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1. Adaptive Back-Stepping Sliding Mode Attitude Tracking of Rigid Spacecraft with disturbances}%uthorCHN{张三丰ffil{1},李四ffil{2} | |||
LU Kunfeng,XIA Yuanqing | |||
Aviation 23 December 2012 | |||
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Abstract:The attitude tracking control problem for rigid spacecraft is investigated in thispaper. A novel adaptive approach is proposed with the utilization of sliding mode control(SMC) and backstepping techniques (BT) to not only achieve accurate attitude tracking control forspacecraft system, but also be robust against the inertia uncertainties and external disturbances. The proposed controller including the merits of SMC, BT and adaptive technique to provide fast response and accurate attitude tracking. The proposed controller is continuous, then it is chattering-free. What's more, the proposed controller does not include any information of unknown inertial matrix, then it can be used widely in practical application. Finally, simulation results are presented to illustrate effectiveness of the control strategies. | |||
TO cite this article:LU Kunfeng,XIA Yuanqing. Adaptive Back-Stepping Sliding Mode Attitude Tracking of Rigid Spacecraft with disturbances}%uthorCHN{张三丰ffil{1},李四ffil{2}[OL].[23 December 2012] http://en.paper.edu.cn/en_releasepaper/content/4502987 |
2. NTSM based finite-time control for 6DOF spacecraft formation flying system | |||
Lan Qixun,Li Shihua | |||
Aviation 13 December 2012 | |||
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Abstract:This paper considers the finite-timecontrol (FTC) problem of 6DOF spacecraft formation flying (SFF)system in the presence of externaldisturbances. Firstly, a nonsingularterminal sliding mode (NTSM) technique a finite time controller is proposed for 6DOF SFF system.Secondly, a finite-time disturbance observer (FTDOB) is introducedto estimate the disturbances , then acomposite controller which consists of a feedback controller basedon NTSM method and feed-forward compensation term based on FTDOBtechnique is obtained to ensure that the 6DOF spacecraft canreach the desired formation in finite time. The merit of theproposed method is that chattering is substantially reduced sincethe switching gain of the controller is only requiredto be greater than the bound of disturbance estimation error ratherthan that of disturbance. Finally,the effectiveness of the proposed methods are shown bysimulation results. | |||
TO cite this article:Lan Qixun,Li Shihua . NTSM based finite-time control for 6DOF spacecraft formation flying system[OL].[13 December 2012] http://en.paper.edu.cn/en_releasepaper/content/4501134 |
3. Review on the Recent Development of Multi-mode Combined Detonation Engine | |||
JIN Le,FAN Wei,WANG Ke | |||
Aviation 03 March 2012 | |||
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Abstract:In the next few years, the development of hypersonic aircraft will be the priority of national defense strategy of many countries, and the significance of the propulsion system applied on the aircraft is self-evident. At present, there are no propulsion systems for the aircraft can be used independently in wide range of Mach numbers and flight envelop. The multi-mode combined detonation engine, which consists of four modes, is a novel propulsion concept proposed at the beginning of this century for potential application on hypersonic cruise or space access. The multi-mode combined detonation engine is thought to be a promising propulsion system which can be used independently in wide range of Mach numbers and flight envelop. Recently, many countries extremely valued the development of multi-mode combined detonation engine and much progress is obtained. A review is made to the recent development of the multi-mode combined detonation engine in this study. The superiority and disadvantages are comparatively analyzed and the major progress for each mode is detailed introduced in the following text. Also, the problems need to be attention in the future development for multi-mode combined detonation engine is discussed. | |||
TO cite this article:JIN Le,FAN Wei,WANG Ke. Review on the Recent Development of Multi-mode Combined Detonation Engine[OL].[ 3 March 2012] http://en.paper.edu.cn/en_releasepaper/content/4469840 |
4. Towards Tightening Worst Case End-to-End Delay Estimates for AFDX Network | |||
Hu Guangyu,Li Jian,Hu Fei,Liu Xue,Zhu Guchuan,ZHU Guchuan | |||
Aviation 08 December 2011 | |||
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Abstract:Avionics Full Duplex Switched Ethernet (AFDX) network is an emerging Ethernet media based technology for the next generation avionic databus. The key problem of AFDX network analysis is to evaluate the worst case end-to-end data transmission delay in order to meet safety-critical application communication requirement, such as the flight control command. In this paper, we use a more accurate Virtual Link (VL) model employing Generic Cell Rate Algorithm (GCRA) to derive tighter worst case end-to-end delay bound. We further verify the proposed approach on a simulation platform. The results prove that the delay performance can be improved by the new GCRA model. | |||
TO cite this article:Hu Guangyu,Li Jian,Hu Fei, et al. Towards Tightening Worst Case End-to-End Delay Estimates for AFDX Network[OL].[ 8 December 2011] http://en.paper.edu.cn/en_releasepaper/content/4452639 |
5. Near Space SAR Imaging Using Subaperture Technique | |||
Xiao Xin,Jing Xiaojun | |||
Aviation 06 December 2011 | |||
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Abstract:Near space, airspace above the ground about 20-100 km, is higher than existing aircraft flight height and lower than existing low orbit satellite, including Stratosphere, mesosphere and part of ionosphere. Near space have some unique advantage, but currently still no effective development and application, while troposphere and low-orbit space is increasingly scarce. Near space SAR geometric model is similar with the aircraft SAR, but little difference brings completely different result. This paper discusses the near space new environment character and proposes that full aperture should be divided into subaperture to adapt new environment character. Then the novel subaperture technique is applied to Range Doppler Algorithm (RDA), and a sub-band combination technique is introduced to compose the subaperture images. Simulation results show that the proposed method indeed seems to be a promising solution to near space SAR imaging. | |||
TO cite this article:Xiao Xin,Jing Xiaojun. Near Space SAR Imaging Using Subaperture Technique[OL].[ 6 December 2011] http://en.paper.edu.cn/en_releasepaper/content/4452905 |
6. A Unified Macro- and Micro-mechanics Constitutive Model of Fully Coupled Fields | |||
SUN Zhigang | |||
Aviation 24 December 2010 | |||
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Abstract:A unified macro- and micro-mechanics constitutive model of fully coupled electro-magneto-thermo-elastic multiphase functional composites is developed in this paper. The model is based upon the hypothesis of periods, the theory of uniformity and the generalized method of cells (GMC). By using the quadratic displacements, electric potentials and magnetic potentials, the accuracy of predicting the materials' constitutive model is improved. The original GMC is also improved in this paper by adopting surface-averaged quantities to be the primary variables that replace the coefficients of micro-displacements, electric potentials and magnetic potentials. Therefore, the computation is effective and efficiency. The prediction of a functional composite's constitutive model was performed and the curves between material constants and the volume fraction of fiber were obtained. | |||
TO cite this article:SUN Zhigang. A Unified Macro- and Micro-mechanics Constitutive Model of Fully Coupled Fields[OL].[24 December 2010] http://en.paper.edu.cn/en_releasepaper/content/4400790 |
7. The helicopter blades aeroelastic stability optimization | |||
Wang Hongzhou ,Liu Yong,Zhang Chenglin | |||
Aviation 30 June 2009 | |||
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Abstract:it deduces the helicopter rotor blade motion and give the aeroelastic stabile condition. The variables is the offset of hinge pretwist angle, coning angle and element mass of blade. The constrains are the stable parameter and frequencies. The objective function is to minimize the blade mass. Using the Sequential Quadratic Programming(NLPQL)algorithm and reliable optimization. It is the result that the blade mass is increased under the constraints being satisfied and all the design parameter’s reliability is 95%. | |||
TO cite this article:Wang Hongzhou ,Liu Yong,Zhang Chenglin. The helicopter blades aeroelastic stability optimization [OL].[30 June 2009] http://en.paper.edu.cn/en_releasepaper/content/33500 |
8. Research on Sliding Mode Control of Folding-Wing Missile’s Lateral Overload | |||
Yang Liang,Yang Jianying | |||
Aviation 23 February 2009 | |||
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Abstract:Considering that the folding-wing missile deploys its wings in short time, and such a transient but complicated process has a strong influence on its math model, we simplify the process into model\ | |||
TO cite this article:Yang Liang,Yang Jianying. Research on Sliding Mode Control of Folding-Wing Missile’s Lateral Overload[OL].[23 February 2009] http://en.paper.edu.cn/en_releasepaper/content/29503 |
9. Experimental Research on Supersonic Combustion in Resistance Heated Facility | |||
Le Jialing,Song Wenyan,Zhong Zipeng | |||
Aviation 03 March 2008 | |||
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Abstract:The resistance heated facility for scramjet combustor experiment is researched in Northwest Polytechnical University. The characteristic and operating parameter of the facility are shown. The maximum total temperature of airflow in the exit of the resistance heater can reach about 1000K corresponding to mass flow rate of 0.73kg/s, heater electric power of 750KW. The preliminary test results of the hydrogen, ethylene and kerosene ignition for the model of scramjet combustor are given at different equivalence ratios. Successful ignition and sustained main stream combustion is achieved with normal fuel injection in combustor entrance total temperature about 1000K, Mach number 2.0 and total pressure 0.8MPa. The preliminary numerical simulation results of flow field of hydrogen combustion are presented. | |||
TO cite this article:Le Jialing,Song Wenyan,Zhong Zipeng. Experimental Research on Supersonic Combustion in Resistance Heated Facility[OL].[ 3 March 2008] http://en.paper.edu.cn/en_releasepaper/content/18960 |
10. PERFORMANCE SIMULTION OF WAVERIDER FOREBODY INTEGRATED WITH HYPERSONIC INLET | |||
Hong Xiao | |||
Aviation 18 November 2005 | |||
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Abstract:The calculation method to compute flow field from given shock wave was developed. With the method, intersected cones that can generate three closed shock waves were designed. The waverider forebody that can generate three attached shock waves and a comparative reference waverider forebody that can generate one attached shock wave and two plane shock waves were designed. To better understand two forebodies’ performance, three dimensional flow field calculation of two forebodies integrated with hypersonic inlet was conducted. The computational results showed that the performance of original waverider with three attached shock wave was great better than that of comparative reference waverider. Compared with the comparative reference model, the flow coefficient and the recovery coefficient of total pressure were increased by 15.38% and 7%, repectively. The uniformity coefficient of inlet outlet was increased by 8.8%.Two waverider forebodies integrated with hypersonic inlet showed better perforemance in high mach number and attack angle than that in low mach number and negative attack angle. CFD predictions showed that the design mach number of waverider forebody should be great than the flight mach number and the design attack angle should be less than that of flight condition. | |||
TO cite this article:Hong Xiao. PERFORMANCE SIMULTION OF WAVERIDER FOREBODY INTEGRATED WITH HYPERSONIC INLET[OL].[18 November 2005] http://en.paper.edu.cn/en_releasepaper/content/3693 |
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