CN106672205B - A kind of large-scale change sweepback supersonic aircraft layout - Google Patents
A kind of large-scale change sweepback supersonic aircraft layout Download PDFInfo
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- CN106672205B CN106672205B CN201611161294.1A CN201611161294A CN106672205B CN 106672205 B CN106672205 B CN 106672205B CN 201611161294 A CN201611161294 A CN 201611161294A CN 106672205 B CN106672205 B CN 106672205B
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- rudder face
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- 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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/12—Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention belongs to field of airplane design, are related to a kind of large-scale change sweepback supersonic aircraft layout designs.It includes fuselage (8), nose-gear (12) and 2 main landing gears (13), it is characterised in that: it further includes the wing (1), upper enging cabin (9) and lower enging cabin (10) of 2 symmetrical configurations.The invention proposes a kind of large-scale change sweepback supersonic aircraft layout designs, and realize following comprehensive performance: aircraft is being owned by higher pneumatic efficiency in high speed and low speed, and possessing good control and stability, aircraft weight itself increases less simultaneously.
Description
Technical field
The invention belongs to field of airplane design, are related to a kind of large-scale change sweepback supersonic aircraft layout designs.
Background technique
Existing large size supersonic aircraft layout can be divided mainly into 4 classes:
1, using low aspect ratio wing, such as Concorde supersonic airliner, such layout low speed and landing stage aircraft are pneumatic
Inefficiency；
2, using variable-sweep wing, such as Figure 160 supersonic bomber, such airplane body weight is larger, and wing
Angle of sweep variation brings aircraft focal variation larger, and needing to take appropriate measures controls the distance of the center of gravity of airplane and focus；
3, " pocket knife " is laid out, and wing is pivotally mounted on fuselage by wing root portion, and wing uses small sweepforward when low speed,
Increasing sweepforward, the last complete sweepforward of wing as speed increases wing, rear becomes leading edge, and entire aircraft is in correction of the flank shape triangle,
For high-speed flight.The layout energy body weight is larger, since wing has sweepforward.
4, oblique flying wing is a kind of flying wing type layout that angle of sweep is variable, and the layout left and right is asymmetric, the maneuverability of aircraft
It is extremely difficult with stability Design, Design of Flight Control is required very high.
In conclusion above scheme has respective advantage and disadvantage, be not able to satisfy following comprehensive performance: aircraft is at a high speed and low
Speed is owned by higher pneumatic efficiency, and possessing good control and stability, aircraft weight itself increases less simultaneously.
Summary of the invention
The purpose of the present invention is: a kind of large-scale change sweepback supersonic aircraft layout designs are proposed, to realize following synthesis
Performance: aircraft is owned by higher pneumatic efficiency in high speed and low speed, possesses good control and stability aircraft weight simultaneously itself
Increase little.
The technical scheme is that a kind of large-scale sweepback supersonic aircraft that becomes is laid out, including fuselage 8, nose-gear 12
With 2 main landing gears 13, it is characterised in that: it further includes the wing 1, upper enging cabin 9 and lower enging cabin of 2 symmetrical configurations
10；The wing root of each wing 1 is connect by becoming sweepback mechanism 7 with the rear portion of fuselage 8, in each 1 rear of wing close to wing root
There are 2 inside rudder faces 2 in position, has rudder face 3 among 2 wings in the middle part of each 1 rear of wing, leans in each 1 rear of wing
There is 1 outside rudder face 4 in the position of nearly wing tip, has 1 wing tip rudder face 5 in the tip location of each wing 1, in each wing 1
There is 1 all moving fin 6 on upper surface, close to the position of wing tip, upper enging cabin 9 is connect with the middle and back of 8 upper surface of fuselage, under
Enging cabin 10 is connect with the middle and back of 8 lower surface of fuselage, and nose-gear 12 is mounted on the front of lower enging cabin 10,2 masters
Undercarriage 13 is separately mounted to the middle part of 21 lower surfaces of wing, has head rudder face 11 in the front of fuselage 8, and entire change sweepback is super
The layout bilateral symmetry of velocity of sound aircraft；Main cabin and/or cargo hold, fuel tank and landing gear compartment are disposed in the inside of each wing 1；
When aircraft low-speed operations, so that wing 1 is in the position at 30 °~50 ° of angle of sweep by becoming sweepback mechanism 7, pass through
Manipulation inside rudder face 2, intermediate rudder face 3, outside rudder face 4, tip rudder face 5 and head rudder face 11 control the pitching movement of aircraft, lead to
The yawing rotation that manipulation all moving fin 6 controls aircraft is crossed, manipulation inside rudder face 2, intermediate rudder face 3, outside rudder face 4 and tip are passed through
Rudder face 5 controls the rolling movement of aircraft, passes through manipulation inside rudder face 2, intermediate rudder face 3, outside rudder face 4, tip rudder face 5 and head
Rudder face 11 carries out maneuver load control, reduces wing 1 and becomes the power and torque in sweepback mechanism 7；
When taking off and landing, aircraft low-speed operations, wing setting is 30 °~50 °, and 1 inside rudder face 2 of wing is lower inclined
10 °~40 °, for improving airplane ascensional force, while nose-gear 12 is released from lower enging cabin 10, and main landing gear 13 is from wing 1
Middle part releases；
When aircraft high-speed flight, wing 1 makes wing 1 be in big sweepback Angle Position, angle of sweep is big by becoming sweepback mechanism 7
In 70 °, inside rudder face 2 is locked.Aircraft is controlled by manipulating intermediate rudder face 3, outside rudder face 4, tip rudder face 5 and head rudder face 11
Pitching movement controls the yawing rotation of aircraft by manipulation all moving fin 6, by manipulating intermediate rudder face 3, outside rudder face 4 and point
The rolling movement of the control aircraft of portion's rudder face 5；By manipulate intermediate rudder face 3, outside rudder face 4, tip rudder face 5 and head rudder face 11 into
The control of row maneuver load reduces wing 1 and becomes the power and torque in sweepback mechanism 7.
The invention has the advantages that proposing a kind of large-scale change sweepback supersonic aircraft layout designs, following synthesis is realized
Performance: aircraft is owned by higher pneumatic efficiency in high speed and low speed, possesses good control and stability aircraft weight simultaneously itself
Increase little.
Detailed description of the invention
Schematic top plan view when Fig. 1 is present invention low-speed operations or take-off and landing
Schematic side view when Fig. 2 is present invention low-speed operations or take-off and landing.
Schematic top plan view when Fig. 3 is high-speed flight of the present invention.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings, referring to Fig. 1 to Fig. 3, a kind of large-scale change sweepback ultrasound
Fast aircraft layout, including fuselage 8, nose-gear 12 and 2 main landing gear 13, it is characterised in that: it further includes 2 symmetrical configurations
Wing 1, upper enging cabin 9 and lower enging cabin 10；The rear portion that the wing root of each wing 1 passes through change sweepback mechanism 7 and fuselage 8
Connection has 2 inside rudder faces 2 close to wing location of root in each 1 rear of wing, has 2 machines in the middle part of each 1 rear of wing
Rudder face 3 among the wing has 1 outside rudder face 4 close to the position of wing tip in each 1 rear of wing, in the tip location of each wing 1
There is 1 wing tip rudder face 5, has 1 all moving fin 6, upper enging cabin 9 on the upper surface of each wing 1, close to the position of wing tip
It is connect with the middle and back of 8 upper surface of fuselage, lower enging cabin 10 is connect with the middle and back of 8 lower surface of fuselage, and nose-gear 12 is pacified
Mounted in the front of lower enging cabin 10,2 main landing gears 13 are separately mounted to the middle part of 21 lower surfaces of wing, in fuselage 8
There is head rudder face 11 in front, the entire layout bilateral symmetry for becoming sweepback supersonic aircraft；Visitor is disposed in the inside of each wing 1
Cabin and/or cargo hold, fuel tank and landing gear compartment；
When aircraft low-speed operations, so that wing 1 is in the position at 30 °~50 ° of angle of sweep by becoming sweepback mechanism 7, pass through
Manipulation inside rudder face 2, intermediate rudder face 3, outside rudder face 4, tip rudder face 5 and head rudder face 11 control the pitching movement of aircraft, lead to
The yawing rotation that manipulation all moving fin 6 controls aircraft is crossed, manipulation inside rudder face 2, intermediate rudder face 3, outside rudder face 4 and tip are passed through
Rudder face 5 controls the rolling movement of aircraft, passes through manipulation inside rudder face 2, intermediate rudder face 3, outside rudder face 4, tip rudder face 5 and head
Rudder face 11 carries out maneuver load control, reduces wing 1 and becomes the power and torque in sweepback mechanism 7；
When taking off and landing, aircraft low-speed operations, wing setting is 30 °~50 °, and 1 inside rudder face 2 of wing is lower inclined
10 °~40 °, for improving airplane ascensional force, while nose-gear 12 is released from lower enging cabin 10, and main landing gear 13 is from wing 1
Middle part releases；
When aircraft high-speed flight, wing 1 makes wing 1 be in big sweepback Angle Position, angle of sweep is big by becoming sweepback mechanism 7
In 70 °, inside rudder face 2 is locked.Aircraft is controlled by manipulating intermediate rudder face 3, outside rudder face 4, tip rudder face 5 and head rudder face 11
Pitching movement controls the yawing rotation of aircraft by manipulation all moving fin 6, by manipulating intermediate rudder face 3, outside rudder face 4 and point
The rolling movement of the control aircraft of portion's rudder face 5；By manipulate intermediate rudder face 3, outside rudder face 4, tip rudder face 5 and head rudder face 11 into
The control of row maneuver load reduces wing 1 and becomes the power and torque in sweepback mechanism 7.
The working principle of the invention is:
Aircraft wing lining is equipped with main cabin and/or cargo hold and fuel tank etc., and similar Flying-wing, such design can make to fly
The load that machine loads directly is balanced by airfoil lift, is reduced the moment of flexure of Wing-Body Configurations junction, is mitigated the construction weight of aircraft.
Airframe is smaller, is only used to connect wing and enging cabin, uses bluff body shape in shape, be allowed to also mention
For certain lift.
Aircraft wing rear uses multiple rudder faces, for controlling the posture of aircraft, controls appropriate reduce by maneuver load
Power and torque on wing and change sweepback mechanism can thus reduce wing and become the design strength of sweepback mechanism, also just drop
Low wing and the construction weight for becoming sweepback mechanism.
Aircraft layout bilateral symmetry can obtain ideal maneuverability and stability by rationally designing.
Aircraft wing angle of sweep is variable, to adapt to different flying speeds, so that aircraft be made to be owned by high speed and low speed
Higher pneumatic efficiency.
Rudder face is lower inclined during take-off and landing on the inside of aircraft wing, improves airplane ascensional force.
The all moving fin of aircraft can meet different flight state shipping-direction stability under the premise of not increasing additional weight
With the requirement of maneuverability.
Embodiment
It is proved by engineering calculation and theory analysis, the present invention can achieve the desired results.
Claims (1)
1. a kind of large-scale sweepback supersonic aircraft that becomes is laid out, including fuselage (8), nose-gear (12) and 2 main landing gears (13),
It is characterized by: it further includes the wing (1), upper enging cabin (9) and lower enging cabin (10) of 2 symmetrical configurations；Each machine
The wing root of the wing (1) is connect by becoming sweepback mechanism (7) with the rear portion of fuselage (8), in each wing (1) rear close to the position of wing root
2 inside rudder faces (2) are equipped with, have rudder face (3) among 2 wings in the middle part of each wing (1) rear, in each wing (1)
Rear has 1 outside rudder face (4) close to the position of wing tip, has 1 wing tip rudder face (5) in the tip location of each wing (1),
There is 1 all moving fin (6) on the upper surface of each wing (1), close to the position of wing tip, on upper enging cabin (9) and fuselage (8)
The middle and back on surface connects, and lower enging cabin (10) connect with the middle and back of fuselage (8) lower surface, and nose-gear (12) is mounted on
The front of lower enging cabin (10), 2 main landing gears (13) are separately mounted to the middle part of 2 wing (1) lower surfaces, in fuselage
(8) front has head rudder face (11), the entire layout bilateral symmetry for becoming sweepback supersonic aircraft；In the interior of each wing (1)
Portion is disposed with main cabin and/or cargo hold, fuel tank and landing gear compartment；
When aircraft low-speed operations, so that wing (1) is in the position at 30 °~50 ° of angle of sweep by becoming sweepback mechanism (7), pass through
Manipulation inside rudder face (2), intermediate rudder face (3), outside rudder face (4), tip rudder face (5) and head rudder face (11) control bowing for aircraft
Face upward movement, the yawing rotation of aircraft controlled by manipulation all moving fin (6), by manipulation inside rudder face (2), intermediate rudder face (3),
The rolling movement of outside rudder face (4) and tip rudder face (5) control aircraft, by manipulation inside rudder face (2), intermediate rudder face (3), outer
Side rudder face (4), tip rudder face (5) and head rudder face (11) carry out maneuver load control, reduce wing (1) and become sweepback mechanism
(7) power and torque on；
When taking off and landing, aircraft low-speed operations, wing setting is 30 °~50 °, on the inside of wing (1) under rudder face (2) partially
10 °~40 °, for improving airplane ascensional force, while nose-gear (12) is released from lower enging cabin (10), main landing gear (13) from
It is released in the middle part of wing (1)；
When aircraft high-speed flight, wing (1) makes wing (1) to be in big sweepback Angle Position, angle of sweep by becoming sweepback mechanism (7)
Greater than 70 °, inside rudder face (2) locking, by manipulating intermediate rudder face (3), outside rudder face (4), tip rudder face (5) and head rudder face
(11) Aircraft Pitch Movement is controlled, the yawing rotation of aircraft is controlled by manipulation all moving fin (6), by manipulating intermediate rudder face
(3), the rolling movement of outside rudder face (4) and tip rudder face (5) control aircraft；By manipulating intermediate rudder face (3), outside rudder face
(4), tip rudder face (5) and head rudder face (11) carry out maneuver load control, reduce wing (1) and become on sweepback mechanism (7)
Power and torque.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161294.1A CN106672205B (en) | 2016-12-15 | 2016-12-15 | A kind of large-scale change sweepback supersonic aircraft layout |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161294.1A CN106672205B (en) | 2016-12-15 | 2016-12-15 | A kind of large-scale change sweepback supersonic aircraft layout |
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| Publication Number | Publication Date |
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| CN106672205A CN106672205A (en) | 2017-05-17 |
| CN106672205B true CN106672205B (en) | 2019-08-20 |
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| CN201611161294.1A Active CN106672205B (en) | 2016-12-15 | 2016-12-15 | A kind of large-scale change sweepback supersonic aircraft layout |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108082471B (en) * | 2017-11-20 | 2021-08-17 | 中国航空工业集团公司西安飞机设计研究所 | Variant supersonic aircraft |
| CN109850180B (en) * | 2019-01-23 | 2020-06-30 | 中国人民解放军国防科技大学 | Wide-speed-range full-wave-rider-varying telescopic pneumatic layout design method for aircraft |
| CN109911199B (en) * | 2019-03-28 | 2021-01-12 | 北京航空航天大学 | Wing tip follow-up buoy of variable sweep wing seaplane |
| CN113511333B (en) * | 2021-06-04 | 2023-10-03 | 沈阳航空航天大学 | Variant flying wing type airplane and variant method thereof |
| CN115258129A (en) * | 2022-07-28 | 2022-11-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Three-fuselage aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2915261A (en) * | 1954-01-26 | 1959-12-01 | Wallis Barnes Neville | Aerodyne with wings having variable sweep-back |
| US2922601A (en) * | 1955-06-06 | 1960-01-26 | Vickers Armstrongs Aircraft | Variable sweepback aeroplane |
| CN102381467A (en) * | 2011-08-31 | 2012-03-21 | 中国航天空气动力技术研究院 | Sweep-changing method of variable aircraft wing |
| CN203714171U (en) * | 2013-08-21 | 2014-07-16 | 林仕华 | High-efficient and stable oblique inverter wing |
| CN105173061A (en) * | 2015-08-13 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plane in supersonic speed plane layout |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103538716B (en) * | 2013-08-21 | 2016-09-07 | 林仕华 | A kind of efficient and stable oblique inversion wing |
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2016
- 2016-12-15 CN CN201611161294.1A patent/CN106672205B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2915261A (en) * | 1954-01-26 | 1959-12-01 | Wallis Barnes Neville | Aerodyne with wings having variable sweep-back |
| US2922601A (en) * | 1955-06-06 | 1960-01-26 | Vickers Armstrongs Aircraft | Variable sweepback aeroplane |
| CN102381467A (en) * | 2011-08-31 | 2012-03-21 | 中国航天空气动力技术研究院 | Sweep-changing method of variable aircraft wing |
| CN203714171U (en) * | 2013-08-21 | 2014-07-16 | 林仕华 | High-efficient and stable oblique inverter wing |
| CN105173061A (en) * | 2015-08-13 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plane in supersonic speed plane layout |
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| CN106672205A (en) | 2017-05-17 |
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