Patent Application
20180023550
The subject invention relates to radio frequency ion thrusters.
Radio frequency ion thrusters typically operate on a propellant such as xenon and include a hollow cathode to neutralize the ion beam emitted by the discharge chamber of the ion generator. See U.S. Pat. No. 9,060,412 incorporated herein by this reference.
The hollow cathode includes an oxide insert which is consumed when the cathode is operated limiting the life of the cathode. Also, a heater is required. A hollow cathode with a C12A7 electride insert is proposed in U.S. Published Application No. 2014/0354138 incorporated herein by this reference and purportedly a heater is not required. Still, in testing, a heater was required for proper operation and such a hollow cathode design may impart constraints for certain types of missions where power is limited or rapid start of the cathode is required.
Because of the difficulty to integrate high-pressure xenon gas vessels onboard small spacecraft, iodine has been proposed for use in electric propulsion devices such as RF ion thrusters. See U.S. Pat. No. 6,609,363 incorporated herein by this reference. Still, a hollow cathode was used as the neutralizer.
The notion of an RF neutralizer for an ion thruster has been studied. See T. Hatakeyama et al., “Preliminary Study on Radio Frequency Neutralizer for Ion Engine,” LEPC-2007-226 (2007) incorporated herein by this reference.
Until now, no known RF ion thruster using iodine as a propellant includes an RF cathode as the neutralizer that also uses iodine as a source of fuel. In the subject invention, both the RF ion thruster and the RF cathode are designed to use iodine in order to, respectively, create ions and neutralizing electrons. As a result, high pressure gas vessels are not required to operate the ion thruster or cathode.
Featured is a system comprising an RF ion thruster including a discharge chamber having a gas inlet and an outlet and a coil about the discharge chamber. An RF cathode is located proximate the discharge chamber outlet of the RF ion thruster and includes a discharge chamber having a gas inlet and an outlet and a coil about the discharge chamber. The system further includes a tank for containing iodine in solid form, a heater associated with said tank to produce iodine vapor, and a feed subsystem fluidly coupling said tank with the RF ion thruster discharge chamber gas inlet and also with the RF cathode discharge chamber gas inlet.
The system further may include an igniter associated with the RF cathode discharge chamber inlet and, in one example, an igniter associated with the RF ion thruster discharge chamber inlet. The RF cathode discharge chamber inlet may include a conduit and the igniter includes spaced conductive electrodes in the conduit coupled to a voltage source and a voltage bias source.
The RF ion thruster may include a conductive grid subsystem proximate the RF ion thruster discharge chamber outlet. In one example, the conductive grid subsystem of the RF ion thruster includes at least two conductive plates with orifices therethough, one said plate supplied with a positive voltage and the other said plate supplied with a negative voltage.
Preferably, the RF cathode includes an electron extractor proximate the RF cathode discharge chamber outlet. In one example, the electron extractor includes a conductive grid subsystem with at least one conductive plate with orifices therethough and a plurality of rearwardly extending members received at least partially in the RF cathode discharge chamber to increase the electron output of the RF cathode. In another example, the electron extractor includes a ring internal to the RF cathode discharge chamber. One preferred ring includes spaced fingers extending therefrom. Further included may be an orifice plate at the RF cathode discharge chamber outlet.
Preferably, the RF ion thruster, the RF cathode, the tank, and the feed subsystem are made of materials resistant to iodine. In one example, the discharge chamber of the RF ion thruster and the discharge chamber of the RE cathode are made of ceramic material. The tank may be made of thermoplastic and includes a metal internal coating to uniformly distribute heat. In one example, the heater includes tape heaters bonded to the coating. Also featured is a novel RF cathode system comprising a ceramic discharge chamber having a gas inlet and an outlet, a coil about the discharge chamber, a tank for containing iodine in solid form, a heater associated with said tank to produce iodine vapor, a feed subsystem fluidly coupling the tank with the RF cathode discharge chamber gas inlet, an igniter associated with the RF cathode discharge chamber inlet including spaced conductive electrodes coupled to a voltage source and a voltage bias source, and an electron extractor proximate the discharge chamber outlet.
Also featured is a method of generating thrust. Iodine is headed to produce iodine vapor. The iodine vapor is fed to an RF ion thruster to produce an ion beam which is neutralized by feeding iodine vapor to an RF cathode producing electrons directed to the ion beam output by the RF ion thruster.
The method may further include increasing the electron output of the RF cathode by placing at least one grid plate proximate the RF cathode and increasing the surface area of the grid plate. There may be two conductive plates with orifices therethough, one plate supplied with a positive voltage and the other plate supplied with a negative voltage.
The method may further include generating seed electrons drawn into the RF cathode. In one example, generating seed electrons includes locating an igniter upstream of the RF cathode. In some embodiments, the method may further include generating seed electrons drawn into the RF ion thruster by locating an igniter upstream of the RF ion thruster.
The method may further include extracting electrons from the RF cathode. In one example, extracting electrons includes placing a ring with fingers extending therefrom inside the RF cathode.
The subject invention, however, in other embodiments, need not achieve all these objectives and the claims hereof should not be limited to structures or methods capable of achieving these objectives.
Other objects, features and advantages will occur to those skilled in the art from the following description of a preferred embodiment and the accompanying drawings, in which:
Aside from the preferred embodiment or embodiments disclosed below, this invention is capable of other embodiments and of being practiced or being carried out in various ways. Thus, it is to be understood that the invention is not limited in its application to the details of construction and the arrangements of components set forth in the following description or illustrated in the drawings. If only one embodiment is described herein, the claims hereof are not to be limited to that embodiment. Moreover, the claims hereof are not to be read restrictively unless there is clear and convincing evidence manifesting a certain exclusion, restriction, or disclaimer.
RF cathode 30 is disposed proximate the discharge chamber outlet 18 of RF ion thruster 12. Cathode or neutralizer 30 includes ceramic discharge chamber 32 with gas inlet 34 and outlet 36. Coil 28 is disposed about discharge chamber 32. A conductive grid subsystem 40 disposed at the outlet 36 may include a conductive plate 42a and optional conductive plate 42b both including orifices therethrough. Plate 42a may be supplied with a negative voltage (e.g., −50 to −200 V) and plate 42b if used is typically at reference potential, 0 volts.
The ceramic material of the discharge chambers 14 and 32 is preferably highly resistant to iodine. In one example, the ceramic material used was alumina. In another example, the ceramic material was Macor. The RF coils 20 and 38 are preferably made of highly conductive material with extremely thin insulation layer for maximum inductance at a 1-10 MHz frequency range. In one example the coil was made of pure silver wire with 0.005″-thick PTFE tubing. In another example the coil was made of pure silver wire with 0.001″-thick polyamide tape or coating for insulation.
Tank 50 stores solid iodine 52 therein (e.g., powder, a solid block of iodine, iodine chips, or the like). Heater 51 associated with tank 50 is used to heat the solid iodine and produce iodine vapor supplied by feed subsystem 54 to the inlet 16 of ion thruster 12 and to the inlet 34 of cathode 30. Tank 50 may be formed from a machined polyetherimide (PEI, trade name Ultem) box with an epoxied or ultrasonically-welded Ultem lid, or a stamp formed thin Hastelloy or Inconel sheet with a welded lid, or a fully welded box made of thin Hastelloy or Inconel sheets. Heater 51 is bonded to the tank exterior and an outer layer of insulation 53 may be included. The heater 51 may also be bonded to the tank 50 interior, with or without additional outer layer of insulation 53.
The various valves, sensors, heaters, and controls associated with a feed system fluidly connecting the tank 50 with the ion thruster and the cathode are not shown in
Preferably, conductive grid plate 42a of the cathode,
Also, an igniter 70,
Because of the corrosiveness of iodine, any component in the system exposed to iodine is preferably made of materials resistant to iodine. Thus, the interior of tank 50, the interior of the conduits of the feed subsystem 54, the interior of chambers 14 and 32, the plates of the conductive grid subsystems 22 and 40, the electron extractor 39,
Another example of an RF cathode 30′ is shown in
The RF cathode of
In one example, iodine tank 50′,
In another example, tank 50″,
Although specific features of the invention are shown in some drawings and not in others, this is for convenience only as each feature may be combined with any or all of the other features in accordance with the invention. The words “including”, “comprising”, “having”, and “with” as used herein are to be interpreted broadly and comprehensively and are not limited to any physical interconnection. Moreover, any embodiments disclosed in the subject application are not to be taken as the only possible embodiments. Other embodiments will occur to those skilled in the art and are within the following claims.
In addition, any amendment presented during the prosecution of the patent application for this patent is not a disclaimer of any claim element presented in the application as filed: those skilled in the art cannot reasonably be expected to draft a claim that would literally encompass all possible equivalents, many equivalents will be unforeseeable at the time of the amendment and are beyond a fair interpretation of what is to be surrendered (if anything), the rationale underlying the amendment may bear no more than a tangential relation to many equivalents, and/or there are many other reasons the applicant cannot be expected to describe certain insubstantial substitutes for any claim element amended.
This application claims benefit of and priority to U.S. Provisional Application Ser. No. 62/319,550 filed Apr. 7, 2016, under 35 U.S.C. §§119, 120, 363, 365, and 37 C.F.R. §1.55 and §1.78, which is incorporated herein by this reference.
This invention was made with U.S. Government support under Contract No. NNX15CC90C awarded by the National Aeronautics and Space Administration (NASA). The Government may have certain rights in the subject invention.
| Number | Date | Country | |
|---|---|---|---|
| 62319550 | Apr 2016 | US |
