Abstract:This paper reviewed and summarized the development situation of micro turbojet engines in the past sixty years. The thrust of micro turbojet engines is less than 100 daN especially. They are characteristic of small size, high rotating speed, low cost and simple structure. They became a global researchful focus as an excellent powerplant of micro and small aerial vehicles, because of the advantages of longer running time, variable thrust, lower infrared radiation value and repeated usage. The micro turbojet engines have been equipped on unmanned combat aerial vehicles, targets for air defense weapons, precision-guided missiles, test vehicles, powered gliders and aerial models.

Abstract:Engine installation and removal trailers are important aircraft support equipments, which affect supportabilty and maintenability of jet fighters directly. US and European countries are world leaders in the field of engine I R trailer products and technologies, which are worth studying and used as a source of reference. There are different design features and specifications for engine I R trailers of different countries, different generations, different models. Therefore comparison is helpful to understand and digest engine I R trailer technologies. This article is based on large quantity of documents and reterences, and comparative studies are performed. By case analysis and vertical and horizontal comparative study,differences and sameness, advangtages and disadvantages of different trailer designs are distinguished. Features of development and evolution of trailers are recognized. Design technologies of trailers are mastered. The study work is expected to prvide important reference to design and development of advanced trailer product of China.

Abstract:The boundary layer blowing is an effective measure to increase the lift of flight vehicles. For a common flight vehicle designed for on-land taking off and landing, the aerodynamic characteristic requirements to on-deck taking off and landing were analyzed based on the project parameters and five schemes were proposed. The lift increase potential of flap and slat steady blowing was researched by numerical simulation. The results indicate that the flap and slat blowing can enhance the lift observably, whereas some interference will appear when both the flap and slat blowing, which lead the slop of lift increase decrease as the blowing moment coefficient augment. When the blowing moment coefficient less than 6%, the maximum lift coefficient can reach about 1.85 and the lift coefficient at 15° of the angle of attack with both the flap and slat blowing can reach about 1.40, from which three schemes can be satisfied for taking off and landing on the deck.

Abstract:Reynolds number is one of the most useful similarity parameters in fluid dynamics which denotes the effect of the viscosity on the fluid flow, it has the important effect on the aerodynamic characteristic of the aircraft. The variable Reynolds number research of the high lift for one of the civil turboprop aircraft is completed by the commercial software CFX in this paper. The effect of Reynolds number on the lift coefficient, pressure distribution, stall characteristic, and the velocity characteristic of the boundary layer are also carefully analyzed. The research indicates that the Reynolds number has the notable effect on the maximum lift coefficient and the stall angle; the state of separation on the wing change obviously under the different Reynolds number, the area of separation become smaller when the Reynolds number increases; the state of the boundary layer is different under the different Reynolds number, when the Reynolds number increases, the velocity profile is fuller, the trend of separation is limited.

Abstract:It is of more significance for improving the prediction accuracy of aircraft aerodynamic performance to predict the transition position of the boundary layer accurately. Selecting the model coupled with SST k-w turbulence model and taking no-pressure-gradient plane as an example, the capability of this model for trapping flow transition automatically was verified. Then the model was applied to study the flow characteristics and aerodynamic performance of NACA 0012 airfoil with pressure gradient, the results from which were compared with the computational result from original SST k-w model and the test data of complete turbulence model. The study shows that the transition position of airfoil surfaces predicted by the model and even the drag coefficients are very good as the angle is less than 12°. While there is a very big deviation as the angle is equal to or bigger than 12°, the reason of which may be that two-dimensional method can not catch three-dimensional effect and unsteady characteristics of separation on airfoil surfaces.

Abstract:In order to reduce the weight of the wing, distribute materials reasonably and improve utilization rate of materials, Two-Step optimization method was proposed for flap structure optimization Design. Taking the conceptual design of flap guide as research object, top-layer and low-layer optimization design as two basic events were analyzed by complex optimization design problem. The top-layer was topology optimization that determined web stiffener forms and low-layer was size optimization that determined thickness distributing of flap guide. During this two-step optimization, this process determined the best structure forms base on minimize structure weight．The results of the calculative examples indicate that the method presented in this paper is feasible and correct, has a significant value in accelerating the engineer realization of the structure optimization．

Abstract:Abstract:When flying in the conditions of icing,aircraft is more probably to arise the phenomena of icing.Once the aircraft iced up,There exists hidden dangers to the safety of the plane.So reducing the harm caused by it that becomes an important research topic.Based on FENSAP-ICE,I will beign the numerical simulation of wings through Improving thermodynamic model of Messinger icing ,which simulates more realistic flight conditions. To analyse changes of aerodynamic characteristics of wings before and after aircraft icing under the different flight conditions,Therefore verity the feasibility of the way through the C3D of FENSAP-ICE.The result indicates that environment temperature will affect the type and thickness of wing icing. the wings iced up,which caused the decrease of lift cofficient and the increase of drag cofficient and affected the areodynamic characteriseics of aircarft seriously.It is obvious that the electrothermal anti-icing system which designed not only can effectively prevent icing on the surface of the wing,but also can deice periodically.

Abstract:The decrease of reliability arise from degeneration can’t be neglected. SVR（Support Vector Regression）would be applied to estimate the degree of degradation and loss of flow coefficient based on the data collected from engine. Nonlinear regression of SVM(support vector machine) is proposed kernel function transform method, the feature space optimization to obtain the optimal classification plane. Mann-Kendall test would be used to estimate the trend and speed of degeneration and judge the degeneration from fault. Simulation shows that SVR could estimate the degree of a parameter, and the technologies of Mann-Kendall could distinguish fault and degeneration.

Abstract:ATC’s task is to ensure safety of the aircraft, it is necessary to run air traffic control system safety assessment and early warning to ensure flight safety. It establishes ATC operation state vector space with starting from the main risk factors influencing running safety based on ATC big data concepts .Using principal component analysis (PCA) to remove the basic vector linear correlation and using clustering analysis to establish the ATC safety warning knowledge base, we can realize the ATC safety assessment and early warning in time. Examples show that the early warning classification analysis method can achieve good classification and safety assessment in the actual operation, it also can provide reference for control department daily decisions.

Abstract:The process of standard classification and identification of aviation regulated substances is not straightforward. Aviation regulated substances are easily classified as ordinary cargo into air transport links, which created safety risks associated with air transport. By analyzing the definition of aviation regulated substances, the scope of hazardous is determined, including anesthesia, tear gas, odor, the acute toxicity (oral, dermal, inhalation), serious eye damage or eye irritation, respiratory or skin sensitization, specific target organ toxicity, aspiration hazard. The unified layered classification scheme for aviation regulated substances is performed on the basis of the assessment guidelines for the health hazard classification of Globally Harmonized System of Classification and Labeling of Chemicals. The methods and standards of identification, data sources, and data processing method are specifically discussed. The types of aviation regulated substances are briefly summarized. In order to guide the actual classification and identification, the classification process of two odorous substances is discussed in detail, which is benefit for ensuring the safety of air transport and counter-terrorism work.

Abstract:A certain UAV can install kinds of payloads at the same time. A kind of Mission Management Computer (MMC) is introduced to manage and make full use of those payloads. All the payloads are controlled by MMC. Telemetry and telecontrol data message of the payloads is managed by MMC. The MMC provide time service for external devices. Payload integration capabilities can be improved by designing the MMC, and achieve independence to run the task system and flight control system. Thus improving the safety of the UAV platform.

Abstract:There are so many studies about the rotor but little about the stator in the research of improving the stability of compressor with plasma flow control. This paper comes up with plasma incentive method at the stator blade suction surface, the flow field characteristics of the stator in a single-stage axial-flow compressor is researched and plasma flow control mechanism of the stator in a single-stage axial-flow compressor is revealed using numerical simulation. The results show that, the axial position of the plasma actuator has an important effect on the stability of compressor, closer to the leading edge of the stator better of the stability. It cannot improve the stability of the compressor when the plasma actuator locates at back of the blade. Because when the plasma actuator locates at the front of the leading edge of the stator, the flow closed to the stator blade is accelerated, the velocity of the main flow increased, it can restrain the flow separation of the stator suction surface effectively and reduce the blockage area, and finally the stability of compressor is improving.

Abstract:Objectively and accuratelySevaluatingSthe safety performance can reflect the safety status of ATC system operation, and identify Sthe weak links in safety management.Finding key process indicators whichSaffect the systemSoperation safetySfrom theSfour aspectsSSof controllers, ATC equipment, environment and management, combining process index and result index to establish the safety performance evaluation index system of air traffic control system.On the basis of fuzzy matter-element analysis, the membership function is improved, and establishes the model ofSATC system safety performance evaluationSbased on the improved fuzzy matter-element analysis method. Finally, the evaluation results of evaluating ATC unit safety performance reflect the safety status of the ATC unit, and I find out the segment through the results which should be improved.

Abstract:With the development of system reliability for aircrafts, human error is becoming one of the main factors leading to flight accidents, as well as the key difficult and challenge for the design and airworthiness authorized departments. Currently, how to certify the compliance of the human factor is still in the theoretical exploration stage for both at home and abroad. Aiming at these above problems, this paper firstly analyzed the airworthiness certification process based on CCAR 25, including the selection of 40 regulations relevant with human factor based on SHELL model and T.E.S.T matrix, also the means of compliance( MOC5 & MOC6 ) for flight test based on Eye-tracking, and finally the data analysis example based on Fuzzy evaluation. The thoughts and methods proposed in this paper has been applied preliminarily in ARJ and can provide the technical support for design and airworthiness certification of human factor and ergonomics for other civil aircrafts.

Abstract:It is a complicated system engineering that the aeronautic equipment maintenance information sharing system which is involved in many factors is established. It can promote the efficiency of aeronautic equipment maintenance information sharing if value chain idea introduced in the construction. On the basis of the value chain model of aeronautic equipment maintenance support information sharing system is established, value-added management model was built and the value of the model was analyzed. It is indicated that the life-cycle maintenance information sharing system based on the value chain theory can effectively improve the economic benefit and military benefit.

Abstract:Compared with traditional metallic material, the introducing of composites brings significant challenges to traditional aircraft design and manufacture process, as well as to the airworthiness certification of the aircraft. In this paper, focused on five key Special Conditions (SCs) of transport category airplane composite structure, the rea-son of establishing a SC, its requirements, and the key points of compliance verification were researched in detail.