CN105398565A - Rear wing modification mechanism for flying wing aircraft - Google Patents
Rear wing modification mechanism for flying wing aircraft Download PDFInfo
- Publication number
- CN105398565A CN105398565A CN201510698527.0A CN201510698527A CN105398565A CN 105398565 A CN105398565 A CN 105398565A CN 201510698527 A CN201510698527 A CN 201510698527A CN 105398565 A CN105398565 A CN 105398565A
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- CN
- China
- Prior art keywords
- flying
- wings
- wing aircraft
- empennage
- aerofoil
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
Abstract
The invention relates to a rear wing modification mechanism for a flying wing aircraft, and is used for real-time limiting according to the changes of flight conditions in the flight process. A conventional flying wing aircraft is an aircraft which is not provided with rear wings, and the main parts of a fuselage are hidden in wings. The flying wing layout is the typical representative of integrating the wings and the fuselage. The integrated fuselage can greatly improve the stealth of the aircraft, but the flying wing aircraft lacks of vertical tails, so that the stability is poor when the flying wing aircraft takes off and lands. Under the premise that the stealth function of the flying wings is not reduced, the low-speed flight stability of the flying wings is improved. Modified V-shaped rear wings are additionally arranged for the flying wings, so that when the flying wing aircraft takes off and lands, the V-shaped rear wings are converted, and the low-speed stability of the flying wings is improved. When the flying wing aircraft enters a cruising phase, the rear wings and the wings are integrated, so that the stealth of the flying wing aircraft is improved.
Description
Technical field
The present invention relates to a kind of empennage variant structure for flying wing aircraft, for carrying out spacing in real time according to state of flight change in flight course.
Background technology
Conventional flying wing does not have empennage and the main portion of fuselage is hidden in the aircraft in wing.Flying-wing is the wing Typical Representative integrated with fuselage.Fuselage integration can improve the stealth of aircraft greatly, but flying wing is owing to lacking vertical fin, the less stable when taking off and land.
Variant all-wing aircraft mechanism worldwide there is no the mechanism of similar scheme at present.
Summary of the invention
Technical matters to be solved by this invention is: by providing a kind of empennage variant mechanism, improves the handling of flying wing aircraft.
A kind of empennage variant mechanism for flying wing aircraft, this mechanism can control the part aerofoil of flying wing aircraft as empennage, comprise self-locking mechanism and inclining rotary mechanism, self-locking mechanism comprises angular transducer, rocking arm, silk braid, leading screw, steering wheel and rotating shaft, and inclining rotary mechanism comprises vert aerofoil and rudder face; Rotating shaft is connected with the aerofoil that verts, and the airfoil tail that verts has rudder face; Steering wheel controls the position of silk braid on leading screw by rocking arm, and drive rotating shaft to rotate thus adjust the angle of the aerofoil that verts, the angle of rotating shaft monitored in real time by angular transducer.
Self-locking mechanism adopts the form of leading screw silk braid, and leading screw is connected with inclining rotary mechanism rotating shaft, servo-actuated when steering wheel drives axis of rotation, locks its position when inclining rotary mechanism is parked in a certain tilt angle.
Vee tail tilt angle scope is 0 ° ~ 45 °, and during cruising condition, empennage is 0 °, and empennage and fuselage are fitted, and realizes the stealthy function of complete machine, and when takeoff condition and landing state, empennage is V shape of tail state, increases the stability of all-wing aircraft low-speed operations.
The beneficial effect of the invention: the present invention is intended to verify a kind of innovative form variant all-wing aircraft concept.The stability of all-wing aircraft low-speed operations is increased under the stealthy function prerequisite not reducing all-wing aircraft self.For all-wing aircraft installs additional can variant vee tail, when flying wing aircraft takes off and land, change vee tail, increase all-wing aircraft low-speed stability; When flying wing aircraft enters cruising phase, empennage and wing combine together raising stealth.
Under different aerial mission, unmanned plane adjustable is out of shape, and changes, thus meet the demand of varying environment between conventional fixed-wing layout and Flying-wing.
A) variant all-wing aircraft aerodynamic arrangement: for the unmanned morphing aircraft of innovation, whether new aerodynamic configuration can stabilized flight will be maximum technical barrier, also there is huge risk in same flight course;
B) variant all-wing aircraft empennage mode:
The empennage of variant all-wing aircraft should possess good aeroperformance in conversion process, mutually coordinate realizing physical construction that empennage is out of shape and controller has higher requirement with complete machine aerodynamic configuration simultaneously, can smooth-going control empennage deformation process, monitoring empennage indexing, empennage still can carry out the flight attitude that superposing control ensures all-wing aircraft in transition process;
C) variant flies to play complete or collected works' focus and center-of-gravity position control program: need to rely on empennage start face and the common start in wing flap start face to eliminate the various labile factors caused in empennage variant process for eliminating full machine focal variation;
D) self-locking mechanism: in variant all-wing aircraft change procedure, the change location accuracy requirement for all-wing aircraft is very high, and all-wing aircraft can be locked in a certain position by self-locking device in real time, guarantees the accuracy that all-wing aircraft changes and reliability.
Accompanying drawing explanation
Fig. 1 is empennage variant mechanism birds-eye view;
Fig. 2 is empennage variant mechanism back view;
The attitude of empennage when Fig. 3 is cruising condition;
The attitude of empennage when Fig. 4 is landing state;
Fig. 5 is the left view of Fig. 4.
Detailed description of the invention
As shown in the figure, a kind of empennage variant mechanism for flying wing aircraft, this mechanism can control the part aerofoil of flying wing aircraft as empennage, comprise self-locking mechanism and inclining rotary mechanism, self-locking mechanism comprises angular transducer 1, rocking arm 2, silk braid 3, leading screw 4, steering wheel 5 and rotating shaft 6, and inclining rotary mechanism comprises vert aerofoil 7 and rudder face 8; Rotating shaft 6 is connected with the aerofoil 7 that verts, and aerofoil 7 afterbody that verts has rudder face 8; Steering wheel 5 controls the position of silk braid 3 on leading screw 4 by rocking arm 2, drives rotating shaft 6 rotate thus adjust the angle of the aerofoil 7 that verts; The angle of angular transducer 1 monitoring rotating shaft 6 in real time.
The aerofoil 7 that verts forms vee tail, and tilt angle scope is 0 ° ~ 45 °, and during cruising condition, empennage is 0 °, and empennage and fuselage are fitted; When takeoff condition and landing state, empennage is V shape of tail state
In self-locking mechanism, steering wheel rotates, and drives screw turns, and screw turns drives silk braid to slide, and the slip that rocking arm follows silk braid changes angle, rotating shaft and rocking arm connection along with rocking arm rotation together with rotate, thus realize axis of rotation.
Rotating shaft is connected with inclining rotary mechanism, and axis of rotation drives in inclining rotary mechanism the aerofoil that verts to vert, thus realizes the change of empennage in flight course.
Angular transducer in self-locking mechanism is used for detecting the rotational angle of rotating shaft, and the rudder face in inclining rotary mechanism can play the effect of elevating rudder.
Claims (2)
1. the empennage variant mechanism for flying wing aircraft, it is characterized in that: this mechanism can control the part aerofoil of flying wing aircraft as empennage, comprise self-locking mechanism and inclining rotary mechanism, self-locking mechanism comprises angular transducer (1), rocking arm (2), silk braid (3), leading screw (4), steering wheel (5) and rotating shaft (6), and inclining rotary mechanism comprises the aerofoil that verts (7) and rudder face (8); Rotating shaft (6) is connected with the aerofoil that verts (7), and the aerofoil that verts (7) afterbody has rudder face (8); Steering wheel (5) controls silk braid (3) position on leading screw (4) by rocking arm (2), drives rotating shaft (6) to rotate thus adjusts the angle of aerofoil (7) of verting; The angle of rotating shaft (6) monitored in real time by angular transducer (1).
2. empennage variant mechanism according to claim 1, is characterized in that: the aerofoil that verts (7) forms vee tail, and tilt angle scope is 0 ° ~ 45 °, and during cruising condition, empennage is 0 °, and empennage and fuselage are fitted; When takeoff condition and landing state, empennage is V shape of tail state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510698527.0A CN105398565A (en) | 2015-10-23 | 2015-10-23 | Rear wing modification mechanism for flying wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510698527.0A CN105398565A (en) | 2015-10-23 | 2015-10-23 | Rear wing modification mechanism for flying wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105398565A true CN105398565A (en) | 2016-03-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510698527.0A Pending CN105398565A (en) | 2015-10-23 | 2015-10-23 | Rear wing modification mechanism for flying wing aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN105398565A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857575A (en) * | 2016-04-11 | 2016-08-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Control surface suitable for course autostability and control of high-aspect-ratio flying wing arranging airplane |
| CN107010205A (en) * | 2017-03-30 | 2017-08-04 | 庆安集团有限公司 | A kind of aircraft and its control method with the empennage that can vert |
| CN108100212A (en) * | 2018-01-29 | 2018-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of adaptive response body Flying-wing fighter plane of low aspect ratio |
| CN109987219A (en) * | 2019-03-22 | 2019-07-09 | 湖北三江航天红峰控制有限公司 | A kind of flat compound rudder system of integration |
| CN110626504A (en) * | 2018-06-22 | 2019-12-31 | 庞巴迪公司 | Wing-body integrated airplane |
| CN111874212A (en) * | 2020-08-06 | 2020-11-03 | 西北工业大学 | Practical stall passing v-tail inclination angle self-adaptive control method |
| CN113335503A (en) * | 2021-05-31 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Control method for variable-configuration unmanned aerial vehicle with high cruising overload maneuver |
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| CN101346276A (en) * | 2005-12-29 | 2009-01-14 | 空中客车德国有限公司 | Airfoil for an aircraft and aircraft |
| US20090230240A1 (en) * | 2008-03-13 | 2009-09-17 | The Boeing Company | Aerodynamic fan control effector |
| CN103057695A (en) * | 2013-01-08 | 2013-04-24 | 西北工业大学 | Combined control surface of tailless airplane |
| CN103600835A (en) * | 2013-11-29 | 2014-02-26 | 石家庄飞机工业有限责任公司 | Aerodynamic configuration of bionic flying wing unmanned aerial vehicle (UAV) |
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2015
- 2015-10-23 CN CN201510698527.0A patent/CN105398565A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101346276A (en) * | 2005-12-29 | 2009-01-14 | 空中客车德国有限公司 | Airfoil for an aircraft and aircraft |
| US20090230240A1 (en) * | 2008-03-13 | 2009-09-17 | The Boeing Company | Aerodynamic fan control effector |
| CN103057695A (en) * | 2013-01-08 | 2013-04-24 | 西北工业大学 | Combined control surface of tailless airplane |
| CN103600835A (en) * | 2013-11-29 | 2014-02-26 | 石家庄飞机工业有限责任公司 | Aerodynamic configuration of bionic flying wing unmanned aerial vehicle (UAV) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857575A (en) * | 2016-04-11 | 2016-08-17 | 中国空气动力研究与发展中心计算空气动力研究所 | Control surface suitable for course autostability and control of high-aspect-ratio flying wing arranging airplane |
| CN107010205A (en) * | 2017-03-30 | 2017-08-04 | 庆安集团有限公司 | A kind of aircraft and its control method with the empennage that can vert |
| CN108100212A (en) * | 2018-01-29 | 2018-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of adaptive response body Flying-wing fighter plane of low aspect ratio |
| CN108100212B (en) * | 2018-01-29 | 2023-09-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Small aspect ratio self-adaptive variant flying wing layout fighter |
| CN110626504A (en) * | 2018-06-22 | 2019-12-31 | 庞巴迪公司 | Wing-body integrated airplane |
| CN110626504B (en) * | 2018-06-22 | 2024-03-19 | 庞巴迪公司 | Wing body fusion aircraft |
| CN109987219A (en) * | 2019-03-22 | 2019-07-09 | 湖北三江航天红峰控制有限公司 | A kind of flat compound rudder system of integration |
| CN109987219B (en) * | 2019-03-22 | 2020-11-13 | 湖北三江航天红峰控制有限公司 | Flat type integrated composite rudder system |
| CN111874212A (en) * | 2020-08-06 | 2020-11-03 | 西北工业大学 | Practical stall passing v-tail inclination angle self-adaptive control method |
| CN113335503A (en) * | 2021-05-31 | 2021-09-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Control method for variable-configuration unmanned aerial vehicle with high cruising overload maneuver |
| CN113335503B (en) * | 2021-05-31 | 2024-01-16 | 中国航空工业集团公司沈阳飞机设计研究所 | Control method for variable-configuration unmanned aerial vehicle with large cruising overload maneuver |
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Application publication date: 20160316 |