Talk:Reactionless drive

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Contents 1 Thornson Inertial Engine 2 moved from inertial drive 3 Zero point theory 4 EMdrive 5 NPOV, inaccuracy and expansion 6 Redirects for disjunction drive and differential sail 7 Centrifugal force drive 8 Introductory statement

[edit] Thornson Inertial Engine

This page conveniently neglects to mention the Thornson Inertial Engine (TIE), although i think there used to be a seperate page for it.

The TIE has, so far, held up to all scrutiny.

- It still works when suspended

- It still works in a vacuum

- It still works when suspended in a vacuum --Arltomem 19:59, 15 August 2006 (UTC)

______________________________________________________________________________________________________________________________ Y'know, the conservation of energy and the conservation of momentum are really aspects of the same thing: in relativity, they combine to become the conservation law for the energy-momentum four-vector. Separating them amounts to pedantry. . . Anville 21:11, 7 June 2006 (UTC)

[edit] moved from inertial drive

Hmmm, there's currently only one link to this page. Aren't Alcubierre drives, Disjunction drives and Diametric drives intertial propulsion engines?

After reading the description of the Alcubierre drive, I would have to say it is not. It is not motion dependent on the function of inertia or internal movement. Indeed, assuming such a wave could be generated, the object to be carried along does not appear to need any moving parts at all. previously unsigned comment by Fresheneesz

Much of this article is a matter of opinion at best. At worst, it is false. If you are reading this believing that this is the last word, look elsewhere. Engines which do not use a propellant have been created, tested, and found functional. The Energy necessary to impart motion has been a problem. Ineffecient design has plagued the field. But, by creating internal momentum and then reabsorbing this momentum does not violate any law of physics. previously unsigned comment by User:71.215.54.11 2006-08-13T21:48:38

I think that a reactionless drive by definition violates the law of conservation of momentum. One cannot "reabsorb" momentum at a later time - thats a violation. Fresheneesz 08:06, 10 September 2006 (UTC)

The entire entry on reactionless propulsion should be deleted until Wikipedia stops its ridiculous policy of letting just anybody add 'information' and instead employs recognised experts (as Google plans to do). There is currently no scientifically accepted proof of the concept. All of the patents are based upon 'schoolboy howlers': the 'centrifugal' force, for instance, is a fictitious one (in the physical sense) and cannot be used to propel anything in space. Even the so-called Wisdom Drive would be reacting against the curvature of space. 'Lifters' exploit the electric wind effect, but there is a long history of the latter being mistaken for anti-gravity. Papers such as the Alcubierre one are purely speculative, and later theoretical papers have revealed flaws in his reasoning. NASA's Breakthrough Propulsion Project, and its enormously wasteful investigation of the non-existent 'Podkletnov effect', have made it the laughing stock of the worldwide physics community. Society trains experts in physics at great expense. It should try listening to them more, instead of to crackpot inventors. —Preceding unsigned comment added by 86.144.25.129 (talk) 05:43, 13 February 2008 (UTC)

[edit] Zero point theory

What about the Zero Point Theory? I don't see any direct reference to this, specifically, although this may or may not be identical to the "inertial drive" mentioned. GrammarGeek 08:36, 26 December 2006 (UTC)

[edit] EMdrive

Here's one that some good publications & agencies seem to believe:

• New Scientist
• [www.freerepublic.com/focus/f-news/1455622/posts Reports of a government grant]

The claim here is basically that photons aren't bound by conservation of momentum, due to the difference between phase velocity and group velocity. Unfortunately, the engineer is quoted saying a production system would be designed to work "at absolute zero"[1], which tends to raise an eyebrow if you've looked at anything by Carnot. Perhaps that's a journalistic misquote, though, because the same source lists superconductors as having "near zero" resistivity.

I'll go ahead and make some redirects to the article from Roger Shawyer and his invention, the EMdrive. I only took two semesters of quantum, and that was years ago, but I remember phase and group velocity being surprising concepts that led to no surprising results. I trust my education more than the authority of The New Scientist, especially after their complete misunderstanding of amorphous alloys[2]; they didn't even mention dislocation theory, but instead printed something misleading and entirely inaccurate.

previously unsigned comment by User:Polyparadigm 2006-09-10T06:51:57

I wish I could read the rest of that new scientist article - however I doubt it would be any more helpful than the second. The second article says that light doesn't obey the conservation of momentum, however that is entirely untrue. Not only that, but the drive supposedly relys on the difference between phase velocity and group velocity. If you understand what group velociy is, then you know it is not the velocity of anything physical. No information, energy, matter, or anything else is transmitted at this "group velocity" - it is simply a pattern that we recognize visually. An equivalent example is two events that happen at close to the same time - like me clapping my hands here, and a star exploding 100 light-years in the distance. Of course I didn't cause the explosion, no information, or anything else was transmitted. But if you consider my hand clap, and the star's explosion to be part of the same entity, then you have a "group velocity" of much much greater than the speed of light. Group velocity cannot drive a spaceship anymore than clapping my hands can make a star explode. Fresheneesz 08:18, 10 September 2006 (UTC)

Thanks for refreshing my memory about group velocity. Yes, it fits the classic profile of using terms people aren't likely to understand the dictionary definition of to sell a bogus technology. It sounds like you're qualified to include this new device in the article; I don't believe I am.

By the way, sorry about the unsigned post. I assure you I didn't mean to be rude. It was late, and I've been off Wikipedia for a while, having gone cold turkey when it started impacting my carreer; I didn't even think of it.--Joel 06:00, 11 September 2006 (UTC)

This is my first posting of any kind to Wikipedia. I agree that invoking group velocity to explain anything sounds fishy, but in the absence of a detailed explanation of this EM drive I'm willing to give it the benefit of the doubt, for the following reason. Solar sails work by transfering some momentum from a photon to the sail, via red-shifting the photon. I could believe that a device could repeatedly transfer momentum from a photon to the drive on each bounce of the photon in a resonating cavity, each time decreasing the frequency of the photon. What is hard to believe is that bounces from one direction transfer more energy than bounces from the opposite direction. But maybe there is some way to selectively control the amount of momentum transferred based on the geometry or composition of the cavity. Ultimately, the photon will have to exit the drive opposite the direction of acceleration to have a net change in momentum of the drive. Of course, there is nothing "reactionless" about such a drive, so it's not violating anything. Until someone puts the technical paper describing the drive on-line, we won't be able to evaluate it carefully. -- User:Solar Fuel 14:23, 11 September 2006 PST

OK, after thinking about it, I realized that you can't transfer any more momentum from a photon to the drive by bouncing it around a resonator and then ejecting it than you would by just ejecting the photon without bouncing it. So the EM drive doesn't seem to make sense. -- User:Solar Fuel 14:46, 11 September 2006 PST

[edit] NPOV, inaccuracy and expansion

This entry seems to have a very snide tone, which is understandable considering that it is mostly about the debunked reactionless drives. However, it is definitely an NPOV issue. It also doesn't correctly define "reactionless drive", and simply states a priori that all such devices would violate Conservation of Momentum. They call that "including the conclusion in the premises", don't they?

It also needs to go into theoretical reactionless drives, such as the Alcubierre Warp. I have also heard of a reactionless drive that works within the boundaries of general relativity, known as "Inertia contol by metric patching", and it would behoove this entry to discuss it. There is, or was, also a page on the NASA site devoted to theoretical ideas for non-rocket based propulsion, including differential sails and similar ideas.

Rather than simply being snide about failures, this entry should discuss the theoretical possibilities of reactionless propulsion.

I'll do some of these changes myself, but I don't have all the resources necessary to make this page anything other than a power trip.

--71.223.34.127 17:28, 19 October 2006 (UTC)

Is the intro's definition incorrect? The first sentence seems pretty accurate to me. Fresheneesz 18:33, 14 December 2006 (UTC)

[edit] Redirects for disjunction drive and differential sail

Many people will probably get to this page searching for information on technologies like the disjunction drive and differential sail, so it should have links to them. 71.223.34.127 17:35, 19 October 2006 (UTC)

Never mind, I fixed my problem, that people would come here looking for theoretical drives, myself. This entry still has some serious NPOV issues, though.71.223.34.127 17:44, 19 October 2006 (UTC)

[edit] Centrifugal force drive

use the concept in a Magnetic Accelerator Gun (Railgun, coilgun) to accelerate and decelerate a mass on an oval track with the corners in the thrust axis. Accellerate on the direction of the thrust, declelerate on the opposite straightaway. The 'thrust' is the difference in centrifugal on the corners, created not by friction, but by continuous magnetic acceleration/decleration.

Don't really know how efficient this would be though. Definitly would need nuclear power to produce significant 'thrust'. Plus a huge moving part. The thrust would be pulsing (reciprocating engines are too), but multiple devices could smooth it out. If the weight was 10% of the mass of the ship and the resulting low-Centrifugal was 3Gs and the resulting high-Centrifugal was 10gs, you would get 1 G of forward acceleration, a pause then 0.3 G of backward acceleration, a pause, repeat (0.7G of profit).

Actually i'm not sure if it would work. The acceleration g-force on teh straightaway is backwards to the direction of desired 'thrust' Same for the decelartion in the opposite direction. The straightaway acceleration/deceleration will probably negate most or all (or more than all) of the centrifigal force profit.

The idea is that sattelite gyroscopes don't use reaction mass to stabilize or initiate rotation. They exploit the momentum from the gyroscopes' centrifugal force. Adding exploitation of molecular or atomic strong force bonds to the centrifugal force exploit of gyroscopes could result in a bigger and better exploit to create a no-reaction-mass net linear thrust (Hey when you are in a drag racer and pull 4 Gs, that seat keeps the human from being left behind).

Maybe having some mag-lev (hey theres already magnetic acceleration / deceleration - rides use it all the time, and mag-lev trains exist too) on the acceleration/deceleration straightaway would remove the negation of the centrifugal force exploit. Just put the wheels on the track (connect mass to ship) in the corners.--GreatInca 22:56, 12 January 2007 (UTC)

Its good that you're thinking so techincally. However, your centifugal force exploit violates the conservation of momentum. The acceleration added to the weight's velocity would come at the cost of the momentum of the 'ship'. What would really happen is that the centrifuge ring would start moving in a circle (in the opposite direction of the weight inside), but no macroscopic linear motion would occur. Fresheneesz 05:52, 10 January 2007 (UTC)

I was hoping mag-lev would enable a cheat. I don't know if an accelerating mag-lev train is puts an equal and opposite force onto the track, because it is floating. If it doesn't, it's an excellent loophole in the momentum conversation law, as long as the float is disabled when it comes to apply the centrifigual force to the ship. It is a mass riding around an oval ring, like the high-roller fair-ride (ovalloid ring with train going around inside, but turn off the ringed track-structure's rotation). Or an very squished super-loop / ring of fire. Add-mag-lev accel to the one straight part, and decel on the opposite straight part, and allow contact on the corners. But if Mag-lev acceleration is creating an opposite force on the track, then there is no loophole to exploit, because the 3rd-law of motion would negate the centrifugal force profit. I don't recall electromag guns having any recoil my Sci_Fi RPG book, so that's why I am thinking of mag-lev / electromag acceleration as a loophole exploit. --GreatInca 22:56, 12 January 2007 (UTC)

Well, sci-fi books sometimes get it wrong. Rail guns do indeed have recoil in the real world. Physical laws don't have loopholes. You say that a mag-lev train is "floating", which is a good description - but remember that whatever you're sitting is making you "float" as well. The electrons in the atoms of your chair are repelling the electrons on the surface of your skin and clothes, which levetates you upward. A maglev train works in a similar way, except it floats a lot higher. Fresheneesz 01:11, 14 January 2007 (UTC)

This page really needs some clean-up. There should be a clear delineation between discussions of the scientific soundness of the general concept, claims to invention, and treatment in science fiction. Right now it reads like a jumbled mess, and the very strict statement that reactionless drives necessarily require the violation of conservation of momentum is both uncited and inaccurate. A quick counter-example is Miguel Alcubierre's warp metric. Whether this solution or others in its class are physical or not is besides the question, none admit non-conversative flow of momentum. --Rev Prez 20:11, 30 March 2007 (UTC)

Well a more accurate definition is a form of propulsion not based around newton's 3rd law See here. Basically, this means that no "reaction" would happen - nothing would be hitting another, thus no momentum would be transfered. So a reactionless propulsion system isn't by *definition* a violation of the conservation of momentum, but according to modern physics, it must be. Without a reaction, momentum would be gained from nowhere. Any sort of Alcubierre metric would have to gain momentum from somewhere - a gravity wave isn't created from nothing. Fresheneesz 06:10, 11 May 2007 (UTC)

I have a friend that has worked on 500KW railgun experiments for the USA military and he said that there is no noticeable recoil when launching projectiles from a non-mounted launcher (mounted on wheels like a old-time pirate ship cannon). So a railgun-driven electro-mag oscillation drive would be feasible, but he said it would be unpractical because of a very poor power-to-weight ratio - electromag rails, fission reactor, and working mass are all very heavy and would have a difficult time competing with ion-drive technology which needs no rails or working masses and can operate off of NPUs which are a lot lighter than fission cores. --YeshuaAgapao (talk) 18:45, 7 April 2008 (UTC)

[edit] Introductory statement

This article deals with debunked claims to have produced a reactionless drive. For examples of theoretically possible drives that do not require a reaction mass, see Breakthrough Propulsion Physics Program.

Is this correct? After reading the Breakthrough Propulsion Physics Program, it seems that all the proposals there require some theories that do not exist yet. It is arguable then whether those approaches are "theoretically possible".

Lucian Busoniu 00:11, 10 May 2007 (UTC)

The remark that there must be mass reaction momentum exchange does not square with the fact that if I turn on a small electromagnet in the presense of an ferromagnetic marble, the marble will begin to move.

Electro-magnetic Field Reaction Propulsion and Electro-dynamic Induction Braking in Space Applications. – By Mark J. Carter

Space propulsion has changed little since mankind took its first tentative steps into space. Even with the incremental advances in the efficiency of chemical fuels; the basic nature of rocketry is still defined by the basic Delta V Rocket Equation with all its limitations; be it the powerful boosters used to obtain orbital velocity or the low impulse Ion Thrusters used to power deep space missions. This ancient approach to propulsion limits both the potential flight parameters of deep space missions and the life span of earth orbiting satellites.

In earth orbiting satellites, the electronics of the satellite may last indefinitely; but the useable lifespan of that satellite is limited by the availability of on-board propellants used for orbital maintenance. Once the chemical propellant is exhausted, the satellite no longer has the capability of maintaining proper station.

The International Space Station is dependent upon chemical propellants to offset orbital decay. The need and use of these chemical propellants increases the potential for catastrophic accident, increases the cost of operational maintenance, and requires the commitment of launch capacity for that purpose.

Interplanetary and deep space missions face similar limitations inherent to dependence on chemical propellants. Although gravitational assist has been a regular tool used in both navigation and imparting changes in specific orbital energy; obtainable velocities, launch windows, and other flight parameters remain severely limited by dependence upon the same Newtonian Propulsion methods used by the ancient Chinese to power their rudimentary rockets. Even Ion Propulsion, which uses electro-magnetic acceleration of the ion fuel to achieve impulse, is still a type of Newtonian Propulsion where the total energy imparted is limited by exhaust velocity and total available fuel mass; as defined by Tsiolkovsky's rocket equation. Newtonian Propulsion may have gotten us to earth orbit and beyond; but it will be Electro-magnetic propulsion that will carry us to the stars. In the mean time, its development will allow us to achieve flight parameters unimaginable when considering only chemical propellants.

The Ampere Defined As Magnetic Force:

Prior to 1948 the ampere was defined, based on Faraday’s Law Of Electrolysis, as the amount of unvarying current, that when passing through a solution of silver nitrate, deposits silver at a rate of .00111800 grams per second.

The ampere was redefined in 1948 as the amount of unvarying current, that when being carried by two infinitely long conductors separated by one meter, would generate a magnetic force between the conductors of 2 X 10-7 Newton per meter of length. This is the Standard International definition of an Ampere.

Electro-magnetic Field Reaction Propulsion and Electro-dynamic Induction Braking when combined with the now and near term future technologies related to super conductivity and other related technologies will introduce a new paradigm in space propulsion.

The Fundamentals Described As A Space Based Experiment:

A simple space based experiment to demonstrate the basic principles of electro-magnetic propulsion is easily imagined. In this experiment a simple coil, a number of accelerometers, a polarity reversing switch, power source, and radio telemetry is used to determine the earth’s electro-magnetic field strength at the range of the experimental package. It would be most advantageous if the coil length is as great as possible. The coil is circuited in series with the polarity reversing switch and the power source. The accelerometers serve to activate the polarity reversing switch. The experiment is then suitably packaged and conventionally launched to a low inclination orbit defined by the optimum induction flux angle. The experimental package is then positioned so that the field coil of the package is aligned so the coil will be at maximum repulsion with earth’s electro-magnetic field when the coil circuit is initially energized.

So positioned, when the switch is initially closed and power is applied to the coil there will be two vector forces acting on the coil.

Since the coil is aligned in repulsion with earth field, one force will be acting along a line that is perpendicular to the earth’s North/South polarity (approximating the line of orbital radius) and will translate to an acceleration vectored along the orbital radius converting circuit energy to increased gravitational potential.

The other force acting on the field coil will translate to torque causing the field coil to begin to rotate about the central axis of the coil length as it begins to align towards the magnetic equilibrium position relative to earth field; that being one of maximum attraction and 180 degrees relative to the maximum repulsive position. In doing so, some of the electrical energy supplied to the field coil will be converted to kinetic rotational energy of the package. As the field coil rotates towards the equilibrium position, the accelerometer reading acceleration along the line of the orbital radius will sense zero acceleration as the angular relationship between the field coil and the earth’s North/South polarity reaches 90 degrees relative to the maximum repulsion or attraction position. The coil polarity control circuit is designed to reverse the polarity of the field coil at this position, thus maintaining a repulsive relationship as the rotational inertia carries the coil package through the 90 degree position.

The timing of the polarity reversing switch is critical for maintaining repulsion; avoid dampening the oscillation, or allowing the package to continue increasing its spin velocity.

As power is applied to the circuit, energy begins to be converted thru linear and rotational acceleration to the gravitational and rotational energy of the package. Without empirical proof, I suggest that the applied coil circuit energy will be the sum of the energy translated to gravitational potential and rotational kinetic energy. That the linear force acting along the line of orbital radius will vary as the cosine of the relative field angle while the force translated to torque about the center axis of the coil will vary as a sine function of the relative field angle. The linear force will approximate the force at 0 degrees (maximum repulsion) times the cosine of the relative field angle. The force imparting torque about the center axis of the field coil will approximate the force imparting torque about the center axis of the field coil at 90 degrees (maximum torque) times the sine of the relative field angle.

Where the moment of inertia of the experimental package is known, Earth’s Electro-Magnetic Field Strength can be derived from acceleration and circuit power.

Attitude Determination and Control Applications On Board Earth Based Satellites:

Using the Earth’s magnetic field as a reaction field in attitude determination and control of earth orbiting satellites was first proposed early on in space science applications history. Current applications include the sensing of relative field angle to determine satellite attitude and the use of electro-magnets to maintain and change satellite attitude. The author believes that widespread application may be limited by the orbital perturbation that would result from earth field/satellite field interaction. Electro-magnetic attitude control, without an Electro-magnetic orbital maintenance regime, would require expenditure of thruster fuel to maintain orbital station. To make electro-magnetic attitude determination and control a viable application, a means of offsetting the orbital perturbation using electro-magnetic propulsive technology rather than chemical thrusters must be developed. Also, the mass and volume fractions of electro-magnetic attitude determination and control technologies must be brought to values where the advantages of the technology offset the mass and volume fractions required. A primary advantage of Electro-magnetic propulsive methods for this application is that it can be accomplished without the complex mechanical components as required in momentum and reaction wheel technology or the fuel and valving required for thrusters. This resulting increase in reliability will serve as further incentive to apply electro-magnetic technology to attitude control.

Increasing Hyperbolic Excess Speed in departure from Earth’s sphere of gravitational influence:

By definition, for an Earth orbital escape mission, the Hyperbolic Excess Speed is the residual speed that remains as the space craft climbs out of the Earth’s gravity well. Simply stated, it approximates the rocket burn out velocity minus the escape velocity at the range of burnout.

It may be possible to increase the Hyperbolic Excess Speed by using magnetic repulsive force generated by propulsion coils aboard the spacecraft acting against Earth’s electromagnetic field. The repulsive force would offset the deceleration of gravity as the space craft moves out of the Earth’s gravity well. This offsetting force would leave more residual or “Hyperbolic Excess Speed” as the space craft leaves the gravitational sphere of influence. If the magnetic repulsive force exceeds the gravitational force, then this force would continue to accelerate the space craft. The additional energy imparted would approximate the applied circuit energy calculated as applied power times time.

By thoughtful design, repulsion can be maintained without using an oscillating polarity strategy (as described in the Space Based Experiment), thus maintaining constant space craft attitude.

Increasing Hyperbolic Excess Speed in Gravity Assist Maneuvers:

A number of deep space missions have used Gravity Assist to either increase or decrease the mechanical energy of the space craft. Although such maneuvers use the gravitational acceleration of the assisting planet to increase or decrease the heliocentric relative velocity of the space craft, the Hyperbolic Excess Speed of the space craft relative to the assisting planet remains unchanged. The reason for this is the relative velocity between the space craft and the assisting planet gained by the acceleration of gravity on the approach trajectory is lost to that same gravitational force on the departure trajectory.

By using Electro-magnetic Field Reaction Propulsion, both additional hyperbolic excess speed relative to the assisting planet and heliocentric relative velocity can be imparted when the assisting planet has a significant magnetic field. In this application the propulsion coil(s) are used in attraction polarity on the approach to the assisting planet. This increases the acceleration above that imparted by gravity alone.

As the space craft begins its departure trajectory from the assisting planet, the relative polarity is reversed and maintained in repulsion. This offsets the deceleration imparted by gravity, and increases both the Hyperbolic Excess Speed of the spacecraft relative to the assisting planet and the Heliocentric Velocity; by adding the energy imparted by the electro-magnetic system to the specific mechanical energy of the space craft.

If desired, the inverse process could be used to decrease spacecraft energy.

Orbital Station Maintenance and Altering Eccentricity:

By using properly timed Electro-magnetic Impulse, in repulsion and in attraction, possibly combined with Electro-dynamic braking; total orbital energy and eccentricity of orbit may be altered. Conceptualization of this regime involves both magnetic impulse and dynamic-braking at specific points in the orbit and could include using the induced dynamic-braking energy to produce vectored magnetic impulse.

Orbital Energy, often described as “The Specific Mechanical Energy”, has two components. These are the kinetic energy per unit mass and the gravitational potential per unit mass. The sum of these two variables equals the specific mechanical energy. In a mass constant orbiting object, when not acted on by any other force than the gravity of the prime focus object; this Specific Mechanical Energy remains constant. In elliptical orbits this energy translates between kinetic energy and gravitational potential energy.

Introductory texts on Astro-dynamics teach that in most cases, a change in the Specific Mechanical Energy of a satellite is accomplished by imparting impulse along the velocity vector. This change in velocity translates to a change in the semi-major axis of orbit. By imparting impulse along the velocity vector the Specific Mechanical Energy can be either increased or decreased with the timing of the impulse relative to periapsis or apoapsis determining orbital eccentricity. Changes in apoapsis are made by imparting impulse at periapsis while impulse to change periapsis is imparted at apoapsis.

In both cases, the impulse either increases or decreases the total orbital energy by imparting a change in orbital velocity. This change in velocity is then translated to a change in gravitational potential by altering the semi-major axis.

It is proposed that changes in the orbital energy of the space craft can be made using Electro-magnetic technology; increasing the orbital energy by increasing the semi-major axis directly through repulsive interaction with earth field or decreasing orbital energy by electro-dynamic braking.

In a properly inclined orbit, generating a magnetic field in repulsion with earth field will begin to impart impulse along the orbital radius, increasing the semi-major axis, thus directly increasing the gravitational potential component of the Specific Mechanical Energy. By imparting magnetic impulse during the entire orbital period, or applying bit impulse relative to apoapsis and periapsis, the orbit can be stepped up and eccentricity controlled. If using conventional chemical propellants, stepping up the orbit is accomplished by increasing the velocity component, translating to gravitational potential, with the impulses timed relative to apoapasis and periapsis to control eccentricity. Experimentation with generating magnetic field in attraction to earth field may yield some surprising results. How will the circuit energy be conserved?

Electro-magnetic Induction Braking (Electro-dynamic Braking) of the space craft will impart a braking force along the vector of orbital velocity, decreasing the orbital energy, and translated to a reduction in gravitational potential. By timing the Electro-dynamic braking inputs relative to periapsis and apoapsis the orbit can be stepped down and eccentricity controlled. Using chemical propellants stepping down the orbit is accomplished by impulse opposite the velocity vector, slowing the spacecraft. The timing of braking impulse relative to periapsis and apoapsis will allow control orbital eccentricity.

Electro-dynamic Induction Braking:

All electro-magnetic induction processes are composed of three primary components; the excitation field, the inductor, and rate of change. The rate of change can be supplied by velocity of the inductor relative to the excitation field, the oscillation of the excitation field in the presence of the inductor, or combination of the two.

For those of you who may have had the opportunity to empirically experience the fundamental physics of induction through experimentation with a simple hand crank generator, that lesson showed the relationship of circuit load to cranking force, and can be extrapolated to the inductive braking of a satellite or asteroid.

In Electro-dynamic Induction braking applications the solar or planet field will provide the excitation field while coils aboard the spacecraft, or the spacecraft/asteroid body itself, serves as the inductor. The spacecraft/asteroid velocity cutting the flux lines of the Solar or Planet field will supply the rate of change component. This induction process will generate a braking force as is inherent in any electro-magnetic induction process. The induced energy will then be dissipated through circuits designed to generate heat for radiative dissipation, conversion to vectored propulsive impulse, or stored for peak power/subsystem applications. Applications of Electro-dynamic braking will include adjustments in semi-major axis and eccentricity; as well as braking to orbit in planetary missions.

Because the orbital velocity of a satellite or asteroid is so high, significant voltage can be developed even though the excitation field may be very weak. The “tether” experiments flown on the space shuttle clearly indicate the validity and potential application of this technology.

Imparting Orbital Escape Energy:

Escape speed, as given in reference material, gives the escape speed at the surface of the body referenced. This escape speed decreases as the radius of orbit increases. If an orbiting spacecraft is given continual magnetic impulse to step up the orbital radius, at some point, the orbital velocity of the spacecraft will approach and then exceed the escape speed at range, thus allowing the spacecraft to “escape” the gravitational sphere of influence of the prime focus body (planet or Sun). Using such a method, a satellite may be given Excess Hyperbolic Speed, not by imparting additional velocity, but by imparting additional gravitational potential until the energy of the spacecraft exceeds that needed to escape the gravitational sphere of influence of the prime focus body.

By initiating high power Electromagnetic impulse in low earth orbit and maintaining this impulse during the outbound trajectory, very high Excess Hyperbolic Speeds might be achieved.

Braking to Orbit:

A space craft approaching Jupiter, or other target body, may have too much energy to establish orbit. By using Electromagnetic Propulsive methods it may be possible to alter both the magnitude and vector of the approach velocity; thus giving an alternative to using chemical propellants or atmospheric braking as the sole methods of reducing the energy of the spacecraft so that it can be captured by the intended prime focus body.

Deep Space Propulsion and Navigation:

Force vectoring will be obtained by very precise control of field strength, field angle, and action time relative to the reaction fields of planets having significant field, the Sun, and once beyond the heliopause; the galactic field. Vector control, when within the magnetic sphere of influence of multiple field sources; will utilize the relationship of reaction field range, reaction field angle, and time span of power input to sum the force vectors from two or more reaction fields to obtain the desired net force vector. An example would be to act in repulsion of earth field for a fixed time at a fixed power and then act in attraction to Sun field for a fixed time at a fixed power. The net vector force would be the vector sum of the two forces. Because of the cosine relationship of repulsion/attraction force to the relative angle between the propulsion coil(s) and fields of the Sun, Earth, Jupiter, or other reaction fields, and if those fields are offset at a substantial angle relative to each other; effective impulse vectoring can be accomplished.

In Closing:

The Delta V imparted by a chemical rocket is limited by the attainable exhaust velocity of the rocket and total fuel mass available. In an Electro-magnetic Field Reaction Propulsion System capable of generating extreme field strength, the Delta V imparted will be limited only by the amount of available applied electrical power and the time span that power is made available.

In all cases, the minute field strengths of the reaction fields at range become usable when the propulsion system is capable of generating extremely strong fields or, in the case of dynamic braking, the induction circuit is capable of maintaining extremely high acceptance when dissipating high power.

The use of Electro-magnetic Propulsion may negate the requirement of waiting for opportune alignment of Jupiter and Saturn for use in Gravity assist maneuvers. The launch windows now continuously open by the ability to use Solar Field in repulsion to give the space craft the kick up that would otherwise require a gravity assist trajectory or maneuver.

A most important ramification of Electro-magnetic Field Reaction Propulsion and Electro-dynamic Braking in Space Applications may be the fundamental change in the logistics of asteroid deflection. This technology will negate the need to carry chemical fuel mass to the asteroid for the purpose of supplying impulse. It will allow mankind to use the orbital energy of the asteroid itself as the prime source of energy for deflection through an integration of Electro-dynamic braking, vectored electro-magnetic impulse, and for powering Newtonian Propulsion Systems that use scavenged mass from the asteroid and accelerate it using propulsion coils. Perhaps, it will cause a re-evaluation of the decision to use nuclear explosive deflection and fractionation as the preferred approach to this impending challenge.

--Mark J. Carter 23:24, 23 September 2007 (UTC)

Excuse me. What is that giant text above? I'm not going to read it, and I doubt anyone else will either. A 10 page essay on propulsion doesn't belong on talk pages here, and frankly i think its just taking up space - it should be archived or deleted.

"The remark that there must be mass reaction momentum exchange does not square with the fact that if I turn on a small electromagnet in the presense of an ferromagnetic marble, the marble will begin to move. "

If its a small electromagnet, you'll probably also notice that the electromagnet will also start to move. This is call magnetic attraction, and follows the law of convservation of momentum. In a frictionless vaccuum, the electromagnet will gain just as much momentum as the ferromagnetic marble loses. A net momentum change of 0. If one or both of those items is attached to something, that something will either contribute or gain momentum - as much momentum as the other contributes or gains. Fresheneesz 03:14, 29 September 2007 (UTC)