CN206344992U - A kind of tailplane and aircraft of high trim ability - Google Patents
A kind of tailplane and aircraft of high trim ability Download PDFInfo
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- CN206344992U CN206344992U CN201621285933.0U CN201621285933U CN206344992U CN 206344992 U CN206344992 U CN 206344992U CN 201621285933 U CN201621285933 U CN 201621285933U CN 206344992 U CN206344992 U CN 206344992U
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Abstract
The utility model discloses a kind of tailplane and aircraft of high trim ability, belong to aviation aircraft technical field, the tailplane includes tailplane main body, and tailplane main body is axially symmetric structure in X-direction and in the Z-axis direction；In the coordinate plane that X-axis and Z axis are constituted, the section of tailplane main body is in fusiformis；In the coordinate plane that X-axis and Y-axis are constituted, tailplane main body is successively decreased successively from the middle to both ends in the size of Y direction, and the junction of the first curved edge and the second curved edge forms smooth round-corner transition；The aircraft includes above-mentioned tailplane.The utility model is strong to the trim ability of airframe, reduces the resistance of tailplane, and lift is high, and the Elevator stall angle of attack is prevented effectively from the danger that aircraft stall is brought than larger.
Description
Technical field
The utility model is related to aviation aircraft technical field, more particularly to a kind of tailplane of high trim ability and flies
Machine.
Background technology
Tailplane abbreviation horizontal tail, is arranged on fuselage afterbody with horizontal, is one of main big part of aircraft, main to use
In the flight attitude for keeping the in-flight stability of aircraft and control aircraft.The first half of horizontal tail is horizontal stabilizer, later half
Portion is elevator, the distribution of weight of control aircraft rise and fall and trim fuselage.
Aircraft is in flight course, the longitudinal axis and come the referred to as angle of attack of the angle between flowing, and it is critical that wing exceedes some in the angle of attack
After value, lift coefficient can reduce with the increase of the angle of attack, cause stall.When stall, aircraft can produce underriding top out of control
Winnow with a dustpan motion, engine vibrates, driver feels to manipulate abnormal, and stall is a kind of breakneck state, should try one's best and avoid.
However, current tailplane resistance ratios are larger, lift not enough, may result in that stall angle is smaller, and the hidden danger of stall compares
Greatly；In addition, current tailplane is inadequate to the trim ability of fuselage weight, it is unfavorable for maintaining the smooth flight of aircraft.
Utility model content
In order to solve the above-mentioned technical problem, the purpose of this utility model is to provide a kind of tailplane of high trim ability
And aircraft, the tailplane resistance is small, lift is high, trim ability is strong；The aircraft stall angle of attack is difficult stall, is beneficial to than larger
Keep the flight attitude of the in-flight stability of aircraft and control aircraft.
To achieve these goals, the technical scheme in the invention for solving the technical problem includes：
A kind of tailplane of high trim ability, including tailplane main body, the tailplane main body in X-direction and
It is axially symmetric structure in the Z-axis direction；In the coordinate plane that X-axis and Z axis are constituted, the section of tailplane main body is in shuttle
Shape；In the coordinate plane that X-axis and Y-axis are constituted, tailplane main body includes linear edge, the first curved edge being sequentially connected
With the second curved edge, the linear edge is arranged along X-direction, and the first curved edge and the second curved edge are symmetrical,
Tailplane main body is successively decreased successively from the middle to both ends in the size of Y direction, the first curved edge and the second curved edge
Junction forms smooth round-corner transition；
Wherein, X-direction is left and right directions, and Y direction is fore-and-aft direction, and Z-direction is above-below direction.
The layout of axially symmetric structure of the tailplane main body in X-direction and in the Z-axis direction, and the first curved edge
Smooth round-corner transition is formed with the junction of the second curved edge, the resistance of tailplane main body is reduced, its lift is improved,
Improve the mobility of aircraft；The round-corner transition of tailplane main body improves the control efficiency of tailplane.
Further technical scheme is：The tailplane main body is P, tailplane master in the maximum length of X-direction
Body is the numerical value corresponding relation of D, D and P in X-Y coordinate such as table 1 in the maximum length of Y direction：
Table 1：
| The length of X-direction | The length of Y direction |
| 1/8P | 0.4D-0.6D |
| 2/8P | 0.65D-0.75D |
| 3/8P | 0.8D-0.9D |
| 4/8P | D |
| 5/8P | 0.8D-0.9D |
| 6/8P | 0.65D-0.75D |
| 7/8P | 0.4D-0.6D |
| P | 0 |
First curved edge and the second curved edge are designed according to the number range of table 1, and all coordinate points are connected into
SPL is to form the first curved edge and the second curved edge.
It is preferred that technical scheme be：The numerical value of the D is chosen by table 2：
Table 2：
Further technical scheme is：The tailplane main body is P, tailplane master in the maximum length of X-direction
Body is the numerical value corresponding relation of M, M and P in X-Z coordinate systems such as table 3 in the maximum gauge of Z-direction：
Table 3：
| The length of X-direction | The thickness of Z-direction |
| 1/8P | 0.55M-0.7M |
| 2/8P | 0.75M-0.85M |
| 3/8P | 0.85M-0.97M |
| 4/8P | M |
| 5/8P | 0.85M-0.97M |
| 6/8P | 0.75M-0.85M |
| 7/8P | 0.55M-0.7M |
| P | 0 |
The thickness in tailplane main body maximum section of area on the coordinate plane that X-axis and Z axis are constituted according to table 3 number
It is worth scope design, all coordinate points is connected into the profile that SPL forms the section.
It is preferred that technical scheme be：The numerical value of the M is chosen by table 4：
Table 4：
When size of the tailplane main body in X-axis, Y-axis and Z-direction meets the scope of above table, its structure design
Rationally, increase the trim ability of horizontal tail, reduce the resistance of horizontal tail, make its resistance small, lift is big, is prevented effectively from stall event.
Further technical scheme is：The tailplane main body uses naca0015 aerofoil profiles.Naca0015 aerofoil profiles are from side
Face sees to form streamline structure, and leading-edge radius is smaller, and maximum gauge position rearward, can make to keep laminar flow on airfoil surface as far as possible
Flowing, to reduce frictional resistance.
The technical scheme in the invention for solving the technical problem also includes：A kind of aircraft, including above-mentioned high trim ability
Tailplane.
The beneficial effects of the utility model are：
1st, tailplane of the present utility model, the layout of axially symmetric structure in X-direction and in the Z-axis direction, and
The junction of first curved edge and the second curved edge forms smooth round-corner transition, makes the flow field of air-flow more stable, air-flow
Flowed through along the first curved edge and the second curved edge, reduce the resistance of tailplane main body, improve its lift, improve aircraft
Mobility；The round-corner transition of tailplane main body improves the control efficiency of tailplane.
2nd, tailplane of the present utility model, by structural parameters reasonable in design, makes its rational in infrastructure, increase horizontal tail
Trim ability, reduces the resistance of horizontal tail, makes its resistance small, and lift is big, is prevented effectively from stall event.
3rd, aircraft of the present utility model, after employing tailplane of the present utility model, control efficiency is high, resistance is small,
Lift is high, and the aircraft stall angle of attack is difficult stall than larger, and trim ability is strong, beneficial to the holding in-flight stability of aircraft
With the flight attitude of control aircraft.
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 planar structure schematic diagram of the utility model embodiment tailplane in X-Y coordinate plane；
Fig. 2 is the side view of the utility model embodiment tailplane；
Fig. 3 is schematic diagram of the utility model embodiment tailplane in the maximum cross-section of X-Z coordinate planes.
In figure：1 tailplane main body, 2 linear edges, 3 first curved edges, 4 second curved edges.
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, Figure 2 and Figure 3, a kind of tailplane of high trim ability, including tailplane main body 1, the water
Horizontal tail wing main body 1 is axially symmetric structure in X-direction and in the Z-axis direction；Such as Fig. 3, the coordinate constituted in X-axis and Z axis is put down
In face, the section of tailplane main body 1 is in fusiformis；Such as Fig. 1, in the coordinate plane that X-axis and Y-axis are constituted, tailplane main body 1
Including the linear edge 2, the first curved edge 3 and the second curved edge 4 being sequentially connected, the linear edge 2 is along X-direction cloth
Put, the first curved edge 3 and the second curved edge 4 symmetrically, tailplane main body 1 Y direction size from centre to
Two ends are successively decreased successively, and the junction of the first curved edge 3 and the second curved edge 4 forms smooth round-corner transition；
Wherein, X-direction is left and right directions, and Y direction is fore-and-aft direction, and Z-direction is above-below direction.
The layout of axially symmetric structure of the tailplane main body 1 in X-direction and in the Z-axis direction, and the first curved side
The junction of the curved edge 4 of edge 3 and second forms smooth round-corner transition, reduces the resistance of tailplane main body 1, improves it
Lift, improves the mobility of aircraft；The round-corner transition of tailplane main body 1 improves the control efficiency of tailplane.
The tailplane main body 1 is P, maximum of the tailplane main body 1 in Y direction in the maximum length of X-direction
Length is D, and tailplane main body is M in the maximum gauge of Z-direction, and the numerical value corresponding relation of P, D and M in coordinate system is as follows
Table：
First curved edge 3, the second curved edge 4 and tailplane main body 1 are on the coordinate plane that X-axis and Z axis are constituted
All coordinate points are connected into SPL and form first by the thickness in the maximum section of area according to the numerical Design of upper table
The profile of curved edge 3, the second curved edge 4 and above-mentioned section.Meanwhile, such as Fig. 2, the tailplane main body 1 is used
Naca0015 aerofoil profiles, the side view of tailplane main body 1 is defined with this.Naca0015 aerofoil profiles form streamlined from the side
Structure, leading-edge radius is smaller, and maximum gauge position rearward, can make to keep Laminar Flow on airfoil surface as far as possible, to reduce
Frictional resistance.
The aircraft of the present embodiment, includes the tailplane of the present embodiment.
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：In the present embodiment, the numerical value corresponding relation such as following table of P, D and M in coordinate system：
| The length of X-direction | The length of Y direction | The thickness of Z-direction |
| 1/8P | 0.575D | 0.658M |
| 2/8P | 0.728D | 0.811M |
| 3/8P | 0.865D | 0.959M |
| 4/8P | D | M |
| 5/8P | 0.865D | 0.959M |
| 6/8P | 0.728D | 0.811M |
| 7/8P | 0.575D | 0.658M |
| P | 0 | 0 |
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：In the present embodiment, the numerical value corresponding relation such as following table of P, D and M in coordinate system：
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 tailplane of high trim ability, including tailplane main body, it is characterized in that, the tailplane main body is in X
Direction of principal axis and be axially symmetric structure in the Z-axis direction；In the coordinate plane that X-axis and Z axis are constituted, section of tailplane main body
Face is in fusiformis；In the coordinate plane that X-axis and Y-axis are constituted, tailplane main body includes linear edge, the first song being sequentially connected
Line edge and the second curved edge, the linear edge arrange that the first curved edge and the second curved edge are mutual along X-direction
Symmetrically, tailplane main body is successively decreased successively from the middle to both ends in the size of Y direction, the first curved edge and the second curved side
The junction of edge forms smooth round-corner transition；
Wherein, X-direction is left and right directions, and Y direction is fore-and-aft direction, and Z-direction is above-below direction.
2. the tailplane of high trim ability according to claim 1, it is characterized in that, the tailplane main body is in X-axis
The maximum length in direction is P, and tailplane main body is the numerical value of D, D and P in X-Y coordinate in the maximum length of Y direction
Corresponding relation such as table 1：
Table 1：
3. the tailplane of high trim ability according to claim 2, it is characterized in that, the numerical value of the D is chosen by table 2：
Table 2：
4. the tailplane of high trim ability according to claim 1 or 2, it is characterized in that, the tailplane main body is in X
The maximum length of direction of principal axis is P, and tailplane main body is the number of M, M and P in X-Z coordinate systems in the maximum gauge of Z-direction
It is worth corresponding relation such as table 3：
Table 3：
5. the tailplane of high trim ability according to claim 4, it is characterized in that, the numerical value of the M is chosen by table 4：
Table 4：
6. the tailplane of the high trim ability described in any one in claim 1,2,3 or 5, it is characterized in that, institute
Tailplane main body is stated using naca0015 aerofoil profiles.
7. a kind of aircraft, it is characterized in that, include the horizontal tail of the high trim ability described in any one in claim 1~6
The wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621285933.0U CN206344992U (en) | 2016-11-28 | 2016-11-28 | A kind of tailplane and aircraft of high trim ability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621285933.0U CN206344992U (en) | 2016-11-28 | 2016-11-28 | A kind of tailplane and aircraft of high trim ability |
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| Publication Number | Publication Date |
|---|---|
| CN206344992U true CN206344992U (en) | 2017-07-21 |
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| CN201621285933.0U Active CN206344992U (en) | 2016-11-28 | 2016-11-28 | A kind of tailplane and aircraft of high trim ability |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516081A (en) * | 2016-11-28 | 2017-03-22 | 顺丰科技有限公司 | Horizontal tail and aircraft with high trimming capacity |
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2016
- 2016-11-28 CN CN201621285933.0U patent/CN206344992U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516081A (en) * | 2016-11-28 | 2017-03-22 | 顺丰科技有限公司 | Horizontal tail and aircraft with high trimming capacity |
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| TR01 | Transfer of patent right | ||
| 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. |