CN205931235U - Amphibious aircraft with automatic balance fin - Google Patents
Amphibious aircraft with automatic balance fin Download PDFInfo
- Publication number
- CN205931235U CN205931235U CN201620864600.7U CN201620864600U CN205931235U CN 205931235 U CN205931235 U CN 205931235U CN 201620864600 U CN201620864600 U CN 201620864600U CN 205931235 U CN205931235 U CN 205931235U
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- tailplane
- angle
- empennage
- aircraft
- fuselage
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Abstract
The utility model discloses an amphibious aircraft with automatic balance fin, include the fuselage and install the engine on the fuselage, the output shaft of engine has an air screw, air screw is located fuselage rear portion upside, the rear portion upside of fuselage is located be provided with a tailplane in the slipstream that air screw produced, tailplane one side its angle of attack when takeoff phase is adjusted to offsetting the angle of the moment of bowing of engine, on the other hand is at the flight in -process as the balanced trimmer of aircraft every single move. During takeoff phase, tailplane's the angle of attack is adjusted to the angle of the moment of bowing of offsetting the engine, even when the aircraft reaches critical take -off speed like this, the engine is flame -out suddenly, and the pitch attitude of aircraft can not change yet to driver's flight safety has been guaranteed. And when aircraft normal flight in -process aloft, tailplane adjusts to suitable angle, as the balanced trimmer of aircraft every single move, plays the function of gesture trim, guarantees the flight stability of aircraft.
Description
Technical field
This utility model is related to amphibious aircraft technical field, more particularly, to a kind of land and water with autobalance empennage
Amphibian.
Background technology
Amphibious aircraft can takeoff and landing on the road of land, simultaneously also can takeoff and landing on the water.With respect to
For motor power line is higher than the amphibious aircraft of the center of gravity of airplane, when motor power increases or reduces, so draw
Play the trend bowed or come back of amphibious aircraft.If amphibious aircraft is in the critical velocity departed,
Now aircraft engine stops working suddenly, then can lead to the new line behavior that amphibious aircraft producing ratio is stronger, this is because sending out
Motivation is stopped working and is led to originally be led to because nose-down pitching moment that thrust produces suddenly disappears.In general, only great driving warp
Test and the driver that aeroplane performance is very familiar to be only possible to operating aircraft accurately and in time in the unexpected feelings producing new line behavior
Keep appropriate pitch attitude under condition, and be not the driving being very familiar to for some driving experiences deficiencies or to aeroplane performance
For member, the behavior that aircraft comes back suddenly tends to lead to aircraft stall and turns on one's side or fall.
For this reason, applicant carried out beneficial exploration and trial, have found result of the above problems, will be detailed below being situated between
The technical scheme continuing produces under this background.
Utility model content
Technical problem to be solved in the utility model：There is provided a kind of guarantee driver's for the deficiencies in the prior art
The amphibious aircraft with autobalance empennage of flight safety.
The technical problem that this utility model is solved can employ the following technical solutions to realize：
A kind of amphibious aircraft with autobalance empennage, including fuselage and be arranged on electromotor on fuselage,
The output shaft of described electromotor is connected with an air propeller, and described air propeller is located on the upside of described fuselage afterbody, and it is special
Levy and be, be located in the slip-stream that described air propeller produces on the upside of the rear portion of described fuselage and be provided with a tailplane, described
Tailplane one side its angle of attack when takeoff phase adjusts the angle of the nose-down pitching moment to the described electromotor of counteracting, on the other hand
The tab as aircraft pitch balance in flight course.
In a preferred embodiment of the present utility model, horizontal projected area S of described tailplane is by below equation
Determine：
S=(2F* △ H)/(CL*P*L* (VL2–VT2))
Wherein, F is the thrust of electromotor；△ H is the difference in height between motor power line height and the center of gravity of airplane；CL is
The lift coefficient of tailplane, 0 CL≤3；P is atmospheric density at that time；L is between the center of gravity of tailplane and the center of gravity of airplane
Distance；The slip-stream that VL produces for air propeller close to tailplane when air-flow average speed；VT is to take off liftoff speed
Degree.
In a preferred embodiment of the present utility model, described tailplane its angle of attack when takeoff phase adjusts to supporting
The angle of nose-down pitching moment of described electromotor of disappearing refers to：The aerodynamic force that described tailplane is subject to when close to takeoff speed is relatively
Reach between the moment that the moment that the center of gravity of airplane is formed and thrust produced by described electromotor are formed with respect to the center of gravity of airplane
Balance.
In a preferred embodiment of the present utility model, the rear portion of described fuselage is located at the rear of described air propeller
It is provided with an empennage, described tailplane is arranged on described empennage.
In a preferred embodiment of the present utility model, described empennage is vee tail, H type tail or cross tail
One of wing.
In a preferred embodiment of the present utility model, it is provided with for adjusting described water in the driving cabin of described fuselage
The governor motion of the angle of attack angle of the horizontal tail wing.
In a preferred embodiment of the present utility model, described governor motion is using the mode that automatically adjusts or manual regulation
Mode is adjusted to the angle of attack angle of described tailplane.
Due to employing technical scheme as above, the beneficial effects of the utility model are：By on the rear portion of fuselage
Side is located in the slip-stream that air propeller produces and is provided with a tailplane, during takeoff phase, the angle of attack of tailplane adjust to
Offset the angle of the nose-down pitching moment of electromotor, accordingly even when when aircraft reaches critical takeoff speed, electromotor stops working suddenly, aircraft
Pitch attitude also will not change, thus ensure that the flight safety of driver.And work as aircraft in the air in normal flight operations,
Tailplane adjusts to suitable angle, as the tab of aircraft pitch balance, plays the function of attitude trim it is ensured that aircraft
Flight stability.
Brief description
In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, below will be to embodiment
Or in description of the prior art the accompanying drawing of required use be briefly described it should be apparent that, drawings in the following description are only
It is some embodiments of the present utility model, for those of ordinary skill in the art, in the premise not paying creative work
Under, other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is three dimensional structure diagram of the present utility model.
Fig. 2 is top view of the present utility model.
Specific embodiment
In order that technological means, creation characteristic, reached purpose and effect that this utility model is realized are easy to understand, under
Face combines and is specifically illustrating, and this utility model is expanded on further.
Referring to Fig. 1, what in figure was given is a kind of amphibious aircraft with autobalance empennage, including fuselage 100 with
And it is arranged on electromotor 200 on fuselage 100, in the present embodiment, electromotor 200 is arranged on the upside of the rear portion of fuselage 100.Send out
The output shaft 210 of motivation 200 is connected with an air propeller (not shown), after air propeller also is located at fuselage 100
On the upside of portion.It is located in the slip-stream that air propeller produces on the upside of the rear portion of fuselage 100 and be provided with a tailplane 120.
Additionally, the rear being located at air propeller at the rear portion of fuselage 100 is provided with an empennage, in the present embodiment, tail
The wing 110 selects vee tail 110, and vee tail 110 has the first medial surface 111 being oppositely arranged and the second medial surface 112.Level
One end 121 of empennage 120 is connected with the first medial surface 111 of vee tail 110, its other end 122 and the second of vee tail 110
Medial surface 112 connects.Certainly, empennage is not limited to the vee tail structure in the present embodiment, can also select H type tail, ten
Font empennage or the empennage of other configurations.In addition, tailplane 120 may be mounted on empennage it is also possible to pass through individually
Mounting structure is set directly on the upside of the rear portion of fuselage, as long as make tailplane 120 be horizontally set on air propeller producing
Slip-stream in.
It is provided with the governor motion of the angle of attack angle for adjusting tailplane 120 in the driving cabin of fuselage 100.Taking off
During the stage, governor motion is manually or automated manner adjusts the angle of attack of tailplane 120 to counteracting electromotor 200
The angle of nose-down pitching moment, the aerodynamic force that is, tailplane 120 is subject to when close to takeoff speed is formed with respect to the center of gravity of airplane
Balance is reached between the moment that moment and thrust produced by electromotor 200 are formed with respect to the center of gravity of airplane, accordingly even when aircraft
When reaching critical takeoff speed, electromotor stops working suddenly, and the pitch attitude of aircraft also will not change, thus ensure that driver's
Flight safety.When aircraft enters aerial normal flight, governor motion is manually or automated manner adjusts tailplane
120 to suitable angle of attack angle, plays the function of attitude trim it is ensured that the flight stability of aircraft.
Horizontal projected area S of the tailplane 120 of amphibious aircraft of the present utility model projects in the horizontal plane
Area can be determined by calculating, be so able to ensure that accuracy and the safety of tailplane 120.Wherein tailplane
120 horizontal projected area S is determined by below equation (1)：
S=(2F* △ H)/(CL*P*L* (VL2–VT2)) (1)
Wherein, F is the thrust of electromotor；
△ H is the difference in height between motor power line height and the center of gravity of airplane；
CL is the lift coefficient of tailplane, 0 CL≤3, and the value of the lift coefficient CL of tailplane is relative with tailplane
The angle of attack of air-flow is directly proportional, and those skilled in the art can be determined by aerofoil profile data book, simultaneously can also be with reference to it
His some factors are determining；
P is atmospheric density at that time；
L is the distance between center of gravity and center of gravity of airplane of tailplane；
The slip-stream that VL produces for air propeller close to tailplane when air-flow average speed；
VT is to take off flying speed.
Of the present utility model ultimate principle and principal character and of the present utility model advantage have been shown and described above.One's own profession
The technical staff of industry it should be appreciated that this utility model is not restricted to the described embodiments, described in above-described embodiment and description
Principle of the present utility model is simply described, on the premise of without departing from this utility model spirit and scope, this utility model is also
Have various changes and modifications, these changes and improvements both fall within the range of claimed this utility model.This utility model
Claimed scope is by appending claims and its equivalent thereof.
Claims (7)
1. a kind of amphibious aircraft with autobalance empennage, including fuselage and be arranged on electromotor on fuselage, institute
The output shaft stating electromotor is connected with an air propeller, and described air propeller is located on the upside of described fuselage afterbody, its feature
It is, be located in the slip-stream that described air propeller produces on the upside of the rear portion of described fuselage and be provided with a tailplane, described water
Horizontal tail wing one side its angle of attack when takeoff phase adjusts to the angle of the nose-down pitching moment offsetting described electromotor, on the other hand exists
As the tab of aircraft pitch balance in flight course.
2. there is the amphibious aircraft of autobalance empennage as claimed in claim 1 it is characterised in that described tailplane
Horizontal projected area S determined by below equation：
S=(2F* △ H)/(CL*P*L* (VL2–VT2))
Wherein, F is the thrust of electromotor；△ H is the difference in height between motor power line height and the center of gravity of airplane；CL is level
The lift coefficient of empennage, 0 CL≤3；P is atmospheric density at that time；L is the distance between center of gravity and center of gravity of airplane of tailplane；
The slip-stream that VL produces for air propeller close to tailplane when air-flow average speed；VT is to take off flying speed.
3. there is the amphibious aircraft of autobalance empennage as claimed in claim 1 it is characterised in that described tailplane
When takeoff phase, its angle of attack adjusts and refers to the angle of the nose-down pitching moment offsetting described electromotor：Described tailplane is close
The moment that the aerodynamic force being subject to during takeoff speed is formed with respect to the center of gravity of airplane and thrust produced by described electromotor with respect to
Balance is reached between the moment that the center of gravity of airplane is formed.
4. there is the amphibious aircraft of autobalance empennage as claimed any one in claims 1 to 3 it is characterised in that
The rear that the rear portion of described fuselage is located at described air propeller is provided with an empennage, and described tailplane is arranged on described empennage
On.
5. there is the amphibious aircraft of autobalance empennage as claimed in claim 4 it is characterised in that described empennage is V
One of type tail, H type tail or cross type tail.
6. there is the amphibious aircraft of autobalance empennage as claimed in claim 4 it is characterised in that driving of described fuselage
Sail the governor motion being provided with the angle of attack angle for adjusting described tailplane in cabin.
7. there is the amphibious aircraft of autobalance empennage as claimed in claim 6 it is characterised in that described governor motion
Using the mode that automatically adjusts or manual regulative mode, the angle of attack angle of described tailplane is adjusted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620864600.7U CN205931235U (en) | 2016-08-10 | 2016-08-10 | Amphibious aircraft with automatic balance fin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620864600.7U CN205931235U (en) | 2016-08-10 | 2016-08-10 | Amphibious aircraft with automatic balance fin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205931235U true CN205931235U (en) | 2017-02-08 |
Family
ID=57922448
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620864600.7U Withdrawn - After Issue CN205931235U (en) | 2016-08-10 | 2016-08-10 | Amphibious aircraft with automatic balance fin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205931235U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184712A (en) * | 2016-08-10 | 2016-12-07 | 上海牧羽航空科技有限公司 | A kind of amphibious aircraft with autobalance empennage |
| 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 |
| CN107264779A (en) * | 2017-06-23 | 2017-10-20 | 昆明鞘翼科技有限公司 | A kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture |
| CN108674653A (en) * | 2018-05-30 | 2018-10-19 | 佛山市神风航空科技有限公司 | A kind of multi-functional unmanned plane |
-
2016
- 2016-08-10 CN CN201620864600.7U patent/CN205931235U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184712A (en) * | 2016-08-10 | 2016-12-07 | 上海牧羽航空科技有限公司 | A kind of amphibious aircraft with autobalance empennage |
| 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 |
| CN107264779A (en) * | 2017-06-23 | 2017-10-20 | 昆明鞘翼科技有限公司 | A kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture |
| CN108674653A (en) * | 2018-05-30 | 2018-10-19 | 佛山市神风航空科技有限公司 | A kind of multi-functional unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170208 Effective date of abandoning: 20190219 |