Design of maritime satellite launch platform

Author(s):  
Yang Jiandong ◽  
Ma Yingliang ◽  
Zhang Tao ◽  
Jin Dong
Keyword(s):  
2016 ◽  
Vol 4 (20) ◽  
pp. 6
Author(s):  
Jakub Hospodka ◽  
Zdeněk Houfek

Space flights are in these days not any more question of technology, but more question of costs. One way how to decrease cost of launch is change of home spaceport. Change of home spaceport for different rockets is a way to achieve more efficient launches to space. The reason is different acceleration achieved from Earth rotation. We added several mathematical calculations of missions to Low Earth Orbit and Geostationary Earth Orbit to show bonuses from Earth rotation and effect of atmospheric drag on specific rockets used these days. We discussed only already used space vessels. Namely Arianne 5, Delta 4 heavy, Proton-M, Zenit and Falcon9. For reaching GEO we discuss possibility of using Hohmman transfer, because none of aforementioned vessels is available for direct GEO entry. As possible place for launch we discussed spaceports Baikonur, Kennedy Space center, Guyana Space center and Sea Launch platform. We present results in form of additional acceleration for each spaceport, and we also project this additional acceleration in means payload increase. In conclusion we find important differences between vessel effectivity based on spaceport used for launch. Change of launch location may bring significant cost decrease for operators.


2016 ◽  
Vol 140 (4) ◽  
pp. 3042-3042
Author(s):  
Karthikeyan Natarajan ◽  
Lakshmi Venkatakrishnan

2012 ◽  
Vol 490-495 ◽  
pp. 1009-1013
Author(s):  
Chang Lin Hu ◽  
Li Yuan Ma ◽  
Yong Jun Li ◽  
Hui Li

The frequencies and vibration modes of a launch platform are acquired through finite element simulation, and their actual values are obtained through modal test. On this basis, constructing objective function for the structure modal parameter relative residual error to be minimum, can transform model updating problem into optimization problem. Then the trust region algorithm is adopted to solve this optimization problem. This algorithm bears better robustness and computing efficiency. Through model updating, the frequency and vibration mode errors are reduced, supplying a basis for further simulation.


IEEE Spectrum ◽  
1996 ◽  
Vol 33 (10) ◽  
pp. 18-25
Author(s):  
D. Dooling
Keyword(s):  

Author(s):  
Timothy R. Conners

NASA Dryden Flight Research Center has completed a preliminary performance analysis of the SR-71 aircraft for use as a launch platform for high-speed research vehicles and for carrying captive experimental packages to high altitude and Mach number conditions. Externally mounted research platforms can significantly increase drag, limiting test time and, in extreme cases, prohibiting penetration through the high-drag, transonic flight regime. To provide supplemental SR-71 acceleration, methods have been developed that could increase the thrust of the J58 turbojet engines. These methods include temperature and speed increases and augmentor nitrous oxide injection. The thrust-enhanced engines would allow the SR-71 aircraft to carry higher drag research platforms than it could without enhancement. This paper presents predicted SR-71 performance with and without enhanced engines. A modified climb-dive technique is shown to reduce fuel consumption when flying through the transonic flight regime with a large external pay load. Estimates are included of the maximum platform drag profiles with which the aircraft could still complete a high-speed research mission. In this case, enhancement was found to increase the SR-71 payload drag capability by 25 percent. The thrust enhancement techniques and performance prediction methodology are described.


Author(s):  
Stephen A. Whitmore ◽  
Zachary S. Spurrier ◽  
Sean D. Walker ◽  
Stephen L. Merkley

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