DE102009036327A1 - Fluid-dynamic actuator for controlling position of small satellite, has transformer and frequency producing element electrically connected to each other such that electrical voltage of spacecraft is transformed into direct current voltage - Google Patents
Fluid-dynamic actuator for controlling position of small satellite, has transformer and frequency producing element electrically connected to each other such that electrical voltage of spacecraft is transformed into direct current voltage Download PDFInfo
- Publication number
- DE102009036327A1 DE102009036327A1 DE102009036327A DE102009036327A DE102009036327A1 DE 102009036327 A1 DE102009036327 A1 DE 102009036327A1 DE 102009036327 A DE102009036327 A DE 102009036327A DE 102009036327 A DE102009036327 A DE 102009036327A DE 102009036327 A1 DE102009036327 A1 DE 102009036327A1
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- Germany
- Prior art keywords
- fluid dynamic
- dynamic actuator
- liquid
- angular momentum
- fluid
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- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 claims description 2
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- BITYAPCSNKJESK-UHFFFAOYSA-N potassiosodium Chemical compound [Na].[K] BITYAPCSNKJESK-UHFFFAOYSA-N 0.000 claims 1
- 238000005086 pumping Methods 0.000 description 9
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- BUHVIAUBTBOHAG-FOYDDCNASA-N (2r,3r,4s,5r)-2-[6-[[2-(3,5-dimethoxyphenyl)-2-(2-methylphenyl)ethyl]amino]purin-9-yl]-5-(hydroxymethyl)oxolane-3,4-diol Chemical compound COC1=CC(OC)=CC(C(CNC=2C=3N=CN(C=3N=CN=2)[C@H]2[C@@H]([C@H](O)[C@@H](CO)O2)O)C=2C(=CC=CC=2)C)=C1 BUHVIAUBTBOHAG-FOYDDCNASA-N 0.000 description 1
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- ZLMJMSJWJFRBEC-UHFFFAOYSA-N Potassium Chemical compound [K] ZLMJMSJWJFRBEC-UHFFFAOYSA-N 0.000 description 1
- 230000005678 Seebeck effect Effects 0.000 description 1
- 229910001128 Sn alloy Inorganic materials 0.000 description 1
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- PWPJGUXAGUPAHP-UHFFFAOYSA-N lufenuron Chemical compound C1=C(Cl)C(OC(F)(F)C(C(F)(F)F)F)=CC(Cl)=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F PWPJGUXAGUPAHP-UHFFFAOYSA-N 0.000 description 1
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Images
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
- B64G1/24—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
- B64G1/283—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using reaction wheels
-
- 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
- B64G1/244—Spacecraft control systems
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K44/00—Machines in which the dynamo-electric interaction between a plasma or flow of conductive liquid or of fluid-borne conductive or magnetic particles and a coil system or magnetic field converts energy of mass flow into electrical energy or vice versa
- H02K44/02—Electrodynamic pumps
Abstract
Description
Die Erfindung dient der gezielten Lageregelung von Satelliten, insbesondere der Lageregelung von Kleinsatelliten. Dafür wird mindestens ein Drehimpuls speicherndes Mittel, dass über eine regelbare Einheit mit Energie versorgt wird, benötigt. Die regelbare Einheit kann dabei in Verbindung mit geeigneten Sensoren der Lageregelung stehen. Das Drehimpuls speichernde Mittel, im folgendem als Fluiddynamischer Aktuator benannt, besteht aus einer Flüssigkeit, die mittels einer regelbaren Pumpe auf einer geschlossenen Bahn bewegt wird. Durch die Beschleunigung der Flüssigkeit wird ein gewünschter Drall zwischen dem Satelliten und der Flüssigkeit ausgetauscht.The The invention serves the purpose of positional positioning of satellites, in particular the attitude control of small satellites. At least an angular momentum storing means that has a controllable unit is powered, needed. The controllable unit can in conjunction with suitable sensors of the position control stand. The angular momentum storing agent, hereinafter referred to as fluid dynamic Named actuator, consists of a liquid by means of a controllable pump is moved on a closed path. By accelerating the liquid becomes a desired Swirl exchanged between the satellite and the liquid.
Stand der TechnikState of the art
Ein
solcher Fluiddynamischer Aktuator (
Die
elektromagnetische Pumpe steht in Verbindung mit einer Steuer- und
Regelbox (
Die
elektromagnetische Pumpe (
Ein
Problem dieser elektromagnetischen Pumpen liegt in dem prinzipiell
sehr geringen Innenwiderstand dieser Pumpenart. Für das
Medium der Flüssigmetalle beträgt der Innenwiderstand
in der Regel nur wenige Milliohm. Dies führt zu Problemen mit
der Energieversorgung der elektromagnetischen Pumpen, da der geringe
Innenwiderstand zu sehr großen Stromflüssen führt,
beziehungsweise es sehr geringer Versorgungsspannungen bedarf. Eine
Lösung des Problems der Stromversorgung bietet das Patent
Ein
weiterer Fluiddynamischer Aktuator ist in dem Patent
Aufgabenstellungtask
Der Erfindung liegt die Aufgabe zu Grunde, geeignete Fluiddynamische Aktuatoren für die Lageregelung von Satelliten, insbesondere Kleinsatelliten vorzustellen. Die Verwendung von Fluiddynamischen Aktuatoren bietet im Vergleich zu der Standartlösung der Reaktionsräder folgende Vorteile. Die genannten Aktuatoren weisen eine höhere Resistenz gegenüber Schocks und Erschütterungen auf und arbeiten quasi Verschleißfrei, wodurch sehr hohe Lebensdauern zu erwarten sind. Außerdem ist die elektrische Leistungsaufnahme der Fluiddynamischen Aktuatoren, gerade für kleine Satelliten, meist wesentlich geringer als bei den Reaktionsrädern.Of the Invention is based on the object, suitable fluid dynamic Actuators for attitude control of satellites, in particular To introduce small satellites. The use of fluid dynamic actuators offers compared to the standard solution of the reaction wheels the following advantages. The mentioned actuators have a higher Resistance to shocks and shocks on and work virtually wear-free, resulting in very high Lifetimes are to be expected. In addition, the electric Power consumption of the fluid dynamic actuators, just for small satellites, usually much smaller than the reaction wheels.
Das
Problem des sehr geringen Innenwiderstandes der elektromagnetischen
Pumpe nach Patent
In
der
In
der
Als
weitere mögliche elektromagnetische Pumpe kann eine Induktionspumpe
dienen. Solche Pumpen sind bekannt aus Publikationen wie der „ELEKTROMAGNETIC
ALKALI METAL PUMP RESEACH PROGRAM” der NASA. Die Induktionspumpe
nutzt die elektromagnetische Induktion. Eine derartige Pumpe ist
in
Die Verwendung von elektromagnetischen Pumpen beschränkt den Einsatz der Flüssigkeit auf elektrisch gut leitende Flüssigkeiten, wie Flüssigmetalle, beispielsweise Eutektika aus Natrium und Kalium, Quecksilber, Gallium-Indium-Zinn Legierungen oder Ionische Flüssigkeiten. Ionische Flüssigkeiten weisen allerdings den Nachteil des geringeren Leitwertes und der chemischen Instabilität auf. Die Verwendung von Flüssigmetallen setzt eine Mindesttemperatur, die über dem Schmelzpunkt der Metalle liegt, voraus.The Use of electromagnetic pumps limits the Use of the liquid on electrically highly conductive liquids, such as liquid metals, for example sodium eutectics and potassium, mercury, gallium-indium-tin alloys or ionic Liquids. However, ionic liquids indicate the disadvantage of lower conductance and chemical instability on. The use of liquid metals sets a minimum temperature, which is above the melting point of the metals, ahead.
Eine
weitere Möglichkeit für den Einsatz Fluiddynamische
Aktuatoren bieten Ionen-Reibungspumpen beziehungsweise Feldemissionspumpen (
Eine
derartige Pumpe ist in
Durch das entgegen gesetzte zusammenschalten von zwei dieser Pumpen können beide Pumprichtungen bedient werden.By the opposite interconnecting of two of these pumps can both pumping directions are operated.
Eine
weitere Lösung ist in der
Eine
weitere Ausgestaltungsvariante des Fluidkanalsystems ist in
Für alle Beispiele ist der Einsatz von Temperatursensoren die die Fluid Temperaturen messen und überwachen vorstellbar.For all examples is the use of temperature sensors which are the fluid Measure and monitor temperatures imaginable.
Zusammenfassung:Summary:
Fluiddynamische Aktuatoren können für die Lageregelung von Satelliten eingesetzt werden. Dabei wird eine Drehimpuls speichernde Flüssigkeit mittels einer Pumpe auf einer geschlossenen Bahn derart beeinflusst, dass das Beschleunigen der Drehimpuls speichernden Flüssigkeit zu einem Reaktionsmoment auf den Satelliten führt, so dass damit eine gezielte Lageänderung des Satelliten möglich wird. Als geeignete Kombination von Pumpe und Drehimpuls speichernde Flüssigkeit eignen sich besonders, ein elektrisch leitendes Fluid kombiniert mit einer elektromagnetischen Pumpe beziehungsweise ein nicht leitendes Fluid kombiniert mit einer Ionenreibungspumpe. Die geschlossene Bahn der Drehimpuls speichernden Flüssigkeit kann vorteilhaft ringförmig gestaltet sein oder durch einen hohlkugelartigen Körper gebildet werden, welcher eine beliebige Kugelströmung innerhalb aller Rotationsebenen zulässt.Fluid dynamic actuators can be used for position control of satellites. In this case, an angular momentum storing liquid with Affected by a pump on a closed path such that the acceleration of the angular momentum storing liquid leads to a reaction torque on the satellite, so that a targeted change in position of the satellite is possible. As a suitable combination of pump and angular momentum storing liquid are particularly suitable, an electrically conductive fluid combined with an electromagnetic pump or a non-conductive fluid combined with an ion friction pump. The closed path of the angular momentum-storing liquid can advantageously be of annular design or be formed by a hollow-sphere-like body which allows any ball flow within all planes of rotation.
ZITATE ENTHALTEN IN DER BESCHREIBUNGQUOTES INCLUDE IN THE DESCRIPTION
Diese Liste der vom Anmelder aufgeführten Dokumente wurde automatisiert erzeugt und ist ausschließlich zur besseren Information des Lesers aufgenommen. Die Liste ist nicht Bestandteil der deutschen Patent- bzw. Gebrauchsmusteranmeldung. Das DPMA übernimmt keinerlei Haftung für etwaige Fehler oder Auslassungen.This list The documents listed by the applicant have been automated generated and is solely for better information recorded by the reader. The list is not part of the German Patent or utility model application. The DPMA takes over no liability for any errors or omissions.
Zitierte PatentliteraturCited patent literature
- - US 2856142 [0002, 0008, 0017] US Pat. No. 2,856,142 [0002, 0008, 0017]
- - DE 10230350 [0005] - DE 10230350 [0005]
- - JP 4055198 [0006] - JP 4055198 [0006]
Claims (19)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009036327A DE102009036327A1 (en) | 2009-08-05 | 2009-08-05 | Fluid-dynamic actuator for controlling position of small satellite, has transformer and frequency producing element electrically connected to each other such that electrical voltage of spacecraft is transformed into direct current voltage |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009036327A DE102009036327A1 (en) | 2009-08-05 | 2009-08-05 | Fluid-dynamic actuator for controlling position of small satellite, has transformer and frequency producing element electrically connected to each other such that electrical voltage of spacecraft is transformed into direct current voltage |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102009036327A1 true DE102009036327A1 (en) | 2011-02-10 |
Family
ID=43430121
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102009036327A Withdrawn DE102009036327A1 (en) | 2009-08-05 | 2009-08-05 | Fluid-dynamic actuator for controlling position of small satellite, has transformer and frequency producing element electrically connected to each other such that electrical voltage of spacecraft is transformed into direct current voltage |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE102009036327A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011105862A1 (en) | 2011-06-23 | 2012-12-27 | Daniel Noack | Actuator for attitude control of spacecrafts, has spin storing medium which is fluidically and electrically conductive, magnetic field generating unit and electrodes standing in connection to electrically conductive liquid |
CN104483972A (en) * | 2014-10-31 | 2015-04-01 | 上海新跃仪表厂 | Spacecraft fluid ring reaction performing mechanism |
CN105923171A (en) * | 2016-05-19 | 2016-09-07 | 中国空间技术研究院 | Modular integrated satellite multifunctional structure and polymers |
WO2017068154A1 (en) * | 2015-10-23 | 2017-04-27 | Centre National D'etudes Spatiales | Inertial actuator for stabilizing and/or pointing a platform in a predetermined direction |
EP3904220A1 (en) * | 2020-04-28 | 2021-11-03 | Universität Stuttgart | Variable angular momentum generating device, in particular for spacecraft attitude control |
EP4114740A4 (en) * | 2020-03-06 | 2024-02-28 | Newspace Systems Pty Ltd | A unit for causing angular momentum about an axis |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2856142A (en) | 1956-07-18 | 1958-10-14 | Gen Electric | Orientation control for a space vehicle |
JPH0455198A (en) | 1990-06-21 | 1992-02-21 | Nec Corp | Momentum wheel |
DE10230350A1 (en) | 2002-06-28 | 2004-01-15 | Technische Universität Dresden | Spacecraft attitude control system has electrically and thermally conducting magnetic fluid rotated in rings by magneto hydrodynamic pump |
-
2009
- 2009-08-05 DE DE102009036327A patent/DE102009036327A1/en not_active Withdrawn
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2856142A (en) | 1956-07-18 | 1958-10-14 | Gen Electric | Orientation control for a space vehicle |
JPH0455198A (en) | 1990-06-21 | 1992-02-21 | Nec Corp | Momentum wheel |
DE10230350A1 (en) | 2002-06-28 | 2004-01-15 | Technische Universität Dresden | Spacecraft attitude control system has electrically and thermally conducting magnetic fluid rotated in rings by magneto hydrodynamic pump |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011105862A1 (en) | 2011-06-23 | 2012-12-27 | Daniel Noack | Actuator for attitude control of spacecrafts, has spin storing medium which is fluidically and electrically conductive, magnetic field generating unit and electrodes standing in connection to electrically conductive liquid |
CN104483972A (en) * | 2014-10-31 | 2015-04-01 | 上海新跃仪表厂 | Spacecraft fluid ring reaction performing mechanism |
CN104483972B (en) * | 2014-10-31 | 2017-04-12 | 上海新跃仪表厂 | Spacecraft fluid ring reaction performing mechanism |
WO2017068154A1 (en) * | 2015-10-23 | 2017-04-27 | Centre National D'etudes Spatiales | Inertial actuator for stabilizing and/or pointing a platform in a predetermined direction |
FR3042924A1 (en) * | 2015-10-23 | 2017-04-28 | Centre Nat D'etudes Spatiales (Cnes) | INERTIAL ACTUATOR FOR STABILIZING AND / OR DECKING A PLATFORM ACCORDING TO A PREDETERMINED DIRECTION |
CN105923171A (en) * | 2016-05-19 | 2016-09-07 | 中国空间技术研究院 | Modular integrated satellite multifunctional structure and polymers |
EP4114740A4 (en) * | 2020-03-06 | 2024-02-28 | Newspace Systems Pty Ltd | A unit for causing angular momentum about an axis |
EP3904220A1 (en) * | 2020-04-28 | 2021-11-03 | Universität Stuttgart | Variable angular momentum generating device, in particular for spacecraft attitude control |
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