GB2115620A - Space craft propelling apparatus - Google Patents
Space craft propelling apparatus Download PDFInfo
- Publication number
- GB2115620A GB2115620A GB08309086A GB8309086A GB2115620A GB 2115620 A GB2115620 A GB 2115620A GB 08309086 A GB08309086 A GB 08309086A GB 8309086 A GB8309086 A GB 8309086A GB 2115620 A GB2115620 A GB 2115620A
- Authority
- GB
- United Kingdom
- Prior art keywords
- propellant
- solenoid
- cylinder
- upright
- rotating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 239000003380 propellant Substances 0.000 claims abstract description 41
- 239000007788 liquid Substances 0.000 claims abstract description 9
- 239000002826 coolant Substances 0.000 claims description 15
- 238000004804 winding Methods 0.000 claims description 15
- 229910000838 Al alloy Inorganic materials 0.000 claims description 10
- 230000003319 supportive effect Effects 0.000 claims description 10
- 238000005086 pumping Methods 0.000 claims description 8
- 229910000831 Steel Inorganic materials 0.000 claims description 7
- 239000010959 steel Substances 0.000 claims description 7
- 238000001816 cooling Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 6
- 230000005611 electricity Effects 0.000 claims description 5
- 239000004411 aluminium Substances 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 239000010949 copper Substances 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 238000005275 alloying Methods 0.000 claims description 2
- 238000007599 discharging Methods 0.000 claims description 2
- 238000010292 electrical insulation Methods 0.000 claims description 2
- 239000008236 heating water Substances 0.000 claims description 2
- 229910052751 metal Inorganic materials 0.000 claims description 2
- 239000002184 metal Substances 0.000 claims description 2
- 238000005096 rolling process Methods 0.000 claims description 2
- 230000002459 sustained effect Effects 0.000 claims description 2
- 238000006243 chemical reaction Methods 0.000 abstract description 4
- 230000015572 biosynthetic process Effects 0.000 abstract description 3
- 238000010521 absorption reaction Methods 0.000 abstract 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 229910001369 Brass Inorganic materials 0.000 description 2
- 239000010951 brass Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 229910052770 Uranium Inorganic materials 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000011491 glass wool Substances 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 229910001234 light alloy Inorganic materials 0.000 description 1
- 230000001613 neoplastic effect Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 239000011226 reinforced ceramic Substances 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- JFALSRSLKYAFGM-UHFFFAOYSA-N uranium(0) Chemical compound [U] JFALSRSLKYAFGM-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02N—ELECTRIC MACHINES NOT OTHERWISE PROVIDED FOR
- H02N11/00—Generators or motors not provided for elsewhere; Alleged perpetua mobilia obtained by electric or magnetic means
- H02N11/006—Motors
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Reciprocating, Oscillating Or Vibrating Motors (AREA)
Abstract
A propelling apparatus for a space craft comprises an upright electromagnetic solenoid (9) in high rotation with a tubular internal vertically vaned core, an extended internally vaned tubular driving shaft axially aligned above it, an inlet for magnetically responsive liquid pumped into the top of the motorized driving shaft in centrifugal downward progression which enters the larger diameter solenoid core with increasing angular velocity through a centrifugal constriction on core base, on emergence the liquid divides and impacts a circular walled confinement within a reaction absorption chamber. Captured by magnetic nodes, adjacent pumps return the opposite reaction absorbed liquid for re-cycle. High amperage direct constant polarity electric current in continual intermittant connection frequency, pulses electro-magnetic energy when disconnection phases occur, the liquid discharges act as a propellant, changing from disc formation to a frusto-conically expanding flare formation and maintain persistant chamber wall impacts. <IMAGE>
Description
SPECIFICATION
A method of propelling a space vehicle and a space vehicle electro-magnetic propellor
I, John Wilkinson of 61, Earl Street, Clayton-lemoors near Accrington, Lancashire, England do hereby declare the invention, for which I pray that a patent be granted to me, and the method by which it is to be performed, to be particularly described in and by the following statement:- This invention relates to a method of propelling a space vehicle and a space vehicle.
Penetration of outer space by combustion rockets used at the present time, do not seem to relate to progress in other fields of technology, in view of the fact that they expend most of their structures and energy to achieve initial space entry, the remnant is limited in navigational means and un-acceptable re-entry speeds.
A form of vehicle which could re-place the combustion rocket with a capability to enter space, return, and still be total in its parts, for long service, and good navigability in all conditions, is the reason for attempting to progress that formation.
According to one aspect of the invention there is provided a method of propelling a space vehicle comprising the steps of: -injecting a magnetically responsive liquid,
hereinafter called propellant, into the top of
an upright cylinder, which is extended at the
top by a frusto-conically converged inlet and
extended at the bottom by a frusto-conically
flared outlet, vanes inside the said cylinder
are fitted running top to bottom; -enclosing the cylinder within the core of an
electro-magnetic solenoid and attaching it to it; -supporting the cylinder and the said solenoid
by inserting their total into a strong outer
casing for cushioning against centrifugal force;; rotating the said strong outer casing round
their common upright axis with an electric
motor situated above the outer casing; -connecting the solenoid windings to an
intermittent direct current electric power
supply at an intermittancy frequency which
allows the solenoid to attain a full charge of
electro-magnetic energy; discharging the said propellant, by switching
on, and then switching off continually, as quickly
as a full charge of electro-magnetic energy will
allow, the aforesaid being the propulsion
frequency; -collecting the outward spiralling discharged
propellant in a non-rotary ring shaped reservoir
made of steel which is magnetized to retain
propellant for re-use;; pumping the propellant from the said reservoir
back to the rotating upright cylinder by means
of pipes and pumps to a receiving chamber
where the pipes converge, the said receiving
chamber outletting the propellant to a nozzle at
the top of the said upright cylinders said frusto
conically converged inlet, and thereby injecting
propellant in a continual sustained supply; cooling the solenoid windings to a low
temperature by having the windings in tubular
section and pumping a low temperature liquid
through their entire length; reducing electrical resistance and weight of the
solenoid by, in example, combining nobium,
copper and aluminium by alloying them, and
making the solenoid tubular windings from the
metal, and cooling them;; insulating coolant delivery pipes from
electricity by fitting non-conductive pipe
connectors to inlet and outlet junctions; controliing resultant torques with gyroscopes.
According to another aspect of the invention there is provided a space vehicle for entering space, comprising, two vertically imposed structures, the inner structure comprising: an upright cylinder extended at the top by a
conically converging inlet and extended at the
bottom by a frusto-conicaily flared outlet, and
internal vanes vertically attached to the total
length of the cylinder; an electro-magnetic solenoid which contains
the upright cylinder in its core; a solenoid supportive casing for cushioning the
solenoid windings against centrifugal force;; a tubular driving shaft extending from the top
of the said supportive casing, for rotating the
supportive casing and its contents at high
speed, and delivering propellant down its
interior vaned tube, outletting to the top of the
rotating upright cylinder; an electric motor armature mounted on the
said driving shaft to rotate the shaft; a four contact slip ring to transmit electric
power to the solenoid and shaft mounted
electric motor armature; a propellant delivery valve defining between
the top of the driving shaft and the said
receiving chamber to transfer non-rotating
propellant to the rotating drive shaft, and a
coolant transfer rotary slide valve; and the
outer structure comprising: an on and off rotary electric switch, variable in
its speed and thus its frequency, to supply the
solenoid with high amperage intermittant
direct electric current, being rotated by a
variable speed electric motor; a large diameter non-rotary ring shaped
reservoir made from magnetized steel to retain
outward spiralling discharged propellant for re
use; pumps for pumping propellant from the said
reservoir back to the upright cylinder; pipes for propellant delivery; a propellant receiving chamber to which the
pipes converge and outlet to the upright
cylinders injection nozzle; a coolant transfer rotary slide valve top with
electrical insulation to stop back feed from the
solenoid;; a propellant transfer delivery valve top collar; a direct current electric generator built of
aluminium alloy in its main structure; -a steam engine to drive the generator, built
mainly of aluminium alloy, to supply all
electricity needed, when the generator is driven
by it; -a water boiler to supply compressed steam to
the steam engine built mainly of aluminium
alloy, and steel; -a nuclear reactor with moderator control for
getting steam by heating water; -a refrigerator for steam condensing and cooling
coolant;; -motorized gyroscopes of which there are two
pairs for back torquing the said outer structure
against the rotating upright cylinder and
horizontally torquing against the space vehicles
total structure to change the direction of travel
by rolling it; -a circuit of wires and pipes with attached
controls, in example, switches, valves and
instruments, for operating the space vehicle; -an outer structure made from aluminium alloy.
For a better understanding of the invention and to show how the same may be carried into effect,
reference will now be made, by way of example, to the accompanying drawings, in which:
Figure 1 is a sectional vertical view of one form
of space vehicle according to the invention, and
Figure 2 is a cross sectional view of the vehicle.
In the case of the illustrated embodiment, the vehicle is an electro-magnetically propelled space vehicle, such as may be used for surveillance, early warning, and defence at combustion rocket apogee's.
As may be seen from Figure 1 the space vehicle comprises of an outer structure 24 of upright integral cylinders of varied diameters made of aluminium alloy, the domed cylinder at the apex contains a pair of diametrically opposed gyroscopes 1 on a rotationally mounted electric motor which rotates in the vertical plane by a divided electric motor, on activation the outer structure rolls to a new direction of travel and is a gyroscopic rudder in effect.
Rotationai stability is achieved by variable speed of the outer structure stabilizer gyroscopes 1 7 and can unify with the top gyroscopes 1 by torque manipulation to all points of direction, the main stability function of the gyroscopes at 1 7 is to torque against the propeller motor 4 to stop the outer structure rotating.
A propellant receiving chamber 2 delivers propellant down the supportive case 7 extended hollow driving shaft, the interior being vaned down its length to pre-centrifuge propellant preparatory to injection into the upright cylinder 8 for electro-magnetic discharge and subsequent emergence from the frusto-conically flared outlet where the propellant centrifugally recedes in particulated neoplastic division to the vertical wall of the impulse reaction absorpsion chamber 25 where the magnetic ring shaped reservoir 21 holds the propellant for re-pumping through the eight centrifugal pumps 22 and outletting to the delivery pipes 10 which are returning propellant back to the aluminium built receiving chamber 2, the way of the aluminium alloy delivery pipes 10 being by passing them through the aluminium alloy tubular outer structure strengthening shores
12 of which there are eight, the electric cables and glass wool insulated coolant pipes are also passed through the hollow shores, the integral rotary electro-magnetic propellor comprises a supportive case 7 and its extended top driving shaft the driving shaft electric motor 4 armature is mounted upon the shaft and connected from the four contact slip ring 6 by rigid rods of copper firmly fixed, the two slip rings armature contacts have a commutation by insulative breaks in the brass rings to operate the armature in proper sequence and are shown at six, 6 the two remaining slip rings are in constant contact with the solenoid windings, an intermittant high amperage passing totally across them to the electro-magnetic solenoid 9, disposed between slip rings 6 and the driving shaft is a coolant delivery slide valve with a grooved interface, the slide valve 5 has seals against coolant leakage and transfers coolant across it to and from the solenoid windings. Steel ball bearings 3 and 11 support the total electro-magnetic propellor. The upright cylinder 8 impulse chamber is a replaceable component because of abrasion made from carbon fibre reinforced ceramic material with pre-cast vertical vanes down the interior.Axially disposed inside the supportive case 7 the solenoid 9 is electrically connected to the slip rings through insulation lined holes in the top of the supportive case 7, where two carbon contacts contact and supply intermittant high amperage direct current to the solenoid windings 9, in the contact phase the current value rises and is opposed for a short time by a back electromotive force until the current ceases to rise, the stored energy is released when the electric current is switched off in the non-contact phase and the propellant in the solenoids core is discharged as the magnetic field collapses and in continual change of the said phases a frequency exists, and in the continual pumping of supply's of electro-magnetically responsive liquid propellant to the rotating upright cylinder 8 the outer structure, and all it contains, will lift by the power of the discharges in reaction to the propellants downward impellation.
The acuminated floor 23 is to stop structural damage if an out of rotation discharge occurs on pump tests when the propellant is in cascade. The area 18 is a control area.
Power is produced by the direct current generator 14, driven by a mechanically advantaged radial steam engine 1 3 through an internal gearbox, the low revolution steam engine driving a high revolution electric generator 14, strong light alloys being used in their construction, the condenser 20 and refrigerator 1 9 condensing exhaust steam for re-cycle, the nuclear reactor 1 6 makes flash steam to drive the steam engine 13, the closed energy system making no exterior demands, other than uranium.
The water boiler 1 5 is shown.
As may be seen on Figure 2, a view of a transmission system is shown, whereby electricity and coolant are transferred to the rotary state, the two outer rings 28 and 29 supply high amperage direct electric current in intermittent pulses, working in the same polarity continually, the rings are slip rings made of brass, with the non-rotary contacts made of carbon. The inner slip rings 30 and 31 supply commutated polarity through electrically insulated segments to motivate the armature of the motor 4 shown on Figure 1.
The slide valve milled circular grooves define between the electric slip rings and the driving shaft, inletting and outletting solenoid winding coolant, the ring in which the grooves are cut, is electically non-conductive to prevent shorting across. The grooves are shown at 26 and 27.
Solenoid coolant being electrically subjected to the same amperage as the solenoid winding slip rings 28 and 29 has also to be electrically nonconductive.
Claims (3)
1. A method of propelling a space vehicle comprising the steps of: -injecting a magnetically responsive liquid,
hereinafter called propellant, into the top of an
upright cylinder which is extended at the top by
a frusto-conically converged inlet and extended
at the bottom by a frusto-conically flared outlet,
vanes inside the said cylinder are fitted running
top to bottom; -enclosing the cylinder within the core of an
electro-magnetic solenoid and attaching it to it; -supporting the cylinder and the said solenoid
by inserting their total into a strong outer
casing for cushioning against centrifugal force; rotating the said outer casing round their
common upright axis with an electric motor
situated above the outer casing;; -connecting the solenoid windings to an
intermittant direct current electric power
supply at an intermittancy frequency which
allows the solenoid to attain a full charge of
electro-magnetic energy; -discharging the said propellant, by switching
on, and then switching off continually, as
quickly as a full charge of electro-magnetic
energy will allow, the aforesaid being the
propulsion frequency; -collecting the outward spiralling discharged
propellant in a non-rotary ring shaped reservoir
made from steel which is magnetized to retain
propellant for re-use;; pumping the propellant from the said reservoir
back to the rotating upright cylinder by means
of pipes and pumps to a receiving chamber
where the pipes converge, the said receiving
chamber outletting the propellant to a nozzle at
the top of the said upright cylinders, said frusto
conically converged inlet, and thereby injecting
propellant in a continual sustained supply; cooling the solenoid windings to a low
temperature by having the windings in tubular
section and pumping a low temperature liquid
through their entire length; reducing electrical resistance and weight of the
solenoid by, in example, combining nobium,
copper and aluminium by alloying them, and
making the solenoid tubular windings from the
metal, and cooling them;; insulating coolant delivery pipes from
electricity by fitting non-conducting pipe
connectors to inlet and outlet junctions; controlling resultant torques with gyroscopes.
2. A method of propelling a space vehicle substantially as hereinbefore described with reference to the accompanying drawings.
3. A space vehicle for entering space having two vertically imposed structures, the inner structure comprising an upright cylinder extended at the top by a conically converging inlet and extended at the bottom by a frusto-conically flared outlet, and internal vanes vertically attached to the total length of the cylinder; an electro-magnetic solenoid which contains
the upright cylinder in its core; a solenoid supportive casing for cushioning the
solenoid windings against centrifugal force; a tubular driving shaft extending from the top
of the said supportive casing, for rotating the
supportive casing and its contents at high
speed, and delivering propellant down its
interior vaned tube, outletting to the top of the
rotating upright cylinder; an electric motor armature mounted on the
said driving shaft to rotate the shaft; a four contact slip ring to transmit electric
power to the solenoid and shaft mounted
electric motor armature; a propellant delivery valve defining between
the top of the driving shaft and the said
receiving chamber to transfer non-rotating
propellant to the rotating drive shaft, and a
coolant transfer rotary slide valve, and the
outer structure comprising:: an on and off rotary electric switch, variable in
its speed and thus its frequency, to supply the
solenoid with high amperage intermittant
direct electric current, being rotated by a
variable speed electric motor; a large diameter non-rotary ring shaped
reservoir made from magnetized steel to retain
outward spiralling discharged propellant for re
use; pumps for pumping propellant from the said
reservoir back to the upright cylinder; pipes for propellant delivery; a propellant receiving chamber to which the
pipes converge and outlet to the upright
cylinders injection nozzle; a coolant transfer rotary slide valve top with
electrical insulation to stop back feed from the
solenoid;; a propellant transfer delivery valve top collar; a direct current electric generator built of
aluminium alloy in its main structure; a steam engine to drive the generator, built
mainly of aluminium alloy, to supply all
electricity needed, when the generator is driven
by it; a water boiler to supply compressed steam to
the steam engine built mainly of aluminium
and steel; a nuclear reactor with moderator control for
getting steam by heating water; a refrigerator for steam condensing and cooling
coolant; ; motorized gyroscopes of which there are two
pairs for back torquing the said outer structure
against the rotating upright cylinder and
horizontally torquing against the space vehicles
total structure to change the direction of travel
by rolling it; a circuit of wires and pipes with attached
controls in example, switches, valves and
instruments, for operating the space vehicle; an outer structure made from aluminium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08309086A GB2115620A (en) | 1982-02-26 | 1983-02-24 | Space craft propelling apparatus |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8205640 | 1982-02-26 | ||
| GB08309086A GB2115620A (en) | 1982-02-26 | 1983-02-24 | Space craft propelling apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2115620A true GB2115620A (en) | 1983-09-07 |
Family
ID=26282083
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08309086A Withdrawn GB2115620A (en) | 1982-02-26 | 1983-02-24 | Space craft propelling apparatus |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2115620A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2583056A (en) * | 2019-01-09 | 2020-10-21 | Scott Ross Alexander | Inter planetary propulsion engine |
| CN113116314A (en) * | 2021-03-31 | 2021-07-16 | 淮南联合大学 | In-cabin vital sign monitoring system based on millimeter wave radar |
| SE2000238A1 (en) * | 2020-12-16 | 2022-06-17 | Stefan Tubman | Vortex Propeller |
-
1983
- 1983-02-24 GB GB08309086A patent/GB2115620A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2583056A (en) * | 2019-01-09 | 2020-10-21 | Scott Ross Alexander | Inter planetary propulsion engine |
| SE2000238A1 (en) * | 2020-12-16 | 2022-06-17 | Stefan Tubman | Vortex Propeller |
| CN113116314A (en) * | 2021-03-31 | 2021-07-16 | 淮南联合大学 | In-cabin vital sign monitoring system based on millimeter wave radar |
| CN113116314B (en) * | 2021-03-31 | 2024-03-15 | 淮南联合大学 | Millimeter wave radar-based cabin vital sign monitoring system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |