CS217151B1 - Aeroplane - Google Patents

Aeroplane Download PDF

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Publication number
CS217151B1
CS217151B1 CS797271A CS727179A CS217151B1 CS 217151 B1 CS217151 B1 CS 217151B1 CS 797271 A CS797271 A CS 797271A CS 727179 A CS727179 A CS 727179A CS 217151 B1 CS217151 B1 CS 217151B1
Authority
CS
Czechoslovakia
Prior art keywords
equal
rudder
hull
wings
height
Prior art date
Application number
CS797271A
Other languages
Czech (cs)
Inventor
Alexandr A Jakovlev
Vjaceslav P Kondratev
Jurij N Virjacev
Boris N Frolisev
Original Assignee
Jakovlev Aleksandr A
Vjaceslav P Kondratev
Jurij N Virjacev
Boris N Frolisev
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Application filed by Jakovlev Aleksandr A, Vjaceslav P Kondratev, Jurij N Virjacev, Boris N Frolisev filed Critical Jakovlev Aleksandr A
Publication of CS217151B1 publication Critical patent/CS217151B1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Compounds Of Unknown Constitution (AREA)
  • Toys (AREA)
  • Professional, Industrial, Or Sporting Protective Garments (AREA)
  • Footwear And Its Accessory, Manufacturing Method And Apparatuses (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Feedback Control In General (AREA)

Description

OUHCAHIS H305? dx3HI/Izí X ΛΒΤΟΡΟΧα,σ G3?;,^E?E£ČGT;37 oaojisHo: 2.II.78OUHCAHIS H305? dx3HI / Iz X ΛΒΤΟΡΟΧα, σ G3?;, ^ E? E £ CGT; 37 oaojisHo: 2.II.78

SanBKa: 3 268I852/4G-28SanBKa: 3 268I852 / 4G-28

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Ha3BafíKe a30dpe τθηο: "ΟπορτηβηηΜ csmojist"__Ha3BafíKe a30dpe τθηο: "ΟπορτηβηηΜ csmojist" __

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CymHOCTB H30ópeTeHHfl saK^ao^asTCH b tom, kto Ha ca- - 2 - MOJieTe nJIOCKOCTH ΧΟρΛ Kpbua Η r0pH30HT3JIBH0r0 OnepeHHflH BSKIOp ΤΑΓΗ flBHraTeJIA pa3MemeHhI B O/UlOH r0pM3OHTaJIBH0KnJIOCKOCTH, ηρΟΧΟΑΗΐϋ,ΘΗ Kepe3 CTpOHTeJIBHyK) ropH3OHT3JIB$I03eHfl5iCa, KpblJIO BbinOJIHeHO ΟΗΜΜβΤρΗ^ΙΗΟίΐ φθρΜΗ c tojhhhhokπροφΗΛΑ (0,25-Q,05)B, a pyjiB HanpaBJíeHHA προ/weH 3a hhík-hhh oÓbqa $K)3eJifl&a Ha BUCOTy, paBHyio (0,25-Q,5Q)H HaCymHOCTB H30ópeTeHHfl sak ^ and ^ b asTCH as who Ca- Ha - 2 - My nJIOCKOCTH ΧΟρΛ Kpbua Η r0pH30HT3JIBH0r0 OnepeHHflH BSKIOp ΤΑΓΗ flBHraTeJIA pa3MemeHhI BO / task r0pM3OHTaJIBH0KnJIOCKOCTH, ηρΟΧΟΑΗΐϋ, ΘΗ Kepe3 CTpOHTeJIBHyK) ropH3OHT3JIB $ I03eHfl5iCa, KpblJIO BbinOJIHeHO ΟΗΜΜβΤρΗ ^ c ΙΗΟίΐ φθρΜΗ tojhhhhokπροφΗΛΑ (0,25-Q, 05) B, and pyjiB HanpaBJíeHHA προ / weH 3a hhík-hhh oÓbqa $ K) 3eJifl & a Ha BUCOTy, paBHyio (0,25-Q, 5Q) H Ha

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Hb- BMG0T3 pyJIH HanpaBJíeHHA H3.H CTpOHTeJIBHOH ropw-aoHTajiBio.Hb- BMG0T3 pyJIH HanpaBJiHHH H3.H CTpOHTeJIBHOH ropw-aoHTajiBio.

KoHCTpyKUHA noACAAeTCA qepiescaMH.KoHCTpyKUHA noACAAeTCA qepiescaMH.

Ha φΗΓ. I CX6M3TITÍAQ Π0Κ833Η ΟΠΟρΤΗΒΗΜΗ CaMOJieT, BH#cóoKy, Ha Φηγ.2 - το se, βηλ CBepxy, Ha Φηγ.3 - προφππΒKphiJia c ajiepoHOM.Ha φΗΓ. I CX6M3TITÍAQ Π0Κ833Η ΟΠΟρΤΗΒΗΜΗ CaMOJieT, BH # cóoKy, Ha .2ηγ.2 - το se, βηλ CBepxy, Ha Φηγ.3 - προφππΒKphiJia c ajiepoHOM.

Ilpe/uiaraeMaid cnopTH3HhiH caMQJieT BKjno^iaeT κρωιο I,ropH3OHTajiBHoe onepeHHe 2, pyjiB HanpaBJíeHHA BepTHKajiBHoroonepeHHA 3, $K)3eJiAjíc 4, cHJiOByio ycTanoBny 5, pyjin βμοοτμ71 nofl$iQ3ejiA3icHhiři rpečeHB 8 h máčen 9.The reaction is carried out with 4, 5, 5, 5, 5, 5, 5, 5, 5, 5, 5, 5, 5, 5, 5, 5, 5, 5, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 9, 11, 11 and 9.

KphiJio I βνποληθηο H3 cHMíieTpwiHhix προφΗΑβκ 10 c pa-flHyCOiá HOCKa ρθΒΗΜΜ (0,03 - 0,05)B H OTHOCHTěJIBHOří tojiuih-hoU, paBHOH (0,15-0,20)B, γλθ B - MecTHaa xopAa Kphua. IIjiockoctb xopň IX Kpmia I h iijiockoctb xopfl 12 ropH-30HTaJIBH0r0 ΟΠθρβΗΗΑ 2 Η ΒΘΚΤΟρ ΤΑΓΗ CHJIOBOH yCT3H0BKH 5npoxoAAT <íepe3 cTpoHTejiBHyio ropn3OHTaJiB 13 $KD3eJiHxca 4.KphiJio I βνποληθηο H3 cHMííTpwiHhix προφΗΑβκ 10 c pa-flHyCOiá HOCKa ρθΒΗΜΜ (0,03 - 0,05) B H OTHOCHTENJIBHOHIJHUHU, PABHOH (0,15-0,20) B, γλθ B - MecTHaa xopAa Kphua. IIjiockoctb xop IX IX Kpmia I h iijiockoctb xopfl 12 ropH-30HTaJIBH0r0 2 po Τρ ΤΑΓΗ CHJIOBOH yCT3H0BKH 5npoxoAAT <íepe3 cTpoHTejiBHyio ropn3OHTaJiB 13 $ KD3eJiHxca 4.

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Ha ropH3OHTaJL&amp;Hoe h sepiHKajiiKoe onepeHHH.Ha ropH3OHTaJL &amp; Hoe h sepiHKajiiKoe onepeHHH.

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V Η tfopMyjia H3oópeTeHHflV Η tfopMyjia H3oópeTeHHfl

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Hb- BhlCOTa pyjifl Η8Πρ3ΒΛβΗΗΗ H3A CTpOHTSJIBHOÍÍ ΓΟρΗ-30ΗΤ3ΑΒΚ).Hb- BhlCOTa pyjifl Η8Πρ3ΒΛβΗΗΗ H3A CTpOHTSJIBHOÍÍ ΓΟρΗ-30ΗΤ3ΑΒΚ).

AriHOIWfcAriHOIWfc

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UeJiL H3oópeTeHHfl - no£hiuieHne μθηθβρθηκβιχ cboííctbupil BhHIOJIHeilHH φΚΓγρ. ΙΐρίϊΜΟΓΟ K ΟόρθΤΗΟΓΟ ΠΟΟΤθΚΘ.UeJiL H3oópeTeHHfl - no £ hiuieHne μθηθβρθηκβιχ cboííctbupil BhHIOJIHeilHH φΚΓγρ. ΪΜΟΓΟρίϊΜΟΓΟ K ΟόρθΤΗΟΓΟ ΠΟΟΤθΚΘ.

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Hb- BhicoTa pyjifl HanpaBaeHHfl nas οτροΗΤβΛΒΗΟϋ ropn-3ΟΗΤΘΛΒΒ.Hb- BhicoTa pyjifl HanpaBaeHHfl nas οτροΗΤβΛΒΗΟϋ ropn-3ΟΗΤΘΛΒΒ.

Claims (1)

PŘEDMĚT VYNÁLEZU Letoun, skládající se z hnacího zařízení, křídla ze symetrických profilů, hřbetu uloženého pod trupem, vodorovnéa svislé ocasní plochy, se vyznačuje tím, že za účelem zvýšení manévrovacích schopností letounu při vykonávání po-loh přímé a zpětné pilotáže je symetrický profil křídlavytvořen s rádiusem špičky ( ),který se rovná (3 až 5 %) B a relativní tloušíka (Cmax),rovnající se (15 až 20 %)B,a směrové kormidlo (3) svislé ocasní plochy je prodlouženoza spodní obvod trupu (4) ve výšce, která se rovná (0,25až 0,5)Hg a je v součinnosti se hřbetem uloženým pod tru-pem (8),přičemž vektor tahu motoru (5),vodorovné ocasníplochy (2) a tětiva (11) křídla (1) jsou umístěny v jedné,rovině,procházející přes základní rovinu (13) trupu (4),kde je B- místní tětiva (11) křídla (1) a Ηβ- výška smě-rového kormidla (3) k základní rovině trupu (4). Uznáno vynálezem na základě výsledků expertizy, provedenéStátním výborem pro vynálezy a objevy SSSR, Moskva, SU. 4 výkresyOBJECT OF THE INVENTION An airplane consisting of a propulsion device, wings of symmetrical profiles, a back under the fuselage, a horizontal and vertical tail, is characterized in that, in order to increase the maneuvering capability of the airplane while performing a straight and reverse piloting, a radius of tip () equal to (3 to 5%) B and a relative thickness (Cmax) equal to (15 to 20%) B; and a rudder (3) of the vertical tail is an extension of the lower torso circumference (4) in a height that is equal to (0.25 to 0.5) Hg and is in conjunction with the spine placed under the tube (8), with the motor thrust vector (5), the horizontal tail surfaces (2) and the chord (11) wings (1) ) are located in one plane passing through the base plane (13) of the hull (4), where B- the local chord (11) is the wing (1) and Ηβ- the height of the rudder (3) to the base plane of the hull (4) ). Recognized by the invention on the basis of the results of expertise made by the USSR State Inventions and Discoveries Committee, Moscow, SU. 4 drawings
CS797271A 1978-11-02 1979-10-24 Aeroplane CS217151B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU782681352A SU764275A1 (en) 1978-11-02 1978-11-02 Sportive airplane

Publications (1)

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CS217151B1 true CS217151B1 (en) 1982-12-31

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Application Number Title Priority Date Filing Date
CS797271A CS217151B1 (en) 1978-11-02 1979-10-24 Aeroplane

Country Status (9)

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AT (1) AT370690B (en)
AU (1) AU529644B2 (en)
CS (1) CS217151B1 (en)
DD (1) DD148454A3 (en)
FR (1) FR2440872A1 (en)
GB (1) GB2048182B (en)
IT (1) IT7927025A0 (en)
SU (1) SU764275A1 (en)
WO (1) WO1980000949A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2452424A1 (en) * 1979-03-27 1980-10-24 Gepal IMPROVEMENTS IN THE STRUCTURE AND LAYOUT OF A CELL, PARTICULARLY FOR THE PRODUCTION OF A TRAINING AIRCRAFT
US4565470A (en) * 1982-07-12 1986-01-21 William E. Mouzavires Apparatus for hand drilling
WO1994000345A1 (en) * 1992-06-30 1994-01-06 Aktsionernoe Obschestvo 'aviatika' Sport-piloting aeroplane
RU2005662C1 (en) * 1992-06-30 1994-01-15 Акционерное общество "Авиатика" Aerobatic plane
US7546979B1 (en) * 2006-09-15 2009-06-16 The Boeing Company Trapezoidal panel pin joint allowing free deflection between fuselage and wing

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1981700A (en) * 1933-09-18 1934-11-20 J L Younghusband Aircraft
GB507714A (en) * 1937-08-02 1939-06-20 Dornier Werke Gmbh Improvements in or relating to aircraft
US3926389A (en) * 1972-05-24 1975-12-16 Messerschmitt Boelkow Blohm Aircraft of a controllable stability
DE2254136A1 (en) * 1972-11-04 1974-05-16 Messerschmitt Boelkow Blohm FOLDING TAIL

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GB2048182A (en) 1980-12-10
FR2440872A1 (en) 1980-06-06
ATA904379A (en) 1982-09-15
GB2048182B (en) 1983-03-30
AT370690B (en) 1983-04-25
SU764275A1 (en) 1982-03-30
IT7927025A0 (en) 1979-11-02
DD148454A3 (en) 1981-05-27
AU529644B2 (en) 1983-06-16
FR2440872B1 (en) 1983-10-14
AU5262179A (en) 1980-05-08
WO1980000949A1 (en) 1980-05-15

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