Research on application of single moving mass in the reentry warhead maneuver

Gao, Cai; Jing, Wuxing; Wei, Pengxin

doi:10.1016/j.ast.2013.07.009

Cited by 33 publications

(6 citation statements)

References 10 publications

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“…Because aerodynamic control surfaces are prone to ablation and degradation by hypersonic flow, internal moving-mass actuation has been used to control reentry vehicles for decades [84]. Gao et al [85] investigated the combined use of moving mass and aileron control. Pitch and yaw were controlled by moving masses along two orthogonal rails, while roll was controlled by ailerons.…”

Section: Moving-mass Control In Spacecraft and Aircraftmentioning

confidence: 99%

Modeling and Control of an Articulated Multibody Aircraft

2022

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Insects use dynamic articulation and actuation of their abdomen and other appendages to augment aerodynamic flight control. These dynamic phenomena in flight serve many purposes, including maintaining balance, enhancing stability, and extending maneuverability. The behaviors have been observed and measured by biologists but have not been well modeled in a flight dynamics framework. Biological appendages are generally comparatively large, actuated in rotation, and serve multiple biological functions. Technological moving masses for flight control have tended to be compact, translational, internally mounted and dedicated to the task. Many flight characteristics of biological flyers far exceed any technological flyers on the same scale. Mathematical tools that support modern control techniques to explore and manage these actuator functions may unlock new opportunities to achieve agility. The compact tensor model of multibody aircraft flight dynamics developed here allows unified dynamic and aerodynamic simulation and control of bioinspired aircraft with wings and any number of idealized appendage masses. The demonstrated aircraft model was a dragonfly-like fixed-wing aircraft. The control effect of the moving abdomen was comparable to the control surfaces, with lateral abdominal motion substituting for an aerodynamic rudder to achieve coordinated turns. Vertical fuselage motion achieved the same effect as an elevator, and included potentially useful transient torque reactions both up and down. The best performance was achieved when both moving masses and control surfaces were employed in the control solution. An aircraft with fuselage actuation combined with conventional control surfaces could be managed with a modern optimal controller designed using the multibody flight dynamics model presented here.

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Section: Moving-mass Control In Spacecraft and Aircraftmentioning

confidence: 99%

Modeling and Control of an Articulated Multibody Aircraft

2022

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“…Menon et al 10 designed a fully actuated attitude control scheme using three moving masses that can move along the three axes of the vehicle body, respectively. Gao et al 11 proposed a polar-coordinate configuration with a single moving mass and a rotating rail to control the pitch and yaw channels. The significant work above represents the typical configurations of MMC, nevertheless, they are all built on the particle moving mass hypothesis, where the control authority and the internal space utilization of the flight vehicles are not sufficiently developed.…”

Section: Introductionmentioning

confidence: 99%

Adaptive coupled attitude-servo control for moving mass flight vehicles with high-mass-ratio

Liu

Zhou

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Moving mass flight vehicles (MMFVs) with high-mass-ratio suffer from a more severe nonlinear attitude-servo coupling than the traditional configurations that are under particle moving mass hypothesis. Therefore, the coupled attitude-servo control problem is investigated in this paper, and an adaptive backstepping sliding mode controller with extended state observers and neural-networks (ABSMC-ENN) is proposed. Based on the formulated control model with strict-feedback form, a sliding mode control law (SMC) with exponential reaching rate and a nonsingular terminal sliding mode control law (NTSMC) are combined to perform the fast and robust tracking of the command angle-of-attack. Considering the disturbances and uncertainties existing in the coupled dynamics, two nonlinear extended state observers (ESOs) are utilized to estimate the total disturbances online for compensation. To further enhance the adaptiveness and dynamic response performances of the controller in various flight conditions, two radial basis function neural networks (RBFNNs) are exploited to optimize the switching gains of the controller in real-time with performance indexes being the functions of tracking errors. Closed-loop stability of the whole system is proved via Lyapunov methodology. Comparison simulation studies considering multiple disturbances, various flight conditions, and different controllers successfully demonstrate the superiority of the ABSMC-ENN in robustness and adaptiveness.

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“…The warhead sub-system design was the concern of many studies 1–7 since it is considered the main objective of the entire design process. Different correlations among warhead sub-system definition and missile objectives were derived and found adequate for use during different missile design phases.…”

Section: Introductionmentioning

confidence: 99%

A preliminary multidisciplinary design procedure for tactical missiles

Khalil

Hashish

Abdalla

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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During missile system development, multidisciplinary design procedure is iteratively implemented based on the missile objective and target nature including internal ballistic, warhead function, and airframe configuration. By applying missile preliminary design, a good estimation for different design parameters can be obtained which will be useful through further detail design process. The aim of this paper is to build a preliminary design procedure for an unguided tactical missile that uses single-stage solid propellant motor to deliver a defined payload mass to a desired ground range. Based on data of available similar mature missile systems, two empirical formulas are developed to serve in the initial sizing of the missile with consideration of slenderness ratio, warhead mass, and desired ground range. Two different design concepts are implemented for tubular and star grains with different propellant compositions and chamber filling coefficients while the body-alone airframe configuration is adopted. The results demonstrate the capability of the proposed design procedure in defining the detailed design parameters. The impact of changing the propellant compositions and chamber filling coefficients on the obtained ground range is also explored.

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Research on application of single moving mass in the reentry warhead maneuver

Cited by 33 publications

References 10 publications

Modeling and Control of an Articulated Multibody Aircraft

Modeling and Control of an Articulated Multibody Aircraft

Adaptive coupled attitude-servo control for moving mass flight vehicles with high-mass-ratio

A preliminary multidisciplinary design procedure for tactical missiles

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