CN108382589A - A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method - Google Patents

A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method Download PDF

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Publication number
CN108382589A
CN108382589A CN201810115106.4A CN201810115106A CN108382589A CN 108382589 A CN108382589 A CN 108382589A CN 201810115106 A CN201810115106 A CN 201810115106A CN 108382589 A CN108382589 A CN 108382589A
Authority
CN
China
Prior art keywords
wing
unmanned plane
landing
fuselage
tails
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
Application number
CN201810115106.4A
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Chinese (zh)
Inventor
薛睿
程熙
魏松原
刘英杰
刘远平
李屹东
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AVIC Chengdu Aircraft Design and Research Institute
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AVIC Chengdu Aircraft Design and Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AVIC Chengdu Aircraft Design and Research Institute filed Critical AVIC Chengdu Aircraft Design and Research Institute
Priority to CN201810115106.4A priority Critical patent/CN108382589A/en
Publication of CN108382589A publication Critical patent/CN108382589A/en
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/13—Propulsion using external fans or propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U70/00—Launching, take-off or landing arrangements
    • B64U70/60—Take-off or landing of UAVs from a runway using their own power

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Wind Motors (AREA)

Abstract

The present invention relates to a kind of overall aerodynamic arrangements of double hair unmanned planes, it is characterized in that, unmanned plane includes fuselage (1), large-size antennae cover (2), wing (4), nacelle (3), propeller (5) and V tails (6) and blocks hook (11), it is characterized in that：The cross sectional shape of fuselage (1) uses ship type, and the aspect ratio of wing (4) is 15 25, and fuselage (1) merges transition with wing (4) shape；It is disposed with wing flap (7), flaperon (8), aileron (9) on wing (4), elerudder (10) is arranged on V tails (6)；Engine is mounted on leading edge of a wing inner segment by wing nacelle (3), and propeller (5) is installed in nacelle front end.The unmanned plane for using short take-off and landing layout can meet the needs of overall, pneumatic, structure and takeoff and landing performance, with flying speed range is wide, lift resistance ratio is high, landing apart from it is short outstanding advantages of, short take-off and landing unmanned plane layout can be used for examining the aerodynamic arrangement's design for the design for beating integrated unmanned plane, Attack UAV, reconnaissance version unmanned plane and extraordinary unmanned plane.

Description

A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method
Technical field
The invention belongs to aviation fields, are related to the pneumatic cloth of a kind of totality that the double hair UAV aerodynamic layouts of high lift-drag ratio use Office and landing occupation mode.
Background technology
It examines and beats integrated unmanned plane generally using normal arrangement, there are following problems：
1. being usually separate unit airscrew engine, have an high regard for relatively low, takeoff distance is long.
2. being influenced by braking ability, landing run is long.
3. for overloading oil, install standby, raising fighting efficiency, inner space is nervous more.
Invention content
The purpose of the present invention is to propose to it is a kind of can short take-off and landing double hair unmanned plane totality aerodynamic arrangements.
The present invention technical solution be：
A kind of overall aerodynamic arrangement of double hair unmanned plane, which includes fuselage 1, large-size antennae cover 2, wing 4, short Cabin 3, propeller 5 and V tails 6 and hook 11 is blocked, it is characterized in that：The cross sectional shape of fuselage 1 uses ship type, and the aspect ratio of wing 4 is 15-25；It is disposed with wing flap 7, flaperon 8, aileron 9 on wing 4, elerudder 10 is arranged on V tails 6；Engine passes through wing Nacelle 3 is mounted on leading edge of a wing inner segment, and propeller 5 is installed in nacelle front end.
The fuselage cross-section uses ship type with rounded corners cross section 1, fuselage 1 to merge transition with 4 shape of wing.
The wing 4 uses rectangle and trapezoidal Combination Design, wing inner segment flat shape to use rectangle, wing outer segment flat Face shape is using trapezoidal.
Fuselage afterbody arrangement blocks hook 11, and 11 and the progress short distance landing of ground arresting system are hooked by blocking.
The engine is using the double hair nacelle layouts of wing.
The V tails 6 are using the double V tails of flare.
Fuselage afterbody arrangement blocks hook 11；11 and the progress short distance landing of ground arresting system are hooked by blocking.
Wing 4, the use of V tails 7 supercritical airfoil, laminar flow airfoil, overcritical laminar flow airfoil or the symmetrical airfoil.
A kind of method of unmanned plane short take-off and landing, the landing method of above-mentioned unmanned plane are as follows：
When taking off, unmanned plane is blocked using Liftable type catch, when unmanned vehicle engine reaches maximum rating, puts down wheel Gear realizes short-distance taking off of unmanned aerial vehicles；
When landing, equipment is blocked using 11 hook ground of hook are blocked, realizes unmanned plane short landing.
This patent has the following advantages that：
(1) high aspect ratio wing is used, aerodynamic arrangement's lift resistance ratio is high, and it is subsonic envelope to be applicable in flying speed；
(2) using double hair propeller layouts, have compared with big thrust loading；
(3) lift catch takes off, and blocks hook and lands, and can meet short take-off and landing requirement；
Therefore, the unmanned plane for using short take-off and landing layout can meet the needs of overall, pneumatic, structure and takeoff and landing performance, With flying speed range is wide, lift resistance ratio is high, landing apart from it is short outstanding advantages of, the short take-off and landing unmanned plane layout can be used for examining Play aerodynamic arrangement's design of the design of integrated unmanned plane, Attack UAV, reconnaissance version unmanned plane and extraordinary unmanned plane.
Description of the drawings
Fig. 1 is unmanned plane total arrangement schematic diagram of the present invention；
Fig. 2 is front view of the present invention；
Fig. 3 is side view of the present invention；
Fig. 4 is unmanned plane vertical view of the present invention and rudder face arrangement schematic diagram.
Specific implementation mode
It is a kind of using double hair short take-off and landing unmanned plane totality aerodynamic arrangements, unmanned plane include fuselage 1, large-size antennae cover 2, Wing 4, nacelle 3, propeller 5 and V tails 6 and hook 11 is blocked, the cross sectional shape of fuselage 1 uses the ship type, the aspect ratio of wing 4 to be 15-25, wing inner segment flat shape use rectangle 4, wing outer segment flat shape to use trapezoidal 4；Wing 4 uses super critical aerofoil Type, laminar flow airfoil or overcritical laminar flow airfoil；It is disposed with wing flap 7, flaperon 8, aileron 9 on wing 4, lifting is arranged on V tails 6 Rudder 1.For engine by wing nacelle 3 in leading edge of a wing inner segment, propeller 5 is installed in nacelle front end.Fuselage afterbody arrangement is blocked Resistance hooks 11.Fuselage 1 merges transition with 4 shape of wing.11 and the progress short distance landing of ground arresting system are hooked by blocking.
Embodiment
A. as shown in Figure 1, unmanned plane is made of fuselage, large-size antennae cover, wing, nacelle and propeller, V tails.
B. as shown in Fig. 2, fuselage uses ship type section.
C. as shown in figure 3, aft body arrangement blocks hook.
D. as shown in figure 4, wing aspect ratio is 15~20.Wing planform rectangle and trapezoidal combination.
E. wing uses high lift-drag ratio supercritical airfoil, laminar flow airfoil or overcritical laminar flow airfoil.
F. as shown in figure 4, rear airfoil end arrangement wing flap, flaperon, aileron.
G. as shown in Figure 1, arranging two engines and propeller by wing nacelle.
H. as shown in Figure 1, fuselage merges transition with wing shape.
I. unmanned plane is blocked using Liftable type catch, when unmanned vehicle engine reaches maximum rating, puts down catch, realized Short-distance taking off of unmanned aerial vehicles.
J. use blocks hooking hook ground and blocks equipment (small-sized electromagnetic type blocks mechanism), realizes unmanned plane short landing.

Claims (9)

1. a kind of overall aerodynamic arrangement of double hair unmanned planes, characterized in that unmanned plane includes fuselage (1), large-size antennae cover (2), wing (4), nacelle (3), propeller (5) and V tails (6) and hook (11) is blocked, it is characterized in that：The cross sectional shape of fuselage (1) Using ship type, the aspect ratio of wing (4) is 15-25, and fuselage (1) merges transition with wing (4) shape；Wing is disposed on (4) Wing flap (7), flaperon (8), aileron (9), arrangement elerudder (10) on V tails (6)；Engine is pacified by wing nacelle (3) Mounted in leading edge of a wing inner segment, propeller (5) is installed in nacelle front end.
2. totality aerodynamic arrangement according to claim 1, characterized in that the fuselage cross-section uses ship type with rounded corners Cross section (1).
3. totality aerodynamic arrangement according to claim 1, characterized in that the wing (4) uses rectangle and trapezoidal group Design is closed, wing inner segment flat shape uses rectangle, and wing outer segment flat shape is using trapezoidal.
4. totality aerodynamic arrangement according to claim 1, characterized in that fuselage afterbody arrangement blocks hook (11), by blocking Resistance hooks (11) and carries out short distance landing with ground arresting system.
5. totality aerodynamic arrangement according to claim 1, characterized in that the engine is using the double hair nacelle cloth of wing Office.
6. totality aerodynamic arrangement according to claim 1, characterized in that the V tails (6) are using the double V tails of flare.
7. totality aerodynamic arrangement according to claim 1, characterized in that fuselage afterbody arrangement blocks hook (11)；By blocking Resistance hooks (11) and carries out short distance landing with ground arresting system.
8. totality aerodynamic arrangement according to claim 1, characterized in that the wing (4), V tails (7) are using overcritical Aerofoil profile, laminar flow airfoil, overcritical laminar flow airfoil or symmetrical airfoil.
9. a kind of method of unmanned plane short take-off and landing, characterized in that the landing method of unmanned plane as described in claim 1 is such as Under：
When taking off, unmanned plane is blocked using Liftable type catch, when unmanned vehicle engine reaches maximum rating, puts down catch, it is real Existing short-distance taking off of unmanned aerial vehicles；
When landing, equipment is blocked using hook (11) hook ground is blocked, realizes unmanned plane short landing.
CN201810115106.4A 2018-02-05 2018-02-05 A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method Pending CN108382589A (en)

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CN201810115106.4A CN108382589A (en) 2018-02-05 2018-02-05 A kind of pair of overall aerodynamic arrangement for sending out unmanned plane and its short take-off and landing method

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111017190A (en) * 2019-12-24 2020-04-17 中国航空工业集团公司西安飞机设计研究所 Large-scale civil passenger plane of integration overall arrangement
CN112407237A (en) * 2020-09-30 2021-02-26 北京北航天宇长鹰无人机科技有限公司 Medium-sized unmanned aerial vehicle with high lift-drag ratio

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CN202642096U (en) * 2012-04-01 2013-01-02 北京航空航天大学 Small-scale unmanned aerial vehicle, as well as onboard arresting gear, ground arresting gear and arresting system thereof
CN103158856A (en) * 2013-04-12 2013-06-19 北京航空航天大学 Light airscrew flying wing aircraft capable of taking off and landing in short distance
CN105857579A (en) * 2016-05-12 2016-08-17 中国航空工业集团公司西安飞机设计研究所 Propeller airplane
CN106494604A (en) * 2015-09-06 2017-03-15 沈观清 Hollow long endurance unmanned aircraft total arrangement
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CN101041380A (en) * 2006-03-23 2007-09-26 李泽奇 Inclined wing airplane and application thereof
CN200939356Y (en) * 2006-08-22 2007-08-29 青岛天骄无人机遥感技术有限公司 Small remote monitoring pilotless plane
CN201023653Y (en) * 2007-04-24 2008-02-20 江西洪都航空工业集团有限责任公司 Large aspect ratio sweep forward wings airplane pneumatic distribution
CN101244764A (en) * 2008-03-07 2008-08-20 王刚 Cascade connection type hybrid power ejection propulsion vehicle for takeoff of airplane
CN202642096U (en) * 2012-04-01 2013-01-02 北京航空航天大学 Small-scale unmanned aerial vehicle, as well as onboard arresting gear, ground arresting gear and arresting system thereof
CN103158856A (en) * 2013-04-12 2013-06-19 北京航空航天大学 Light airscrew flying wing aircraft capable of taking off and landing in short distance
CN106494604A (en) * 2015-09-06 2017-03-15 沈观清 Hollow long endurance unmanned aircraft total arrangement
WO2017042291A1 (en) * 2015-09-08 2017-03-16 Swiss Aerobotics Ag Aircraft for transport and delivery of payloads
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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111017190A (en) * 2019-12-24 2020-04-17 中国航空工业集团公司西安飞机设计研究所 Large-scale civil passenger plane of integration overall arrangement
CN112407237A (en) * 2020-09-30 2021-02-26 北京北航天宇长鹰无人机科技有限公司 Medium-sized unmanned aerial vehicle with high lift-drag ratio

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Application publication date: 20180810