NZ740992B2 - Internal wire-triggered pulsed cathodic arc propulsion system - Google Patents
Internal wire-triggered pulsed cathodic arc propulsion systemInfo
- Publication number
- NZ740992B2 NZ740992B2 NZ740992A NZ74099216A NZ740992B2 NZ 740992 B2 NZ740992 B2 NZ 740992B2 NZ 740992 A NZ740992 A NZ 740992A NZ 74099216 A NZ74099216 A NZ 74099216A NZ 740992 B2 NZ740992 B2 NZ 740992B2
- Authority
- NZ
- New Zealand
- Prior art keywords
- cathode
- trigger
- propulsion system
- cathodic arc
- pulsed cathodic
- Prior art date
Links
- 230000001960 triggered effect Effects 0.000 title claims abstract 3
- 238000010891 electric arc Methods 0.000 claims abstract 9
- 239000012212 insulator Substances 0.000 claims abstract 4
- 239000007787 solid Substances 0.000 claims abstract 3
- 230000005684 electric field Effects 0.000 claims abstract 2
- 239000003990 capacitor Substances 0.000 claims 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims 4
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims 4
- 229910052799 carbon Inorganic materials 0.000 claims 4
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims 3
- 229910052721 tungsten Inorganic materials 0.000 claims 3
- 239000010937 tungsten Substances 0.000 claims 3
- OYPRJOBELJOOCE-UHFFFAOYSA-N Calcium Chemical compound [Ca] OYPRJOBELJOOCE-UHFFFAOYSA-N 0.000 claims 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims 2
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims 2
- 239000004411 aluminium Substances 0.000 claims 2
- 229910052782 aluminium Inorganic materials 0.000 claims 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims 2
- 229910052797 bismuth Inorganic materials 0.000 claims 2
- JCXGWMGPZLAOME-UHFFFAOYSA-N bismuth atom Chemical compound [Bi] JCXGWMGPZLAOME-UHFFFAOYSA-N 0.000 claims 2
- 229910052791 calcium Inorganic materials 0.000 claims 2
- 239000011575 calcium Substances 0.000 claims 2
- 229910052804 chromium Inorganic materials 0.000 claims 2
- 239000011651 chromium Substances 0.000 claims 2
- 229910052742 iron Inorganic materials 0.000 claims 2
- 229910052749 magnesium Inorganic materials 0.000 claims 2
- 239000011777 magnesium Substances 0.000 claims 2
- 229910052750 molybdenum Inorganic materials 0.000 claims 2
- 239000011733 molybdenum Substances 0.000 claims 2
- 229910052759 nickel Inorganic materials 0.000 claims 2
- 239000003870 refractory metal Substances 0.000 claims 2
- 229910052715 tantalum Inorganic materials 0.000 claims 2
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims 2
- 229910052718 tin Inorganic materials 0.000 claims 2
- 239000010936 titanium Substances 0.000 claims 2
- 229910052719 titanium Inorganic materials 0.000 claims 2
- 229910052720 vanadium Inorganic materials 0.000 claims 2
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims 2
- 235000015842 Hesperis Nutrition 0.000 claims 1
- 235000012633 Iberis amara Nutrition 0.000 claims 1
- 239000000956 alloy Substances 0.000 claims 1
- 229910045601 alloy Inorganic materials 0.000 claims 1
- 239000002131 composite material Substances 0.000 claims 1
- 230000003628 erosive effect Effects 0.000 claims 1
- 238000007493 shaping process Methods 0.000 claims 1
Classifications
-
- 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
- B64G1/405—Ion or plasma engines
-
- 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
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
-
- 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
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0012—Means for supplying the propellant
-
- 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
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters
Abstract
Disclosed is a pulsed cathodic arc propulsion system for use in a spacecraft. The system includes a solid conductive or semiconductive cathode and an an anode having a potential difference relative to said cathode. The potential difference creates an electric field between said anode and said cathode. Further included is an insulated electrical trigger comprising a trigger pin and an insulator between said trigger pin and said cathode, said insulated electrical trigger adapted to trigger an arc discharge from a point on an outer surface of said cathode when said insulated electrical trigger and said cathode are in a vacuum or a near vacuum space environment. The insulated electrical trigger is bounded within the cathode so that the point at which the arc discharge is triggered is located on the outer surface of said cathode, said anode and said cathode being arranged so that the arc discharge propels the spacecraft. The insulated electrical trigger comprises a trigger power supply configured to operate in the vacuum or the near vacuum space environment and to apply a charging voltage in the range of 50V to 500V between the cathode and the anode and to generate a trigger pulse of 1.2kV or less with a first duration of 3 µs or less to create a high current surface flashover across said insulator between the trigger pin and the outer surface of the cathode to create a plasma. The trigger power supply is further configured to maintain the production of the plasma by applying a burning voltage of between 30V and 100V between the cathode and the anode for a second duration of between 20 µs to 500 µs after the trigger pulse.
Claims (25)
1. A pulsed cathodic arc propulsion system for use in a spacecraft comprising: a solid cathode, wherein said cathode is solid and is conductive or semiconductive; an anode having a potential difference relative to said cathode, said potential 5 difference creating an electric field between said anode and said cathode; and an insulated electrical trigger comprising a trigger pin and an insulator between said trigger pin and said cathode, said insulated electrical trigger adapted to trigger an arc discharge from a point on an outer surface of said cathode when said insulated electrical trigger and said cathode are in a vacuum or a near vacuum space environment, said 10 insulated electrical trigger being bounded within the cathode so that the point at which the arc discharge is triggered is located on the outer surface of said cathode, said anode and said cathode being arranged so that the arc discharge propels the spacecraft, wherein the insulated electrical trigger comprises a trigger power supply configured to operate in the vacuum or the near vacuum space environment and to apply a charging 15 voltage in the range of 50V to 500V between the cathode and the anode and to generate a trigger pulse of 1.2kV or less with a first duration of 3 µs or less to create a high current surface flashover across said insulator between the trigger pin and the outer surface of the cathode to create a plasma, and the trigger power supply is further configured to maintain the production of the plasma by applying a burning voltage of between 30V and 100V 20 between the cathode and the anode for a second duration of between 20 µs to 500 µs after the trigger pulse.
2. The pulsed cathodic arc propulsion system according to claim 1, wherein the cathode is selected from the group consisting of: magnesium, titanium, carbon, aluminium, calcium, 25 carbon, vanadium, molybdenum, tungsten, tantalum, tin, bismuth, nickel, iron and chromium.
3. The pulsed cathodic arc propulsion system according to claim 1, wherein the cathode is an alloy or composite comprising at least one of magnesium, titanium, carbon, aluminium, 30 calcium, carbon, vanadium, molybdenum, tungsten, tantalum, tin, bismuth, nickel, iron or chromium.
4. The pulsed cathodic arc propulsion system according to any one of the preceding claims, wherein the insulated electrical trigger is a wire which protrudes from the cathode at speci for response amendments - 14.02.23(1004549998.1).docx a trigger point on the outer surface of the cathode, and further wherein the insulated electrical trigger is internal to the cathode.
5. The pulsed cathodic arc propulsion system according to any one of the preceding 5 claims, wherein the insulated electrical trigger is located at a trigger point on the outer surface of the cathode, said trigger point being within a perimeter of said outer surface.
6. The pulsed cathodic arc propulsion system according to claim 5, wherein said trigger point is located at or adjacent to a centre of the outer face of the cathode.
7. The pulsed cathodic arc propulsion system according to claim 6, wherein said trigger point is located on or proximal to an edge of a centre-bored hole of said cathode, wherein at least part of said insulated electrical trigger is located within said centre-bored hole. 15
8. The pulsed cathodic arc propulsion system according to claim 5, wherein the trigger point is located less than one half of the distance from the centre of the outer surface of the cathode to the circumference of the outer surface of the cathode.
9. The pulsed cathodic arc propulsion system according to claim 8, wherein the trigger 20 point is located less than one quarter of the distance from the centre of the outer surface of the cathode to the circumference of the outer surface of the cathode.
10. The pulsed cathodic arc propulsion system according to any one of the preceding claims, wherein said trigger pin comprises a refractory metal.
11. The pulsed cathodic arc propulsion system according to claim 10, wherein said refractory metal is tungsten.
12. The pulsed cathodic arc propulsion system according to any one of the preceding 30 claims, wherein said plasma forms a plasma plume normal to the outer surface of the cathode.
13. The pulsed cathodic arc propulsion system according to any one of the preceding claims, further comprising: speci for response amendments - 14.02.23(1004549998.1).docx a feed mechanism to control movement of said cathode relative to said insulated electrical trigger.
14. The pulsed cathodic arc propulsion system according to claim 13, wherein said feed 5 mechanism includes a worm drive, said worm drive including a worm wheel adapted to engage a worm screw forming part of said cathode, said worm wheel being driven by a motor.
15. The pulsed cathodic arc propulsion system according to claim 13, wherein said feed 10 mechanism includes a spring biased to advance the cathode, relative to said trigger, as said insulated electrical cathode wears from said arc discharge.
16. The pulsed cathodic arc propulsion system according to claim 12, further comprising: a magnetic nozzle for directing said plasma plume.
17. The pulsed cathodic arc propulsion system according to claim 16, wherein said magnetic nozzle includes at least one permanent magnet.
18. The pulsed cathodic arc propulsion system according to any one of the preceding 20 claims, further comprising: a magnetic guide adapted to steer the point of arc discharge on the upper surface of said cathode.
19. The pulsed cathodic arc propulsion system according to claim 18, wherein said 25 magnetic guide includes at least one of a magnetic coil or a permanent magnet.
20. A spacecraft propulsion system comprising the pulsed cathodic arc propulsion system of any one of the preceding claims. 30
21. A spacecraft comprising the spacecraft propulsion system of claim 20, wherein the spacecraft is selected from the group consisting of: rockets, space shuttles, satellites, and space stations. speci for response amendments - 14.02.23(1004549998.1).docx
22. The pulsed cathodic arc propulsion system according to any one of the preceding claims, further comprising a main capacitor bank (C ) configured to dissipate stored energy through the cathode to maintain production of the plasma after triggering. 5
23. The propulsion system according to claim 22 wherein the insulated electrical trigger further comprises a pulse control and termination system which controls grounding of the main capacitor bank to terminate the trigger pulse a predetermined time period after triggering. 10
24. The pulsed cathodic arc propulsion system according to claim 23, wherein the pulse control and termination system uses pulse shaping to change a magnitude of a current of the arc discharge to control an erosion profile of the cathode.
25. The pulsed cathodic arc propulsion system according to claim 24 further comprising a 15 steering device to steer cathode spots across the upper surface of the cathode, the steering device comprising the main capacitor bank (C ) in series with an inductor (L ) and switch (S ), wherein the main capacitor bank is in parallel with a set of sub-banks of capacitors where each capacitor of the set of sub-banks of capacitors is in series with a respective inductor and a respective switch, and the pulse control and termination system controls 20 operations of each switch. speci for response amendments - 14.02.23(1004549998.1).docx
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AU2015903748A AU2015903748A0 (en) | 2015-09-15 | Internal wire-triggered pulsed cathodic arc propulsion system | |
| PCT/AU2016/050846 WO2017045020A1 (en) | 2015-09-15 | 2016-09-09 | Internal wire-triggered pulsed cathodic arc propulsion system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| NZ740992A NZ740992A (en) | 2023-12-22 |
| NZ740992B2 true NZ740992B2 (en) | 2024-03-26 |
Family
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