CN107226199A - A kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus - Google Patents
A kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus Download PDFInfo
- Publication number
- CN107226199A CN107226199A CN201610170148.9A CN201610170148A CN107226199A CN 107226199 A CN107226199 A CN 107226199A CN 201610170148 A CN201610170148 A CN 201610170148A CN 107226199 A CN107226199 A CN 107226199A
- Authority
- CN
- China
- Prior art keywords
- wing flap
- aircraft
- body wing
- door body
- landing gear
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power-Operated Mechanisms For Wings (AREA)
Abstract
The invention belongs to Horizontal Take-off and Landing hypersonic aircraft technical field, and in particular to a kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus.The present invention includes body, front deck door body wing flap, rear deck door body wing flap and main landing gear.Main landing gear is arranged in aircraft body center of mass, opens aircraft MLG Door is horizontal, and forward and backward hatch door is used as front deck door body wing flap and rear deck door body wing flap after opening.The present invention solves existing level landing hypersonic aircraft and is difficult to while ensureing the technical problem of good high-speed flight performance and good low-speed operations performance, the function of to aircraft aid in control using hatch door is realized, the control ability of aircraft is improved.
Description
Technical field
The invention belongs to Horizontal Take-off and Landing hypersonic aircraft technical field, and in particular to a kind of Horizontal Take-off and Landing flies
Row device undercarriage door/body wing flap integrated apparatus.
Background technology
Horizontal Take-off and Landing hypersonic aircraft is that one kind can be from ground runway horizontal take-off, landing, Neng Gou
The reusable hypersonic aircraft of air suction type of the hypersonic distance flight of near space.Aircraft was both needed
There is good hypersonic flight performance, in addition it is also necessary to preferably low-speed operations performance is taken into account, to meet
The demand of drop and climbing flight state.
Under conditions of flight vehicle aerodynamic profile is certain, low speed aerodynamic characteristic and the high speed pneumatic characteristic of aircraft
Contradict.To ensure good hypersonic aerodynamic characteristic, external HyFly plans at present and X-51A etc.
Mainly by the way of rocket assist, aircraft is accelerated to compared with High Mach number for hypersonic cruise air vehicle,
But do not consider the low-speed performance of aircraft, it is impossible to suitable for Horizontal Take-off and Landing hypersonic aircraft.For water
Flat landing hypersonic aircraft, the U.S., Russia, Germany, Japan etc. in the design process, to take into account
Aircraft low-speed operations performance, adds the aerodynamic lift area of aircraft, but causes therewith to high ultrasound
The adverse effect of fast flight aerodynamics, such as Skylon, Quicksat etc..
At present, in hypersonic aircraft design process, for reduce wave resistance, main wing aerofoil using big sweepback,
The layout of little Zhan strings, position rearward, and uses trailing edge rudder, and control efficiency is low, it is impossible to which the traditional aviation of arrangement flies
The wing flap of row device, it is necessary to by other design increases take off and descent in lift.
Conventional Take-off and Landing frame door design is the mode opened along aircraft to both sides, to reduce what is produced during flight
Aerodynamic drag, considers without other designs.Undercarriage door is designed as along the aircraft side that rear side is opened forward
Formula, can be used as wing flap in aircraft takeoff and landing phases and uses, and increase the lift and control ability of aircraft.
Undercarriage door is closed after aircraft takeoff, and the aeroperformance in high-speed flight stage is not influenceed.
The content of the invention
The technical problem to be solved in the invention is：Horizontal Take-off and Landing hypersonic aircraft is difficult to while ensureing good
Good high-speed flight performance and good low-speed operations performance.
Present invention employs following technical scheme：
The present invention a kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus, including body and
Main landing gear, main landing gear is arranged at below body, in addition to front deck door body wing flap and rear deck door body wing flap；
Main landing gear is arranged in aircraft body center of mass, by aircraft MLG Door to frame head and tail direction
Open, forward and backward hatch door is used as front deck door body wing flap and rear deck door body wing flap after opening.
The front deck door body wing flap and rear deck door body wing flap are opened downwards along aircraft normal direction.
When aircraft is shut down, the front deck door body wing flap is in along before aircraft to opening, rear deck door body
Wing flap is in and opened completely to opening, hatch door along after aircraft, and main landing gear is in stretching state.
During aircraft rolling start, front deck door body wing flap reduces opening angle, and segmentation is deflected down；Afterwards
The segmentation of hatch door body wing flap is deflected down.
During aircraft flight, the main landing gear is packed up, and front deck door body wing flap and rear deck door body wing flap are closed
Close.
In aircraft descent, the front deck door body wing flap and rear deck door body wing flap are opened, by main landing gear
Release；After main landing gear is released, front deck door body wing flap and rear deck door body wing flap improve aircraft lift；Flying
Row device is alightinged run the stage, and the deflection of front deck door body wing flap is slowed down as maximum resistance area, to aircraft
Shut down.
The beneficial effects of the invention are as follows：
(1) a kind of Horizontal Take-off and Landing aircraft landing gear hatch door of the invention/body wing flap integrated design, Neng Goushi
For the hypersonic aircraft of Horizontal Take-off and Landing, while having ensured good low-speed operations performance；
(2) a kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus of the invention, is realized high
Supersonic aircraft landing process lift coefficient improves 5%-12%, improves the pneumatic property of hypersonic flight section
Energy；
(3) a kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus of the invention, realizes profit
To aircraft aid in the function of control with hatch door, improve the control ability of aircraft.
Brief description of the drawings
Fig. 1 is a kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus provided by the present invention
Schematic three dimensional views；
Fig. 2 is forward and backward hatch door body/wing flap lift-rising schematic diagram provided by the present invention；
Fig. 3 is the present invention and conventional Take-off and Landing frame cabin aircraft lift index contrast figure.
In figure：1- bodies, 2- front deck door body wing flap, 3- rear deck door body wing flap, 4- main landing gears.
Embodiment
With reference to the accompanying drawings and examples to a kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap of the present invention
Integrated apparatus is described further.
As shown in figure 1, a kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus of the present invention,
Including body 1, front deck door body wing flap 2, rear deck door body wing flap 3 and main landing gear 4.Main landing gear 4 is arranged
In the center of mass of aircraft body 1, by the hatch door of aircraft main landing gear 4 to aircraft head, tail direction
Open, forward and backward hatch door is used as front deck door body wing flap 2 and rear deck door body wing flap 3 after opening.
As shown in Fig. 2 front deck door body wing flap 2 is opened downwards along aircraft normal direction, with aviation aircraft wing
Trailing edge high lift device is similar, is used as the main accessories of aircraft high lift device；Rear deck door body wing flap 3 is along flight
Device normal direction is opened downwards, and coordinating angle of pitch during aircraft low-speed operations to carry out start, there is provided additional wing liter
Power.
Front deck door body wing flap 2, rear deck door body wing flap 3 and main landing gear 4 take separate start controlling party
Case, the control of front deck door body wing flap 2, rear deck door body wing flap 3 and main landing gear 4 in aircraft different conditions
Scheme is as follows：
(1) when aircraft is shut down, front deck door body wing flap 2 is in along aircraft and axially opens shape to heading
State, rear deck door body wing flap 3 is in along aircraft and axially opens state to tail, and hatch door is opened completely, and master rises and falls
Frame 4 is in stretching state；
(2) during aircraft rolling start, the segmentation of front deck door body wing flap 2 is deflected down, and forms aircraft
Body wing flap；The segmentation of rear deck door body wing flap 3 deflects down to form aircraft body wing flap.The He of front deck door body wing flap 2
The deflection angle of rear deck door body wing flap 3 is adjusted accordingly according to aircraft to lift and the demand of control, it is ensured that
Aircraft has enough take off lift and control abilities；
(3) during aircraft flight, main landing gear 4 is packed up, front deck door body wing flap 2 and the rear deck door body flap
The wing 3 is closed, to ensure that flight vehicle aerodynamic profile is smooth；
(4) in aircraft descent, front deck door body wing flap 2 and rear deck door body wing flap 3 are opened, and will be led
Fall frame 4 to release；After main landing gear 4 is released, front deck door body wing flap 2 and rear deck door body wing flap 3 improve flight
Device lift；The race stage is slided in aircraft lands, front door 2 is deflected to be slowed down as maximum resistance area,
Shut down to aircraft.
As shown in figure 3, having, showing that the present invention can be carried significantly without hatch door body wing flap lift coefficient comparison diagram
High coefficient of lift combined.
The present invention is explained in detail above in conjunction with drawings and examples, but the present invention be not limited to it is above-mentioned
Embodiment, in the knowledge that those of ordinary skill in the art possess, can also not depart from the present invention
Various changes can be made on the premise of objective.The content not being described in detail in the present invention can use existing skill
Art.
Claims (6)
1. a kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus, including body (1) and master
Undercarriage (4), main landing gear is arranged at below body (1), it is characterised in that：Also include the front deck door body flap
The wing (2) and rear deck door body wing flap (3)；Main landing gear (4) is arranged in aircraft body (1) center of mass,
Aircraft main landing gear (4) hatch door is opened to frame head and tail direction, forward and backward hatch door is used as front deck after opening
Door body wing flap (2) and rear deck door body wing flap (3).
2. a kind of Horizontal Take-off and Landing aircraft landing gear hatch door according to claim 1/body wing flap is integrally disguised
Put, it is characterised in that：The front deck door body wing flap (2) and rear deck door body wing flap (3) are along aircraft method
To downward unlatching.
3. a kind of Horizontal Take-off and Landing aircraft landing gear hatch door according to claim 1 or 2/body wing flap one
Makeup is put, it is characterised in that：When aircraft is shut down, the front deck door body wing flap (2) is in along before aircraft
To opening, rear deck door body wing flap (3) is in and opened completely to opening, hatch door along after aircraft,
Main landing gear (4) is in stretching state.
4. a kind of Horizontal Take-off and Landing aircraft landing gear hatch door according to claim 1 or 2/body wing flap one
Makeup is put, it is characterised in that：During aircraft rolling start, front deck door body wing flap (2) reduces opening angle
Degree, segmentation is deflected down；Rear deck door body wing flap (3) segmentation is deflected down.
5. a kind of Horizontal Take-off and Landing aircraft landing gear hatch door according to claim 1 or 2/body wing flap one
Makeup is put, it is characterised in that：During aircraft flight, the main landing gear (4) is packed up, front deck door body
Wing flap (2) and rear deck door body wing flap (3) are closed.
6. a kind of Horizontal Take-off and Landing aircraft landing gear hatch door according to claim 1 or 2/body wing flap one
Makeup is put, it is characterised in that：In aircraft descent, the front deck door body wing flap (2) and rear deck door body
Wing flap (3) is opened, and main landing gear (4) is released；After main landing gear (4) is released, front deck door body wing flap
(2) and rear deck door body wing flap (3) improve aircraft lift；Race stage, front door are slided in aircraft lands
Body wing flap (2) deflection is slowed down as maximum resistance area, is shut down to aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610170148.9A CN107226199A (en) | 2016-03-23 | 2016-03-23 | A kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610170148.9A CN107226199A (en) | 2016-03-23 | 2016-03-23 | A kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107226199A true CN107226199A (en) | 2017-10-03 |
Family
ID=59931549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610170148.9A Pending CN107226199A (en) | 2016-03-23 | 2016-03-23 | A kind of Horizontal Take-off and Landing aircraft landing gear hatch door/body wing flap integrated apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107226199A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220274689A1 (en) * | 2021-02-26 | 2022-09-01 | Airbus Operations Limited | Aircraft system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060032981A1 (en) * | 2004-04-20 | 2006-02-16 | Frederic Fort | Aerodynamic airflow deflector for aircraft landing gear |
| US20060060707A1 (en) * | 2003-04-07 | 2006-03-23 | Chow Leung C | Landing gear door assembly |
| CN101312875A (en) * | 2005-11-21 | 2008-11-26 | 空中客车法国公司 | Landing gear casing provided with a box structure |
| CN103857591A (en) * | 2011-09-30 | 2014-06-11 | 空中客车营运有限公司 | Improved front landing-gear well |
-
2016
- 2016-03-23 CN CN201610170148.9A patent/CN107226199A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060060707A1 (en) * | 2003-04-07 | 2006-03-23 | Chow Leung C | Landing gear door assembly |
| US20060032981A1 (en) * | 2004-04-20 | 2006-02-16 | Frederic Fort | Aerodynamic airflow deflector for aircraft landing gear |
| CN101312875A (en) * | 2005-11-21 | 2008-11-26 | 空中客车法国公司 | Landing gear casing provided with a box structure |
| CN103857591A (en) * | 2011-09-30 | 2014-06-11 | 空中客车营运有限公司 | Improved front landing-gear well |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220274689A1 (en) * | 2021-02-26 | 2022-09-01 | Airbus Operations Limited | Aircraft system |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20171003 |