An improved load relief wind model for the Delta launch vehicle

Blanchet, Pat; Bartos, Bruce

doi:10.2514/6.2001-841

Cited by 7 publications

(2 citation statements)

References 3 publications

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“…The angle of attack sensor senses the accessional angle which produced by both wind profiles and the flight dynamic angle of attack. The initial control law could be expressed as Equation (8), and after correction the control law becomes Equation (9).…”

Section: B Load Relief System Of Atlas/centaur Launch Vehiclementioning

confidence: 99%

Control Enhanced and Parameterized Load Relief technology for a Launch Vehicle

Yang

Tang

2015

AIAA Modeling and Simulation Technologies Conference

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The major disturbance to the launch vehicle during the high dynamic pressure period is inflight winds, and it causes extra aerodynamic load and significant magnitude of bending moment. Load relief system is used to decrease the aerodynamic load by reducing the angle of attack to increase the launching capability. This paper focuses on the load control technology when the launch vehicle passes through the strong wind area. Firstly, by analyzing and simulating the load relief system of the traditional launch vehicles including long march 3A, atlas/centaur, Saturn Ⅴ, titan Ⅲ and Ariane 5, this paper points out the advantages and disadvantages of classical passive trajectory correction method and four active load control methods. Besides, the control enhanced and parameterized technology (CEPT) is putted forward from the active disturbance rejection control (ADRC) and load relief cell. On the one hand, the error signal observed by the modified state observer is introduced to compensate the uncertain error signal observed by extended state observer in the ADRC loop; on the other hand, the load relief cell is introduced into the initial control system to enhance the load relief capability; at last, the control law of the CEPT controller is parameterized, a method is given to select the gains in the control law, and the load restriction effect under the combination of CEPT and initial controller is shown. Taking a kind of liquid launch vehicle as an example, and considering the inherent elastic vibration and liquid sloshing, this paper compares the load relief effect under different control architectures motioned above. The simulation result indicates that the CEPT controller expands the range of the parameters, enhances the disturbance rejection capacity for the flight control system, and efficiently improves the load control effect.

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Section: B Load Relief System Of Atlas/centaur Launch Vehiclementioning

confidence: 99%

Control Enhanced and Parameterized Load Relief technology for a Launch Vehicle

Yang

Tang

2015

AIAA Modeling and Simulation Technologies Conference

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“…The open-loop method uses the information of wind data to design the optimal trajectory that minimizes the aerodynamic load on the launch vehicle prior to the launch. 2,[5][6][7] The most important drawback of the open-loop load relief method is its inherent vulnerability to unexpected changes of the wind profile. A closed-loop method was developed to overcome this weakness.…”

Section: Introductionmentioning

confidence: 99%

Load relief control of launch vehicle using aerodynamic angle estimation

Park

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the load relief scheme around the period of the maximum dynamic pressure and the traditional minimum-drift scheme during the other period is proposed. An aerodynamic angle estimator is also developed using a Kalman filter for the feedback of the load relief control. Numerical simulation is conducted to demonstrate the performance of the proposed strategy as well as the potential benefits.

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