Electron Air Hypersonic Propulsion
Aviation, in general, and aerospace in particular needs new propulsion systems which allow the craft to reach high speeds by cheaper and more efficient methods. Author offers a new propulsion system using electrons for acceleration of the craft and having a high efficiency. As this system does not heat the air, it does not have the heating limitations of conventional air ramjet hypersonic engines. Offered engine can produce a thrust from a zero flight speed up to the desired space apparatus speed. It can work in any planet atmosphere (gas, liquid) and at very high altitude. The system can use apparatus surface for thrust and braking. For energy the system uses high voltage electricity which is not a problem if you have an appropriate electrostatic generator connected with any suitable engine.
Non-rocket space launch and flight
At present, rockets are used for launches and flights into space. They have been intensively developed since World War II when the German engineer F. Von Braun designed the first long distance rocket FAU-2. In the subsequent 60 years liquid and solid rockets reached the peak of their development. Their main shortcomings are (1) very high cost of space launching $20,000 – 50,000/kg; (2) large fuel consumption; (3) fuel storage problems because the oxidizer and fuel (for example; oxygen and hydrogen) require cryogenic temperatures, or they are poisonous substances (for example; nitric acid, N2O3). In the past years the author and other scientists have published a series of new methods which promise to revolutionize space launching and flight. These include the cable accelerator, circle launcher and space keeper, space elevator transport system, space towers, kinetic towers, the gas-tube method, sling rotary method, asteroid employment, electromagnetic accelerator, tether system, Sun and magnetic sails, solar wind sail, radioisotope sail, electrostatic space sail, laser beam, kinetic anti-gravitator (repulsitor), Earth– Moon or Earth–Mars non-rocket transport system, multi-reflective beam propulsion system, electrostatic levitation, etc. There are new ideas in aviation which can be useful for flights in planet atmosphere. Some of these have the potential to decrease launch costs thousands of times, other allow the speed and direction of space apparatus to be changed without the spending of fuel. The author summarizes some revolutionary methods for scientists, engineers, students, and the public. He seeks attention from the public, engineers, inventors, scientists for these innovations and he hopes the media, government and the large aerospace companies will increase research and development activity in these areas. Non-Rocket Space Launch and Flight, Version 3 All Chapters 5 -
Effects of reservoir volume on performance of pulse tube cooler.
A pulse tube cooler has the advantages of long-life and low-vibration over conventional cryocoolers such as G-M and Stirling coolers because of the absence of moving parts at low temperature. On the other hand, the combination of a reservoir and orifice is indispensable to optimize the performance of pulse tube coolers. In order to make the pulse tube cooler compact for practical applications, the volume of reservoir should be minimized. This paper analyzes the effects of the reservoir volume on the thermodynamic performance of various components in a simple orifice and a double-inlet pulse tube cooler by combining a linearized model with a thermodynamic analysis. Expressions of entropy production for those components are presented. The results show that the reservoir volume has a significant influence on the entropy production in the various components when the reservoir to pulse tube volume ratio is smaller than about 5. The ratio is important to determine the minimum reservoir volume for a pulse tube cooler. Optimum settings for a double-inlet pulse tube cooler are also discussed.