Dynamic stability conditions for a rolling flight vehicle applying continuous actuator

Koohmaskan, Yousof; Arvan, Mohammad Reza; Vali, Ahmad Reza; Behazin, Farid

doi:10.1016/j.ast.2015.02.007

Cited by 15 publications

(11 citation statements)

References 20 publications

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“…The angular motion extracted from the high dynamic process is known as coning motion, 1,2 and brings many troubles to control system design, [3][4][5][6][7] attitude resolving 8-10 and navigation. 11,12 The extra drag is generated by coning motion, and reduces the range and performance of flight carriers unexpectedly.…”

Section: Introductionmentioning

confidence: 99%

Measuring and solving real coning motion of spinning carriers

Zhang

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Coning motion of spinning carriers is a complex rotating motion with various forms that include single circular motion, double circular motion and multiple circular motion. Due to the fact that it is difficult to describe the real coning motion of double circular motion and multiple circular motion by the common method of attack angle and sideslip angle (A-S), a cone frame and cone angles are defined to describe coning motion. Through analysis of measuring the relationship between coning motion and inertial devices such as gyroscopes and accelerometers, an inertial measuring method is proposed to build the measuring equation and resolving equation. A geometry-solving algorithm of real coning motion is derived in detail, and radiuses of large circle and real cone circle are obtained as well. A flight simulation of a spinning carrier with coning motion is designed and used to verify the measuring method and the geometry-solving algorithm. The result shows that: (1) the inertial measuring method has the same validity as A-S method to describe coning motion, but is superior to A-S method for the reason of providing the rotation information of carriers; (2) due to coupling relationship, the rotating angle is equal to the subtraction of roll angle and precession angle; (3) the real precession angle and the real nutation angle are calculated by the geometry-solving algorithm, and the real coning motion is obtained finally.

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Section: Introductionmentioning

confidence: 99%

Measuring and solving real coning motion of spinning carriers

Zhang

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…This instability mechanism was further examined by Koohmaskan et al. 4 The hinge moment can be considered as an extraneous disturbance to the actuator, and its effect can be reduced using an appropriately designed controller. Hence, the original actuator controller design failed, and Figure 1 shows the unstable coning motion of the spinning missile with this controller.…”

Section: Introductionmentioning

confidence: 99%

Retuning the actuator proportional–integral–derivative controller of spinning missiles

Zhou

Yang

Zhao

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The hinge moment acting on the actuator will cause an out-of-plane moment, which is a destabilizing factor to the angular motion of spinning missiles. A new tuning criterion for the actuator controller is proposed to decrease the out-of-plane moment. It is noted that the integral element does not decrease the out-of-plane moment. A carefully designed proportional–derivative controller with some compromises can ensure the stability of the missile and provide good performance for the actuator.

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“…In addition, low requirement for flight control gyros, accelerometers, and actuators results in a relatively low cost for RAV. These advantages make this kind of vehicles become attractive and promising in military situations [1][2][3]. However, due to the rolling motion, the dynamics of pitch and yaw channels can be highly coupled with each other, which makes the attitude control design intractable.…”

Section: Introductionmentioning

confidence: 99%

“…Since the reference command for angular rate loop has been obtained in (16) in the previous section, following the process of TLC, the corresponding control for nominal system in (3) can be calculated as follows (, ) ( Next, the objective is to estimate the uncertainty 2 Δd in (23). Also, an extended state X 5 is introduced as the uncertainty 2 Δd , the system (3) is rewritten as …”

Section: B Control Design For Angular Rate Loopmentioning

confidence: 99%

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Variable structure attitude control for a rolling aerial vehicle via extended state observer

Chen

Yan

Wang

et al. 2016

2016 14th International Workshop on Variable Structure Systems (VSS)

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-A novel attitude control scheme is proposed for a rolling aerial vehicle (RAV) with large uncertainties. Firstly, the RAV highly coupled nonlinear system is separated into attitude loop and angular loop via backstepping technique. The nominal states are calculated based on the procedure of trajectory linearization control (TLC). Then, extended state observers (ESO) are applied to estimate the uncertainties in the RAV system. Meanwhile, a feedback linearization-based controller is synthesized for the attitude loop using the estimated uncertainties, and an ESO-based sliding mode controller is synthesized for the angular rate loop. The stability of the closedloop system is studied. Simulation results with comparisons are presented to demonstrate the feasibility of the proposed control scheme.

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Dynamic stability conditions for a rolling flight vehicle applying continuous actuator

Cited by 15 publications

References 20 publications

Measuring and solving real coning motion of spinning carriers

Measuring and solving real coning motion of spinning carriers

Retuning the actuator proportional–integral–derivative controller of spinning missiles

Variable structure attitude control for a rolling aerial vehicle via extended state observer

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