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Inventi Impact - Aerospace Engineering

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    Journal Scope:

    Quarterly published in print and online ‘Inventi Rapid/Impact: Aerospace Engineering’ publishes high quality unpublished as well as high impact pre-published research and reviews catering to the needs of researchers and professionals. It focuses on multidimensional aspects of aerospace engineering, particularly - aerodynamics, computational fluid dynamics, wind tunnel testing of buildings and structures, aerospace structures and materials, dynamics and control, real-time data acquisition, space engineering and construction, lunar base construction, field and remote sensing, robotics, etc

  • ACTUATOR FAULT DIAGNOSIS IN A BOEING 747 MODEL VIA ADAPTIVE MODIFIED TWO-STAGE KALMAN FILTER
    Fikret Caliskan, Youmin Zhang, N Eva Wu, Jong-Yeob Shin    Download Full Text

    An adaptive modified two-stage linear Kalman filtering algorithm is utilized to identify the loss of control effectiveness and the magnitude of low degree of stuck faults in a closed-loop nonlinear B747 aircraft. Control effectiveness factors and stuck magnitudes are used to quantify faults entering control systems through actuators. Pseudorandomexcitation inputs are used to help distinguish parti...

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  • AIRLOADS CORRELATION OF THE UH-60A ROTOR INSIDE THE 40- BY 80-FOOT WIND TUNNEL
    I-Chung Chang, Thomas R Norman, Ethan A Romander    Download Full Text

    The presented research validates the capability of a loosely coupled computational fluid dynamics (CFD) and comprehensive rotorcraft analysis (CRA) code to calculate the flowfield around a rotor and test standmounted inside a wind tunnel.TheCFD/CRA predictions for the Full-Scale UH-60A Airloads Rotor inside the National Full-Scale Aerodynamics Complex (NFAC) 40- by 80- Foot Wind Tunnel at NASA Ame...

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  • NUMERICAL CALCULATION OF EFFECT OF ELASTIC DEFORMATION ON AERODYNAMIC CHARACTERISTICS OF A ROCKET
    Laith K Abbas, Dongyang Chen, Xiaoting Rui    Download Full Text

    The application and workflow of Computational Fluid Dynamics (CFD)/Computational Structure Dynamics (CSD) on solving the static aeroelastic problem of a slender rocket are introduced. To predict static aeroelastic behavior accurately, two-way coupling and inertia relief methods are used to calculate the static deformations and aerodynamic characteristics of the deformed rocket. The aerodynamic coe...

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  • AN EFFICIENT NONLINEAR FILTER FOR SPACECRAFT ATTITUDE ESTIMATION
    Bing Liu, Zhen Chen, Xiangdong Liu, Fan Yang    Download Full Text

    Increasing the computational efficiency of attitude estimation is a critical problem related to modern spacecraft, especially for those with limited computing resources. In this paper, a computationally efficient nonlinear attitude estimation strategy based on the vector observations is proposed.The Rodrigues parameter is chosen as the local error attitude parameter, to maintain the normalization ...

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  • BOOST FULL BRIDGE BIDIRECTIONAL DC/DC CONVERTER FOR SUPERVISED AERONAUTICAL APPLICATIONS
    Alberto Cavallo, Beniamino Guida, Luigi Rubino    Download Full Text

    The More Electrical Aircraft concept requires electronic devices able to efficiently and safely convert electrical power between different voltage levels. Theentire realization of a bidirectional DC/DC converter, fromdesign to validation phase, is here discussed in detail. First, a boost full bridge electrical structure is selected, adopting a Parallel Input Parallel Output (PIPO) interleaving tec...

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  • WIND TUNNEL TESTING ON START/UNSTART CHARACTERISTICS OF FINITE SUPERSONIC BIPLANE WING
    Hiroshi Yamashita, Naoshi Kuratani, Masahito Yonezawa, Toshihiro Ogawa, Hiroki Nagai, Keisuke Asai, Shigeru Obayashi    Download Full Text

    This study describes the start/unstart characteristics of a finite and rectangular supersonic biplane wing. Two wing models were tested in wind tunnels with aspect ratios of 0.75 (model A) and 2.5 (model B). The models were composed of a Busemann biplane section. The tests were carried out using supersonic and transonic wind tunnels over a Mach number range of 0.3 = ??8 = 2.3 with angles of att...

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