carrier-based aircraft is landing on the dynamic deck, it is also proved that the model is comprehensive and suitable for any abnormal landing situation.

Multi-body dynamic system simulation of carrier-based aircraft ski-jump takeoff

The flight safety is threatened by the special flight conditions and the low speed of carrier-based aircraft ski-jump takeoff. The aircraft carrier motion, aircraft dynamics, landing gears and wind field of sea state are comprehensively considered to dispose this multidiscipline intersection problem. According to the particular naval operating environment of the carrier-based aircraft ski-jump takeoff, the integrated dynamic simulation models of multi-body system are developed, which involves the movement entities of the carrier, the aircraft and the landing gears, and involves takeoff instruction, control system and the deck wind disturbance. Based on Matlab/Simulink environment, the multi-body system simulation is realized. The validity of the model and the rationality of the result are verified by an example simulation of carrier-based aircraft ski-jump takeoff. The simulation model and the software are suitable for the study of the multidiscipline intersection problems which are involved in the performance, flight quality and safety of carrier-based aircraft takeoff, the effects of landing gear loads, parameters of carrier deck, etc.

Optimization and verification of single pilot operations model for commercial aircraft based on biclustering method

Commercial aircraft crews have experienced a trend from five-person crew to dual-pilot crew.Arised from both technological and market demands,Single Pilot Operations(SPO)is considered an important development direction in modern aviation technology.In this paper,starting from Dual-Pilot Operations(DPO),the piloting process,decision-making process and decisionmaking mode of DPO for commercial aircraft are studied to obtain the operational requirements of SPO.Then,based on above analysis,the operational mechanism of SPO is studied and the core technology of SPO mode is proposed.Next,a new closed frequent bicluster mining algorithm named FsCluster is proposed for the optimization of the SPO model,and the other efficient bicluster mining algorithm named TsCluster is proposed for the analysis and verification of the SPO model.Finally,a typical flight phase scenario is modelled by Magic System of System,and combined with the proposed algorithms for analysis and verification to determine whether the SPO mode can meet the DPO requirements.

5种机型军事飞行人员急性缺氧耐力情况统计分析

目的调查研究5种机型军事飞行人员急性缺氧耐力现状,为军事飞行人员飞行安全保障提供依据。方法选择2018-2021年在海军青岛特勤疗养中心参加航空生理训练的1299名军事飞行人员,按飞行机型将飞行人员分为歼击机组、教练机组、运输机组、轰炸机组和直升机组。对5种机型军事飞行人员急性缺氧耐力水平和急性缺氧耐力评定等级分布情况进行比较分析。结果歼击机组和教练机组军事飞行人员急性缺氧有效意识时间均长于运输机组、轰炸机组和直升机组军事飞行人员(P<0.05),并且这种差异存在于缺氧耐力评定等级为合格组和优秀组人员中。5种机型飞行人员缺氧耐力等级的分布比例比较,差异有统计学意义(χ^(2)=25.267,P<0.001)。歼击机和教练机飞行人员的缺氧耐力优秀率高于运输机、轰炸机和直升机军事飞行人员(P<0.05)。结论目前我军5种机型飞行人员的急性缺氧有效意识时间长短存在差异,不同机型军事飞行人员急性缺氧耐力评定等级的分布也不完全相同,航空卫生保障部门应当给予关注。

Numerical simulation of aircraft arresting process with an efficient full-scale rigid-flexible coupling dynamic model

The arresting process of carrier-based aircraft is widely recognized as a challenging task,characterized by the highest accident rate among all carrier-based aircraft operations.Dynamic simulation plays a crucial role in assessing the intricate responses of the arresting process,favoring the design of carrier-based aircraft.An efficient and accurate rigid-flexible coupling model for analyzing the dynamic response of the arresting process is proposed.By combining the dynamic characteristics of airframe,landing gear,arresting hook and arresting gear system,the rigid-flexible coupling dynamic model is established to reflect the relative motion of the coupling parts and arresting load.The dynamic model is verified through simulations of landing gear landing drops and by comparing the arresting simulation results with corresponding data in the US military standard.Additionally,simulations of the arresting process under different off-center distance and aircraft yaw angle are conducted to obtain the dynamic response of the aircraft during the arresting process.The result indicates that the rigid-flexible coupling dynamic model proposed is effective for analyzing the arresting dynamics response of carrier-based aircraft.The axial force of the arresting cable on both sides of the hook engagement point,pitch and yaw angle of aircraft are inconsistent under yaw and off-center arresting.The analysis method and obtained results provide valuable references for assessing the dynamic responses of carrier-based aircraft during arresting process and offer valuable in-sights in the design of carrier-based aircraft.