Aerodynamic design and performance of a bent-axis geometry vehicle

Rutledge, Walter; Polansky, Gary F.; Clark, Edward L.

doi:10.2514/3.25997

Cited by 5 publications

(3 citation statements)

References 7 publications

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“…In [5] it has demonstrated that these hinge moments can be controlled to within acceptable design specifications with proper selections of vehicle center of gravity location or vehicle tail section length. However, the result is obtained under the assumption of constant freestream conditions and ideal gas behavior, neglecting the effects of boundary layer transition and base pressure.…”

Section: Introductionmentioning

confidence: 97%

“…In order to design the variable-bend-tail geometry vehicle for level flight missions, which is governed by the ability of the hinge actuators, to overcome the aerodynamic hinge moments experienced by the movable aft section or tail section, many works [5][6][7][8] has researched on the aerodynamics design and performance analysis of the bentaxis geometry vehicle and variable-bend-tail vehicle. In [5] it has demonstrated that these hinge moments can be controlled to within acceptable design specifications with proper selections of vehicle center of gravity location or vehicle tail section length.…”

Section: Introductionmentioning

confidence: 99%

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Attitude Controller Design for Variable-Bend-Tail Vehicle

Guo

Zhou

2009

2009 International Conference on Intelligent Human-Machine Systems and Cybernetics

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According to the problem of attitude control for variable-bend-tail vehicle, the mathematics models are established and the robust attitude control system is proposed based on variable structure control theory. The movement model of the bend tail section is derived from considering the coupling mutual action between tail and front of vehicle, and the nonlinear mathematics dynamic model of variable-bendtail vehicle is built by introducing the semi-body frame and the semi-velocity frame adopting the muti-rigid body dynamics model method. The acceleration control system for variablebend-tail vehicle is designed to improve the preciseness and robustness of the whole attitude control system by applying the tail deflection angular rate applying variable structure control theory. Finally an illustrative example is given to show preliminarily that the model is valid and that the attitude control scheme can meet the need of performance of system and have the capabilities of the celerity and robustness.

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Section: Introductionmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

Attitude Controller Design for Variable-Bend-Tail Vehicle

Guo

Zhou

2009

2009 International Conference on Intelligent Human-Machine Systems and Cybernetics

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“…1 shows that the inertial load from the mass of the nose cone tends to balance the lift load and the sum of all torques around the hinge points is zero when the design condition is found. However, because of low mass of canard fin, inertial force F Ifin much less than lift force F Lfin and balancing of hinge moments is not feasible [3], [4].…”

Section: Introductionmentioning

confidence: 99%

Conceptual design of a type fuze of oscillating nose cone for two-dimension trajectory correction

Han

Wang

2011

2011 6th IEEE Conference on Industrial Electronics and Applications

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A design scheme for two-dimension trajectory correction fuze, actuating by oscillating its nose cone was proposed. Based on the design criterions of compatibility, safety, reliability and economics the structure of oscillating nose cone integrating with the original fuze system was built. The dynamic simulations for some low rolling rocket were performed by using the six degree-of-freedom control ballistic equations. The results show that the principle of oscillating nose cone for fuze is able to realize the function of two-dimension trajectory correction.

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Aerodynamic Analysis of a Vehicle Tanker

Buil

Castejón

2009

Journal of Fluids Engineering

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The aim of this article is the presentation of a series of aerodynamic improvements for semitrailer tankers, which reduce the aerodynamic resistance of these vehicles, and, consequently, result in a positive impact on fuel consumption, which is substantially reduced (up to 11%). To make the analysis the computational fluid dynamics (CFD) methodology, using FLUENT, has been used since it allows simulating some geometries and modifications of the geometry without making physical prototypes that considerably increase the time and the economical resources needed. Three improvements are studied: the aerodynamic front, the undercarriage skirt, and the final box adaptor. First they are studied in isolation, so that the independent contribution of each improvement can be appreciated, while helping in the selection of the most convenient one. With the aerodynamic front the drag coefficient has a reduction of 6.13%, with the underskirt 9.6%, and with the boat tail 7.72%. Finally, all the improvements are jointly examined, resulting in a decrease of up to 23% in aerodynamic drag coefficient.

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Aerodynamic design and performance of a bent-axis geometry vehicle

Cited by 5 publications

References 7 publications

Attitude Controller Design for Variable-Bend-Tail Vehicle

Attitude Controller Design for Variable-Bend-Tail Vehicle

Conceptual design of a type fuze of oscillating nose cone for two-dimension trajectory correction

Aerodynamic Analysis of a Vehicle Tanker

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