CN203528809U - Winged four-duct micro aerial vehicle - Google Patents
Winged four-duct micro aerial vehicle Download PDFInfo
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- CN203528809U CN203528809U CN201320610452.2U CN201320610452U CN203528809U CN 203528809 U CN203528809 U CN 203528809U CN 201320610452 U CN201320610452 U CN 201320610452U CN 203528809 U CN203528809 U CN 203528809U
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- duct
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Abstract
The utility model relates to a winged four-duct micro aerial vehicle. The winged four-duct micro aerial vehicle comprises ducts, a fan, a power system support and a flying wing type inverse Zimmerman wing, two power system supports are arranged on each of the upper surface and the lower surface of the flying wing type inverse Zimmerman wing, one end of each power system support is connected with the duct, and a fan is arranged in the duct. The winged four-duct micro aerial vehicle has the beneficial effects that firstly, the winged four-duct micro aerial vehicle has the advantages of rapidness in cruising, capability of hovering, low noise, autonomy for flight and easiness in control; and secondly, the winged four-duct micro aerial vehicle can realize multi-posture control, and the control method is simple and has good flexibility and the mobility, therefore, the winged four-duct micro aerial vehicle can carry out specific tasks under complex special conditions.
Description
Technical field
The utility model relates to a kind of aircraft, relates in particular to a kind of wing four duct minute vehicles that have.
Background technology
Aspect the Military Application of minute vehicle (MAV, Micro Aerial Vehicle) operational detection under city and MODEL OVER COMPLEX TOPOGRAPHY, there are potentiality widely, become at present countries in the world study hotspot.In early days, the technology feature sizes that U.S. national defense advanced research projects agency proposes MAV is 6-20cm, mission payload is the imagination of 1-18g, but with regard to current technical merit, the mission payload that wants to reach autonomous flight 10km and practical level is housed, therefore the MAV load-carrying capacity that is less than 20cm is inadequate, and US military is given priority to the MAV of 33-41cm in recent years.Aspect military practicality, the minute vehicle of particularly scouting as urban operation, require it to cruise fast, flexible property is good, can hovering, low noise, autonomous flight, be easy to control etc.
Fixed-wing MAV flies before can realizing at a high speed, but does not have the ability of vertical lift and hovering; Duct aircraft is compared with screw propeller aircraft, the in the situation that of same-handed oar diameter and power consumption, can produce larger pulling force.In addition, duct has improved the safety in utilization of aircraft, and has reduced aerodynamics noise.Yet duct aircraft, when front flying, is inhaled in the complex flowfield of stream in the place ahead incoming flow and screw propeller, Airflow Environment is very complicated.In recent years, under its application prospect stimulates, duct aircraft has become an international study hotspot.Such duct aircraft can hover and vertical lift, and the forward direction pulling force that can utilize duct to lean forward to produce flies before realizing helicopter mode low speed, but nose-up pitching moment and resistance increase rapidly with forward flight speed, so they are only applicable to the occasion of hovering and low-speed operations performance.Chinese patent discloses a kind of blended wing-body minute vehicle, and owing to there being trailing edge elevon, for the utility model, it is more difficult that complex structure is controlled.A kind of duct, wing combined micro aircraft are separately disclosed, although have hovering, vertical lift and fast before the function that flies, more control difficulty and the cost of having increased of flight control surface.Not yet find in the market to combine fixed-wing and the two aircraft feature of duct, have fast cruise, maneuverability, can hovering, low noise, autonomous flight and be easy to the advantages such as control a kind ofly have the wing four duct minute vehicles.
Summary of the invention
The purpose of this utility model is to provide a kind of wing four duct minute vehicles that have, this minute vehicle combination fixed-wing and the two aircraft feature of duct, have fast cruise, maneuverability, can hovering, low noise, autonomous flight and be easy to the advantages such as control.
The utility model is achieved like this, it comprises duct, fan, mount for power system, flying wing type inverse zimmerman wing, it is characterized in that: flying wing type inverse zimmerman wing upper and lower surface is respectively installed two mount for power systems, each mount for power system one end connects duct, and fan is equipped with in duct the inside.
Duct described in the utility model and fan form ducted fan power system, by controlling four ducted fan rotating speeds sizes, control force and moments and realize attitude and control, and duct adopts S3016 aerofoil profile, and fan adopts S3010 aerofoil profile.
Attitude mode described in the utility model, comprises hovering, vertical lift, pitching, rolling and driftage etc.
Flying wing type inverse zimmerman wing described in the utility model adopts S3010 aerofoil profile.
Effect of the present utility model is: (1) adopts the graceful aerodynamic arrangement of the anti-Zimmer of flying wing type, there is good aeroperformance, mission payload space is provided to greatest extent, produce enough lift, be conducive to arrange various airborne equipments, (2) have fast cruise, can hovering, low noise, autonomous flight and be easy to control advantage, (3) can realize many attitude controls, control method is simpler, and flexible property is good, is more conducive to complete particular task under complicated specific condition.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Fig. 2 is flying wing type inverse zimmerman wing of the present utility model plane figure schematic diagram.
Fig. 3 is ducted fan structural representation of the present utility model.
Fig. 4 is fan contour structures schematic diagram of the present utility model.
Fig. 5 is mission profile schematic diagram of the present utility model.
Fig. 6 is that schematic diagram is controlled in sporting flying of the present utility model.
Duct 2, fan 3, mount for power system 4, flying wing type inverse zimmerman wing in the drawings, 1.
The specific embodiment
As shown in Figure 1, the utility model is to come like this work and enforcement, it comprises duct 1, fan 2, mount for power system 3 and flying wing type inverse zimmerman wing 4, it is characterized in that: flying wing type inverse zimmerman wing 4 upper and lower surfaces are respectively installed two mount for power systems 3, each mount for power system 3 one end connect duct 1, and fan 2 is equipped with in duct the inside.Described duct 1 and fan 2 form ducted fan power system, and duct 1 adopts S3016 aerofoil profile, and fan 2 and flying wing type inverse zimmerman wing 4 all adopt S3010 aerofoil profile, and body coordinate axle is OXYZ, and ducted fan power system stagger angle is
, its S. A. is parallel with body X-axis.
As shown in Figure 2, Figure 3, Figure 4, b in flying wing type inverse zimmerman wing 4,
,
represent that respectively wing length, leading edge minor axis length and trailing edge minor axis are long, parameter value is
, aspect ratio
, minor axis ratio
, flying wing type inverse zimmerman wing 4 aeroperformance major influence factors are
with
, can obtain optimum pneumatic layout by Optimization Design.Ducted fan power system parameter is: fan 2 diameters
, duct 1 internal diameter
, duct 1 external diameter
, duct 1 height
, blade tip gap
, cone angle
, fan 2 is to duct 1 entrance distance
, population parameter is in Table 1:
Table 1 is novel the wing four duct minute vehicle population parameters
As shown in Figure 5, have the wing four duct minute vehicles can carry out urban operation scouting or the civilian task such as take photo by plane, wherein mainly comprise 11 task legs, it is respectively:
(1) task leg A-B-take off vertically and climb,
(2) task leg B-C-horizontal transition,
(3) task leg C-D-level cruise,
(4) task leg D-E-vertical transition,
(5) task leg E-F-vertically decline,
(6) F-G-hovering of task leg and rolling posture adjustment,
(7) task leg G-H-vertically climb,
(8) task leg H-I-horizontal transition,
(9) task leg I-J-level cruise,
(10) task leg J-K-vertical transition,
(11) task leg K-L-vertical decline and landing.
There are the athletic posture adjustment such as the wing four duct minute vehicles hover, vertical lift, pitching, rolling can complete this task.
As shown in Figure 6, motion attitude control mode realizes by controlling the rotating speed of four ducted fans, and fan 2A is all conter clockwise mutually with fan 2C rotary speed direction, and fan 2B is all cw mutually with fan 2D rotary speed direction, specific as follows:
(1) vertical lift and hovering
(2) luffing
Increase (reducing) fan 2B and fan 2C rotating speed simultaneously, keep fan 2A and fan 2D rotating speed constant, ducted fan thrust produces (bowing) moment that comes back, and can realize luffing.
(3) rolling movement
Rolling movement rotates by fan the reactive torque producing to be realized.Increase (reducing) fan 2A and fan 2C rotating speed simultaneously, keep fan 2A and fan 2C rotating speed constant, produce the reactive torque contrary with fan 2A rotating speed, thereby realize the rolling movement contrary with fan 2A rotating speed, otherwise can realize reciprocal rolling movement.
(4) yawing rotation
Increase (reducing) fan 2C and fan 2D rotating speed simultaneously, keep fan 2A and fan 2B rotating speed constant, ducted fan thrust produces yawing moment, can realize yawing rotation.
Claims (3)
1. one kind has the wing four duct minute vehicles, it comprises duct, fan, mount for power system, flying wing type inverse zimmerman wing, it is characterized in that: flying wing type inverse zimmerman wing upper and lower surface is respectively installed two mount for power systems, each mount for power system one end connects duct, and fan is equipped with in duct the inside.
2. a kind of wing four duct minute vehicles that have according to claim 1, is characterized in that: described duct and fan form ducted fan power system, and duct adopts S3016 aerofoil profile, and fan adopts S3010 aerofoil profile.
3. a kind of wing four duct minute vehicles that have according to claim 1, is characterized in that: described flying wing type inverse zimmerman wing adopts S3010 aerofoil profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320610452.2U CN203528809U (en) | 2013-09-30 | 2013-09-30 | Winged four-duct micro aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320610452.2U CN203528809U (en) | 2013-09-30 | 2013-09-30 | Winged four-duct micro aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203528809U true CN203528809U (en) | 2014-04-09 |
Family
ID=50415053
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320610452.2U Expired - Fee Related CN203528809U (en) | 2013-09-30 | 2013-09-30 | Winged four-duct micro aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203528809U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628115A (en) * | 2016-11-25 | 2017-05-10 | 烟台南山学院 | Four-duct flying-wing type unmanned aerial vehicle |
| CN108263600A (en) * | 2016-12-30 | 2018-07-10 | 深圳光启空间技术有限公司 | Aircraft |
-
2013
- 2013-09-30 CN CN201320610452.2U patent/CN203528809U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628115A (en) * | 2016-11-25 | 2017-05-10 | 烟台南山学院 | Four-duct flying-wing type unmanned aerial vehicle |
| CN108263600A (en) * | 2016-12-30 | 2018-07-10 | 深圳光启空间技术有限公司 | Aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140409 Termination date: 20140930 |
|
| EXPY | Termination of patent right or utility model |