DE1181066B - Engine control device for planes equipped with several engines - Google Patents
Engine control device for planes equipped with several enginesInfo
- Publication number
- DE1181066B DE1181066B DEM49011A DEM0049011A DE1181066B DE 1181066 B DE1181066 B DE 1181066B DE M49011 A DEM49011 A DE M49011A DE M0049011 A DEM0049011 A DE M0049011A DE 1181066 B DE1181066 B DE 1181066B
- Authority
- DE
- Germany
- Prior art keywords
- engine
- thrust
- fuel
- engines
- control device
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
- B64C29/0058—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with vertical jet
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Description
Triebwerksregeleinrichtung für mit mehreren Triebwerken ausgerüstete Flugzeuge Die Erfindung betrifft eine Triebwerksregeleinrichtung für mit mehreren Triebwerken ausgerüstete Flugzeuge, bei welchen zur Vermeidung eines einseitigen Schubmomentes die Brennstoffzuführung beeinflußbar ist und bei Ausfall eines Triebwerkes eines der anderen Triebwerke in seiner Leistung drosselbar ist.Engine control device for those equipped with several engines Aircraft The invention relates to an engine control device for a plurality of Aircraft equipped with engines, in which to avoid a one-sided Thrust torque, the fuel supply can be influenced and if an engine fails one of the other engines can be throttled in its power.
Bei Fluggeräten mit mehreren Hubtriebwerken für senkrechtes Starten und Landen besteht bei ungewollt starker Verringerung des Schubes eines der Hubtriebwerke ein starkes Drehmoment, das vom Piloten bzw. der automatischen Steuerung nicht mehr voll ausgeglichen werden kann. In einem solchen Fall überschlägt sich das Flugzeug, und es ist für den Piloten kaum möglich, sich mit Sicherheit aus dem Flugzeug herauszuschießen, um mit dem Fallschirm niederzugehen.For aircraft with several lift engines for vertical take-off and landing occurs in the event of an unintentionally strong reduction in the thrust of one of the lift engines a strong torque that the pilot or the automatic control no longer needs can be fully balanced. In such a case the plane overturns, and it is hardly possible for the pilot to shoot himself out of the aircraft with certainty, to parachute down.
Die Erfindung hat sich die Beseitigung dieser vor allem bei Versuchsflugzeugen und Fluggestellen auftretenden Gefahr zur Aufgabe gestellt und löst die Aufgabe dadurch, .daß für Senkrechtstartflugzeuge je ein den Kraftstoff abschaltender, auf eine bestimmte Schubkraftschwelle einstellbarer Geber im Schubstrahl eines jeden Triebwerkes angeordnet ist.The invention has the elimination of this especially in test aircraft and flying racks are set to the task and solves the task because of the fact that for vertical take-off planes there is one that switches off the fuel a certain thrust threshold adjustable transmitter in the thrust jet of each Engine is arranged.
Ein Merkmal der Erfindung ist, daß der Geber aus einer an einem gegen Federkraft zu betätigenden Hebel befindlichen Angriffsfläche für den Schubstrahl besteht.A feature of the invention is that the encoder from one to one against Spring force to be actuated lever located attack surface for the thrust jet consists.
Das vom Geber ausgehende Signal wird erfindungsgemäß auf einen Knickhebel an der Kraftstoffsteuerung derart übertragen, daß der Kraftstoffhahn unabhängig von der Stellung der Kraftstoffsteuerung geschlossen wird.According to the invention, the signal emanating from the transmitter is transmitted to an articulated lever transmitted to the fuel control in such a way that the fuel cock is independent is closed by the position of the fuel control.
Ein weiteres Merkmal der Erfindung ist, daß alle Triebwerke von jedem beliebigen Triebwerk eines Fluggerätes aus durch schubgesteuerte Geber abschaltbar sind.Another feature of the invention is that all thrusters from each any engine of an aircraft can be switched off by thrust-controlled sensors are.
Eine beispielsweise Ausführung des Erfindungsgedankens wird in der Zeichnung dargestellt.An example implementation of the inventive concept is in the Drawing shown.
Im Schubstrahl des Triebwerkes 1' ist eine Fahne 5, 5', die über einen Hebel 9, 9' mit der Haltefeder 6 verbunden ist, beweglich angebracht. Im Schwebeflug, d. h. bei nahezu vollem Schub, steht diese Fahne in der stark ausgezogen gezeichneten Stellung 5. Sobald der Schub nachläßt, z. B. durch Triebwerksschaden sich stark vermindert, zieht die Haltefeder 6 den Hebel 9 an und bringt die Fahne in die gestrichelt gezeichnete Stellung 5. über eine mechanische übertragung, z. B. einen Seilzug 4, 4', wird gegen eine Federspannung 8 ein Knickhebel 10, 10' am zugehörigen Triebwerk 1 betätigt und damit die Stellung der Fahne 5, 5' jeweils auf den Kraftstoffhahn 2, 2' übertragen.A flag 5, 5 ', which is connected to the retaining spring 6 via a lever 9, 9', is movably attached in the thrust jet of the engine 1 '. In the hover flight, ie at almost full thrust, this flag is in the strongly drawn out position 5. As soon as the thrust decreases, z. B. is greatly reduced by engine damage, the retaining spring 6 pulls the lever 9 and brings the flag in the position shown in dashed lines 5. via a mechanical transmission, z. B. a cable 4, 4 ', a toggle lever 10, 10' on the associated engine 1 is actuated against a spring tension 8 and thus the position of the flag 5, 5 'is transferred to the fuel tap 2, 2'.
Auf diese Weise ist es möglich, unabhängig von der Stellung des Kraftstoffhahns und des Steuergestänges 3 den Kraftstoffhahn zu schließen.In this way it is possible regardless of the position of the fuel tap and the control linkage 3 to close the fuel cock.
Durch Anbringen der Fahnen an jedem der Hubtriebwerke eines Fluggerätes und der Verschaltung aller Triebwerke untereinander im Sinne der angegebenen Vorrichtung lassen sich gleichzeitig mehrere Triebwerke beim Ausfall eines Triebwerkes abschalten. Dabei wird der Abschaltvorgang von Triebwerk zu Triebwerk durch die angegebene Vorrichtung gegenseitig unterstützt.By attaching the flags to each of the lifting engines of an aircraft and the interconnection of all engines with one another in the sense of the specified device several engines can be switched off at the same time if one engine fails. The shutdown process from engine to engine is carried out by the specified device mutually supported.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM49011A DE1181066B (en) | 1961-05-10 | 1961-05-10 | Engine control device for planes equipped with several engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM49011A DE1181066B (en) | 1961-05-10 | 1961-05-10 | Engine control device for planes equipped with several engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE1181066B true DE1181066B (en) | 1964-11-05 |
Family
ID=7306397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DEM49011A Pending DE1181066B (en) | 1961-05-10 | 1961-05-10 | Engine control device for planes equipped with several engines |
Country Status (1)
| Country | Link |
|---|---|
| DE (1) | DE1181066B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1281269B (en) * | 1964-06-02 | 1968-10-24 | Ver Flugtechnische Werke G M B | Jet control for high flyers |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE679417C (en) * | 1938-02-18 | 1939-08-04 | Arado Flugzeugwerke G M B H | Device for automatic shutdown of assigned motors located on both sets of the aircraft longitudinal axis if one of these motors fails |
-
1961
- 1961-05-10 DE DEM49011A patent/DE1181066B/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE679417C (en) * | 1938-02-18 | 1939-08-04 | Arado Flugzeugwerke G M B H | Device for automatic shutdown of assigned motors located on both sets of the aircraft longitudinal axis if one of these motors fails |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1281269B (en) * | 1964-06-02 | 1968-10-24 | Ver Flugtechnische Werke G M B | Jet control for high flyers |
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