CN106828872B - Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage - Google Patents
Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage Download PDFInfo
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- CN106828872B CN106828872B CN201710073704.5A CN201710073704A CN106828872B CN 106828872 B CN106828872 B CN 106828872B CN 201710073704 A CN201710073704 A CN 201710073704A CN 106828872 B CN106828872 B CN 106828872B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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- Fluid Mechanics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of high altitude long time tandem rotor aircraft aerodynamic arrangements using high rear wing support empennage, belong to aerodynamic configuration of aircraft design field.In the present invention, aircraft uses cylindrical cross-section fuselage, the preceding wing of high aspect ratio and rear wing, " V " type tail, vertical fin；Wherein, preceding wing is lower single-blade, is symmetrically mounted on fuselage front half section；" V " type tail is two, is symmetrically mounted on the fuselage second half section；Afterwards wing by " V " tail support in the way of be mounted on the taper of " V " type tail；Vertical fin is mounted below afterbody；Engine is mounted on above afterbody.The present invention is laid out in the case where guaranteeing identical wing area using the tandem wing, be can avoid using big length, and then reduce the requirement of wing structure intensity and toughness, is conducive to mitigate aircraft weight, increases payload；Take reasonable pneumatic face fit system that there is better flight stability and maneuverability under the premise of guaranteeing that aerodynamic characteristic is excellent.
Description
Technical field
The invention belongs to aerodynamic configuration of aircraft design fields, and in particular to it is a kind of using " V " type support empennage make after
The high altitude long time tandem rotor aircraft aerodynamic arrangement set on wing.
Background technique
The purposes that high altitude long time aircraft has its special in terms of being scouted when battlefield is long with Atmospheric sounding in upper air, especially
In recent years, high altitude long time aircraft had received widespread attention as a kind of multi-functional optimal in structure, development.But high-altitude is long
Endurance aircraft is more demanding to flying quality, pneumatic quality etc., especially requires under the premise of enough lift, has
Biggish lift resistance ratio.
In order to meet above-mentioned requirements, the normal arrangement of super large aspect ratio, the big span is generallyd use both at home and abroad.When aircraft flies
When scanning frequency degree is lower, for the wing with same lift face area, the bigger aspect ratio of use is conducive to reduce luring for wing
Resistance is led, to obtain higher lift resistance ratio.Simultaneously as bigger aspect ratio is used, in order to guarantee to have enough wings
Area needs to provide enough lift using big length.
However, being obtained after using super large aspect ratio, big length since the length of wing is bigger than the thickness of wing and chord length
It is more, thus may there is a problem of rigidity of structure deficiency.In flight course, easily forms malformation and interact work with aerodynamic force
Aeroelasticity phenomenon has considerable influence to the safety of aircraft and performance, can reduce driving efficiency, wing liter
Force coefficient slope, in some instances it may even be possible to generate fulminant flutter, diverging within flight envelope, or even cause structure to damage suddenly and make
At aircraft accident.To solve this problem, the mode for reinforcing wing rigidity is generallyd use, the relative thickness of aerofoil profile is such as increased or is made
It can reduce the aeroperformance of aircraft with the relative thickness of the better spar of rigidity property, but excessive increase aerofoil profile, and rigidity
The better spar structure weight of performance can greatly increase, so that aircraft payload reduces.
To meet the requirement that high altitude long time aircraft has enough lift, there is a kind of tandem wing aerodynamic arrangement.It should
Layout includes former and later two wings, and rear wing can generate advantageous interference to preceding wing, but preceding wing can generate not rear wing
Benefit interference.In addition, two interplane interference strengths change with angle of attack variation, so that both wings lift increment also changes correspondingly, Quan cause
The pneumatic focus moving range of machine is larger, influences flying quality.In order to meet high altitude long time aircraft high-lift, high lift-drag ratio
It is required that needing the influence to tandem wing layout structure parameters to aerodynamic characteristic to further investigate, also to obtain a kind of optional gas
Dynamic placement scheme.
Summary of the invention
The present invention from pneumatic design angle, deeply ground by the aerodynamic interference being laid out between the wing of front and back to the tandem wing
Study carefully, proposes a kind of high altitude long time tandem rotor aircraft aerodynamic arrangement using high rear wing support empennage, provide a kind of knot
Structure performance and all good high altitude long time Flight Vehicle Design technical solution of aeroperformance.
Studies have shown that preceding wing tip changes the induction intensity of rear wing with difference in height and changes, and then machine after change
The span is equipped on rear wing and is conducive to be promoted the whole aeroperformance of double-vane face layout to flowing；Due to rear wing stationary point higher-pressure region
Forward thrust is generated to preceding wing, so that preceding wing drag reduces, to substantially increase the lift resistance ratio of preceding wing；Preceding wing pair
Wing can generate and wash effect under induction afterwards, so that rear wing aerodynamic performance is declined；Wing can be subtracted using smaller chord length afterwards
Inductive effect is washed under weak front wing is unfavorable to rear wing.
Therefore, aerodynamic configuration of aircraft of the present invention wing and above sets wing cloth after smaller chord length before placing an order using larger chord length
It sets；And the arrangement of " V " type tail support is utilized, the rigidity of structure of wing after smaller chord length is set in enhancing.Afterbody peace
Equipped with fanjet and vertical tail.
High altitude long time tandem rotor aircraft aerodynamic arrangement provided by the invention using high rear wing support empennage, aircraft
Using cylindrical cross-section fuselage, the preceding wing of high aspect ratio and rear wing, " V " type tail, vertical fin；Wherein, preceding wing is to place an order
The wing is symmetrically mounted on fuselage front half section；" V " type tail is two, is symmetrically mounted on fuselage second half section, 45 ° of the upper counterangle；Wing afterwards
The taper of " V " type tail is mounted in the way of the support of " V " tail；Vertical fin is mounted below afterbody；Engine is mounted on
Above afterbody.
The advantages of aerodynamic configuration of aircraft of the present invention, is:
(1) it in the case where guaranteeing identical wing area, is laid out using the tandem wing, can avoid using big length, and then drop
Low wing structure intensity and toughness requirement, is conducive to mitigate aircraft weight, increases payload.
(2) it utilizes " V " type tail to support, is imitated being set on wing after smaller chord length with reducing front wing to the unfavorable interference of rear wing
It answers, is conducive to the whole aerodynamic characteristic for improving double-vane face layout, improves complete machine lift resistance ratio.
(3) front wing uses larger chord length, and rear wing uses smaller chord length, rear wing is made full use of to subtract the advantageous interference of front wing
Few unfavorable interference of the front wing to rear wing.
(4) wing, " V " tail and fuselage constitute closed triangular structure afterwards, enhance the knot of rear wing He " V " tail
Structure strength and stiffness are conducive to mitigate aircraft weight, improve structure efficiency.
(5) reasonable pneumatic face fit system is taken, under the premise of guaranteeing that aerodynamic characteristic is excellent, with common tandem wing cloth
Office compares, and present invention layout has better flight stability and maneuverability.
Detailed description of the invention
Fig. 1 is aerodynamic configuration of aircraft overall schematic of the present invention；
Fig. 2 is aerodynamic configuration of aircraft overall top view of the present invention；
Fig. 3 is aerodynamic configuration of aircraft entirety side view of the present invention；
Fig. 4 is aerodynamic configuration of aircraft entirety main view of the present invention；
Fig. 5 is that aerodynamic configuration of aircraft of the present invention compares common tandem wing layout lift resistance ratio with angle of attack variation curve graph；
In figure: 1. fuselages；Wing before 2.；Wing after 3.；4. wing flap；5. aileron；6. engine；" 7. V " tail stabilization 8.
" V " tail vane face；9. vertical fin stabilization；10. rudder.
Specific embodiment
The present invention is described further below with reference to attached drawing.
In aerodynamic configuration of aircraft provided by the invention, aircraft using cylindrical cross-section fuselage 1, compared with high aspect ratio before
Wing 2 and rear wing 3, " V " type tail, vertical fin, as shown in figures 1-4.Wherein, preceding 2 chord length of wing is larger, for lower single-blade, symmetrically
It is mounted on fuselage front half section；" V " type tail is two, is symmetrically mounted on the fuselage second half section, the upper counterangle is close to 45 °；3 string of wing afterwards
Length is smaller, and the taper of " V " type tail is mounted in the way of the support of " V " tail；Vertical fin is mounted below 1 tail portion of fuselage；Start
Machine 6 is mounted on 1 upper rear of fuselage.
Such as Fig. 2, preceding 2 rear of wing arrangement wing flap 4 and aileron 5, aileron 5 is to control aircraft rolling；Wing 3 is same afterwards
It can also arrange wing flap and aileron；Such as Fig. 3, " V " type tail includes " V " tail stabilization 7 and " V " the tail vane face 8 for being arranged in rear,
" V " tail stabilization 7 is to guarantee aircraft pitching stability, and " V " tail vane face 8 is to control aircraft pitching；Vertical fin includes hanging down
Tail stabilization 9 and the rudder 10 for being arranged in rear, vertical fin stabilization 9 is to guarantee aircraft course stability, rudder 10
To control vehicle yaw.
Specific relative position and aircraft entirety aeroperformance between the preceding wing 2 and rear wing 3 is closely related, needs
It is determined according to the requirement of pneumatic design.According to interplane interference mechanism, rear wing 3, which has preceding wing 2, favorably to be interfered, and preceding wing
Wing 3, which exists, after 2 pairs washes effect under induction；When rear wing 3 is in the wake zone of preceding 2 wingtip vortex of wing, preceding 2 wingtip vortex of wing
Rear 3 wingtip partial pneumatic performance of wing is significantly affected, and before rear wing 3 leaves when the wake zone of 2 wingtip vortex of wing,
There will be weakened for the effect of washing under the induction of preceding wing 2.And in order to improve aircraft complete machine lift resistance ratio, it on the one hand needs as far as possible
The advantageous interference using rear wing 3 to preceding wing 2, on the other hand need to weaken preceding wing 2 as far as possible to rear wing 3 not
Benefit interference.The influence generated therefore, it is necessary to the difference in height difference value set on rear wing 3 is analyzed.
Embodiment: it is that 3 times of chord length layouts are whole in contrast to common tandem wing layout that Fig. 5, which gives and sets difference in height on rear wing 3,
Body lift resistance ratio is with the three dimensional analysis curve of angle of attack variation, and ordinate LDR is lift resistance ratio, and abscissa AOA is the angle of attack, after h3c-3D is
It is 3 times of chord length layouts that difference in height is set on wing 3, and h0c-3D is common tandem wing layout, and front and back wing wing uses
NACA4412 aerofoil profile, mean chord are 0.75m, aspect ratio 26.7.As can be seen that when the after wing 3 being laid out in the present invention
On when setting with certain altitude difference, aircraft can be made integrally to obtain bigger lift resistance ratio.This illustrates the high rear wing support of the present invention
The aerodynamic arrangement of empennage can obtain when rationally designing has more preferably pneumatic efficiency than common tandem rotor aircraft, is able to satisfy
The requirement of high altitude long time aircraft.
Claims (1)
1. using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage, it is characterised in that: described flies
In Hang Qi aerodynamic arrangement, aircraft uses cylindrical cross-section fuselage, the preceding wing of high aspect ratio and rear wing, " V " type tail, hangs down
Tail；Wherein, preceding wing is lower single-blade, is symmetrically mounted on fuselage front half section；" V " type tail is two, after being symmetrically mounted on fuselage
Half section, 45 ° of the upper counterangle；Afterwards wing by " V " tail support in the way of be mounted on the taper of " V " type tail；Vertical fin is mounted on fuselage
Below tail portion；Engine is mounted on above afterbody；The preceding airfoil chord is long to be greater than rear wing chord length；
Preceding trailing edge arrangement wing flap and aileron, aileron is to control aircraft rolling；" V " type tail includes " V " tail stabilization
With " V " the tail vane face for being arranged in rear, " V " tail stabilization is to guarantee aircraft pitching stability, and " V " tail vane face is to control
Aircraft pitching；Vertical fin includes vertical fin stabilization and the rudder for being arranged in rear, and vertical fin stabilization is to guarantee that aircraft navigates
To stability, rudder is to control vehicle yaw；
Afterwards wing " V " tail support by way of on set with difference in height, above set difference in height be 3 times of chord lengths.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710073704.5A CN106828872B (en) | 2017-02-10 | 2017-02-10 | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710073704.5A CN106828872B (en) | 2017-02-10 | 2017-02-10 | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106828872A CN106828872A (en) | 2017-06-13 |
| CN106828872B true CN106828872B (en) | 2019-10-29 |
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| CN201710073704.5A Active CN106828872B (en) | 2017-02-10 | 2017-02-10 | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11273901B2 (en) * | 2018-09-17 | 2022-03-15 | UAVOS Holdings Limited | Method for controlling an aircraft, and an aircraft (variants) |
| CN110104160B (en) * | 2019-04-24 | 2021-01-01 | 北京航空航天大学 | Middle-distance coupling folding double-wing aircraft |
| CN112644686B (en) * | 2020-12-25 | 2023-03-24 | 中国航天空气动力技术研究院 | Tandem wing overall arrangement solar energy unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB563467A (en) * | 1942-03-27 | 1944-08-16 | Phillips & Powis Aircraft Ltd | Improvements in aircraft |
| US4390150A (en) * | 1976-01-13 | 1983-06-28 | The Boeing Company | Tandem wing airplane |
| RU2410289C1 (en) * | 2009-12-14 | 2011-01-27 | Государственное образовательное учреждение высшего профессионального образования Казанский государственный технический университет им. А.Н. Туполева | Two-deck aircraft with rotary wings spaced apart by vertical tail |
| CN204399478U (en) * | 2014-12-04 | 2015-06-17 | 天津全华时代航天科技发展有限公司 | A kind of tandem wing formula unmanned plane |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443344A (en) * | 2014-11-13 | 2015-03-25 | 南京航空航天大学 | Passenger plane with joined-wing configuration |
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2017
- 2017-02-10 CN CN201710073704.5A patent/CN106828872B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB563467A (en) * | 1942-03-27 | 1944-08-16 | Phillips & Powis Aircraft Ltd | Improvements in aircraft |
| US4390150A (en) * | 1976-01-13 | 1983-06-28 | The Boeing Company | Tandem wing airplane |
| RU2410289C1 (en) * | 2009-12-14 | 2011-01-27 | Государственное образовательное учреждение высшего профессионального образования Казанский государственный технический университет им. А.Н. Туполева | Two-deck aircraft with rotary wings spaced apart by vertical tail |
| CN204399478U (en) * | 2014-12-04 | 2015-06-17 | 天津全华时代航天科技发展有限公司 | A kind of tandem wing formula unmanned plane |
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| CN106828872A (en) | 2017-06-13 |
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