VERIFICATION OF A COMPUTATIONAL DYNAMIC MODEL OF A LAUNCH VEHICLE STRUCTURE

2018 ◽  
Vol 49 (1) ◽  
pp. 93-103
Author(s):  
Aleksandr Georgievich Bakhtin ◽  
Vasilii Aleksandrovich Titov
Keyword(s):  
Dynamic Model ◽  
Launch Vehicle ◽  
Vehicle Structure

scholarly journals Attenuation of the effects produced by the bending modes of a flexible launch vehicle using second order filters

2020 ◽  
Vol 2 (1) ◽  
pp. 48-55
Author(s):  
Ioana-Carmen Boglis ◽  
Adrian M. Stoica
Keyword(s):  
Adaptive Control ◽  
Dynamic Model ◽  
Control Algorithm ◽  
Launch Vehicle ◽  
Model Reference Adaptive Control ◽  
Model Reference ◽  
Bending Modes ◽  
Adaptive Control Algorithm ◽  
Model Reference Adaptive

This article describes the application of an adaptive control algorithm for the atmospheric phase control of a launch vehicle. A dynamic model representing the pitch motion of the launch vehicle is introduced. As the bending modes can cause instability, the first threebending modes are modelled. A case study on design of the bending filters for a flexible launch vehicle using a model reference adaptive control is conducted to demonstrate its effectiveness.

Characteristics Analysis and Optimization of Flying-Wing Vehicle Structure

2014 ◽  
Vol 1077 ◽  
pp. 177-184 ◽  
Author(s):  
Hong Xia Zhou ◽  
Bin Liu
Keyword(s):  
Dynamic Model ◽  
Axial Force ◽  
Structural Characteristics ◽  
Torsional Rigidity ◽  
Bending Rigidity ◽  
Static Test ◽  
Wing Span ◽  
Resonance Test ◽  
Vehicle Structure ◽  
Characteristics Analysis

To study structural characteristics of flying-wing vehicle, static and dynamic model of half wing span, static and dynamic model of all wing span, optimization model were established. Based on associated static test and ground resonance test data, these models were modified to implement static, dynamic and optimization analysis. Results demonstrated that structural bending and torsional deformations are mainly at outer wing surface. Torsion at inner wing is positive, while torsion at outer wing is negative. Total spar axial force along the wing span increases gradually from inner wing to outer wing and then decreases gradually after reaching the inner-outer wing interface. After axial force is transmitted to the inner wing, it is going to concentrate at the rear spar obviously. Structural bending rigidity and torsional rigidity satisfy requirements of both static force and flutter, without flutter problem of main structural mode. Viewed from the optimization size, ±45° and 0° skin at inner-outer wing turn thickens significantly. This can increase structural bending and torsional rigidity, which is good for satisfying multiple constraints comprehensively.

The Displacement Measurement of Ground Wind Loads for Launch Vehicle

2014 ◽  
Vol 568-570 ◽  
pp. 100-105
Author(s):  
Tao Wang ◽  
Ze Huan Huang ◽  
Hui Zhang ◽  
Bin Zheng
Keyword(s):  
Image Processing ◽  
Digital Image Processing ◽  
Pressure Measurement ◽  
Measurement Model ◽  
Launch Vehicle ◽  
Displacement Measurement ◽  
Wind Pressure ◽  
Wind Loads ◽  
Structure Model ◽  
Vehicle Structure

This paper presented a method of the displacement measurement of ground wind loads for launch vehicle based on laser and Digital Image Processing Technology. The launch vehicle structure model was built by calculating the wind pressure. Measurement model and algorithm for single laser were given. In view of nonrigid component, a method for computing the centroid displacement was presented. Error analysis and error reducing measures were preliminarily discussed.

Dynamic analysis for vertical soft landing of reusable launch vehicle with landing strut flexibility

2018 ◽  
Vol 233 (4) ◽  
pp. 1377-1396 ◽  
Author(s):  
Shuai Yue ◽  
Hong Nie ◽  
Ming Zhang ◽  
Mingyang Huang ◽  
He Zhu ◽  
...  
Keyword(s):  
Dynamic Model ◽  
Friction Force ◽  
Coupling Model ◽  
Launch Vehicle ◽  
Force Model ◽  
Soft Landing ◽  
Inertia Moment ◽  
Reusable Launch Vehicle ◽  
Beam Type ◽  
Tip Mass

Based on oleo-honeycomb dampers, a 6-DOF vertical soft landing dynamic model for reusable launch vehicle considering landing strut flexibility is constructed. In order to better analyze the lateral deflection and friction force of the “cantilever beam” type landing strut, a new model for strut is incorporated. Static analysis is first performed based on the rotation angle compatibility equations to attain the equivalent inertia moment. Then the strut lateral vibration model and friction force model are obtained by simplifying it as viscoelastic beam with a tip mass. After that, the ADAMS models are established to perform the comparison and verification analysis of the 6-DOF dynamic model. The results show that the results of 6-DOF dynamic model can approximately approach to the results of rigid-flex coupling model established in ADAMS. Furthermore, the research of the influence of assembly gap between cylinders and bearings, bearing’s elastic modulus, friction coefficient and initial overlapping length on the vehicle landing performance is carried out. The results show that each parameter has different influence on the landing performance, and a reasonable selection of these parameters accordingly enables a higher landing performance.

Automation of Transient Flight Loads Estimation for Spacecraft Design

1993 ◽  
Author(s):  
Srinivas Kodiyalam
Keyword(s):  
Dynamic Model ◽  
Launch Vehicle ◽  
Vehicle Dynamic ◽  
Spacecraft Design ◽  
Solar Arrays ◽  
Modal Model ◽  
Flight Loads ◽  
Stick Model ◽  
Fixed Interface ◽  
Vehicle Dynamic Model

Abstract Quick and effective estimation of transient dynamic flight loads is a critical part of the spacecraft design process. In this work, a transient base drive procedure is used to estimate the flight loads on a spacecraft, during the spacecraft design iterations. In this base drive procedure, only the spacecraft dynamic model is used as against a coupled spacecraft-launch vehicle dynamic model. The well established fixed interface modal model representation, with a determinate interface, is used for the spacecraft substructure. The second part of this paper is on a new, constrained optimization based procedure for notching the qualification level sine vibration loads, specified by the launch vehicle organization. Finally, the base drive and the sine vibration notch procedures are demonstrated on a spacecraft stick model and a spacecraft structure with solar arrays.

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