Army hypersonic compact kinetic-energy missile laser window design

Russell, G.; Cayson, Stephen C.; Jones, Michael W. M.; Carriger, Wendy; Mitchell, Robert; Strobel, Forrest; Rembert, Michael; Gibson, David

doi:10.1117/12.488475

Cited by 4 publications

(3 citation statements)

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“…From Fig. 8, we can see that the temperature is in good agreement with Russell et al (2003). Therefore, the following work will be done using the proposed method.…”

Section: Aerothermoelastic Model Verificationmentioning

confidence: 71%

“…To determine the accuracy of the proposed method, the results are compared with those from Russell et al (2003). From Fig.…”

Section: Aerothermoelastic Model Verificationmentioning

confidence: 99%

“…Combined with the presence of high-pressure loads, severe heating can cause a complete material failure and affect the normal performance of other instruments underneath the window (Heubner et al, 1995). The window design requires (Russell et al, 2003): (1) accommodating the severe highly transient aeroheating and resulting thermal gradients; (2) providing an effective seal to prevent gas flow into the laser guidance electronics volume; (3) minimizing aerodynamic loads by surface flush; (4) minimizing dynamic effects on the window due to launch and flight shocks; (5) providing an adequate surface finish and transmissibility for the laser wavelength of interest.…”

Section: Introductionmentioning

confidence: 99%

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Numerical simulation of aerodynamic heating and stresses of chemical vapor deposition ZnS for hypersonic vehicles

Liu

Zhu

et al. 2014

J. Zheijang Univ.-Sci.

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Abstract:Hypersonic vehicles subjected to strong aerodynamic forces and serious aerodynamic heating require more stringent design for an infrared window. In this paper, a finite element analysis is used to present the distributions of thermal and stress fields in the infrared window for hypersonic vehicles based on flowfield studies. A theoretical guidance is provided to evaluate the influence of aerodynamic heating and forces on infrared window materials. The aerodynamic heat flux from Mach 3 to Mach 6 flight at an altitude of 15 km in a standard atmosphere is obtained through flowfield analysis. The thermal and stress responses are then investigated under constant heat transfer coefficient boundary conditions for different Mach numbers. The numerical results show that the maximum stress is higher than the material strength at Mach 6, which means a failure of the material may occur. The maximum stress and temperatures are lower than the material strength and melting point under other conditions, so the material is safe.

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“…From Fig. 8, we can see that the temperature is in good agreement with Russell et al (2003). Therefore, the following work will be done using the proposed method.…”

Section: Aerothermoelastic Model Verificationmentioning

confidence: 71%

“…To determine the accuracy of the proposed method, the results are compared with those from Russell et al (2003). From Fig.…”

Section: Aerothermoelastic Model Verificationmentioning

confidence: 99%