Showing papers in "Aerospace Science and Technology in 2015"

TL;DR: In this article, the authors described experimental research into the initiation and propagation of rotating detonation for liquid kerosene and gaseous air mixtures, where the main subsystems were described: fuel and air feeding system, initiation and measurement system, and methods of measurement and calculation of the mass flow rate for each mixture component.

TL;DR: In this paper, the authors have considered the three dimensional heat and mass transfer with magnetic effects for the flow of a nanofluid between two parallel plates in a rotating system and applied Homotopy Analysis Method (HAM) to see the validity of analytical solution, a numerical solution using RK-4 method coupled with shooting method has also been sought Both the solutions are found to be in excellent agreement to capture the effects of involved physical parameters graphical representation of the flow are included with comprehensive discussions.

TL;DR: In this article, the authors investigated linear thermal buckling of a composite conical shell made from a polymeric matrix and reinforced with carbon nanotube fibres, under the assumption of first order shear deformation shell theory, Donnell kinematic assumptions and von Karman type of geometrical nonlinearity.

TL;DR: The experimental results prove that the proposed three-dimensional real-time path planning method is applicable to various dynamic environments.

TL;DR: In this article, a second order sliding mode controller based on geometric homogeneity approach is proposed to design a globally robust and globally finite-time convergent attitude controller for a rigid spacecraft.

TL;DR: The proposed mixture of experts (ME) approach, which is based on the divide-and-conquer principle, is concluded that the ME technique is both necessary and sufficient for modeling the aerodynamic coefficients for surrogate-based mission analysis.

TL;DR: In this paper, a nonlinear adaptive feedback control law is developed by employing special potential functions and a kind of time-varying sliding manifold, to enable the spacecraft formation in a specific configuration by taking into account the obstacle avoidance requirement while tracking a moving target in a way of cooperation or not.

TL;DR: An integrated robust adaptive controller for 6DOF relative motion is designed, where parametric uncertainties of the chaser spacecraft are estimated online by using gradient adaptive method, and dynamic coupling effect resulting from unknown inertial parameters of the target is handled with a norm-estimation-based adaptive method.

TL;DR: In this paper, a new continuous robust impact angle constraint guidance law with finite-time convergence is proposed for intercepting maneuvering targets with unknown acceleration bounds, which can achieve more accurate interception with a wide range of intercept angles and superior overall performance than traditional NTSM algorithm.

TL;DR: In this paper, an optimisation strategy is developed to account for a known possible morphing system within the aerodynamic optimisation process itself, which allows for the limitations of the system to be considered from the start of the design process.

TL;DR: In this article, the effects of the wall temperature and Prandtl number on the predicted results have been analyzed, as well as the grid independency analysis, and the influence of cavity location, the length-to-depth ratio of the cavity and the molecular weight of the injectant on the flow field properties have been investigated.

TL;DR: The need for a higher TRL category indicating a proven technology demonstrated through extended operations, and its definition and sufficiency are considered.

TL;DR: In this paper, a computationally low-cost isogeometric finite element model was proposed to study the thermal and thermo-mechanical behavior of bi-directional functionally graded material (FGM) beam structures.

TL;DR: In this paper, an adaptive fuzzy fractional order sliding mode control (FFOSMC) is introduced for a high performance servo actuation system that is subjected to aerodynamic loads and uncertainties.

TL;DR: In this article, an experimental program was conducted to study the low Reynolds number aerodynamics of ten UAVs having aspect ratios ranging from 2 to 5. The measurements showed that all wings exhibited sensitivity to changes in aspect ratio and Reynolds number and no hysteresis in angle of attack was observed over the range of Reynolds numbers tested.

TL;DR: In this paper, a numerical investigation is performed to analyse the suppression of boundary layer separation first on a NACA 0015 airfoil and subsequently in a highly loaded subsonic compressor stator cascade using two different active flow control techniques: synthetic jet actuators (SJA) and continuous jet actuator (CJA).

TL;DR: In this paper, the damping effect of a Helmholtz resonator is optimized by tuning its neck area in real-time to stabilize an unstable combustion system over a broad frequency range.

TL;DR: In this paper, a distributed cooperative guidance with arbitrary impact angle constraint is proposed, which consists of a local control term to achieve zero miss distance and the desired impact angle, and a cooperative control term for achieving the consensus of impact time.

TL;DR: In this article, robust optimal position and attitude controllers are designed by using an integral sliding mode control method to combine a second order sliding mode controller with the derived inverse optimal controller or optimal Lyapunov controller.

TL;DR: In this article, an integrated guidance and control law for multiple missiles attacking targets cooperatively is developed, using the dynamic surface control theory and disturbance observation technology, and the modeling error, aerodynamic parameters perturbation and external disturbance are regarded as system uncertainties.

TL;DR: In this paper, a leader-following formation control and heading synchronization for a group of quadcopters is proposed. And the leader quadcopter moves along a prescribed path to guide the formation.

TL;DR: In this article, a novel method of optimizing the control parameters in the automatic carrier landing system of F/A-18A is developed, which is based on simplified Brain Storming Optimization (BSO) algorithm.

TL;DR: An overview of the capabilities of a new open-source pre- and post-processing tool for Computational Fluid Dynamics simulations, called Cassiopee, and its architecture and handled data, which are based on CGNS standard are described.

TL;DR: In this paper, a neural network approach for modeling of unsteady aerodynamic characteristics in a wide angle-of-attack range is considered in a transonic cruiser, which is a canard configuration with forced small-amplitude oscillations.

TL;DR: In this article, the effect of equivalence ratio and fuel distribution on combustion performance of the dual-mode scramjet engine was investigated by numerical simulations and experiments in the presence of kerosene injected in front of the first cavity.

TL;DR: In this article, an adaptive decoupling synchronous controller (ADSC) is proposed to eliminate the coupling term between hydraulic actuators and electro-hydrostatic actuators, which can greatly improve the system reliability and effectively avoid potential commonmode/common cause (CM/CC) failure.

TL;DR: In this article, a hybrid controller is developed and applied to a quadrotor to attenuate the chattering effects, and to achieve finite time convergence and robustness aims, which has been proved using the classic Lyapunov criterion.

TL;DR: In this paper, thermal buckling analysis of functionally graded rectangular nanoplates is investigated, in order to consider the size effects, nonlocal elasticity theory and third-order shear deformation theory are used.

TL;DR: In this paper, a simple nonlinear proportional-derivative-type (PD-type) saturated finite-time controller (SFTC) is proposed for attitude stabilization of a rigid spacecraft.

TL;DR: In this article, a robust optimization algorithm for computationally efficient airfoil design under mixed (inherent and epistemic) uncertainty using a multi-fidelity approach is presented, where both the design and the mixed uncertain parameters are the independent variables of the surrogate model.