Expendable launch system

Abstract: 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 -

Abstract: The CRRES mission is a joint NASA and US Department of Defense undertaking to study the near-Earth space environment and the effects of the Earth's radiation environment on state-of-the-art microelectronic components To perform these studies, CRRES was launched with a complex array of scientific payloads These included 24 chemical canisters which were released during the first 13 months of the mission at various altitudes over ground observation sites and diagnostic facilities The CRRES system was launched on July 25,1990, from Cape Canaveral Air Force Station on an Atlas I expendable launch vehicle into a low-inclination geosynchronous transfer orbit The specified mission duration was 1 year with a goal of 3 years The satellite subsystems support the instrument payloads by providing them with electrical power, command and data handling, and thermal control This review briefly describes the CRRES observatory and mission, and provides an introduction to the CRRES instrumentation technical notes contained within this issue

Abstract: Stanford University and California Polytechnic State University have combined efforts to develop a means of launching small picosatellites called CubeSat. The CubeSat is a 10cm cube weighting 1 kg or less. The launching system developed will provide launches for three satellites in one launcher tube. The first mission for this launcher will be to fly six tubes to launch as many as 24 CubeSats in May 2002 on a Kosmotras, Dnepr ELV from Bikinour, Ukraine. Stanford and Cal Poly are providing active technical support for the CubeSat developers, which are mostly universities. Once the CubeSats have been developed by the universities and other customers, they will be sent to Cal Poly for final testing, insertion into the launcher then shipped to One Stop Satellite Solutions in Ogden, Utah where they will be mounted on the OSSS Multiple Payload Adapter, then sent to Russia and integrated onto the Dnepr. TABLE OF CONTENTS

Abstract: This paper presents an analysis of the scenario of small satellite and its correspondent launch vehicles. The miniaturization of electronics, together with reliability and performance increase as well as reduction of cost, have allowed the use of commercials-off-the-shelf in the space industry, fostering the Smallsat use. An analysis of the launched Smallsats during the last 20 years is accomplished and the main factors for the Smallsat (r)evolution, outlined. Based on historic data, future scenarios for different mass categories of Smallsats are presented. An analysis of current and future launch vehicles reveals that we are currently in a phase of transition, where old launch vehicles get retired and new ones enter the market. However, the satellite launch vehicle business has been established to carry payloads of thousands of kilos into low Earth orbit and has not adjusted itself to the market of Smallsats. As a result, there is only 1 launch vehicle for dedicated Smallsat launches commercially available, but it carries a high price tag. Several small lowcost launch vehicles under development are identified and the challenges to overcome, discussed. Since these small launch vehicles have similar complexity as huge launch vehicles, high development costs are intrinsic, leading to a high specific price (USD/kg payload).