IL247953B2 - Propulsion system - Google Patents
Propulsion systemInfo
- Publication number
- IL247953B2 IL247953B2 IL247953A IL24795316A IL247953B2 IL 247953 B2 IL247953 B2 IL 247953B2 IL 247953 A IL247953 A IL 247953A IL 24795316 A IL24795316 A IL 24795316A IL 247953 B2 IL247953 B2 IL 247953B2
- Authority
- IL
- Israel
- Prior art keywords
- section
- propulsion system
- pump
- vehicle
- liquid
- Prior art date
Links
- 239000007788 liquid Substances 0.000 claims description 35
- 238000000034 method Methods 0.000 claims description 13
- 238000006243 chemical reaction Methods 0.000 claims description 7
- 230000003213 activating effect Effects 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 2
- 230000007704 transition Effects 0.000 description 16
- 150000002500 ions Chemical group 0.000 description 6
- 235000015842 Hesperis Nutrition 0.000 description 4
- 235000012633 Iberis amara Nutrition 0.000 description 4
- 239000000126 substance Substances 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 2
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 description 2
- 229910052753 mercury Inorganic materials 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H99/00—Subject matter not provided for in other groups of this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/409—Unconventional spacecraft propulsion systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Linear Motors (AREA)
- Control Of Position Or Direction (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
Description
35173/IL/16-ORP PROPULSION SYSTEM Field of the InventionThe invention is in the field of space travel. Specifically the invention is from the field of systems used to propel spacecraft and other objects in space.
Background of the InventionDeep space travel has long been limited by the propulsion systems used therefor. There are generally two types of space travel propulsion systems. The first type is used for overcoming gravitational forces. Taking off from the surface and leaving earth's atmosphere are examples of space travel stages which require a propulsion system of the first type. The second type is used for maneuvering a space vehicle in an environment lacking significant gravitational forces, i.e. in outer space. Adjusting a space vehicle's trajectory and velocity while in outer space are examples of space travel stages which require a propulsion system of the second type. The present invention relates to a system of the second type.
The most widely used method of spacecraft propulsion relies on chemical combustion rockets. This method is limited by the amount of fuel that a spacecraft can carry. Thus spacecraft are accelerated to the desired speed and then coast to their targets. If designed to land on another celestial body, a similar amount of fuel will be required for deceleration.
Another type of propulsion system is ion thrusters, which create propulsion force by expelling ions through a nozzle 180 degrees from the intended direction of motion. Although the specific impulse (Isp) of ion thruster systems is relatively high compared to advanced chemical rockets (in the 35173/IL/16-ORP order of a few thousands for ion thrusters, compared to 450 for chemical rockets), the absolute forces these systems produce are minute, in the order of a few milli-Newtons. Furthermore, ion thrusters also require some form of consumables to produce ions.
Alternatively to the above methods that are currently used in the art, it has been suggested that water or hydrogen could be heated by an onboard nuclear reactor, thereby generating jets of hot gas through the nozzles. Although this method of propulsion force production is more efficient, in terms of Isp, than chemical rockets, it is still based on the expulsion of mass to create thrust and requires a supply of a suitable mass.
Alternatively to the previously described methods, US 2,886,976 describes a propulsion system, a "Dean Drive", which attempts to convert, by mechanical means, centrifugal motion into a unidirectional force. This system, however, was never properly demonstrated as able to provide a propulsive force in free space.
In addition to the problem of the weight and volume of fuel that must be carried to operate the propulsion system, extended space travel, both for manned and unmanned vehicles is hampered by the sheer length of time needed to cover the distances involved. Thus a method of continuously accelerating (and deaccelerating) a vehicle on a deep space mission that does not depend on mass expulsion would be very desirable.
It is therefore a purpose of the present invention to provide a system and method of space vehicle propulsion that minimizes the deficiencies of the prior art.
It is another purpose of the present invention to provide a system and method of space vehicle propulsion that does not depend on mass expulsion. 35173/IL/16-ORP Further purposes and advantages of this invention will appear as the description proceeds.
Summary of the InventionIn a first aspect the invention is a propulsion system attached to a space vehicle for propelling the space vehicle in an essentially gravity free environment. The system comprises:a) a closed tube comprised of a semi-circular shaped first section of tubing;b) a second section of tubing having a cross-sectional area significantly greater than the cross-sectional area of the first section;c) two transitional sections that join the ends of the first section of tubing to the ends of the second section of tubing;d) a circulation pump, the rate of flow of which can be controlled, located in the second section;e) a non-compressible liquid forced by the pump to circulate continuously around the closed tube.
In an embodiment of the propulsion system the second section has a semicircular shape. In another embodiment the second section is straight.
In embodiments of the propulsion system reaction forces developed from the pump of a first system are cancelled out by placing a second identical system with the liquid circulating in the opposite direction side by side with the first system.
Embodiments of the propulsion system are configured so that the propulsion system can be stopped and restarted at will.
Embodiments of the propulsion system are mounted in so that the propulsion system can be rotated in order to provide force in any desired 35173/IL/16-ORP direction. In these embodiments the system can be configured to be rotated 180° from the initial direction in which the vehicle is moving in order to provide a braking force.
In a second aspect the invention is a method of propelling a vehicle on an extended space flight. The method comprises:a) attaching to the space vehicle at least one propulsion system according to claim 1; andb) activating the pump to cause the non-compressible liquid to circulate continuously around the closed tube;wherein, the differences in diameters of the first and second sections of tubing will cause the velocity of the non-compressible liquid in the first section to be larger than the velocity of the non-compressible liquid in the second section resulting in a net radial force that will cause the vehicle to accelerate.All the above and other characteristics and advantages of the invention will be further understood through the following illustrative and non-limitative description of embodiments thereof, with reference to the appended drawings.
Brief Description of the Drawings- Fig. 1 schematically illustrates a propulsion system according to an embodiment of the present invention; and- Fig. 2 schematically illustrates a propulsion system according to another embodiment of the present invention.
Detailed Description of Embodiments of the InventionThe present invention relates to a system and method for obtaining vehicle propulsion based on the control and manipulation of a device producing a centrifugal force within the vehicle, and converting this force into a directional one. The system is based on the use of electric motors to supply 35173/IL/16-ORP the energy, thus it is assumed that sufficient electric power can be available, e.g. produced by solar panels attached to the propelled vehicle or a nuclear power plant.
Fig. 1 schematically illustrates a propulsion system according to an embodiment of the present invention. For sake of simplifying the description, directions are marked in Fig. 1 as north and south. According to this embodiment, the system comprises a toroidal tube 101 with two sections, the first of which having a significantly larger cross section than the second.
Toroidal tube 101 comprises a first section 102 having a relatively larger cross section, at the southern region of the tube, and a second section 1having a smaller cross section, at the northern region. The radius of tube 101 with respect to section 103 is marked R. The two sections, i.e. 102 and 103, are connected by two transition sections 108 and 109. The tube contains a non-compressible liquid, e.g. water, alcohol or mercury, denoted in Fig. 1 by wave-like arrows 104, and a circulation pump 105, the rate of flow of which can be controlled, situated within section 102 of the tube at the south. Assuming counter-clockwise movement of the fluid in tube 101, as shown in the figure, liquid enters a first side 106 of the pump, and is forced out the other side 107 of the pump. Due to the action of the pump, liquid 104 flows from transition section 109, through pump 105, and towards transition section 108. Due to the different cross-sectional areas of sections 102 and 103, the liquid accelerates at the entrance to section 103, i.e. at transition section 108, and decelerates at the exit, i.e. at transition section 109. The velocity of the liquid in section 103 is therefore higher than in section 102.
The increase in velocity of the liquid occurs in transition section 108, and is equal to the ratio between the cross sectional areas of sections 102 and 103. 35173/IL/16-ORP In addition the ratio between the mass of the liquid in section 102 and the mass of the liquid in section 103 is also equal to the ratio between the cross sectional areas of sections 102 and 103. The parameter K defined in Eq. defines the relation between the velocities, between the masses, and 5 between the cross sections, wherein Vs is the velocity of liquid passing through southern section 102, Vn is the velocity of liquid passing through northern section 103, Mn is the mass of the liquid in a given length of tube in the northern section 103, Ms is the mass of the liquid in the same length of tube the in southern section 102, Ss is the cross sectional area of section 10 102 and Sn is the cross sectional area of section 103.
Eq. 1 Yn Ms 55 Vs Mn Sn Centrifugal forces, acting radially at any point on the tube, are defined by 15 Eq. 2, wherein f is a centrifugal force exerted on the tube by the liquid, M is the mass of a given length of the liquid, V is the velocity of the liquid within the section 102, which is defined as the flow rate of pump 105 divided by the cross section area S, and R is the radius of the centerline of tube 101. r M*V2f _ ------- Eq. 2 A control length of mass Ms from section 102 of the tube speeds up by a factor of K when entering the section 103 of the tube. The mass Mn of the same control length in section 103 will be equal to 1/K times the mass Ms in 25 section 102. The velocity Vn of the mass in section 103 will be VS*K, compared to its velocity Vs in section 102. 35173/IL/16-ORP The centrifugal forces in the northern region have a value defined by Eq. obtained by combining Eq. 1 and Eq. 2, wherein fs is the centrifugal force acting on section 102, and fn is the centrifugal force acting on section 103.
Eq. 3 =KMn*Vn R MS*V% R fnfs Upon integrating the centrifugal forces fn acting on the northern section of the tube, along its arc length from transition section to transition section, while neglecting the arc lengths of the transition sections (they should be taken into consideration in a more thorough calculation, but are taken to be vanishingly small herein to simplify the explanation of the invention), it is found that Fn, the total force, which points due north, equals 2 * fn.Fn = 2*fn Eq. 4 Similarly, upon integrating the centrifugal forces fs acting on the southern section of the tube along the arc length of the southern section and neglecting the arc length of the transition sections, it is found that Fs, the total force acting due south, equals 2 * fs.Fs = 2*fs Eq. 5 Combining these last two results with Eq. 3, it is found thatFn = K*Fs. Eq. 6 Therefore the net forces FNet acting due north can therefore be described 25 according to Eq. 7FNet = Fn-Fs = (K-1)*Fs Eq. 7 The magnitude of the directional force is determined by the dimensions and characteristics of the system, e.g. the radius R of tube 101, the cross section 35173/IL/16-ORP areas of sections 102 and 103, the mass of the liquid 104, and the flow rate of circulation pump 105, as is expressed in Eq. 8, which is derived using the above equations 2, 5, and 7.
Fnet = (K- 1)*2*^ Eq. 8 According to this embodiment of the invention, reaction forces develop from the action of the pump. In order to cancel these reaction forces two systems as described above can be assembled side by side, each with opposite liquid flow directions, i.e. different orientations of the pump.
Fig. 2 schematically illustrates a propulsion system according to another embodiment of the present invention. For sake of simplifying the description, directions are marked as north and south in Fig. 2. According to this embodiment, the system comprises a semi-toroidal tube 201, with a straight first section 202 in the southern region of the tube and an arched second section 203 in the northern region of the tube. The two sections, i.e. 202 and 203, are connected by two transition sections 208 and 209. The tube contains a non-compressible liquid, e.g. water, alcohol or mercury, denoted in Fig. 2 by wave-like arrows 204, and a pump 205 situated within section 202 of the tube. Assuming counter clockwise flow as shown in the figure, liquid enters a first side 206 of the pump, and is forced out the other side 207 of the pump. Due to the action of the pump, liquid 204 flows from transition section 209, through the pump 205, and towards transition section 208. Due to the different cross-section areas of sections 202 and 203, the liquid accelerates at the entrance to section 203, i.e. at transition section 208, and decelerates at the exit, i.e. at transition section 209.
In this embodiment the southern region develops no centrifugal force, therefore the direction of the net force produced by the system is directed north, with respect to the system. Because the southern region develops no 35173/IL/16-ORP centrifugal force theoretically the diameters of the two sections of tube could be the same, but the system is much more efficient if the straight section has a larger cross-sectional area.
According to this embodiment of the invention, reaction forces develop from the action of the pump. In order to cancel these reaction forces, two systems as described above can be assembled side by side, each with opposite liquid flow directions, i.e. different orientation of the pump.
A numerical example for the second embodiment will now be provided for sake of demonstrating the invention. Sizes and quantities in this example are according to a specific embodiment of the present invention, and are not meant to be limiting in any way. It is obvious that other sizes and quantities can be used depending on the circumstances of a particular application of 15 the invention.
Given the diameter d of the northern section 203 as 0.3 meters, then the 0.07m2. Given the radius R cross section S of section 203 will be S =of the system as 3 meters, then the volume v of the liquid in the section 2will be v=n*R*S = 0.66 m3. Given the flow rate Q of pump 205 as 25 liters per second, which is equivalent to 0.025 m3 per second, then the velocity vt of the liquid within section 203 will be V! = — = 0.357—. Given the totalH 1 S sec mass Mi of the liquid in section 203 as 660 kg, then the centrifugal force f in any direction at the northern section 203 in units of Newtons will be v2 25 f = Mi * — = 28.04 N. The net force F due north is the sum of the 1 1 R centrifugal forces in all directions which is equal to = J^[/ * Sin(a)da] = 2* f = 56.08N , where a = 180° — 6 and Q is the arc length of the transition sections (see Fig. 1). Given that the system comprises two propulsion systems in order to overcome pump reaction forces, the total force due north 35173/IL/16-ORP is Ft = 2*F = 2* 56.08 = 112.16N. Given the total mass Ms of a space vehicle is 5000 kg, then according to Newton's second law of motion, the linear acceleration as of a spacecraft propelled by a system according to this!?• . • Ft 112.16 ??? ? m embodiment is a? =— = ------- = 0.022— -s Ms 5000 sec2 Assuming that a spacecraft is on a mission to Mars and that acceleration is required for passing half the distance, given the total distance s from the spacecraft's initial position, when first activating the propulsion system, to Mars is 90 * 106 km = 90 * 109 meters, then the time the spacecraft requires to reach maximum velocity, and to reach the midpoint between Earth and Mars, using a propulsion system according to the present example, is t =J2 *¦^ = 2.023 * 106seconds = 23.414days. The time required to reach Mars, assuming that deceleration is entirely performed from the midpoint onwards, is therefore 2 * t = 46.828 days. This result is considerably lower than any current prediction for spacecraft travel time to mars using conventional propulsion systems. The maximum velocity vs of a spacecraft using the propulsion system of the present invention at the midpoint between Earth and Mars is Vs =a *t = 0.022 * 2.023 * 106 = 44506 — which is equivalent to 44.506 km per second. sec The above calculation doesn't take into consideration the initial velocity given by the launch rocket or the additional deceleration needed at Mars due to the initial velocity before the system of the invention is activated.
Both embodiments of the propulsion system that are described herein can be stopped and restarted at will. They can also be mounted in a gimbal system so that they can be rotated in order to provide force in any desired direction, including 1800 from the initial position, to provide a braking force when so desired.
Claims (8)
1./IL/16-ORP - 12 - Claims 1. A propulsion system attached to a space vehicle for propelling the space vehicle in an essentially gravity free environment, the system comprising:a) a closed tube comprised of a semi-circular shaped first section of tubing;b) a second section of tubing having a cross-sectional area significantly greater than the cross-sectional area of the first section;c) two transitional sections that join the ends of the first section of tubingto the ends of the second section of tubing;d) a circulation pump, the rate of flow of which can be controlled, located in the second section;e) a non-compressible liquid forced by the pump to circulate continuouslyaround the closed tube.
2. The propulsion system of claim 1, wherein the second section has a semicircular shape.
3. The propulsion system of claim 1, wherein the second section is straight.
4. A propulsion system according to claim 1, wherein reaction forces developed from the pump of a first system are cancelled out by placing a second identical system with the liquid circulating in the opposite direction side by side with the first system.
5. A propulsion system according to claim 1 configured so that the propulsion system can be stopped and restarted at will.
6. A propulsion system according to claim 1 mounted in so that the propulsion system can be rotated in order to provide force in any desired direction. 30 35173/IL/16-ORP - 13 -
7. A propulsion system according to claim 6, wherein the propulsion system is configured to be rotated 180° from an initial direction in which the vehicle is moving in order to provide a braking force.
8. A method of propelling a vehicle on an extended space flight the method comprising:a) attaching to the space vehicle at least one propulsion system according to claim 1; andb) activating the pump to cause the non-compressible liquid to circulate continuously around the closed tube;wherein, the differences in diameters of the first and second sections of tubing will cause the velocity of the non-compressible liquid in the first section to be larger than the velocity of the non-compressible liquid in the second section resulting in a net radial force that will cause the vehicle to accelerate. 15
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IL247953A IL247953B2 (en) | 2016-09-21 | 2016-09-21 | Propulsion system |
| PCT/IL2017/051056 WO2018055612A1 (en) | 2016-09-21 | 2017-09-19 | Propulsion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IL247953A IL247953B2 (en) | 2016-09-21 | 2016-09-21 | Propulsion system |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| IL247953A0 IL247953A0 (en) | 2017-01-31 |
| IL247953B1 IL247953B1 (en) | 2023-03-01 |
| IL247953B2 true IL247953B2 (en) | 2023-07-01 |
Family
ID=57907537
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| IL247953A IL247953B2 (en) | 2016-09-21 | 2016-09-21 | Propulsion system |
Country Status (2)
| Country | Link |
|---|---|
| IL (1) | IL247953B2 (en) |
| WO (1) | WO2018055612A1 (en) |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2798427A1 (en) * | 1999-09-09 | 2001-03-16 | Alexis Defarge | Vehicle propulsion unit has thrust produced by centrifuged fluid and resultant pressure differences between front and rear walls of housing |
-
2016
- 2016-09-21 IL IL247953A patent/IL247953B2/en unknown
-
2017
- 2017-09-19 WO PCT/IL2017/051056 patent/WO2018055612A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| IL247953B1 (en) | 2023-03-01 |
| IL247953A0 (en) | 2017-01-31 |
| WO2018055612A1 (en) | 2018-03-29 |
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