DE626386C - Aircraft tailplane - Google Patents

Aircraft tailplane

Info

Publication number
DE626386C
DE626386C DEH136141D DEH0136141D DE626386C DE 626386 C DE626386 C DE 626386C DE H136141 D DEH136141 D DE H136141D DE H0136141 D DEH0136141 D DE H0136141D DE 626386 C DE626386 C DE 626386C
Authority
DE
Germany
Prior art keywords
aircraft
tail
wing
wings
tail unit
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.)
Expired
Application number
DEH136141D
Other languages
German (de)
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
FRITZ HUTH DR
Original Assignee
FRITZ HUTH DR
Publication date
Priority to DEH136141D priority Critical patent/DE626386C/en
Application granted granted Critical
Publication of DE626386C publication Critical patent/DE626386C/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
    • B64C39/068—Aircraft not otherwise provided for having disc- or ring-shaped wings having multiple wings joined at the tips

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Description

Der Zweck der vorliegenden Bauart ist dieThe purpose of the present design is

Schaffung eines Flugzeuges, das bei geringem Eigengewicht formsteif, dabei trudelsicher, leicht zu fliegen und mit geringer Geschwindigkeit zu landen ist.Creation of an aircraft that is dimensionally stable with a low dead weight, while being spin-proof, easy to fly and land at low speed.

Diese Eigenschaften werden dadurch erreicht, daß die Enden des Leitwerkes mit den Flügeln verbunden sind, wobei das Leitwerk in einer die. Flügelebene schneidenden Ebene liegt.These properties are achieved in that the ends of the tail unit with the wings are connected, the empennage in a die. Wing plane intersecting plane lies.

ίο Durch diese Anordnung ist eine feste Raumkonstruktion geschaffen, da die Flügel durch das »Leitwerk wirksam versteift werden. Weil die Leitwerkkanten sowohl schräg nach vorn als auch schräg nach oben gerichtet sind, er-ίο This arrangement creates a solid room construction created because the wings are effectively stiffened by the »tail unit. Because the tail edges are both sloping forward as well as being directed obliquely upwards,

t5 gibt sich beim Seitwärtsgleiten des Flugzeuges ein schräges Anblasen des Leitwerkes unter großem Anstellwinkel, das starke aufrichtende Kräfte an der Vorderkante des Leitwerkes erzeugt.t 5 , when the aircraft glides sideways, the tail unit is blown at an angle at a large angle of attack, which generates strong righting forces at the leading edge of the tail unit.

ao Durch diese Wirkung unterscheidet sich das Flugzeug nach vorliegender Erfindung von solchen Ausführungen, bei denen am Tragwerk Zusatzflächen angeordnet sind, die nur -der Quersteuerung dienen können.ao This is what makes it different Aircraft according to the present invention of such designs, in which on the wing Additional surfaces are arranged that can only be used for lateral control.

Die Abb. 1 bis 4 zeigen Ausführungsformen des neuen Flugzeuges, und zwar stellen Abb. 1 bis 3 einen Hochdecker, Abb. 4 einen Tiefdecker dar. Die Flügel 1 sitzen an dem Rumpf 4.Figs. 1 to 4 show embodiments of the new aircraft, namely Fig. 1 through 3 a high-wing aircraft, Fig. 4 a low-wing aircraft. The wings 1 sit on the fuselage 4.

Am anderen Ende des Rumpfes, und zwar beim Hochdecker der Abb. 1 unten, beim Tiefdecker der Abb. 4 oben, sind die Leitflossen 2 befestigt, deren anderes Ende mit dem Flügel 1 verbunden ist. An den Leitflossen 2 sitzen die beweglichen Flossen 3.At the other end of the fuselage, namely with the high-wing aircraft in Fig. 1 below, with the low-wing aircraft 4 above, the guide fins 2 are attached, the other end to the wing 1 connected is. The movable fins 3 sit on the guide fins 2.

Werden die rechte und die linke Flosse gleichsinnig verstellt, so wirken sie als Höhensteuer. Wird dagegen eine Flosse nach oben, die andere nach unten verstellt, so wirken sie als Quersteuer. Dies ist bei der vorliegenden Konstruktion möglich, da sich die Steuerflossen vom Rumpf ende nach vorn bis zu den Flügeln erstrecken. Natürlich können die Tragenden der Flügel 1 auch besondere Quersteuer tragen. Diese fehlen, wenn die Leitwerkteile an den Flügelenden angreifen.If the right and left fins are adjusted in the same direction, they act as a height control. If, on the other hand, one fin is adjusted upwards and the other downwards, they work as aileron. This is possible with the present design, since the control fins extend forward from the end of the fuselage to the wings. Of course, the wearers can the wing 1 also carry special ailerons. These are missing if the tail parts are attached to the Attack wingtips.

Claims (2)

Patentansprüche:Patent claims: 1. Flugzeugleitwerk, dadurch gekennzeichnet, daß die Enden des Höhenleitwerkes mit den Tragflügeln verbunden sind und die Leitwerkebene die der Flügel schneidet.1. aircraft tail, characterized in that the ends of the horizontal tail are connected to the wings and the tail plane intersects the wing. 2. Flugzeugleitwerk nach Anspruch 1, dadurch gekennzeichnet, daß die Ruder des Leitwerkes in an sich bekannter Weise sowohl gleichsinnig als auch gegensinnig bewegbar sind..2. aircraft tail unit according to claim 1, characterized in that the rudder of the tail unit in a manner known per se, both in the same direction and in opposite directions are movable .. Hierzu 1 Blatt Zeichnungen1 sheet of drawings
DEH136141D Aircraft tailplane Expired DE626386C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEH136141D DE626386C (en) Aircraft tailplane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEH136141D DE626386C (en) Aircraft tailplane

Publications (1)

Publication Number Publication Date
DE626386C true DE626386C (en) 1936-02-25

Family

ID=7177445

Family Applications (1)

Application Number Title Priority Date Filing Date
DEH136141D Expired DE626386C (en) Aircraft tailplane

Country Status (1)

Country Link
DE (1) DE626386C (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105905277A (en) * 2016-04-19 2016-08-31 北京航空航天大学 Air vehicle aerodynamic configuration with trailing edge supporting wing

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105905277A (en) * 2016-04-19 2016-08-31 北京航空航天大学 Air vehicle aerodynamic configuration with trailing edge supporting wing

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