CN109319113A - A kind of Concord - Google Patents
A kind of Concord Download PDFInfo
- Publication number
- CN109319113A CN109319113A CN201710639967.8A CN201710639967A CN109319113A CN 109319113 A CN109319113 A CN 109319113A CN 201710639967 A CN201710639967 A CN 201710639967A CN 109319113 A CN109319113 A CN 109319113A
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- CN
- China
- Prior art keywords
- wing
- concord
- engine
- present
- nosing
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
-
- 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
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/40—Varying angle of sweep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/54—Varying in area
- B64C3/546—Varying in area by foldable elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/10—Aircraft characterised by the type or position of power plant of gas-turbine type
- B64D27/12—Aircraft characterised by the type or position of power plant of gas-turbine type within or attached to wing
-
- 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
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
Abstract
The present invention relates to aircraft systems design, in particular to a kind of Concord.Concord includes fuselage, wing and engine, the engine uses variable cycle engine, the afterbody is embedded in the engine, the air intake duct of the engine is located at the abdomen of the aft body, extends along the fuselage axis is parallel to heading.The variable cycle engine technology that Concord of the present invention uses, is decreased obviously the oil consumption rate of supersonic cruise；In addition, the engine installation form of Concord of the present invention, is on the one hand utilized the space of body after-contraction section, aerodynamic drag is reduced, on the other hand makes aircraft wing configuration succinct, is conducive to the lift efficiency for improving aircraft.
Description
Technical field
The present invention relates to aircraft systems design, in particular to a kind of Concord.
Background technique
High subsonic speed passenger plane designing technique is highly developed at present, and 16.5 pneumatic efficiency is difficult to break through.Cruising speed is greater than
The Concord of 2.35Ma can reach higher pneumatic efficiency, and effectively shorten the flight time.First generation supersonic airliner is such as
For consonance with figure -144 because have the shortcomings that oil consumption is high, less economical, noise pollution is big, the service time is very short just to have exited history
Stage.
Summary of the invention
The object of the present invention is to provide a kind of Concords, to solve or mitigate existing for existing Concord extremely
A few problem.
The technical scheme is that
A kind of Concord, including fuselage, wing and engine, the engine use variable cycle engine, institute
It states and is embedded in the afterbody in engine, the air intake duct of the engine is located at the abdomen of the aft body, and edge is parallel to
The fuselage axis extends to heading.
Optionally, the wing includes the inner wing, wing centre section and outer wing at different angles of sweep.
Optionally, the inner wing angle of sweep is 70°~80 °, the wing centre section angle of sweep is 55°~60 °, the outer wing sweepback
Angle is 36°~40 °.
Optionally, the outer wing is that can rotate around the string in wing centre section segmentum laterale portion.
Optionally, the fuselage includes nosing and aft body；
The nosing cross section is circle, and the slenderness ratio of the nosing is greater than 15；
The aft body cross section be ellipse, it is highly equal with the nosing cross-sectional height, width be with
1.44 times of the nosing cross-sectional diameter.
Optionally, the aft body is connect with the wing using blended wing-body mode.
Optionally, the Concord further include:
Center of gravity regulating oil tank is arranged in the afterbody, and center of gravity regulating oil tank is connected to other fuel tanks, and passes through fuel oil
System adjusts the fuel storage position between the center of gravity regulating oil tank and other fuel tanks.
Invention effect:
1) the variable cycle engine technology that Concord of the present invention uses, under keeping the oil consumption rate of supersonic cruise obvious
Drop.
2) the engine installation form of Concord of the present invention, is on the one hand utilized the space of body after-contraction section, subtracts
Small aerodynamic drag, on the other hand makes aircraft wing configuration succinct, is conducive to the lift efficiency for improving aircraft.
Detailed description of the invention
Fig. 1 is the main view of Concord of the present invention；
Fig. 2 is the left view of Concord of the present invention；
Fig. 3 is the bottom view of Concord of the present invention.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
1 to Fig. 3 Concord of the invention is described in further details with reference to the accompanying drawing.
In current Concord, such as consonance Concord is using jet engine, oil consumption rate with
Fighter plane is similar；Figure -144 uses small by-pass ratio turbofan instead, and oil consumption rate slightly reduces.The oil consumption of two class engines
Rate-rate curve variable gradient is very big, and speed is greater than 1.6Ma, and oil consumption rate is increased rapidly with speed increase.This is aircraft economy
Property be deteriorated, the limited major reason of cruising speed.
In addition, aircraft cruise pneumatic efficiency depends on cruise Mach number and cruise lift resistance ratio.Consonance and -144 passenger planes of figure
Aerodynamic arrangement's form is similar, cruises lift resistance ratio between 7.3~7.5.But show by theoretical calculation: by optimizing aircraft
Aerodynamic configuration, reduces cruise wave resistance and component interference drag, and the lift resistance ratio of Concord 2.35Ma cruise can reach 8.5 left sides
It is right.Therefore, the lift resistance ratio of current Concord is to be improved.
Further, by improving cruising speed, it also can be improved aircraft pneumatic efficiency.The cruise of consonance and -144 passenger planes of figure
2.03 or so, cruising speed needs to be further increased Mach number.
For this purpose, the present invention provides a kind of Concords；Concord may include fuselage, wing and start
Machine.
Wherein, engine uses variable cycle engine, is embedded in the enging cabin of afterbody in engine, engine
Air intake duct 1 is located at the abdomen of aft body, extends along fuselage axis is parallel to heading.
The dynamical system of current most of Concord haves the shortcomings that the oil consumption rate of hypersonic speed cruise is too big.
And variable cycle engine can adjust the parameters of engine according to flying speed, make engine oil consumption rate in 2.0 Mach number
1.1kg/ (kgf.h) lower level can be still maintained, and influence of the speed to oil consumption rate is insensitive, when 2.5 Mach number is sent out
The oil consumption rate of motivation does not exceed 1.25kg/ (kgf.h).Aircraft supersonic cruise can be effectively reduced using variable cycle engine
Oil consumption controls take-off weight.
In addition, consonance is mounted below wing with TU-144 passenger plane engine at present, this installation form is conducive to subtract
Small wing loads, it is easy to repair, but the lift efficiency of wing can be also destroyed simultaneously, increase component interference drag and frictional resistance,
Especially it is unfavorable for reducing drag due to shock wave in supersonic flight.To reduce drag due to shock wave and bottom pressure drag, supersonic speed visitor
Machine afterbody contraction section is elongated.Concord of the present invention shrinks more engines by afterbody is embedded in countersunk arrangement
First section can utilize this segment space, be second conducive to the frictional resistance, component interference drag and the drag due to shock wave that reduce aircraft.
Dynamical system uses abdomen intake type, and the air intake duct of engine is located at two main starting and falls between frame.
Therefore, the variable cycle engine technology that Concord of the present invention uses, keeps the oil consumption rate of supersonic cruise obvious
Decline.In addition, the engine installation form of Concord of the present invention, is on the one hand utilized the space of body after-contraction section, subtracts
Small aerodynamic drag, on the other hand makes aircraft wing configuration succinct, is conducive to the lift efficiency for improving aircraft.
In Concord of the present invention, wing, which can according to need, is arranged to a variety of suitable shapes；In the present embodiment, machine
The wing may include the inner wing 21, wing centre section 22 and outer wing 23 at different angles of sweep.And the angle of sweep of inner wing 21, wing centre section 22 and outer wing 23 is same
Sample, which can according to need, carries out suitable setting, and in the present embodiment, preferably 21 angle of sweep of inner wing is 70°~80 °, 22 sweepback of wing centre section
Angle is 55 °~60 °, and 23 angle of sweep of outer wing is 36 °~40 °.Concord of the present invention passes through three sections of change angle of sweep wing configurations
Design, wave resistance when reducing transonic flight when the movement and supersonic flight of pneumatic focus, can make aircraft subsonic speed with
Higher lift resistance ratio is all had when supersonic cruise.
Further, outer wing 23 is that can rotate around the string in 22 segmentum laterale portion of wing centre section, is equivalent to the design of folding outer wing,
Maximum folded angle is 90 °；Wing tip folding can reduce aircraft in the drag due to shock wave of supersonic cruise, while make up aircraft
Directional static stability loss in high-altitude when high-performance cruise, improves the flight quality of aircraft, to guarantee aircraft subsonic speed and surpass
Subsonic cruise all has higher lift resistance ratio, and is conducive to reduce vertical fin area, and the course for improving the cruise of aircraft hypersonic speed is quiet
Stability.When subsonic cruise, outer segment wing and wing main plane are in same string plane.Supersonic cruise, outer segment wing
Perpendicular to wing main plane, reduce aspect ratio, is conducive to reduce drag due to shock wave, while the course static-stability for increasing aircraft is led
Number.
Further, in Concord of the present invention, fuselage includes nosing 31 and aft body 32.Nosing 31 is horizontal
Section is circle, and the slenderness ratio of nosing 31 is greater than 15.32 cross section of aft body is ellipse, height and nosing
31 cross-sectional heights are equal, and width is 1.44 times with 31 cross-sectional diameter of nosing.Also, aft body 32 is adopted with wing
It is connected with blended wing-body mode.
Concord of the present invention is guaranteeing that airframe has by variable diameters body configuration and blended wing-body technology
While sufficiently large slenderness ratio, the available space of fuselage is made full use of, is conducive to the passenger capacity and fuel oil that increase aircraft, improves
The economy of aircraft.
Further, Concord of the present invention further includes center of gravity regulating oil tank 4；Center of gravity regulating oil tank 4 is arranged in fuselage tail
Portion, center of gravity regulating oil tank 4 are connected to other fuel tanks, and by between fuel system center-of-gravity regulating regulating oil tank 4 and other fuel tanks
Fuel storage position, thus achieve the purpose that adjust center of gravity of airplane position.
In addition, Concord of the present invention uses heat-resisting material, it can be improved cruising speed to pneumatic efficiency is improved, subtract
It is significant to increase voyage for small take-off weight.But the temperature that traditional aircraft construction material is able to bear is lower, 2.5 Mach of productions
Raw Aerodynamic Heating temperature is the limit that traditional structural materials are able to bear, therefore uses lightening fire resistant material (such as titanium alloy)
It is the means for improving cruising speed.Also, the noise of supersonic flight and take-off weight are closely related, Concord of the present invention
Take-off weight control is in 130t hereinafter, can improve the noise pollution of Concord.
Concord of the present invention will be illustrated with a specific design example below:
Concord design objective:
Cruising altitude: 180000m, cruising speed 2.5Ma, voyage 8500km, 120 people of passenger capacity, takeoff distance
1500m, velocity of approach 72m/s.
Design procedure is as follows:
1) aircraft wing load and thrust ratio calculate:
Calculate output: wing load: 515.3kg/m2, thrust ratio: 0.3836.
2) aircraft configuration is determined:
According to design performance index, technical solution of the present invention and calculate gained wing area, the Concord of design
Aerodynamic arrangement is as shown in Fig. 1-Fig. 3.
3) cruising condition aerodynamics evaluation:
The aerodynamics evaluation data of the configuration Concord cruising condition are shown in Table 1:
1 cruising altitude aerodynamics evaluation of table
4) engine thrust requirements calculate
Engine quantity: 3, using elongated afterbody contraction section, by engine by being embedded in body in countersunk arrangement
It is interior；Cruising thrust loss: 73%, then required engine sea level maximum thrust is 15.6kN
5) fuel oil quality needed for cruising calculates:
Engine cruises average fuel economy rate as 1.25kg/ (kgf.h), and supersonic cruise is 8 using lift resistance ratio, then required to patrol
Boat fuel oil quality is 47.7t.
6) maximum take-off weight calculates:
Crew: 6；Standby oil: 5500kg；Unavailable oil: 269kg；Empty weight coefficient: 0.463；Cruise fuel oil matter
Coefficient of discharge: 0.383；Then aircraft Maximum Take-off Mass is 124.6t.
In conclusion Concord distribution form of the present invention, aircraft lift resistance ratio is 8 or more, and cruising speed is on 2.5 left sides
The right side, aircraft pneumatic efficiency can effectively improve the economy of aircraft 20 or so.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (7)
1. a kind of Concord, including fuselage, wing and engine, which is characterized in that the engine is using change circulation
Engine is embedded in the afterbody in the engine, and the air intake duct (1) of the engine is located at the abdomen of the aft body
Portion extends along the fuselage axis is parallel to heading.
2. Concord according to claim 1, which is characterized in that the wing includes the inner wing at different angles of sweep
(21), wing centre section (22) and outer wing (23).
3. Concord according to claim 2, which is characterized in that inner wing (21) angle of sweep is 70 °~80 °,
Wing centre section (22) angle of sweep is 55 °~60 °, and outer wing (23) angle of sweep is 36 °~40 °.
4. Concord according to claim 2, which is characterized in that the outer wing (23) is can be around the wing centre section
(22) the string rotation in segmentum laterale portion.
5. Concord according to claim 1, which is characterized in that the fuselage includes nosing (31) and fuselage
Back segment (32)；
Nosing (31) cross section is circle, and the slenderness ratio of the nosing (31) is greater than 15；
Aft body (32) cross section is ellipse, highly equal with the nosing (31) cross-sectional height, width
For 1.44 times with the nosing (31) cross-sectional diameter.
6. Concord according to claim 5, which is characterized in that the aft body (32) and the wing use
Blended wing-body mode connects.
7. Concord according to claim 1, which is characterized in that further include:
Center of gravity regulating oil tank (4) is arranged in the afterbody, and center of gravity regulating oil tank (4) is connected to other fuel tanks, and passes through combustion
Oil system adjusts the fuel storage position between the center of gravity regulating oil tank (4) and other fuel tanks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710639967.8A CN109319113A (en) | 2017-07-31 | 2017-07-31 | A kind of Concord |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710639967.8A CN109319113A (en) | 2017-07-31 | 2017-07-31 | A kind of Concord |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109319113A true CN109319113A (en) | 2019-02-12 |
Family
ID=65245510
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710639967.8A Pending CN109319113A (en) | 2017-07-31 | 2017-07-31 | A kind of Concord |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109319113A (en) |
-
2017
- 2017-07-31 CN CN201710639967.8A patent/CN109319113A/en active Pending
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190212 |
|
| WD01 | Invention patent application deemed withdrawn after publication |