CN105366049A - Vertical takeoff and landing unmanned aerial vehicle - Google Patents

Vertical takeoff and landing unmanned aerial vehicle Download PDF

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Publication number
CN105366049A
CN105366049A CN201510828381.7A CN201510828381A CN105366049A CN 105366049 A CN105366049 A CN 105366049A CN 201510828381 A CN201510828381 A CN 201510828381A CN 105366049 A CN105366049 A CN 105366049A
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CN
China
Prior art keywords
wing
vuav
fuselage
ducted fan
thrust
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
Application number
CN201510828381.7A
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Chinese (zh)
Inventor
姚宗信
贺集乐
胡婕
岳智敏
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Original Assignee
Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC filed Critical Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority to CN201510828381.7A priority Critical patent/CN105366049A/en
Publication of CN105366049A publication Critical patent/CN105366049A/en
Pending legal-status Critical Current

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Abstract

The invention discloses a vertical takeoff and landing unmanned aerial vehicle including a fuselage, wings, two lifting duct fans, a thrust duct fan, and a balancing duct fan; the wings can be arranged at two sides of the fuselage in a folded manner; the two lifting duct fans are respectively arranged on the root parts of the wings and at two sides of a symmetric axis of the medium rear section of the fuselage; the thrust duct fan is arranged at the tail part of the fuselage; the balancing duct fan is arranged at the head part of the fuselage; in the takeoff, flying and landing processes of the vertical takeoff and landing unmanned aerial vehicle, the balancing duct fan is used for providing the nose-up pitching moment and the nose-down pitching moment required for longitudinal pitching attitude control in a vertical takeoff and landing stage; the thrust duct fan is used for providing a forward thrust force required for level flight; the lifting duct fans are used for providing a vertical lifting force. The vertical takeoff and landing unmanned aerial vehicle can take off and land vertically on a civil ship, and has better flight performance than a helicopter.

Description

A kind of VUAV
Technical field
The present invention relates to unmanned air vehicle technique field, be specifically related to a kind of VUAV.
Background technology
At present, existing rato/hit the fixed-wing unmanned plane netting recovery continuing a journey and load capacity cannot meet actual requirement.Therefore, active demand one class is applicable to the vertical takeoff and landing boat-carrying unmanned plane of civilian naval vessel (about displacement 1-5 kiloton), to complete boat duration, speed is fast, scope is wide supervision and scouting.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one the problems referred to above of prior art.
Summary of the invention
The object of the present invention is to provide a kind of VUAV to overcome or at least alleviate at least one the problems referred to above of the prior art.
For achieving the above object, the invention provides a kind of VUAV, described VUAV comprises: fuselage; Wing, described wing is can be arranged on fuselage both sides by folding mode; Lift ducted fan, described lift ducted fan is two, and is all arranged on wing root, axis of symmetry both sides, fuselage posterior segment; Thrust ducted fan, described thrust ducted fan is arranged on afterbody; Trim ducted fan, described trim ducted fan is arranged on fuselage head; Wherein, described VUAV taking off-flight-descent in, described trim ducted fan for provide the longitudinal pitch attitude of vertical takeoff and landing stage control needed for new line and nose-down pitching moment; Thrust ducted fan for provide flat fly required before propelling thrust; Lift ducted fan is used for providing vertical lift.
Preferably, described fuselage and wing form the pneumatic contour structures of medium aspect ratio wing anury.
Preferably, described fuselage is of a size of 10 meters from head to tail, wing span 15 meters.
Preferably, described wing is ditrigon at the projecting direction perpendicular to described aerofoil surface.
Preferably, the leading edge of described wing is connected by smooth curve with forebody plane projection intrinsic curve, entirety is S wiggle shape.
Preferably, the tip station upset 85 degree of described wing, thus form wing tip flank.
Preferably, described VUAV comprises yaw rudder further, and described yaw rudder is arranged on described wing tip flank.
Preferably, described VUAV comprises vector spout further, the quantity of described vector spout is two, described two vector spouts are arranged in wing lower surface, its distance apart from fuselage datum line accounts for 35% of fuselage length, its distance apart from the leading edge of a wing accounts for 30% of this place's chord length, for providing the rolling moment needed for the lateral attitude control of vertical takeoff and landing stage.
Preferably, described VUAV comprises elevating rudder and aileron further, and described elevating rudder and described aileron are arranged on the trailing edge of wing.
VUAV of the present invention can on civilian naval vessel vertical takeoff and landing, and have and at least double than the better airworthiness of helicopter, cruising speed and time.Solve the persistent surveillance problem of take off landing and the wide area marine environment of boat-carrying small space preferably.
Accompanying drawing explanation
Fig. 1 is the structural representation of VUAV according to a first embodiment of the present invention.
Reference numeral:
1 Fuselage 21 Wing tip
2 Wing 6 Vector spout
3 Lift ducted fan 7 Elevating rudder
4 Thrust ducted fan 8 Aileron
5 Trim ducted fan
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Fig. 1 is the structural representation of VUAV according to a first embodiment of the present invention.
Described VUAV as shown in Figure 1 comprises fuselage 1, wing 2, lift ducted fan 3, thrust ducted fan 4 and trim ducted fan 5.
See Fig. 1, in the present embodiment, wing, 2 are arranged on fuselage 1 both sides in collapsible mode; Lift ducted fan 3 is two, and is all arranged on the axis of symmetry both sides, posterior segment of the root of wing 2, fuselage 1; Thrust ducted fan 4 is arranged on the afterbody of fuselage 1; Trim ducted fan 5 is arranged on the head of fuselage 1; Wherein, VUAV taking off-flight-descent in, trim ducted fan 5 for provide the longitudinal pitch attitude of vertical takeoff and landing stage control needed for new line and nose-down pitching moment; Thrust ducted fan 4 for provide flat fly required before propelling thrust; Lift ducted fan 3 is for providing vertical lift.
In the present embodiment, fuselage 1 and wing 2 form the pneumatic contour structures of medium aspect ratio wing anury.
In the present embodiment, fuselage 1 be of a size of 10 meters from head to tail, wing span 15 meters.Be understandable that, above-mentioned size is only in an embodiment, and the concrete size of the VUAV of the application can sets itself as required.Such as, be of a size of 8 meters from head to tail, wing span 14 meters or other sizes.
In the present embodiment, wing 2 is ditrigon at the projecting direction perpendicular to described aerofoil surface.Particularly, wing is approximate Double delta wing, and its leading edge is connected by smooth curve with forebody plane projection intrinsic curve, entirety is S wiggle shape.
In the present embodiment, the leading edge of wing 2 is connected by smooth curve with forebody plane projection intrinsic curve, entirety is S wiggle shape.
In the present embodiment, wing tip 21 partial switching 85 degree of wing 2, thus form wing tip flank.
In the present embodiment, VUAV comprises yaw rudder further, and yaw rudder is arranged on the flank of wing tip 21.The tip station of described wing turning over about 80-90 degree, form wing tip flank, for providing the flat yawing moment flown needed for stage course attitude stabilization, wherein wing tip flank configuring yaw rudder, for providing the flat yawing moment flown needed for stage course gesture stability
In the present embodiment, VUAV comprises vector spout 6 further, the quantity of vector spout 6 is two, two vector spouts 6 are arranged in wing lower surface, its distance apart from fuselage datum line accounts for 35% of fuselage length, its distance apart from the leading edge of a wing accounts for 30% of this place's chord length, for providing the rolling moment needed for the lateral attitude control of vertical takeoff and landing stage.
In the present embodiment, described VUAV comprises elevating rudder 7 and aileron 8 further, and elevating rudder 7 and aileron 8 are arranged on the trailing edge of wing.
In the present embodiment, elevating rudder and aileron are arranged in the trailing edge of wing, elevating rudder is positioned at inboard root, aileron is positioned at tip outside wing, elevating rudder for provide flat fly stage longitudinal pitch attitude control needed for new line and nose-down pitching moment, aileron for provide flat fly stage lateral attitude control needed for rolling moment; Wing upwards can overturn 120-150 degree, realize wing-folding at folding burbling area place, can conveniently store on applied naval vessel and transport.
Adopt the beneficial effect of above scheme: owing to have employed the Design of Aerodynamic Configuration embedding ducted fan hybrid lift mechanism based on fixed-wing, the vertical tension that unmanned plane both can utilize lift ducted fan to provide realizes vertical and landing takeoff, and the pressure reduction lift that fixed wing can be utilized again to provide obtains higher flying speed and power operation efficiency in the flat stage that flies; Make unmanned plane integrate vertical takeoff and landing and performance during long boat, solve the persistent surveillance problem of take off landing and the wide area marine environment of boat-carrying small space preferably.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.

Claims (9)

1. a VUAV, is characterized in that, described VUAV comprises:
Fuselage (1);
Wing (2), described wing (2) is can be arranged on fuselage (1) both sides by folding mode;
Lift ducted fan (3), described lift ducted fan (3) is two, and is all arranged on the axis of symmetry both sides, posterior segment of the root of wing (2), fuselage (1);
Thrust ducted fan (4), described thrust ducted fan (4) is arranged on the afterbody of fuselage (1);
Trim ducted fan (5), described trim ducted fan (5) is arranged on the head of fuselage (1); Wherein,
Described VUAV taking off-flight-descent in, described trim ducted fan (5) for provide the longitudinal pitch attitude of vertical takeoff and landing stage control needed for new line and nose-down pitching moment; Thrust ducted fan (4) for provide flat fly required before propelling thrust; Lift ducted fan (3) is for providing vertical lift.
2. VUAV as claimed in claim 1, it is characterized in that, described fuselage (1) and wing (2) form the pneumatic contour structures of medium aspect ratio wing anury.
3. VUAV as claimed in claim 2, is characterized in that, described fuselage (1) be of a size of 10 meters from head to tail, wing span 15 meters.
4. VUAV as claimed in claim 3, it is characterized in that, described wing (2) is ditrigon at the projecting direction perpendicular to described aerofoil surface.
5. VUAV as claimed in claim 4, is characterized in that, the leading edge of described wing (2) is connected by smooth curve with forebody plane projection intrinsic curve, entirety is S wiggle shape.
6. VUAV as claimed in claim 5, is characterized in that, wing tip (21) partial switching 85 degree of described wing (2), thus forms wing tip flank.
7. VUAV as claimed in claim 6, it is characterized in that, described VUAV comprises yaw rudder further, and described yaw rudder is arranged on the flank of described wing tip (21).
8. VUAV as claimed in claim 7, it is characterized in that, described VUAV comprises vector spout (6) further, the quantity of described vector spout (6) is two, described two vector spouts (6) are arranged in wing lower surface, its distance apart from fuselage datum line accounts for 35% of fuselage length, its distance apart from the leading edge of a wing accounts for 30% of this place's chord length, for providing the rolling moment needed for the lateral attitude control of vertical takeoff and landing stage.
9. VUAV as claimed in claim 8, it is characterized in that, described VUAV comprises elevating rudder (7) and aileron (8) further, and described elevating rudder (7) and described aileron (8) are arranged on the trailing edge of wing.
CN201510828381.7A 2015-11-24 2015-11-24 Vertical takeoff and landing unmanned aerial vehicle Pending CN105366049A (en)

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106005394A (en) * 2016-07-22 2016-10-12 中国航空工业集团公司西安飞机设计研究所 Rescue aircraft
CN106314789A (en) * 2016-08-31 2017-01-11 张峣 Wing, fixed-wing aircraft and fixed-wing aircraft lifting method
CN106586001A (en) * 2016-11-30 2017-04-26 中国电子科技集团公司第三十八研究所 Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration
CN107539472A (en) * 2017-09-29 2018-01-05 清华大学 A kind of single lift culvert vertical take-off and landing aircraft based on tilting duct
CN107628244A (en) * 2017-09-29 2018-01-26 清华大学 A kind of double lift culvert vertical take-off and landing aircrafts based on tilting duct
CN108033012A (en) * 2017-12-13 2018-05-15 四川宝天智控系统有限公司 VTOL fixed-wings unmanned plane and its fixed wing structure
CN108100253A (en) * 2018-01-26 2018-06-01 广州广鸿航空科技有限公司 A kind of off-loading high lift device applied on unmanned plane
WO2019080442A1 (en) * 2017-10-26 2019-05-02 深圳光启合众科技有限公司 Rotorcraft
CN109911194A (en) * 2018-11-22 2019-06-21 周雯韵 A kind of short distance or vertically taking off and landing flyer using distributed power system

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106005394A (en) * 2016-07-22 2016-10-12 中国航空工业集团公司西安飞机设计研究所 Rescue aircraft
CN106314789A (en) * 2016-08-31 2017-01-11 张峣 Wing, fixed-wing aircraft and fixed-wing aircraft lifting method
CN106586001A (en) * 2016-11-30 2017-04-26 中国电子科技集团公司第三十八研究所 Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration
CN107539472A (en) * 2017-09-29 2018-01-05 清华大学 A kind of single lift culvert vertical take-off and landing aircraft based on tilting duct
CN107628244A (en) * 2017-09-29 2018-01-26 清华大学 A kind of double lift culvert vertical take-off and landing aircrafts based on tilting duct
WO2019080442A1 (en) * 2017-10-26 2019-05-02 深圳光启合众科技有限公司 Rotorcraft
CN108033012A (en) * 2017-12-13 2018-05-15 四川宝天智控系统有限公司 VTOL fixed-wings unmanned plane and its fixed wing structure
CN108100253A (en) * 2018-01-26 2018-06-01 广州广鸿航空科技有限公司 A kind of off-loading high lift device applied on unmanned plane
CN109911194A (en) * 2018-11-22 2019-06-21 周雯韵 A kind of short distance or vertically taking off and landing flyer using distributed power system

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Application publication date: 20160302