Contents
(Abstracts of some manuscripts submitted by Dr. A.Bolonkin for World Space Congress-2002)
Abstract 8a of Non-rocket trip (circle) for WSC, date 11-23-01
World Space Congress-2002. IAC 02-IAA.1.3.03
Author proposes a methods of flights to outer Space, described in his book "Non Rockets Flights in Space", which is in preparation for publication.
In this article the method named "Bolonkin Space Trip" and facilities for delivering load and people into outer Space are presented. This method uses, in general, the centrifugal forces of a closed-loop rope (cable) and mechanical engine located on planet or space ship.
The author proposes project "Space station at 140 km altitude" for tourists and scientists in three versions. This project requires artificial materials (fibers, whiskers, nanotubes) with a ratio of tensile strength to density from 278 km (conventional fiber with tensile strength 600 kg/sq.mm and density 1,8 g/cub.cm) to 4444 km (nanotubes). A whisker with a ratio of 2286 km was created in 1988. This is the whisker Cd, which has the tensile strength 8000 kg/sq.mm and density 3.5 g/cub.cm.
Experimental carbon nanotubes have tensile strength 200 Giga-Pascals (20,000 kg/sq.mm) and specific density 1.8 g/cc (MWNT) and 0.8 g/cc (SWNT)(1994). They have the ratio 11,111 km and 25,000 km respectively. The theoretical limit of tensile strength is 10 times more. The USA will produce about 300 kg nanotubes in 2002.
The report contains the theory of estimation and computation of suggested installations. They include: a maximum speed giveb the tensile strength and specific density of material, maximum lift force installation, specific lift force in planet’s gravitation field, admissible local load, angle and local deformation of material in different cases, internal pressure in installation, accessible maximum of altitudes of space cabin, speed which space ship can obtain from installation, power of installation, passenger elevator, etc. Some data from project are below.
Author suggests and researches one for a method of flights to outer Space, described in book "Flights in Space without Rockets", described in his book "Non Rocket Flights in Space" which is preparation for publication.
In this article the method named "Bolonkin Space Launcher" and facilities for delivering load and people into outer Space are presented. Space ship is accelerated by mechanical engine located on Earth and connected to the ship by drive cable.
The author proposes project "Men Cable Launcher to Outer Space" . This project requires artificial materials (fibers, whiskers, nanotubes) with a ratio of tensile strength to density about 2000 km. A whisker with a ratio of 2286 km was created in 1988. This is the whisker Cd, which has the tensile strength H=8000 kg/sq.mm and density D=3.5 g/cc.
Experimental carbon nanotubes have tensile strength 200 Giga-Pascals (20,000 kg/sq.mm) and specific density 1.8 g/cc (MWNT) and 0.8 g/cc (SWNT)(1994). They have strength to density 11,111 km and 25,000 km respectively. The theoretical limit of tensile strength is 5-10 times more. About 300 kg of nanotubes will be produced in the USA in 2002.
This report contains the theory of estimation and computation of suggested installations and projects. They include: cross-section area and weight of a cable of a constant cross-section area, cross-section area and optimal weight of a cable an EQUAL (constant) stress, cross-section area of cable of equal (constant) stress for wing suspension system, estimation a loss of speed of an wing apparatus when that across via atmosphere, maximum distance between supports of suspension systems, sag of cable from its weight and curvature of the Earth, estimation of range of wing projectile in atmosphere, equation for an estimation a wave drag of edge cable for supersonic velocity, energy stored by rotary flywheel per one kg cable, etc. Some data from project are below.
Author suggests and develops theory, for methods of flights to outer Space, described in his book "Non Rocket Flight in Space", which is preparation for publication.
In this article the method named "Bolonkin Space Launcher" and facilities for delivering payload and missiles into outer Space and any points on the Earth are presented. This missile is accelerated by mechanical engine located on Earth and connected to the missile by drive cable.
The author proposes project "Non-rocket Missile (Payload) Launcher into Outer Space and Any Points to the Earth" . This project requives an artificial materials (fibers) with admissible tensile strength 250 kg/sq.mm. Fibers TM9 with tensile strength 600 kg/sq.mm and density g=1.79 g/cc already exist. A whisker with a ratio of 2286 km was created in 1988. This is the whisker Cd, which has the tensile strength 8000 kg/sq.mm and density 3.5 g/cc.
Experimental carbon nanotubes have tensile strength 200 Giga-Pascals (20,000 kg/sq.mm) and specific density 1.8 g/cc (MWNT) and 0.8 g/cc (SWNT)(1994). They have strength to density 11,111 km and 25,000 km respectively. The theoretical limit of tensile strength is 5-10 times more.About 300 kg of nanotubes will be produced in the USA in 2002.
The report contains the theory of estimation and computation of suggested installations. They include: cross-section area and weight of a cable of a constant cross-section area, cross-section area and weight of a cable an equal (optimal)(constant) stress, cross-section area of cable of equal (constant) stress for wing suspension system, estimation a loss of speed of an wing apparatus when that across via atmosphere, maximum distance between supports of suspension systems, sag of cable from its weight and curvature of the Earth, estimation of range of wing projectile in atmosphere, equation for an estimation a wave drag of edge cable for supersonic velocity, energy stored by rotary flywheel per one kg cable, etc. Some data from project are provided below.
Abstract
Author proposes special gas rocket in a tube, which utilizes the tube walls as a moving container for compressed air. He suggests special burn programs (fuel injections), which allow to use of an internal apparatus as a rocket. Author applies a long tube (up to 1-3 km) placed for mobility and aiming into the water and connected to ship. It would use a cheap oxidizer and fuel: compressed air or gaseous oxygen and kerosene.
The research, computations show that the Launcher can give a projectile of 15 tons a speed up to 5-9 km/sec. The author also shows that, when projectile crosses the Earth’s atmosphere with trajectory near to vertical direction, a loss of speed and the weight of terminal protection is very little.
The proposed Launcher can deliver up to 85,000 tons of payload to the Space annually for cost $1-2 per LB. The Launcher can be also used for delivery of mail or express parcels about 500-1000 tons per day over long distances, for example, from one continents to another and geherate profit of to up 5-10 millions dollars every day.
Also, during war, this launch system could deliver munitions to tangents thousands to tens thousands kilometers away.
Advantages of offered Space launcher:
1)The suggested Launcher is placed in water it becomes mobile and can be aimed (by adjusting the azimuth) to any point in space or on the Earth.
2)The suggested "rocket engine into tube" is different from conventional rocket engines and has advantages:
a)it is simplest; b)it does not move heavy tanks of compressed oxidizers; c)it allows to reach a very high ratio of fuel mass (compressed air + kerosene) to a payload mass (up to 30).
3)The vacuum above the payload/piston eliminates the air resistance.
4)The launcher can be hidden under water surface.
5)In the event of an accident, the high pressures under the water can help to contain the explosive materials and avoid injuring people.
6) Conventional fuels and oxidizers (such as air or gaseous oxygen) can be used with the proposed Launch System.
The main advantage of the proposed launch system is a very low cost for payload delivery into space and over long distances. Expensive fuels, complex system control, expensive rockets, airborne computers, and complex devices are not required. The cost of payload delivery to space would drop by a factor a thousand. In addition, large payloads could be launched into space (on the order of thousands of tons a year) using a single launch system. This launch system is simple and does not require high-technology equipment. Any non-industrialized country could easily develop the launch system and the cost of this launch system is ten times lower than of contemporary rocket systems.
Computations show that if the launch tube is designed to have a diameter of 2 - 5 m, a length of 2 - 3 km, and gas pressure of 200 - 800 atmospheres, then 5 – 20 tons of payloads per a launch could be deliver to Earth orbit. If the launch frequency is 30 minutes, then 45 - 8s5 thousand tons of payload could be delivered to space per year at production costs of 2 - 10 dollars per kg.
During peace time, this launch system can be also used to delivery of mail or express parcels over long distances (for example, from one continent to another) and give a profit 5-10 millions dollars per day.
The figures shows: the estimation of velocity, length of barrel, acceleration via initial pressure air and % of gaseous oxygen in air; loss of velocity in atmosphere via shot velocity; cost delivery via annual payload and cost of installation; etc.
The author has the more detail research this concept and its innovations, which solve problems, which appear in research, computation, development, and design of the suggested Launcher. The author is prepared to submit his research and to discuss the problems with serious organizations wanting to research and develop this invention. Patent applications are 09/013,008; 09/349,235; 10/051,813.
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