3 edition of Thermal analysis of a hypersonic wing test structure found in the catalog.
Thermal analysis of a hypersonic wing test structure
by Aeronautical Engineering Dept., California Polytechnic State University in San Luis Obispo, CA
Written in English
|Statement||prepared by Dr. Doral R. Sandlin, Neil J. Swanson, Jr.|
|Series||NASA-CR -- 185319., NASA contractor report -- NASA CR-185319.|
|Contributions||Swanson, Neil J., United States. National Aeronautics and Space Administration.|
|The Physical Object|
The aero-thermal analysis of a hypersonic vehicle is of fundamental interest for designing its thermal protection system. The aero-thermal environment predictions over several critical regions of the hypothesized lifting body vehicle, including the stagnation region of the nose-cap, cylindrically swept leading edges, fuselage-upper, and fuselage-lower surfaces, are discussed. Consumer Product Design Course covered in the Program make the students to understand various stages of Design process like design concept creation, function creation, Ergonomics, Detailed design, Virtual Validation, prototype & testing methodology, History of .
The longest previous hypersonic scramjet flight test performed by a NASA X in was faster, but lasted only about 12 seconds and used less logistically supportable hydrogen fuel. Following an extensive analysis of flight data from the XA's first hypersonic flight test, slight modifications are planned to strengthen the rear seal area. Aerothermoelastic analysis of the hypersonic wing shows that the structure may bear a severely worsening thermal environment when there is uncertainty in heat flux during hypersonic flight. Not merely the average temperature, but also the temperature gradient distribution of the structure rises, which might make designs created using.
Product and Tool Design course at Hypersonic Tech Solutions is a specialized branch aims to concentrates on new product development of any product line such as Consumer product line/ medical device/Industrial products which are used in day to day life. It also covers the tool design required for mass production of products. The tool design deals with design of Punch & dies (metal stamping. To fulfill the design objective of a structure and thermal protection system, accurate load environment prediction is very important, so we present a high-fidelity aerothermoelastic load calculation method based on a partitioned computational fluid dynamics/computational structural dynamics/computational thermal dynamics (CFD/CSD/CTD) coupling analysis. For the data transformation between the.
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The three-dimensional finite element modeling techniques developed for the thermal analysis of a hypersonic wing test structure (HWTS) are described. The computed results are compared to measured test : Doral R. Sandlin, Neil J.
Swanson. Get this from a library. Thermal analysis of a hypersonic wing test structure: final technical report, October - April [Doral R Sandlin; Swanson, Neil J.; United States.
National Aeronautics and Space Administration.]. Get this from a library. Development of a thermal and structural model for a NASTRAN finite-element analysis of a hypersonic wing test structure. [Jaap Lameʹris; Dryden Flight Research Facility.].
A fully integrated finite element method encompassing structural, thermal, and aerodynamic analysis was applied to the evaluation of the Hypersonic Wing Test Structure (HWTS), a heavily instrumented demonstration component simulating the wing of a Mach-8 aircraft.
The HWTS was tested under a combination of mechanical loads and heating time : Glenn Morris. NASA Contractor Report DeVE!lo~)ment of a Thermal and Stru~ctural Model for a NASTRAN Finit:e-E~lement Analysis of a Wing Test Structure Jaap Lameris The University of Kansas Center for Research, Inc., Lawrence, Kansas While there are numerous texts and papers on thermal stress analysis, practical examples and experience on light gage aircraft structures are limited.
A research program has been undertaken to demonstrate the present state of the art, verify methods of analysis, gain experience in their use, and develop engineering judgement in thermal stress analysis.
In reference , the aeroelastic and aerothermoelastic analysis of the hypersonic wing was carried out using 5 structural Figure 7, case 1 presents the first five vibration modes and frequencies of the wing without considering aerodynamic heating 2 presents the first five vibration modes and frequencies of the heated wing at and.
Development and Testing of Hypersonic Flutter Test Capability. Time-adaptive loosely coupled analysis on fluid–thermal–structural behaviors of hypersonic wing structures under sustained aeroheating.
Aerospace Science and Technology, Vol. 78 Modeling and Analysis of Fluid-Thermal-Structure Coupling Problems for Hypersonic Vehicles. wing panel. A fourth thermal stress analysis was performed on a mid-span wing segment.
Thermal stress analysis and panel deformation results are presented. Keywords: Thermal stress, fore wing panel, aft wing panel, unit panel, mid wing. Introduction 1 Hypersonic flight vehicles are subjected to severe aerodynamic heating during flights.
A thermal-vibration test system is established by combining the high-temperature transient heating simulation system and vibration test apparatus, and this system can carry out experimental research on the thermal modal of high-temperature-resistant composite wing structure of hypersonic flight vehicles under high temperature environment with °C.
Thermal analysis includes nonlinear transient heat conduction with radiation on the external wing surface and inside the internal cavities of the structure. Thermal effects are included in structural analysis through dependence of material prop-erties on temperature and through geometric effects due to thermal stresses.
Numerical test cases. Hypersonic wing test structure design, analysis, and fabrication transient structural thermal calculations, extensive NASTRAN computer modeling, and structural optimization. After geometry was established for the total wing, part of the wing (85 sq ft) was designed, fabricated, and assembled into a test structure to experimentally verify.
The design and optimization of hypersonic aircraft is severely impacted by the high temperatures encountered during flight as they can lead to high thermal stresses and a significant reduction in material strength and stiffness. This reduction in rigidity of the structure requires innovative structural concepts and a stronger focus on aeroelastic deformations in the early design and.
To perform heat-transfer analysis of hypersonic aerospace vehicle structure with different honeycomb cell geometry. Key words: hexagonal core, square core, Inconel sandwich structure, Adhesive, ANSYS 1 Introduction Hypersonic flight vehicles such as the Space Shuttle orbiter are subjected to severe aerodynamic heating during flight missions.
will be able to validate hypersonic aerothermodynamic design database and passenger experiments, including Thermal Protection System (TPS) and hot structures.
The flight test bed, named VIPER-G1, is a prototype winged vehicle, embodying the critical technologies. the thermal protection system design for the hypersonic flight vehicle. InCuller carried out the fluid-thermal-structure simulation on the hypersonic flight vehicle and validate.
Structural temperatures were measured on a hypersonic wing test structure during a heating test that simulated a Mach 8 thermal environment. Measured data are compared to design calculations and temperature predictions obtained from a finite-difference thermal analysis.
Therefore, thermal buckling analysis of the Hyper-X wing panels could be reduced to the thermal buckling analysis of that unit panel. An example of a recent hot structure is the new hypersonic flight research vehicle called Hyper-X reaching the test velocity (of Mach 7.
The development of a thermal and structural model for a hypersonic wing test structure using the NASTRAN finite-element method as its primary analytical tool is described.
A detailed analysis was defined to obtain the temperature and thermal stress distribution in the whole wing as well as the five upper and lower root panels. Topics will include an introduction to hypersonic flight from a historical perspective, HCV and TAV performance requirements, design methodology, aerodynamics, propulsion, structures, flight mechanics/stability & control, thermal management, design convergence, off-design performance analysis, the role of CFD, ground & flight testing, and.
A. Misra, in Lightweight Composite Structures in Transport, Hypersonic air-breathing propulsion. Hypersonic vehicles fly faster than five times the speed of sound and can enable a new class of flight vehicles that enable faster access to space, rapid military response at long range, and faster means of commercial air travel.
Traditionally, rocket boosters have been used for.Time-adaptive loosely coupled analysis on fluid–thermal–structural behaviors of hypersonic wing structures under sustained aeroheating Aerospace Science and Technology, Vol.
78 Design of the Nonlinear Cruise Controllers for Hypersonic Vehicle.A Hypersonic Structure. to which the X's heat-sink wing structure was subjected during a high-heating mission. Dark areas indicate the higher temperature. More than 75 flights of the X to high temperatures have demonstrated the soundness of the basic load-thermal-stress analysis.
Much remains unknown about the magnitude of the.