DE1129833B - Airplane with an air-breathing jet engine in the fuselage tail - Google Patents
Airplane with an air-breathing jet engine in the fuselage tailInfo
- Publication number
- DE1129833B DE1129833B DEM43470A DEM0043470A DE1129833B DE 1129833 B DE1129833 B DE 1129833B DE M43470 A DEM43470 A DE M43470A DE M0043470 A DEM0043470 A DE M0043470A DE 1129833 B DE1129833 B DE 1129833B
- Authority
- DE
- Germany
- Prior art keywords
- fuselage
- air inlets
- air
- airplane
- trunk
- 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
- 238000007493 shaping process Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Flugzeug mit einem luftatmenden Strahltriebwerk im Rumpfheck Es sind Flugzeuge bekannt, bei denen im Rumpfheck ein oder mehrere luftatmende Strahltriebwerke angeordnet sind. Bei diesen Flugzeugen sind die Lufteinläufe als Flugdüsen ausgebildet, die seitlich über die Rumpfkontur vorstehen.Airplane with an air-breathing jet engine in the fuselage tail There are Known aircraft in which one or more air-breathing jet engines in the fuselage tail are arranged. In these aircraft, the air inlets are designed as flight nozzles, which protrude laterally over the fuselage contour.
Die Erfindung besteht im wesentlichen darin, daß der Rumpf vor den Lufteinläufen so verjüngt ist und die Lufteinläufe und das Triebwerksaggregat so angeordnet und geformt sind, daß die Außenwand der Lufteinläufe und des Triebwerksaggregates die Fortsetzung der Rumpfkontur vor der Rumpfverjüngung zu einem sich verjüngenden Rumpfheck bilden.The invention consists essentially in the fact that the fuselage in front of the Air inlets are so tapered and the air inlets and the engine assembly are so are arranged and shaped that the outer wall of the air inlets and the engine assembly the continuation of the trunk contour before the trunk taper to a tapered one Form fuselage stern.
Durch die erfindungsgemäße Ausbildung wird ein glatterer Verlauf der Strömung am Rumpfheck erreicht und insbesondere bei überschallgeschwindigkeit die Entstehung von Stoßwellen vermindert.The inventive training is a smoother course of the Flow reached at the rear of the fuselage and especially at supersonic speed The generation of shock waves is reduced.
Um den Widerstand des Rumpfes weiter zu verringern, umschließen die Lufteinläufe erfindungsgemäß das Rumpfheck ringförmig, so daß eine gute Absaugung der Grenzschicht erzielt wird. Für den gleichen Zweck kann zwischen den Lufteinläufen und dem Triebwerksaggregat einerseits und dem Rumpfheck andererseits ein Kanal mit ringförmigem Querschnitt vorgesehen sein, durch den die Grenzschicht durch den Sog der Treibgase abgesaugt wird.To further reduce the resistance of the trunk, enclose the According to the invention, air inlets form the rear of the fuselage in a ring-shaped manner, so that good suction the boundary layer is achieved. For the same purpose can be between the air inlets and the engine unit on the one hand and the rear fuselage on the other hand with a channel annular cross-section through which the boundary layer through the suction the propellant gases are sucked off.
Zweckmäßig ist das Triebwerksaggregat mit den Lufteinläufen als lösbares Rumpfheck ausgebildet.The engine assembly with the air inlets is expedient as a detachable one Rear fuselage trained.
In den Zeichnungen ist ein Ausführungsbeispiel der Erfindung dargestellt. Es zeigt Fig. 1 das Rumpfheck mit den Lufteinläufen und dem Triebwerksaggregat im Schnitt.In the drawings, an embodiment of the invention is shown. It shows Fig. 1 the rear fuselage with the air inlets and the engine assembly in the Cut.
Fig. 2, 3 und 4 je einen Schnitt durch das Rumpfheck unmittelbar vor den Lufteinläufen mit je zwei, vier bzw. drei Triebwerken nebeneinander.2, 3 and 4 each a section through the rear fuselage immediately before the air inlets with two, four or three engines next to each other.
Die Triebwerke TW liegen im Rumpfheck und sind um die Mittellinie des Rumpfes R gruppiert. Die heißen Treibgase treten bei A am Rumpfende aus.The TW engines are located in the rear of the fuselage and are around the center line of the trunk R grouped. The hot propellant gases exit at A at the end of the fuselage.
Die Einläufe E der Triebwerke liegen als ringförmige Taschen am Außenumfang des Rumpfes. Vor den Einläufen verjüngt sich der Rumpf um die Stärke der Eintrittsöffnungen der Einläufe, so daß die Außenwand der Einläufe die Fortsetzung der Rumpfkontur bildet. Die Einläufe und die Triebwerke sind so geformt, daß sie ein sich verjüngendes, widerstandsarmes Rumpfheck ergeben, das als geschlossene Baugruppe bei T lösbar mit dem Rumpf verbunden ist.The inlets E of the engines are located as annular pockets on the outer circumference of the trunk. In front of the inlets, the trunk tapers by the thickness of the inlet openings of the inlets, so that the outer wall of the inlets is the continuation of the fuselage contour forms. The inlets and engines are shaped to create a tapered, result in a low-resistance fuselage tail, which can be detached as a closed assembly at T. connected to the fuselage.
Zwischen den Einläufen und den Triebwerken einerseits und dem Rumpfheck andererseits liegt ein im Querschnitt ringförmiger Kanal, durch den die Grenzschicht des Rumpfes abfließen kann.Between the inlets and the engines on the one hand and the rear of the fuselage on the other hand, there is a channel with an annular cross-section through which the boundary layer the trunk can drain.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM43470A DE1129833B (en) | 1959-11-24 | 1959-11-24 | Airplane with an air-breathing jet engine in the fuselage tail |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM43470A DE1129833B (en) | 1959-11-24 | 1959-11-24 | Airplane with an air-breathing jet engine in the fuselage tail |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE1129833B true DE1129833B (en) | 1962-05-17 |
Family
ID=7304673
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DEM43470A Pending DE1129833B (en) | 1959-11-24 | 1959-11-24 | Airplane with an air-breathing jet engine in the fuselage tail |
Country Status (1)
| Country | Link |
|---|---|
| DE (1) | DE1129833B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1146761B (en) * | 1961-06-28 | 1963-04-04 | Messerschmitt Ag | Arrangement of jet engines in the end of the fuselage of an aircraft |
| DE1256079B (en) * | 1962-03-03 | 1967-12-07 | Messerschmitt Ag | Arrangement of dual-circuit engines at the rear of aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB711719A (en) * | 1951-12-20 | 1954-07-07 | Sncan | Improvements in aircraft equipped with a propelling motor at the rear |
| US2721715A (en) * | 1951-09-28 | 1955-10-25 | Chance Vought Aircraft Inc | Flush inlet |
| US2755040A (en) * | 1951-10-10 | 1956-07-17 | Glenn L Martin Co | Air intake system for an aircraft |
| US2812912A (en) * | 1953-08-06 | 1957-11-12 | Northrop Aircraft Inc | Inclined engine installation for jet aircraft |
-
1959
- 1959-11-24 DE DEM43470A patent/DE1129833B/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2721715A (en) * | 1951-09-28 | 1955-10-25 | Chance Vought Aircraft Inc | Flush inlet |
| US2755040A (en) * | 1951-10-10 | 1956-07-17 | Glenn L Martin Co | Air intake system for an aircraft |
| GB711719A (en) * | 1951-12-20 | 1954-07-07 | Sncan | Improvements in aircraft equipped with a propelling motor at the rear |
| US2812912A (en) * | 1953-08-06 | 1957-11-12 | Northrop Aircraft Inc | Inclined engine installation for jet aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1146761B (en) * | 1961-06-28 | 1963-04-04 | Messerschmitt Ag | Arrangement of jet engines in the end of the fuselage of an aircraft |
| DE1256079B (en) * | 1962-03-03 | 1967-12-07 | Messerschmitt Ag | Arrangement of dual-circuit engines at the rear of aircraft |
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