CN206344991U - A kind of aircraft of nose-up pitching moment - Google Patents
A kind of aircraft of nose-up pitching moment Download PDFInfo
- Publication number
- CN206344991U CN206344991U CN201621284482.9U CN201621284482U CN206344991U CN 206344991 U CN206344991 U CN 206344991U CN 201621284482 U CN201621284482 U CN 201621284482U CN 206344991 U CN206344991 U CN 206344991U
- Authority
- CN
- China
- Prior art keywords
- fuselage
- top surface
- tailplane
- aircraft
- minimum point
- 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
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a kind of aircraft of nose-up pitching moment, it is related to aviation aircraft technical field, its structure includes fuselage and empennage, the empennage includes vertical tail and tailplane, vertical tail is arranged on the rear portion of the fuselage, and tailplane is arranged on the top of vertical tail, forms T-shaped empennage, one lug boss is set on the top surface of fore-body, and being seamlessly transitted between the lug boss and fuselage afterbody makes the top surface formation streamline surface of fuselage.Difference in height between the peak and minimum point of fuselage top surface is D, and the difference in height between tailplane upper surface and the minimum point of fuselage top surface is H, 2H ＞ D ＞ 0.3H.The top surface of the utility model fore-body is raised so that flow field is deflected, and the flow field of the upper and lower surface of tailplane is no longer symmetrical, now generates nose-up pitching moment to fuselage, it is ensured that stabilization of the aircraft in flight course.
Description
Technical field
The utility model is related to aviation aircraft technical field, more particularly to a kind of aircraft of nose-up pitching moment.
Background technology
Tailplane abbreviation horizontal tail, installed in fuselage afterbody, is mainly used in keeping the in-flight stability of aircraft and control
The flight attitude of aircraft processed.However, in actual application, tailplane is being designed without considering the influence of fuselage, makes it
Action effect is had a greatly reduced quality.Generally, tailplane is arranged on the afterbody of fuselage, is influenceed by fuselage flow field, often
Weaken the lift that tailplane is produced, produce with pre- interim different effect, cause to take off slowly, climbing ability it is weak, aircraft
Poor anti jamming capability in flight course, is unfavorable for controlling the flight attitude of aircraft and improves the stability of flight.
Utility model content
In order to solve the above-mentioned technical problem, the purpose of this utility model is to provide a kind of aircraft of nose-up pitching moment, and this flies
The tailplane of machine produces a downward power, so as to produce a nose-up pitching moment to fuselage, beneficial to holding aircraft awing
Stability and control aircraft flight attitude.
To achieve these goals, the technical scheme in the invention for solving the technical problem includes：
A kind of aircraft of nose-up pitching moment, including fuselage and empennage, the empennage include vertical tail and tailplane, vertically
Empennage is arranged on the rear portion of the fuselage, and tailplane is arranged on the top of vertical tail, T-shaped empennage is formed, in fore-body
Top surface on a lug boss is set, being seamlessly transitted between the lug boss and fuselage afterbody makes the top surface of fuselage form streamlined
Face.
Fuselage top surface convexes to form streamline surface so that flow field is deflected.The flow field of the upper and lower surface of tailplane
No longer symmetrical, now the flow velocity of lower surface is higher than upper surface, therefore tailplane generates downward lift F, for fuselage,
Here it is nose-up pitching moment.
Further technical scheme is：Difference in height between the peak and minimum point of fuselage top surface is on D, tailplane
Difference in height between the minimum point of surface and fuselage top surface is H, 2H ＞ D ＞ 0.3H.
In the technical solution of the utility model, lug boss refers to being arranged on the part entirely heaved on fuselage top surface,
One point of top highest for the lug boss that the peak of fuselage top surface refers to.
Through studying and experiment is found, only in D ＞ 0.3H, the downward lift F of tailplane just can than more significant, and
With D increase, F also can gradually increase.Meanwhile, for T-shaped empennage, if D>2H, then turbulent flow can occur for fuselage trailing edge
Separation, causes the aeroperformance rapid drawdown of horizontal tail, and then fail.Therefore, it is set as 2H ＞ D ＞ 0.3H, to keeping aircraft in flight
In stationarity and control aircraft flight attitude it is the most favourable.
A kind of preferred technical scheme is：Difference in height between the peak and minimum point of fuselage top surface is D, tailplane
Difference in height between the minimum point of upper surface and fuselage top surface is H, D=0.6H.
Another preferred technical scheme is：Difference in height between the peak and minimum point of fuselage top surface is D, horizontal tail
Difference in height between the minimum point of wing upper surface and fuselage top surface is H, D=1.0H.
Another preferred technical scheme is：Difference in height between the peak and minimum point of fuselage top surface is D, horizontal tail
Difference in height between the minimum point of wing upper surface and fuselage top surface is H, D=1.3H.
The value of difference in height D between the peak and minimum point of fuselage top surface in 0.6H, 1.0H or 1.3H, generation
Nose-up pitching moment is in most suitable scope, and the stability of aircraft flight is preferable.
Further technical scheme is：The minimum point of fuselage top surface is located at the tail end of fuselage.The minimum point position of fuselage top surface
In the rearmost end of fuselage, it is laminar flow in the flowing of aircraft surfaces to make air, it is to avoid turbulization, aircraft is suffered in flight course
Resistance is minimum, and aircraft flight stability is best.
Further technical scheme is：Described tailplane is symmetrical airfoil.Arc above and below the tailplane of symmetrical airfoil
Line is symmetrical, is easy to the calculating to lift F and control, optimal effect of the manipulation is obtained, in addition, symmetrical airfoil is in all aerofoil profiles
Resistance is minimum.
The beneficial effects of the utility model are：
1st, fuselage top surface convexes to form streamline surface so that flow field is deflected, the stream of the upper and lower surface of tailplane
Field is no longer symmetrical, and now the flow velocity of lower surface is higher than upper surface, therefore tailplane generates downward lift F, to fuselage
Speech, generates nose-up pitching moment, and appropriate nose-up pitching moment can make aircraft reach that pitching is balanced, it is ensured that the normal flight of aircraft, increase
The antijamming capability of strong aircraft.
2nd, the difference in height between the peak and minimum point of fuselage top surface is D, tailplane upper surface and fuselage top surface
Difference in height between minimum point is H, 2H ＞ D ＞ 0.3H so that the downward lift F of tailplane than more significant, take off and
The maneuverability and stability of climbing are more preferable.
The utility model includes above beneficial effect, still, implements any product of the present utility model and it is not absolutely required to
Reach all the above beneficial effect simultaneously.
Brief description of the drawings
Fig. 1 is the topology layout figure of the utility model embodiment tailplane and fuselage；
Fig. 2 is the parameter layout of the utility model embodiment tailplane and fuselage.
In figure：1 tailplane, 2 fuselages.
Embodiment
In order to be better understood by the technical solution of the utility model, with reference to Figure of description and specific embodiment to this
Utility model is described further.
Embodiment one：
As shown in figure 1, a kind of aircraft of nose-up pitching moment, including fuselage 2 and empennage, the empennage includes vertical tail and water
The horizontal tail wing 1, vertical tail is arranged on the rear portion of the fuselage 2, and tailplane 1 is arranged on the top of vertical tail, forms T-shaped tail
The wing, setting to seamlessly transit between a lug boss, the rear portion of lug boss and fuselage 2 on the anterior top surface of fuselage 2 makes fuselage 2
Top surface formation streamline surface.
Described tailplane 1 is symmetrical airfoil, and the minimum point of the top surface of fuselage 2 is located at the tail end of fuselage 2.The top surface of fuselage 2
Minimum point be located at fuselage 2 rearmost end, make air aircraft surfaces flowing be laminar flow, it is to avoid turbulization, aircraft fly
Suffered resistance is minimum during row, and aircraft flight stability is best.
The top surface of fuselage 2 convexes to form streamline surface so that flow field is deflected.Arrow represents the top of fuselage 2 in Fig. 1
Flow field, after flow field deflects, the flow field of the upper and lower surface of the tailplane 1 of symmetrical airfoil is no longer symmetrical, now lower surface
Flow velocity be higher than upper surface, therefore tailplane 1 generates downward lift F, for fuselage 2, here it is nose-up pitching moment.
The tailplane of symmetrical airfoil about 1 camber line it is symmetrical, be easy to the calculating to lift F and control, obtain optimal behaviour
Vertical effect, in addition, resistance of the symmetrical airfoil in all aerofoil profiles is minimum.
As shown in Fig. 2 difference in height between the peak and minimum point of the top surface of fuselage 2 is D, the upper surface of tailplane 1 with
Difference in height between the minimum point of the top surface of fuselage 2 is H, D=0.6H.
Through studying and experiment is found, only in D ＞ 0.3H, the downward lift F of tailplane just can than more significant, and
With D increase, F also can gradually increase.Meanwhile, D should be less than 2H, for T-shaped empennage, if D>2H, then fuselage trailing edge
Can occur turbulence separation, cause the aeroperformance rapid drawdown of horizontal tail, and then fail.
Embodiment two：
The present embodiment is repeated no more with the identical feature of embodiment one, and the present embodiment feature different from embodiment one exists
In：Difference in height between the peak and minimum point of the top surface of fuselage 2 is D, and the upper surface of tailplane 1 is minimum with the top surface of fuselage 2
Difference in height between point is H, D=1.0H.
Embodiment three：
The present embodiment is repeated no more with the identical feature of embodiment one, and the present embodiment feature different from embodiment one exists
In：Difference in height between the peak and minimum point of the top surface of fuselage 2 is D, and the upper surface of tailplane 1 is minimum with the top surface of fuselage 2
Difference in height between point is H, D=1.3H.
In the utility model, difference in height D and the upper surface of tailplane 1 between the peak and minimum point of the top surface of fuselage 2
The relation between height difference H between the minimum point of the top surface of fuselage 2 is not limited to several values described in embodiment, and D can also take
More than other values that 0.3H is less than 2H.
Above description is only the preferred embodiment of the application and the explanation to institute's application technology principle.People in the art
Member should be appreciated that utility model scope involved in the application, however it is not limited to the particular combination of above-mentioned technical characteristic
Technical scheme, while should also cover in the case where not departing from utility model design, by above-mentioned technical characteristic or its be equal
Feature be combined formed by other technical schemes.Such as features described above has with (but not limited to) disclosed herein
The technical characteristic for having similar functions carries out technical scheme formed by replacement mutually.
Claims (7)
1. a kind of aircraft of nose-up pitching moment, including fuselage and empennage, the empennage include vertical tail and tailplane, vertical end
The wing is arranged on the rear portion of the fuselage, and tailplane is arranged on the top of vertical tail, forms T-shaped empennage, it is characterized in that, in machine
A lug boss is set on the anterior top surface of body, being seamlessly transitted between the lug boss and fuselage afterbody makes the top surface formation stream of fuselage
Line style face.
2. a kind of aircraft of nose-up pitching moment according to claim 1, it is characterized in that, the peak and minimum point of fuselage top surface
Between difference in height be D, difference in height between tailplane upper surface and the minimum point of fuselage top surface is H, 2H ＞ D ＞ 0.3H.
3. a kind of aircraft of nose-up pitching moment according to claim 2, it is characterized in that, the peak and minimum point of fuselage top surface
Between difference in height be D, difference in height between tailplane upper surface and the minimum point of fuselage top surface is H, D=0.6H.
4. a kind of aircraft of nose-up pitching moment according to claim 2, it is characterized in that, the peak and minimum point of fuselage top surface
Between difference in height be D, difference in height between tailplane upper surface and the minimum point of fuselage top surface is H, D=1.0H.
5. a kind of aircraft of nose-up pitching moment according to claim 2, it is characterized in that, the peak and minimum point of fuselage top surface
Between difference in height be D, difference in height between tailplane upper surface and the minimum point of fuselage top surface is H, D=1.3H.
6. a kind of aircraft of nose-up pitching moment described in any one in Claims 1 to 5, it is characterized in that, fuselage top surface
Minimum point be located at fuselage tail end.
7. a kind of aircraft of nose-up pitching moment described in any one in Claims 1 to 5, it is characterized in that, described water
The horizontal tail wing is symmetrical airfoil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621284482.9U CN206344991U (en) | 2016-11-28 | 2016-11-28 | A kind of aircraft of nose-up pitching moment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621284482.9U CN206344991U (en) | 2016-11-28 | 2016-11-28 | A kind of aircraft of nose-up pitching moment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206344991U true CN206344991U (en) | 2017-07-21 |
Family
ID=59322507
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621284482.9U Active CN206344991U (en) | 2016-11-28 | 2016-11-28 | A kind of aircraft of nose-up pitching moment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206344991U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741851A (en) * | 2016-11-28 | 2017-05-31 | 顺丰科技有限公司 | A kind of aircraft of nose-up pitching moment |
-
2016
- 2016-11-28 CN CN201621284482.9U patent/CN206344991U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741851A (en) * | 2016-11-28 | 2017-05-31 | 顺丰科技有限公司 | A kind of aircraft of nose-up pitching moment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9545993B2 (en) | Aircraft stability and efficient control through induced drag reduction | |
| CN102282070B (en) | Horizontal stabilising surface of an aircraft | |
| US8657226B1 (en) | Efficient control and stall prevention in advanced configuration aircraft | |
| US3411738A (en) | Airfoil tip | |
| US9926071B2 (en) | Spin resistant aircraft configuration | |
| CN103231795A (en) | Corporate aircraft engine upper placement and front swept wing duck type layout | |
| CN208412143U (en) | A kind of aerodynamic arrangement being coupled wing unmanned plane | |
| CN203666968U (en) | Negative dihedral aerofoil winglet structure | |
| CN106945822B (en) | A kind of method and apparatus for the pitching controlling aircraft | |
| Boermans | Research on sailplane aerodynamics at Delft University of Technology | |
| CN206344991U (en) | A kind of aircraft of nose-up pitching moment | |
| US20180105255A1 (en) | Aircraft having supporting fuselage | |
| CN107458583A (en) | A kind of Flying-wing's aircraft course control device based on active Flow Control technology | |
| CN207607638U (en) | Flying-wing's aircraft course control device based on active Flow Control technology | |
| CN106828872B (en) | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage | |
| CN207902734U (en) | A kind of unmanned plane of aerodynamic arrangement | |
| CN106741851A (en) | A kind of aircraft of nose-up pitching moment | |
| CN104554739A (en) | Air inlet lip for improving and adjusting course stability of double-engine wing-body blending tailless configuration | |
| US20110180672A1 (en) | Airplane with aerodynamic stall-prevention layout and pertinent longitudinal stability arrangement | |
| CN106516082A (en) | T-shaped empennage and aircraft with same | |
| EP3551533B1 (en) | Aircraft slat | |
| Liu et al. | Flow patterns and aerodynamic characteristics of a wing-strake configuration | |
| CN206344993U (en) | A kind of T-shaped empennage and the aircraft equipped with T-shaped empennage | |
| JP6452877B1 (en) | High lift, airplane wing, hydrofoil hydrofoil, and airplane engine cowl | |
| CN209366446U (en) | A kind of gyroplane tail structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210729 Address after: 518063 5th floor, block B, building 1, software industry base, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Fengyi Technology (Shenzhen) Co.,Ltd. Address before: 518061 Intersection of Xuefu Road (south) and Baishi Road (east) in Nanshan District, Shenzhen City, Guangdong Province, 6-13 floors, Block B, Shenzhen Software Industry Base Patentee before: SF TECHNOLOGY Co.,Ltd. |
|
| TR01 | Transfer of patent right |