CN206939053U - A kind of sheet aircraft in the back installation fin wing - Google Patents
A kind of sheet aircraft in the back installation fin wing Download PDFInfo
- Publication number
- CN206939053U CN206939053U CN201720737994.4U CN201720737994U CN206939053U CN 206939053 U CN206939053 U CN 206939053U CN 201720737994 U CN201720737994 U CN 201720737994U CN 206939053 U CN206939053 U CN 206939053U
- Authority
- CN
- China
- Prior art keywords
- sheet
- fin wing
- fin
- wing
- fuselage
- 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.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a kind of sheet aircraft in the back installation fin wing, belongs to technical field of aerospace.Including sheet aircraft and the fin wing, the fin wing is arranged on the back of the sheet fuselage of the sheet aircraft, is arranged in pairs and uses, the fin wing being arranged in pairs can equidirectional rotation and change and act power with the relative motion state of air-flow, or opposite direction rotates and changes its assembled state and produce torque, active force or torque put on sheet fuselage, adjust the navigation posture of airborne vehicle.The fin wing is made up of fin wing plate and fin wing axle, and fin wing axle is horizontally disposed with along sheet fuselage length direction, and fin wing plate can be using fin wing axle as axis rotation.The utility model, which the function such as can balance for the hovering translation of sheet aircraft, stable sea and provide, to be aided in or direct driving force, effectively adjustment aircraft navigation posture, and more meet the flight mechanism of sheet aircraft, can be to a certain extent instead of possessing identical above-mentioned function but not meeting the conventional lighter-than-air vehicles structure of sheet aircraft flight.
Description
Technical field
A kind of sheet aircraft in the back installation fin wing is the utility model is related to, belongs to technical field of aerospace.
Background technology
Man-carrying aircraft can be divided into fixed-wing and the major class of rotary wings two, and fixed-wing is common in Horizontal Take-off and Landing airborne vehicle（Such as spray
Gas formula passenger plane）, and rotary wings are common in VTOL airborne vehicle（Such as helicopter）.The technical merit just reached at present is come
Say, Fixed-Wing can be easy to operate with high-speed flight, but need to rely on runway landing.Rotary wing aircraft can vertically rise
Drop, it is not required to rely on runway landing, strong adaptability, but mechanism is lacked of proper care, manipulation is complicated, and flying speed is slow, and fuel efficiency is low.
Using sheet fuselage, can solve VTOL meets horizontal flight two to new vertical landing airborne vehicle again later
Kind of offline mode and caused contradiction, by as the new developing direction of VTOL airborne vehicle.But the special knot of sheet fuselage
The problem of structure brings some new to the gesture stability of airborne vehicle again, is mainly shown as：（1）Laminar character.Sheet fuselage it is special
Structural requirement controlling organization is likewise supplied with the characteristic of sheet.（2）Control moment is big.Relative to existing airborne vehicle, sheet fuselage
Special construction improve stability of the sheet machine airborne vehicle in both direction in length and breadth, it is therefore desirable to pitching moment and yaw forces
Square is bigger.（3）Compatibility.Attitude coutrol mechanism needs equally to be capable of compatible two kinds of flight operating modes of VTOL and horizontal flight
It is required that.（4）Harmony.Sheet machine airborne vehicle has the advantages of inherent flight mechanism is coordinated, and attitude coutrol mechanism can only show this
A little advantages, it is impossible to spoiling the harmony property.（5）Balance.Sheet machine airborne vehicle is using rotor VTOL, it is necessary in hovering phase
Possess balance ability, and horizontal flight then requires without this.Therefore need to design an effectively reliable provisional moment of torsion
Balance control mechanism.（6）Reliability.Sheet machine airborne vehicle has decoupled the flight requirement of mutual restriction, has simple and reliable excellent
Point, attitude coutrol mechanism can only show these advantages, it is impossible to destroy.（7）Intuitive.Sheet machine Aircraft requirements gesture stability machine
Structure is simple and easy to do, control effect is intuitively easy to get.（8）Accuracy.The sensing of sheet machine Aircraft requirements attitude coutrol mechanism is clear and definite,
It can be precisely controlled.Therefore sheet aircraft needs some special structures to improve or make up sheet aircraft sheet
The distinctive technological deficiency of body.
Utility model content
The technical problems to be solved in the utility model is to balance rotor torque, overcoming sheet aircraft speed relatively low
Brought in the flight attitude control brought the problem of low flow velocity air force deficiency with sheet fuselage to the gesture stability of airborne vehicle
The problems such as control moment increases, a kind of sheet aircraft in the back installation fin wing is proposed, do not destroying sheet fuselage sky
Aircraft state is effectively controlled on the premise of aerodynamic characteristics, makes up the technological deficiency of sheet aircraft.
In order to solve the above technical problems, the utility model provides a kind of sheet aircraft in the back installation fin wing,
Including sheet aircraft and the fin wing, the fin wing is arranged on the back of the sheet fuselage of the sheet aircraft（That is fuselage
Top）, be arranged in pairs and use（It is provided with two fin wings）；The fin wing being arranged in pairs can it is equidirectional rotation and change and air-flow
Relative motion state act power, or opposite direction is rotated and changes its assembled state and produce torque, and active force or torque are applied
Sheet fuselage is added on, adjusts the navigation posture of airborne vehicle.When airborne vehicle is in hovering working condition, rotor produces downwash flow,
The equidirectional deflection of the fin wing can produce translational thrust, realize fuselage transverse translation.
The fin wing is made up of fin wing plate and fin wing axle, and fin wing axle is horizontally disposed with along sheet fuselage length direction, fin wing plate
Can by mechanism controls powered by conventional energy, using fin wing axle as axis rotation, allow the fin wing avoid blocking windstream, downwash flow and on
Air-flow is risen, sheet aircraft is fully met and must be compatible with three kinds of road driving, VTOL and horizontal flight for the fin wing
The requirement of operating mode.
The fin wing is large area laminated structure, enough air force controls can be produced in hovering flight using its aerofoil
The navigation posture of airborne vehicle processed, the sheet fuselage of the fin wing and the airborne vehicle are generally aligned in the same plane, and the fin wing plate of the fin wing can be around fin
Wing axle rotates to be closed flat forms one with sheet fuselage.
The fin wing is installed vertically on the back of sheet fuselage, and two fin wings are pacified by boundary's Symmetrical vertical of airborne vehicle rotor shaft
Back loaded on sheet fuselage, former and later two fin wings can be rotated with equidirectional rotation or opposite direction.The fin wing is in sheet fuselage back
It is forward and backward when using equidirectional rotation in pairs, translational thrust can be produced, realizes fuselage transverse translation.The fin wing is in sheet fuselage back
Moment of torsion can be produced during the forward and backward paired rotation using opposite direction, realizes that fuselage rotates or balances antitorque of rotor, by increasing the fin wing
The aerofoil and the mutual distance of the fin wing of plate, the torque of control airborne vehicle navigation posture can be increased.
>=2, the depth-width ratio and length-width ratio of sheet fuselage are generally 3-10 to the depth-width ratio and length-width ratio of the sheet fuselage.
The fin wing plate is Large Rigid structure, to increase stability and enlarging moment.Fin wing plate can use large area
Rigidity thin-wall construction, the contour line of fin wing plate is streamlined.Fin wing plate surface is generally continuous level, or using aircraft wing
Pneumatic curved surface, ensure continuous, the smooth motion of air-flow.
Airborne vehicle is under floating state, and rotor produces downwash flow, when the front and rear fin wing is left-leaning, sheet aircraft
It is traversing to the left；During the equal Right deviation of the front and rear fin wing, sheet aircraft is traversing to the right；When preceding fin wing "Left"-deviationist, skeg wing Right deviation, sheet
Aircraft turns counterclockwise；When preceding fin wing Right deviation, skeg wing "Left"-deviationist, sheet aircraft rotates clockwise；The fin wing is also
Rotor can be utilized to produce downwash flow sheet aircraft is applied to turn left（Or turn right）Torque realize fine setting, it is accurate flat
Weigh antitorque of rotor.Under airborne vehicle level flight condition, the tendency of the fin wing will not interfere to horizontal flight.Airborne vehicle road
Under transport condition, the fin wing, which is toppled over, to be laid flat, and is disturbed with reducing crosswind for caused by airborne vehicle road driving, improves stability.Boat
During pocket emergency landing, the vertical fin wing, to reduce blocking for air upflow, stored with starting the spin of airborne vehicle rotor as early as possible
Energy, improve the security of unpowered forced landing.
The utility model can effectively safeguard sheet fuselage characteristic, can realize two kinds of work of VTOL and horizontal flight
While pattern is effectively compatible, rotor torque balance is provided for sheet airborne vehicle, standard of fuselage rotates, hovering translates, navigation is steady
Allocate the functions such as weighing apparatus.Utility model method more meets global design and the flight mechanism of sheet aircraft, can be certain
Replace possessing identical above-mentioned function in degree but do not meet the conventional lighter-than-air vehicles of sheet fuselage characteristic.Compared with prior art, have
Have mechanism coordinate, simple in construction, cost is cheap, reliability is high, adaptability is good, can effectively overcome sheet aircraft speed
In the relatively low flight attitude control brought the problem of low flow velocity air force deficiency and gesture stability of the sheet fuselage to airborne vehicle
The advantages of the problems such as bringing control moment to increase, it can be widely applied to the fields such as man-carrying aircraft or unmanned plane.
Brief description of the drawings
Fig. 1 is the utility model schematic diagram.
In figure：1- sheet aircrafts, the 2- fin wings, 3- fin wing axles, 4- fin wing plates.
Embodiment
Specific embodiment of the present utility model is further described in detail below in conjunction with the accompanying drawings, it is unreceipted in embodiment
Technology or product, be prior art or can by buy obtain conventional products.
Embodiment 1：As shown in figure 1, this sheet aircraft in the back installation fin wing, including depth-width ratio is 3, length and width
Than the sheet aircraft 1 and the fin wing 2 for 10, the fin wing 2 is arranged on the back of the sheet fuselage of the sheet aircraft 1
I.e. fuselage roof, be arranged in pairs and use（It is provided with two fin wings）；The fin wing 2 being arranged in pairs can it is equidirectional rotation and change
Act power with the relative motion state of air-flow, or opposite direction rotates and changes its assembled state and produce torque, active force or
Torque puts on sheet fuselage, adjusts the navigation posture of airborne vehicle.When airborne vehicle is in hovering working condition, rotor is washed under producing
Air-flow, the deflection of the fin wing can produce translational thrust, realize fuselage transverse translation.The fin wing 2 is made up of fin wing plate 4 and fin wing axle 3, the fin wing
Axle 3 is horizontally disposed with along sheet fuselage length direction, and fin wing plate 4 can be turned by mechanism controls powered by conventional energy with fin wing axle 3 for axle center
It is dynamic, allow the fin wing to avoid blocking windstream, downwash flow and ascending air, fully meeting sheet aircraft must for the fin wing
The requirement of palpus compatible three kinds of road driving, VTOL and horizontal flight operating modes.The fin wing 2 is large area laminated structure, utilizes it
Aerofoil produces the navigation posture of enough air force control airborne vehicles, the sheet of the fin wing 2 and the airborne vehicle in hovering flight
Fuselage is generally aligned in the same plane, and the fin wing plate 4 of the fin wing 2 can rotate to be closed flat around fin wing axle 3 forms one with sheet fuselage.The fin wing 2 hangs down
The straight back for being installed on sheet fuselage, is used, two fin wings 2 claim using airborne vehicle rotor shaft as bound pair in pairs between two parties in sheet fuselage
It is installed vertically on the back of sheet fuselage.The fin wing that uses in pairs is synchronous, when deflecting in the same direction, can produce translational thrust, realize machine
Body transverse translation.The fin wing that uses in pairs is synchronous, when reversely deflecting, and can produce moment of torsion, realize that fuselage rotates or balance rotor is anti-
Moment of torsion.Fin wing plate 4 uses large area rigidity thin-wall construction, to increase stability and enlarging moment；The contour line of fin wing plate 4 is stream
Line style, surface are continuous level, ensure continuous, the smooth motion of air-flow.
Embodiment 2：As shown in figure 1, this sheet aircraft in the back installation fin wing, including depth-width ratio is 10, length
Wide sheet aircraft 1 and the fin wing 2 than for 3, the fin wing 2 are arranged on the back of the body of the sheet fuselage of the sheet aircraft 1
Portion is fuselage roof, is arranged in pairs and uses（It is provided with two fin wings）；The fin wing 2 being arranged in pairs can rotate in same direction and change
Power is acted with the relative motion state of air-flow, or is rotated backward and is changed its assembled state and produce torque, active force or power
Square puts on sheet fuselage, adjusts the navigation posture of airborne vehicle.The fin wing 2 is made up of fin wing plate 4 and fin wing axle 3, and fin wing axle 3 is along piece
Shape fuselage length direction is horizontally disposed with, and fin wing plate 4 can be axis rotation with fin wing axle 3 by mechanism controls powered by conventional energy, allows fin
The wing avoids blocking windstream, downwash flow and ascending air, fully meets sheet aircraft and must be compatible with for the fin wing
The requirement of three kinds of road driving, VTOL and horizontal flight operating modes.The fin wing 2 is large area laminated structure, can utilize its wing
Face produces the navigation posture of enough air force control airborne vehicles, the sheet machine of the fin wing 2 and the airborne vehicle in hovering flight
Body is generally aligned in the same plane, and the fin wing plate 4 of the fin wing 2 can rotate to be closed flat around fin wing axle 3 forms one with sheet fuselage.Use in pairs
Two fin wings 2 claim the back that is installed vertically on sheet fuselage by bound pair of the rotor shaft of airborne vehicle；The two fin wings are synchronous, deflection in the same direction
When, translational thrust can be produced, realizes fuselage transverse translation；The two fin wings are synchronous, when reversely deflecting, and can produce moment of torsion, realize fuselage
Rotate or balance antitorque of rotor.Fin wing plate 4 uses Large Rigid structure, and its contour line is streamlined, surface is continuous flat
Face, ensure continuous, the smooth motion of air-flow.
Embodiment 3：As shown in figure 1, this sheet aircraft in the back installation fin wing, including depth-width ratio is 4, length and width
Than the sheet aircraft 1 and the fin wing 2 for 8, the fin wing 2 is arranged on the back of the sheet fuselage of the sheet aircraft 1
I.e. fuselage roof, be arranged in pairs and use（It is provided with two fin wings）；The fin wing 2 being arranged in pairs can it is equidirectional rotation and change
Act power with the relative motion state of air-flow, or opposite direction rotates and changes its assembled state and produce torque, active force or
Torque puts on sheet fuselage, adjusts the navigation posture of airborne vehicle.When airborne vehicle is in hovering working condition, rotor is washed under producing
Air-flow, the deflection of the fin wing can produce translational thrust, realize fuselage transverse translation.The fin wing 2 is made up of fin wing plate 4 and fin wing axle 3, the fin wing
Axle 3 is horizontally disposed with along sheet fuselage length direction, and fin wing plate 4 can be turned by mechanism controls powered by conventional energy with fin wing axle 3 for axle center
It is dynamic, allow the fin wing to avoid blocking windstream, downwash flow and ascending air, fully meeting sheet aircraft must for the fin wing
The requirement of palpus compatible three kinds of road driving, VTOL and horizontal flight operating modes.The fin wing 2 is large area laminated structure, utilizes it
Aerofoil produces the navigation posture of enough air force control airborne vehicles in hovering flight；The sheet of the fin wing 2 and the airborne vehicle
Fuselage is generally aligned in the same plane, and the fin wing plate 4 of the fin wing 2 can rotate to be closed flat around fin wing axle 3 forms one with sheet fuselage.The fin wing 2 hangs down
The straight back for being installed on sheet fuselage, two fin wings 2 are respectively arranged on airborne vehicle rotor shaft both sides, on sheet fuselage it is forward and backward into
To using, the aerofoil and the mutual distance of the fin wing of fin wing plate 4, the torque of increase control airborne vehicle navigation posture are increased.The two fin wings
When synchronously, deflecting in the same direction, translational thrust can be produced, realizes fuselage transverse translation；The two fin wings are synchronous, when reversely deflecting, and can produce
Moment of torsion, realize that fuselage rotates or balanced antitorque of rotor.Fin wing plate 4 uses Large Rigid thin-wall construction, and its contour line is stream
Line style, the continuous pneumatic curved surface that surface is aircraft wing, ensure continuous, the smooth motion of air-flow.
Technology contents of the present utility model are described above in conjunction with accompanying drawing, but the scope of protection of the utility model is not
It is limited to the content, can also be not depart from this practicality new in one skilled in the relevant art's possessed knowledge
Technology contents of the present utility model are made a variety of changes on the premise of type objective, it is all the spirit and principles of the utility model it
It is interior, any modification, equivalent substitution and improvements done etc., it should be included within the scope of protection of the utility model.
Claims (10)
- A kind of 1. sheet aircraft in the back installation fin wing, it is characterised in that：Including sheet aircraft（1）And fin The wing（2）, the fin wing（2）Installed in the sheet aircraft（1）Sheet fuselage back, be arranged in pairs and use, in pairs The fin wing of setting（2）Can equidirectional rotation and change and act power with the relative motion state of air-flow, or opposite direction is rotated and changed Become its assembled state and produce torque, active force or torque put on sheet fuselage, adjust the navigation posture of airborne vehicle.
- 2. the sheet aircraft according to claim 1 in the back installation fin wing, it is characterised in that：The fin wing （2）By fin wing plate（4）With fin wing axle（3）Form, fin wing axle（3）It is horizontally disposed with along sheet fuselage length direction, fin wing plate（4）Can With fin wing axle（3）For axis rotation.
- 3. the sheet aircraft according to claim 1 or 2 in the back installation fin wing, it is characterised in that：The fin The wing（2）For large area laminated structure, the navigation of enough air force control airborne vehicles is produced in hovering flight using its aerofoil Posture, the fin wing（2）It is generally aligned in the same plane with the sheet fuselage of the airborne vehicle, can be closed flat and form one with sheet fuselage.
- 4. the sheet aircraft according to claim 1 or 2 in the back installation fin wing, it is characterised in that：The fin The wing（2）It is installed vertically on the back of sheet fuselage, two fin wings（2）Claim to be installed vertically on sheet using airborne vehicle rotor shaft as bound pair The back of fuselage, former and later two fin wings（2）It can be rotated with equidirectional rotation or opposite direction.
- 5. the sheet aircraft according to claim 4 in the back installation fin wing, it is characterised in that：The fin wing （2）It is forward and backward in pairs in use, fin wing plate can be increased in sheet fuselage back（4）Aerofoil and the mutual distance of the fin wing, increase control The torque of airborne vehicle navigation posture processed.
- 6. the sheet aircraft according to claim 1 in the back installation fin wing, it is characterised in that：The sheet machine The depth-width ratio and length-width ratio of body are >=2.
- 7. the sheet aircraft according to claim 6 in the back installation fin wing, it is characterised in that：The sheet machine The depth-width ratio and length-width ratio of body are 3-10.
- 8. the sheet aircraft according to claim 1 or 2 in the back installation fin wing, it is characterised in that：The fin Wing plate（4）For Large Rigid structure.
- 9. the sheet aircraft according to claim 1 or 2 in the back installation fin wing, it is characterised in that：The fin Wing plate（4）Large area rigidity thin-wall construction can be used, the contour line of fin wing plate is streamlined.
- 10. the sheet aircraft according to claim 1 or 2 in the back installation fin wing, it is characterised in that：The fin Wing plate（4）Surface is continuous level, or the pneumatic curved surface using aircraft wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720737994.4U CN206939053U (en) | 2017-06-23 | 2017-06-23 | A kind of sheet aircraft in the back installation fin wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720737994.4U CN206939053U (en) | 2017-06-23 | 2017-06-23 | A kind of sheet aircraft in the back installation fin wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206939053U true CN206939053U (en) | 2018-01-30 |
Family
ID=61364850
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720737994.4U Active CN206939053U (en) | 2017-06-23 | 2017-06-23 | A kind of sheet aircraft in the back installation fin wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206939053U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107140182A (en) * | 2017-06-23 | 2017-09-08 | 昆明鞘翼科技有限公司 | A kind of sheet aircraft that the fin wing is installed at back |
-
2017
- 2017-06-23 CN CN201720737994.4U patent/CN206939053U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107140182A (en) * | 2017-06-23 | 2017-09-08 | 昆明鞘翼科技有限公司 | A kind of sheet aircraft that the fin wing is installed at back |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107176286B (en) | Double-duct fan power system-based foldable fixed wing vertical take-off and landing unmanned aerial vehicle | |
| CN207208447U (en) | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems | |
| CN104085532B (en) | A kind of control method of tilting rotor transport plane | |
| CN204895858U (en) | Aerial variant stationary vane four -axis unmanned aerial vehicle of VTOL | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| WO2020083352A1 (en) | Flying car and flying car control method | |
| CN104816824A (en) | Fixed structure type vertical takeoff and landing aircraft based on dual-flight control system and control method for fixed structure type vertical takeoff and landing aircraft | |
| AU2013357155A1 (en) | Convertible aircraft provided with two ducted rotors at the wing tips and with a horizontal fan in the fuselage | |
| CN105059542A (en) | Vertical take-off and landing fixed wing long-endurance air vehicle | |
| WO2023000571A1 (en) | Flying car | |
| CN106218887A (en) | A kind of vertically taking off and landing flyer of distributed-power device layout | |
| CN206511122U (en) | A kind of VTOL Fixed Wing AirVehicle | |
| CN106828918A (en) | A kind of Three-wing-surface vertically taking off and landing flyer | |
| CN108501639A (en) | A kind of hovercar | |
| CN110282117A (en) | A kind of city VTOL aircraft having wing-folding storage function | |
| CN107140208A (en) | STOL top load multiaxis fans wing unmanned plane | |
| CN103523223B (en) | Transverse course control system and transverse course control method for flying wing configuration | |
| CN108045569A (en) | A kind of semi-ring rotor aircraft | |
| CN208775003U (en) | A kind of tilting wing unmanned plane with complex pneumatic rudder face | |
| CN107140182A (en) | A kind of sheet aircraft that the fin wing is installed at back | |
| CN206939053U (en) | A kind of sheet aircraft in the back installation fin wing | |
| CN206552261U (en) | A kind of tilting rotor wing unmanned aerial vehicle | |
| CN103407444B (en) | Based on the Fixed Wing AirVehicle of the landing technology that hovers | |
| CN108423167A (en) | A kind of double control system aircraft | |
| CN105460202A (en) | Variable-wing unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |