CN108583839A - A kind of Small General Aircraft - Google Patents

A kind of Small General Aircraft Download PDF

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Publication number
CN108583839A
CN108583839A CN201810407689.8A CN201810407689A CN108583839A CN 108583839 A CN108583839 A CN 108583839A CN 201810407689 A CN201810407689 A CN 201810407689A CN 108583839 A CN108583839 A CN 108583839A
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CN
China
Prior art keywords
wing
fuselage
starboard
small general
port
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.)
Granted
Application number
CN201810407689.8A
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Chinese (zh)
Other versions
CN108583839B (en
Inventor
李吉
李明富
杨林
杨映根
郑乐易
林辉
吴墙铵
赵兴
李健
曾浩芸
霍蔚峰
刘楚雨
何智林
蔡瀚宇
汤献金
冯任杰
唐文静
张靖
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.)
Chengdu Aeronautic Polytechnic
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Chengdu Aeronautic Polytechnic
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Publication date
Application filed by Chengdu Aeronautic Polytechnic filed Critical Chengdu Aeronautic Polytechnic
Priority to CN201810407689.8A priority Critical patent/CN108583839B/en
Publication of CN108583839A publication Critical patent/CN108583839A/en
Application granted granted Critical
Publication of CN108583839B publication Critical patent/CN108583839B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • B64C1/0009—Aerodynamic aspects
    • 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
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/08—Stabilising surfaces mounted on, or supported by, wings

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Toys (AREA)
  • Tires In General (AREA)

Abstract

The invention discloses a kind of Small General Aircrafts, including port wing, starboard wing, fuselage, T-type empennage, banjo fixing butt jointing and undercarriage；Port wing and starboard wing include wing-body, wing flap, aileron and winglet；Fuselage passes on left banjo fixing butt jointing setting port wing, starboard wing is arranged by banjo fixing butt jointing in the right side of fuselage, T-tail is arranged in the rear end of fuselage, undercarriage is set to the bottom of fuselage, solves the problems, such as that the previous general-purpose aircraft wasting of resources, waste fuel oil, fuselage are easily destroyed, do not need a large amount of aircrafts in teaching to illustrate different wings or other structures aircraft.

Description

A kind of Small General Aircraft
Technical field
The present invention relates to general-purpose aircraft field, especially a kind of Small General Aircraft.
Background technology
The aerodynamic arrangement that existing general-purpose aircraft uses is laid out for Conventional pneumatic, and the present invention uses asymmetric layout, same There are a variety of various forms of aircaft configurations on airplane, largely save resource；Winglet is increased, for can Operation of landing gear reduces resistance while saving fuel oil；Set fuselage to tadpole shape, endpiece is elongate, and fuselage is not easy to be broken It is bad；The Small General Aircraft of the present invention can be used to educate and use, and uses asymmetrical design, reaches and given expression on an airplane Various difference aircaft configurations, various different aircaft configurations can be given expression to by not needing many airplanes, save resource.
Invention content
To solve problems of the prior art, the present invention provides a kind of Small General Aircraft, solve previous logical Easily be destroyed with the aircraft wasting of resources, waste fuel oil, fuselage, do not need a large amount of aircrafts in teaching illustrate different wings or The problem of other structures aircraft.
The technical solution adopted by the present invention is：A kind of Small General Aircraft, including port wing, starboard wing, fuselage, T-type tail The wing, banjo fixing butt jointing and undercarriage；Port wing and starboard wing include wing-body, wing flap, aileron and winglet；A left side for fuselage Port wing is arranged by banjo fixing butt jointing in side, and starboard wing is arranged by banjo fixing butt jointing in the right side of fuselage, and T shape tails are arranged in the rear end of fuselage The wing, undercarriage are set to the bottom of fuselage.
Preferably, port wing is more web-type wings, and starboard wing is Liang Shi wings, the winglet of port wing and starboard wing It is compound angle of sweep eddy diffusion device winglet.
Preferably, fuselage is tadpole shape streamlined fuselage.
Preferably, the banjo fixing butt jointing of port wing connects for distributing, and the banjo fixing butt jointing of starboard wing is that centralization connects.
Preferably, undercarriage is retractable landing gear.
Preferably, the layout of port wing, starboard wing, fuselage and T-type empennage is laid out for general-purpose aircraft.
Preferably, the material of afterbody is composite material.
Small General Aircraft of the present invention has the beneficial effect that：
1. fuselage is tadpole shape, endpiece is elongate, has not only met structural strength needs, but also can guarantee fairshaped fuselage not It is destroyed.
2. using a kind of asymmetrical tactic pattern, port wing is more web-type wings such as on an airplane wing, and Corresponding starboard wing is then beam type wing, has saved resource.
3. being provided with winglet, it is same to reduce resistance for retractable landing gear for a device being mounted on wing When save fuel oil.
Description of the drawings
Fig. 1 is a kind of vertical view of Small General Aircraft of the present invention.
Fig. 2 is a kind of left view of Small General Aircraft of the present invention.
Fig. 3 is a kind of vertical view of Small General Aircraft of the present invention.
Fig. 4 is a kind of port wing figure of Small General Aircraft of the present invention.
Fig. 5 is a kind of starboard wing figure of Small General Aircraft of the present invention.
Fig. 6 is a kind of fuselage afterbody figure of Small General Aircraft of the present invention.
Fig. 7 is a kind of gear down figure of Small General Aircraft of the present invention.
Fig. 8 is that a kind of undercarriage of Small General Aircraft of the present invention is packing up figure.
Fig. 9 is a kind of gear up figure of Small General Aircraft of the present invention.
Figure 10 is a kind of undercarriage figure of Small General Aircraft of the present invention.
Figure 11 is a kind of fuselage vertical view of Small General Aircraft of the present invention.
Figure 12 is a kind of fuselage side view of Small General Aircraft of the present invention.
Reference numeral：1- port wings, 2- starboard wings, 3- fuselages, 4-T type tails, 5- undercarriages, 6- wing-bodies, the 7- flap The wing, 8- ailerons, 9- winglets.
Specific implementation mode
The embodiment of the present invention is described in detail below in conjunction with the accompanying drawings.
The specific implementation mode of the present invention is described below, in order to facilitate understanding by those skilled in the art this hair It is bright, it should be apparent that the present invention is not limited to the ranges of specific implementation mode, for those skilled in the art, As long as various change is in the spirit and scope of the present invention that the attached claims limit and determine, these variations are aobvious and easy See, all are using the innovation and creation of present inventive concept in the row of protection.
As shown in Figures 1 to 10, a kind of Small General Aircraft, including port wing 1, starboard wing 2, fuselage 3, T-type empennage 4, Banjo fixing butt jointing and undercarriage 5；Port wing 1 and starboard wing 2 include wing-body 6, wing flap 7, aileron 8 and winglet 9；Fuselage Port wing 1 is arranged in 3 banjo fixing butt jointing that passes on left, and the right side of fuselage 3 passes through banjo fixing butt jointing and starboard wing 2, the rear end of fuselage 3 is arranged T-tail 4 is set, and undercarriage 5 is set to the bottom of fuselage 3.
For the present embodiment when implementing, using asymmetrical tactic pattern, port wing 1 is more abdomens for port wing 1 and starboard wing 2 Board-like wing, and corresponding starboard wing 2 is beam type wing, has saved many materials.
The port wing 1 of this programme is more web-type wings, and starboard wing 2 is Liang Shi wings, the wing of port wing 1 and starboard wing 2 Tip winglet 9 is compound angle of sweep eddy diffusion device winglet.
For the present embodiment when implementing, using asymmetrical tactic pattern, port wing 1 is more abdomens for port wing 1 and starboard wing 2 Board-like wing, and corresponding starboard wing 2 is beam type wing, has saved many materials.
The fuselage 3 of this programme is tadpole shape streamlined fuselage.
For the present embodiment when implementing, because fuselage is tadpole shape, endpiece is elongate, in order to both meet structural strength need It wants, and can guarantee that fairshaped fuselage is not destroyed, so answering material shell using rear body, i.e. tadpole fuselage afterbody is all to use entirely Material material is answered to make.
The banjo fixing butt jointing of the port wing 1 of this programme connects for distributing, and the banjo fixing butt jointing of starboard wing 2 is that centralization connects.
For the present embodiment when implementing, the connection of fuselage and wing is unsymmetric structure, and the banjo fixing butt jointing with port wing is Distributing connects, and is that centralization is connect with the banjo fixing butt jointing of starboard wing.
The undercarriage 5 of this programme is retractable landing gear.
The port wing 1 of this programme, starboard wing 2, fuselage 3 and T-type empennage 4 layout be general-purpose aircraft layout.
The material of 3 tail portion of fuselage of this programme is composite material.
For the present embodiment when implementing, because fuselage is tadpole shape, endpiece is elongate, in order to both meet structural strength need It wants, and can guarantee that fairshaped fuselage is not destroyed, so answering material shell using rear body, i.e. tadpole fuselage afterbody is all to use entirely Multiple material material model makes for CCF300.
As shown in figure 11, there are from top to bottom totally 10 key points in the vertical view of fuselage, if fuselage length is 1, then first The ratio that the distance of key point to appearance profile line accounts for fuselage is 0.01819；The distance of second key point to appearance profile line accounts for The ratio of fuselage is 0.05231；The ratio that the distance of third key point to appearance profile line accounts for fuselage is 0.08183；4th closes The ratio that the distance of key point to appearance profile line accounts for fuselage is 0.09362；The distance of 5th key point to appearance profile line accounts for machine The ratio of body is 0.08290；The ratio that the distance of 6th key point to appearance profile line accounts for fuselage is 0.05308；7th is crucial The ratio that the distance of point to appearance profile line accounts for fuselage is 0.04339；The distance of 8th key point to appearance profile line accounts for fuselage Ratio be 0.03054；The with regard to the distance of key point to appearance profile line, to account for the ratio of fuselage be 0.01754；Tenth key point To appearance profile line distance account for fuselage ratio be 0.26467.
As shown in figure 12, there are 9 key points, the first key point to left outside shape contour line in the side view of fuselage from top to bottom Distance to account for the ratio of fuselage be 0.03757, the ratio that the distance of the first key point to right appearance profile line accounts for fuselage is 0.01461；The distance of second key point to left outside shape contour line accounts for the ratio 0.06205 of fuselage, the second key point to right shape The ratio that the distance of contour line accounts for fuselage is 0.01874；The distance of third key point to left outside shape contour line accounts for the ratio of fuselage It is 0.07999, it is 0.02268 that the distance of third key point to right appearance profile line, which accounts for the ratio of fuselage,；4th key point to a left side The ratio that the distance of appearance profile line accounts for fuselage is 0.06678, and the distance of the 4th key point to right appearance profile line accounts for fuselage Ratio is 0.09124；The ratio that the distance of 5th key point to left outside shape contour line accounts for fuselage is 0.07910, the 5th key point To right appearance profile line distance account for fuselage ratio be 0.08087；The distance of 6th key point to left outside shape contour line accounts for machine Body ratio is 0.05970, and it is 0.04230 that the distance of the 6th key point to right appearance profile line, which accounts for the ratio of fuselage,；7th is crucial The ratio that the distance of point to left outside shape contour line accounts for fuselage is 0.04563, and the distance of the 7th key point to right appearance profile line accounts for The ratio of fuselage is 0.02738；The ratio that the distance of 8th key point to left outside shape contour line accounts for fuselage is the 0.02924, the 8th The ratio that the distance of key point to right appearance profile line accounts for fuselage is 0.01518；9th key point to left outside shape contour line away from It is 0.01691 from the ratio of fuselage is accounted for, it is 0.00820 that the distance of the 9th key point to right appearance profile line, which accounts for the ratio of fuselage,.

Claims (7)

1. a kind of Small General Aircraft, which is characterized in that including port wing (1), starboard wing (2), fuselage (3), T-type empennage (4), Banjo fixing butt jointing and undercarriage (5)；The port wing (1) and starboard wing (2) include wing-body (6), wing flap (7), aileron (8) With winglet (9)；The fuselage (3) passes on left banjo fixing butt jointing setting port wing (1), and the right side of the fuselage (3) is logical Banjo fixing butt jointing setting starboard wing (2), the rear end setting T-tail (4) of the fuselage (3) are crossed, the undercarriage (5) is set to machine The bottom of body (3).
2. a kind of Small General Aircraft according to claim 1, which is characterized in that the port wing (1) is more web-types Wing, the starboard wing (2) are Liang Shi wings, after the winglet (9) of the port wing (1) and starboard wing (2) is compound Sweep angle eddy diffusion device winglet.
3. a kind of Small General Aircraft according to claim 1, which is characterized in that the fuselage (3) is tadpole shape streamline Shape fuselage.
4. a kind of Small General Aircraft according to claim 1, which is characterized in that the banjo fixing butt jointing of the port wing (1) It is connected for distributing, the banjo fixing butt jointing of the starboard wing (2) is that centralization connects.
5. a kind of Small General Aircraft according to claim 1, which is characterized in that the undercarriage (5) is deployable and collapsible Undercarriage.
6. a kind of Small General Aircraft according to claim 1, which is characterized in that the port wing (1), starboard wing (2), The layout of fuselage (3) and T-type empennage (4) is laid out for general-purpose aircraft.
7. a kind of Small General Aircraft according to claim 1, which is characterized in that the material of fuselage (3) tail portion is Composite material.
CN201810407689.8A 2018-05-02 2018-05-02 Small-size general purpose aircraft Active CN108583839B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810407689.8A CN108583839B (en) 2018-05-02 2018-05-02 Small-size general purpose aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810407689.8A CN108583839B (en) 2018-05-02 2018-05-02 Small-size general purpose aircraft

Publications (2)

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CN108583839A true CN108583839A (en) 2018-09-28
CN108583839B CN108583839B (en) 2020-09-29

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5645250A (en) * 1993-08-26 1997-07-08 Gevers; David E. Multi-purpose aircraft
US6293497B1 (en) * 1996-10-22 2001-09-25 The Boeing Company Airplane with unswept slotted cruise wing airfoil
US20030057327A1 (en) * 2001-09-27 2003-03-27 Carroll Ernest A. Miniature, unmanned aircraft with automatically deployed parachute
US20030066932A1 (en) * 2001-09-27 2003-04-10 Carroll Ernest A. Miniature, unmanned aircraft with interchangeable data module
US20130099053A1 (en) * 2011-10-19 2013-04-25 The Boeing Company Mid-Wing Multi-Deck Airplane
US20170050720A1 (en) * 2015-08-20 2017-02-23 The Boeing Company Mitigation of surface discontinuities between flight control surfaces and an airframe of an aircraft

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5645250A (en) * 1993-08-26 1997-07-08 Gevers; David E. Multi-purpose aircraft
US6293497B1 (en) * 1996-10-22 2001-09-25 The Boeing Company Airplane with unswept slotted cruise wing airfoil
US20030057327A1 (en) * 2001-09-27 2003-03-27 Carroll Ernest A. Miniature, unmanned aircraft with automatically deployed parachute
US20030066932A1 (en) * 2001-09-27 2003-04-10 Carroll Ernest A. Miniature, unmanned aircraft with interchangeable data module
US20130099053A1 (en) * 2011-10-19 2013-04-25 The Boeing Company Mid-Wing Multi-Deck Airplane
US20170050720A1 (en) * 2015-08-20 2017-02-23 The Boeing Company Mitigation of surface discontinuities between flight control surfaces and an airframe of an aircraft

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