Chengdu Aircraft Design Institute

Chengdu, China

Chengdu Aircraft Design Institute

Chengdu, China
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Ma R.,Chengdu Aircraft Design Institute | Li J.,AVIC Composite Co. | Gui J.,AVIC Composite Co. | Shi F.,AVIC Composite Co. | Zhang B.,AVIC Composite Co.
Hangkong Cailiao Xuebao/Journal of Aeronautical Materials | Year: 2017

Two kinds of prepregs ZT7G/LT-03A(unidirectional carbon fiber prepreg) and ZT7G3198P/LT-03A(plain carbon fabric prepreg) were used to manufacture three Bateches of composites by vacuum process and autoclave process respectively. The physical properties of the prepregs and mechanical properties of composite were tested. The performance, fiber volume content and porosity of composites manufactured by vacuum cure and autoclave process show that the physical property retention rates of vacuum cured composites are all over 75%, some even more than 100%. Interlaminar shear strength keeps the lowest retention rate and warp tensile strength keeps the highest retention in unidirectional carbon fiber composites. For fabric composite material, compression strength keeps the lowest and warp tensile strength keeps the highest retention. Vacuum cured composites perform lower fiber volume content and higher porosity, which are the main reasons of the lower performance. © 2017, Editorial Board of Journal of Aeronautical Materials. All right reserved.


Zeng X.,Chengdu Aircraft Design Institute | Peng J.,Chengdu Aircraft Design Institute | Yue C.,Chengdu Aircraft Design Institute
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2016

The flight path of a vehicle with large wing is affected more obviously by the disturbance flow field in separation from the parent aircraft, and the precision of the aerodynamic disturbance database is demanded to be further improved. A simplified dispersion aerodynamic parameter model is put forward and a series of flight data estimation methods are introduced, combining the characteristics of the aerodynamic disturbance in separation. The flight data identification result and the six-degree-freedom flight dynamic simulation result show that the aerodynamic model and flight data estimation methods proposed in this paper are effective. The precision of the aerodynamic database is improved by correcting with the identified dispersion aerodynamic parameter model, and the precision of the flight simulation for separation safety analysis can be also improved. © 2016, Press of Chinese Journal of Aeronautics. All right reserved.


Wang Y.,Nanjing University of Aeronautics and Astronautics | Liu L.,Chengdu Aircraft Design Institute | Xing Y.,Nanjing University of Aeronautics and Astronautics | Yang Z.,Aircraft Maintenance Engineering College
Advances in Mechanical Engineering | Year: 2017

The aerospace plane is an innovative kind of reusable aircraft, which is able to reach the low earth orbit flying like the conventional plane. Two kinds of aerospace plane wing structures are designed and parameterized for the delta wing with a strake, one of which is an equal percentage multi-web structure, and the other is a parallel multi-web structure. The two types of structure layouts were analyzed in the subsonic, transonic, supersonic, and hypersonic conditions using the finite element method. Contrasting the strength and stiffness characteristics, and estimating the structure weight, it demonstrated that the parallel multi-web wing had better performance than the equal percentage multi-web wing in terms of mechanical characteristic and weight. Then, based on the parameterized parallel multi-web wing, the thicknesses of webs, skins, and ribs were optimized to reduce the structure weight. © The Author(s) 2017.


Li Q.,Beihang University | Feng D.,Shanghai Aircraft Manufacturing Co. | Mei Z.,Chengdu Aircraft Design Institute
Jisuanji Jicheng Zhizao Xitong/Computer Integrated Manufacturing Systems, CIMS | Year: 2016

Aiming at the problems that frequent changes of aircraft configuration and relative weakness of management tools in aircraft using process, a simplified configuration management method for aircraft life cycle was presented. By taking batch type configuration and single configuration in manufacturing stage as managed objects, a combination of aircraft configuration tree with multi-view product information was used to conduct the aircraft configuration management and traceability during aircraft in service aiming at aircraft maintenance, engine parameter changes, modifications, technical changes, overhaul and others caused by maintenance and support services. Simultaneously, the product validation file for each configuration item in the aircraft configuration was established so as to conduct product data management and aircraft configuration version retroactive. The application results showed that the management played an important role in ensuring consistency of product data, improving aircraft management and reducing maintenance blindness in decision-making. © 2016, CIMS. All right reserved.


Tian Y.,Beihang University | Liu H.,Beihang University | Yin J.,Chengdu Aircraft Design Institute | Luo M.,Beihang University | And 2 more authors.
Chinese Journal of Aeronautics | Year: 2015

Simulation-based training is a promising way to train a carrier flight deck crew because of the complex and dangerous working environment. Quantitative evaluation of simulation-based training quality is vital to make simulation-based training practical for aircraft carrier marshalling. This paper develops a personal computer-based aircraft carrier marshalling simulation system and a cave automatic virtual environment (CAVE)-based immersive environment. In order to compare the training effectiveness of simulation-based training and paper-based training, a learning cubic model is proposed and a contrast experiment is carried out as well. The experimental data is analyzed based on a simplified Kirkpatrick's model. The results show that simulation-based training is better than paper-based training by 26.80% after three rounds of testing, which prove the effectiveness of simulation-based aircraft carrier marshalling training. © 2015 Production and hosting by Elsevier Ltd.


Sheng Y.,Nanjing University of Aeronautics and Astronautics | Xiong K.,Nanjing University of Aeronautics and Astronautics | Bian K.,Nanjing University of Aeronautics and Astronautics | Xiong X.,Chengdu Aircraft Design Institute | And 2 more authors.
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2013

The numerical mode of carbon fiber T-joints was built by finite element analysis software, and its cohesive mode technique. The damage formation, extension and failing process of T-joints under tensile load were investigated. Then the static tension test was carried out on the carbon fiber T-joints. The test results demonstrate that the initial damage load was between 9.8 kN and 12.0 kN, and after the damage appeared, the bearing value on the T-joints descends sharply (approximately by 27%-38%). The ultimate damage load is between 8.0 kN and 8.6 kN, which is slightly lower than the initial one, because the filling area was destroyed. Both of the numerical and test results confirm that the filling area is the weakest part of the T-joints where the damage first appears. The crack then rapidly spreads to the glue film around the filling area. It was the peeling off of the glue film that accounts mostly for the failure of T-joints.


Zhang S.-L.,Nanjing University of Aeronautics and Astronautics | Shan Y.,Nanjing University of Aeronautics and Astronautics | Zhang Y.,Chengdu Aircraft Design Institute | Zhang J.-Z.,Nanjing University of Aeronautics and Astronautics
Tuijin Jishu/Journal of Propulsion Technology | Year: 2012

To get the structure of single expansion ramp nozzle (SERN) with good pneumatic performance and small infrared radiation, based on CFD/IR numerical calculations, the effects of slots area ratio, angle of slots and nozzle pressure ratio (NPR) on the aerodynamic and infrared radiation characteristics were revealed for the SERN. The results show that on the condition of low NPR, the slots form the "aerodynamic boundary" to improve the aerodynamic performances of the nozzle. On the condition of high NPR, the hot gas enters the slots to decrease the thrust coefficient. With the slots, the infrared radiation intensity of SERN is largely decreased. The infrared radiation intensity is decreased 90% at 0° on XOY plane. With increase of slots area ratio, the infrared radiation intensity is decreased. The angle of slots has little effect on infrared radiation intensity of SERN.


Zhang P.-H.,China Aerodynamics Research And Development Center | Wang M.,Chengdu Aircraft Design Institute | Deng Y.-Q.,China Aerodynamics Research And Development Center | Chen X.-L.,China Aerodynamics Research And Development Center
Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica | Year: 2013

The method based on overset unstructured grid technique is developed for the simulation of cavity flows and store separation. The numerical simulation for typical cavity flows and separation trajectory of WPFS model have achieved good agreement with experimental data and shown a promising capability for applications. The numerical simulation of door operation and store separation trajectory has been made to investigate the unsteady effects on aerodynamic characteristics of the door flap. It is found that under certain conditions, the door's movement has a strong effect on aerodynamic characteristics of the door flap, which must be seriously considered during the door flap and control system design procedure. Under current conditions, all the store separation procedure is safe. The present research provides a technical support for door flap design and store separation evaluation.


Chen J.,Nanjing University of Aeronautics and Astronautics | Chen J.,Chengdu Aircraft Design Institute | Zhou J.,Nanjing University of Aeronautics and Astronautics
Nanjing Hangkong Hangtian Daxue Xuebao/Journal of Nanjing University of Aeronautics and Astronautics | Year: 2014

Airborne antennas system is the major contributor of aircraft scattering, which plays an important role in the aircraft stealth. Focusing on the airborne antennas design and layout for the fourth generation fighter, the design of airborne antenna system with low scattering is studied and the principles and performance are discussed. The radar cross section (RCS) is reduced and the layout design is presented to maintain the system performance. ©, 2014, Nanjing University of Aeronautics an Astronautics. All right reserved.


Cui H.,Northwestern Polytechnical University | Li Y.,Northwestern Polytechnical University | Liu Y.,Northwestern Polytechnical University | Guo J.,Chengdu Aircraft Design Institute | Xu Q.,Chengdu Aircraft Design Institute
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2010

The cohesive zone model (CZM) was employed to simulate the delamination and random crack initiation in composite joints. A bilinear cohesive law incorporating mode I, II and mixed mode was presented, which was validated by the simulation of double cantilever beam (DCB) test. Cohesive elements were inserted into the space between every two solid elements to predict the random crack initiation in the filler at the root of the composite joint. The composite joint was simulated under pull-off load, and the numerical result is in good agreement with experimental one. In addition, a series of simulation was carried out under different conditions, i.e. different strength of matrix and adhesive, different radius and different filler property. The numerical result shows that the strengths of matrix, adhesive and filler have great influence on the loading capability and the failure modes of the composite joint. The performance of the structure increases with increasing the filler radius.

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