CN106697261B - A kind of aircraft double freedom control surface - Google Patents
A kind of aircraft double freedom control surface Download PDFInfo
- Publication number
- CN106697261B CN106697261B CN201611024000.0A CN201611024000A CN106697261B CN 106697261 B CN106697261 B CN 106697261B CN 201611024000 A CN201611024000 A CN 201611024000A CN 106697261 B CN106697261 B CN 106697261B
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- rotating shaft
- transverse
- axial
- control surface
- steering engine
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- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 abstract 3
- 230000000149 penetrating effect Effects 0.000 description 6
- 238000005096 rolling process Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a kind of aircraft double freedom control surfaces, comprising: T shape shaft, axial rocker arm, lateral steering engine, cross-brace bearing, control surface, steering engine cable, lateral rocker arm, axial spring bearing, pedestal and axial steering engine；Wherein, the T shape shaft includes lateral shaft and longitudinal shaft, wherein lateral shaft is connected with longitudinal shaft, wherein the longitudinal direction shaft is located in the pedestal；The longitudinal direction shaft is connected by axial spring bearing with pedestal；The control surface is connected by the cross-brace bearing with the lateral shaft.The present invention solves the problems, such as that existing control surface control moment is single, realizes that axially and transversely double freedom rotates control surface around aircraft.
Description
Technical Field
The invention relates to the field of overall design of aircrafts, in particular to a double-freedom-degree control surface of an aircraft.
Background
Conventional aircraft often employ multiple control surfaces to generate forces and moments to maintain or change the attitude of the aircraft. Generally, the control surface is limited by the structural form, the direction of the generated moment is different for the control surface at different positions, and the finished control function is also different. Advanced aircraft aerodynamic configuration has cancelled and has been unfavorable for a plurality of control surfaces of stealthy, has highly fused appearance usually, and radar scattering cross-section has obtained and has reduced by a wide margin, but requires the aircraft to have the novel control surface or the thrust vector device of ideal control efficiency to realize the good maneuverability of aircraft simultaneously, and current technical scheme adopts the mode of fracture formula rudder/wingtip rudder and multiunit elevon combination.
Disclosure of Invention
The technical problem solved by the invention is as follows: compared with the prior art, the double-freedom-degree control surface of the aircraft is provided, the problem that the control moment of the existing control surface is single is solved, and the control surface rotates around the axial direction and the transverse double-freedom-degree of the aircraft.
The purpose of the invention is realized by the following technical scheme: a two degree-of-freedom control surface for an aircraft, comprising: the device comprises a T-shaped rotating shaft, an axial rocker arm, a transverse steering engine, a transverse supporting bearing, a control surface, a steering engine cable, a transverse rocker arm, an axial supporting bearing, a base and an axial steering engine; the T-shaped rotating shaft comprises a transverse rotating shaft and a longitudinal rotating shaft, wherein the transverse rotating shaft is connected with the longitudinal rotating shaft, and the longitudinal rotating shaft is positioned in the base; the longitudinal rotating shaft is connected with the base through an axial supporting bearing; the control surface is connected with the transverse rotating shaft through the transverse supporting bearing; the longitudinal rotating shaft is connected with an axial steering engine through the axial rocker arm, and the axial steering engine is arranged in the base; the transverse rotating shaft is connected with a transverse steering engine through the transverse rocker arm, and the transverse steering engine is connected with the control surface; the steering engine cable is arranged in the first cavity in a penetrating mode and the second cavity in a penetrating mode and is connected with the transverse steering engine.
In the double-degree-of-freedom control surface of the aircraft, the axial rocker arm is sleeved on the longitudinal rotating shaft, wherein the axial rocker arm is provided with a through hole, the longitudinal rotating shaft is provided with another through hole corresponding to the through hole of the axial rocker arm, and the axial rocker arm is fixedly connected with the longitudinal rotating shaft by a pin penetrating through the through hole of the axial rocker arm and the through hole of the longitudinal rotating shaft.
In the double-degree-of-freedom control surface of the aircraft, the transverse rocker arm is sleeved on the transverse rotating shaft, wherein the transverse rocker arm is provided with a through hole, the transverse rotating shaft is provided with another through hole corresponding to the through hole of the transverse rocker arm, and the transverse rocker arm is fixedly connected with the transverse rotating shaft by a pin penetrating through the through hole of the transverse rocker arm and the through hole of the transverse rotating shaft.
In the aircraft two-degree-of-freedom control surface, the axial rocker arm is provided with a first fork lug, and a shaft of the axial steering engine is connected with the first fork lug.
In the aircraft two-degree-of-freedom control surface, the transverse rocker arm is provided with a second forked lug, and a shaft of the transverse steering engine is connected with the second forked lug.
In the double-freedom-degree control surface of the aircraft, the control surface is provided with a first mounting bracket, and the transverse steering engine is fixedly connected with the mounting bracket.
In the aircraft two-degree-of-freedom control surface, a second mounting bracket is arranged in the base, and the axial steering engine is connected with the second mounting bracket.
In the above-mentioned aircraft two degree of freedom control surfaces, still include: the rotating shaft supporting seat is arranged in the base, and the T-shaped rotating shaft is arranged in the rotating shaft supporting seat.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention realizes that the operation surface of the aircraft rotates around the axial and transverse two-degree-of-freedom of the aircraft through the T-shaped rotating shaft, and realizes control moments of the aircraft in 3 directions of pitching, rolling and yawing;
(2) the invention can enable the operation surface to automatically rotate around the aircraft in two degrees of freedom in the axial direction and the transverse direction through the axial steering engine and the transverse steering engine.
Drawings
FIG. 1 is a schematic structural view of a two degree-of-freedom control surface of the aircraft of the present invention;
FIG. 2 is another schematic illustration of a configuration of a two degree-of-freedom control surface of the aircraft of the present invention;
fig. 3 is a partial structural schematic view of a two-degree-of-freedom control surface of the aircraft of the present invention.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings:
fig. 1 is a schematic structural view of a two-degree-of-freedom control surface of the aircraft of the present invention. Fig. 2 is another schematic structural view of the two-degree-of-freedom control surface of the aircraft of the present invention. As shown in fig. 1 and 2, the two-degree-of-freedom control surface of the aircraft comprises a T-shaped rotating shaft 1, an axial rocker arm 2, a transverse steering engine 3, a control surface transverse support bearing 4, a control surface 5, a steering engine cable 6, a transverse rocker arm 7, an axial support bearing 8, a base 9, a rotating shaft support seat 10 and an axial steering engine 11; wherein,
the T-shaped rotating shaft 1 comprises a transverse rotating shaft 110 and a longitudinal rotating shaft 120, wherein the transverse rotating shaft 110 is connected with the longitudinal rotating shaft 120, and the transverse rotating shaft 110 is located in the base 9. Specifically, the transverse rotating shaft 110 and the longitudinal rotating shaft 120 are vertically connected to each other; the longitudinal rotating shaft 120 is a simply supported beam structure and is a moving shaft; the transverse rotating shaft 110 is a cantilever beam structure and is a fixed shaft. It should be noted that the aircraft two-degree-of-freedom control surface is installed on the aircraft, the transverse rotating shaft 110 is parallel to the transverse direction of the aircraft, and the longitudinal rotating shaft 120 is parallel to the axial direction of the aircraft.
The longitudinal axis 120 is connected to the base 9 by means of an axial support bearing 8. Specifically, the support bearing 8 is fixedly connected with the base 9, the longitudinal rotating shaft 120 is disposed in the axial support bearing 8, the axial direction of the longitudinal rotating shaft 120 is the same as the axial direction of the axial support bearing 8, and the longitudinal rotating shaft 120 can rotate around the axial direction.
The control surface 5 is connected to the transverse axis of rotation 110 by means of a transverse support bearing 4. Specifically, the transverse rotating shaft 110 is disposed in the transverse support bearing 4, the axial direction of the transverse rotating shaft 110 is the same as the axial direction of the transverse support bearing 4, and the control surface 5 can rotate around the axial direction of the transverse rotating shaft 110. Further, since the control surface 5 is connected to the transverse rotating shaft 110, when the longitudinal rotating shaft 120 rotates, the transverse rotating shaft 110 is driven to rotate around the longitudinal rotating shaft 120, so as to drive the control surface 5 to rotate around the longitudinal rotating shaft 120.
The longitudinal rotating shaft 120 is connected with an axial steering engine 11 through an axial rocker arm 2, and the axial steering engine 11 is arranged in the base 9. Specifically, axial rocking arm 2 and longitudinal rotating shaft 120 fixed connection, axial steering wheel 11 rotates with axial rocking arm 2 to be connected, and axial steering wheel 11 during operation can make axial rocking arm 2 move about in figure 1 to drive longitudinal rotating shaft 120 around its axial rotation. It should be understood that the axial steering engine 11 is further connected to an external controller through a cable, and the controller controls the movement of the axial steering engine 11.
The transverse rotating shaft 110 is connected with a transverse steering engine 3 through a transverse rocker arm 7, and the transverse steering engine 3 is connected with a control surface 5. Specifically, the transverse rocker arm 7 is fixedly connected with the transverse rotating shaft 110, the transverse steering engine 3 is rotatably connected with the transverse rocker arm 7, the transverse steering engine 3 is fixedly connected with the other end of the control surface 5, when the transverse steering engine 3 works, the transverse rocker arm 7 is fixedly connected with the transverse rotating shaft 110, the transverse rocker arm 7 and the transverse rotating shaft 110 are in a static state, the transverse steering engine 3 can move, and the transverse steering engine 3 is fixedly connected with the control surface 5, so that the transverse steering engine 3 drives the control surface 5 to rotate around the transverse rotating shaft 110.
First cavity 121 has been seted up to longitudinal axis 120's first half, and second cavity 111 has been seted up to transverse axis 110, and first cavity 121 is linked together with second cavity 111, and steering wheel cable 6 wears to locate first cavity 121 and second cavity 111 and is connected with transverse steering wheel 3. Specifically, through the arrangement mode of the steering engine cable 6, the space is saved, and the steering engine cable 6 is well protected. The steering engine cable 6 is also required to be connected with a controller, and the controller is used for controlling the motion of the transverse steering engine 3.
When the device works, under the control of the axial steering engine 11, the longitudinal rotating shaft 120 is driven to rotate through the axial rocker arm 2, so that the control surface 5 rotates around the longitudinal rotating shaft 120 in the axial direction; under the control of the transverse steering engine 3, the control surface 5 is driven to rotate around the transverse rotating shaft 110 through the transverse rocker arm 7; the control surface can rotate around the axial and transverse degrees of freedom of the aircraft under the composite control of the axial steering engine 11 and the transverse steering engine 3, and control moments in pitching, rolling and yawing 3 directions of the aircraft are realized.
In the embodiment, the operation surface of the aircraft rotates around the axial and transverse two-degree-of-freedom of the aircraft through the T-shaped rotating shaft, and control moments in pitching, rolling and yawing 3 directions of the aircraft are realized; and this embodiment can make the operation face automatic round aircraft axial and horizontal two degree of freedom rotation through axial steering wheel and horizontal steering wheel.
As shown in fig. 1, the axial rocker arm 2 is sleeved on the longitudinal rotating shaft 120, wherein the axial rocker arm 2 is provided with a through hole, the longitudinal rotating shaft 120 is provided with another through hole corresponding to the through hole of the axial rocker arm 2, and the axial rocker arm 2 and the longitudinal rotating shaft 120 are fixedly connected by a first pin 121 penetrating through the through hole of the axial rocker arm 2 and the through hole of the longitudinal rotating shaft 120.
As shown in fig. 1, the transverse rocker arm 7 is sleeved on the transverse rotating shaft 110, wherein the transverse rocker arm 7 is provided with a through hole, the transverse rotating shaft 110 is provided with another through hole corresponding to the through hole of the transverse rocker arm 7, and the transverse rocker arm 7 is fixedly connected with the transverse rotating shaft 110 by a second pin 111 penetrating through the through hole of the transverse rocker arm 7 and the through hole of the transverse rotating shaft 110.
Fig. 3 is a partial structural schematic view of a two-degree-of-freedom control surface of the aircraft of the present invention. As shown in fig. 3, the axial rocker arm 2 is provided with a first fork lug 210, and the shaft of the axial steering engine 11 is connected with the first fork lug 210. Specifically, the shaft of the axial steering engine 11 is rotatably connected with the first fork lug 210, so that the axial steering engine 11 drives the axial rocker arm 2 to rotate, and further drives the longitudinal rotating shaft 120 to rotate.
Fig. 3 is a partial structural schematic view of a two-degree-of-freedom control surface of the aircraft of the present invention. The transverse rocker arm 7 is provided with a second forked lug 710, and the shaft of the transverse steering engine 3 is connected with the second forked lug 710. Specifically, the shaft of the lateral steering engine 3 is rotatably connected with the second forked lug 710.
In the above embodiment, as shown in fig. 1, the control surface 5 is provided with a first mounting bracket 51, and the transverse steering engine 3 is fixedly connected with the first mounting bracket 51. The first mounting bracket 51 plays a role of fixing and supporting the transverse steering engine 3.
In the above embodiment, as shown in fig. 1, a second mounting bracket 91 is disposed in the base 9, and the axial steering engine 11 is connected to the second mounting bracket 91. The second mounting bracket 91 plays a role of fixing and supporting the axial steering engine 11.
In the above embodiment, as shown in fig. 1, the aircraft two-degree-of-freedom control surface further includes: the rotating shaft supporting seat 10, the rotating shaft supporting seat 10 are disposed in the base 9, and the T-shaped rotating shaft 1 is disposed in the rotating shaft supporting seat 10. The rotating shaft supporting seat 10 plays a role in supporting and fixing the T-shaped rotating shaft 1.
The invention realizes that the operation surface of the aircraft rotates around the axial and transverse two-degree-of-freedom of the aircraft through the T-shaped rotating shaft, and realizes control moments of the aircraft in 3 directions of pitching, rolling and yawing; in addition, the invention can enable the operation surface to automatically rotate around the aircraft in two degrees of freedom in the axial direction and the transverse direction through the axial steering engine and the transverse steering engine.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.
Claims (8)
1. A two degree-of-freedom control surface for an aircraft, comprising: the device comprises a T-shaped rotating shaft (1), an axial rocker arm (2), a transverse steering engine (3), a transverse supporting bearing (4), a control surface (5), a steering engine cable (6), a transverse rocker arm (7), an axial supporting bearing (8), a base (9) and an axial steering engine (11); wherein,
the T-shaped rotating shaft (1) comprises a transverse rotating shaft (110) and a longitudinal rotating shaft (120), wherein the transverse rotating shaft (110) is connected with the longitudinal rotating shaft (120), and the longitudinal rotating shaft (120) is positioned in the base (9);
the longitudinal rotating shaft (120) is connected with the base (9) through an axial supporting bearing (8);
the control surface (5) is connected with the transverse rotating shaft (110) through the transverse supporting bearing (4);
the longitudinal rotating shaft (120) is connected with an axial steering engine (11) through the axial rocker arm (2), and the axial steering engine (11) is arranged in the base (9);
the transverse rotating shaft (110) is connected with a transverse steering engine (3) through the transverse rocker arm (7), and the transverse steering engine (3) is connected with the control surface (5);
first cavity (121) have been seted up to first half of longitudinal rotating shaft (120), second cavity (111) have been seted up in transverse rotating shaft (110), first cavity (121) with second cavity (111) are linked together, steering wheel cable (6) wear to locate first cavity (121) with second cavity (111) and with transverse steering wheel (3) are connected.
2. The aircraft two-degree-of-freedom control surface of claim 1, wherein: the axial rocker arm (2) is sleeved on the longitudinal rotating shaft (120), wherein a through hole is formed in the axial rocker arm (2), another through hole corresponding to the through hole of the axial rocker arm (2) is formed in the longitudinal rotating shaft (120), and the axial rocker arm (2) is fixedly connected with the longitudinal rotating shaft (120) through the through hole of the axial rocker arm (2) and the through hole of the longitudinal rotating shaft (120) which are penetrated through pins.
3. The aircraft two-degree-of-freedom control surface of claim 1, wherein: horizontal rocking arm (7) cover is located horizontal pivot (110), wherein, the through-hole has been seted up in horizontal rocking arm (7), another through-hole corresponding with the through-hole of horizontal rocking arm (7) is seted up in horizontal pivot (110), passes the through-hole of horizontal rocking arm (7) and the through-hole of horizontal pivot (110) through the pin with horizontal rocking arm (7) and horizontal pivot (110) fixed connection.
4. The aircraft two-degree-of-freedom control surface of claim 2, wherein: the axial rocker arm (2) is provided with a first fork lug (210), and the shaft of the axial steering engine (11) is connected with the first fork lug (210).
5. The aircraft two-degree-of-freedom control surface of claim 3, wherein: the transverse rocker arm (7) is provided with a second forked lug (710), and the shaft of the transverse steering engine (3) is connected with the second forked lug (710).
6. The aircraft two-degree-of-freedom control surface of claim 1, wherein: the control surface (5) is provided with a first mounting bracket (51), and the transverse steering engine (3) is fixedly connected with the first mounting bracket (51).
7. The aircraft two-degree-of-freedom control surface of claim 1, wherein: a second mounting bracket (91) is arranged in the base (9), and the axial steering engine (11) is connected with the second mounting bracket (91).
8. The aircraft two degree-of-freedom control surface of claim 1, further comprising: the rotating shaft supporting seat (10), the rotating shaft supporting seat (10) is arranged in the base (9), and the T-shaped rotating shaft (1) is arranged in the rotating shaft supporting seat (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611024000.0A CN106697261B (en) | 2016-11-14 | 2016-11-14 | A kind of aircraft double freedom control surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611024000.0A CN106697261B (en) | 2016-11-14 | 2016-11-14 | A kind of aircraft double freedom control surface |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106697261A CN106697261A (en) | 2017-05-24 |
| CN106697261B true CN106697261B (en) | 2019-05-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611024000.0A Active CN106697261B (en) | 2016-11-14 | 2016-11-14 | A kind of aircraft double freedom control surface |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102717888A (en) * | 2012-06-20 | 2012-10-10 | 重庆大学 | Flap assembly of aircraft |
| CN202765290U (en) * | 2012-08-10 | 2013-03-06 | 南昌航空大学 | Airplane capable of achieving wing fixing and vertical take-off and landing based on three-shaft flight control board |
| EP2851288A1 (en) * | 2013-09-24 | 2015-03-25 | Embraer , S.A. | Aerodynamic surface drive mechanism |
| CN105752319A (en) * | 2016-02-01 | 2016-07-13 | 李苏杭 | Fixed wing aircraft adopting full-DOF (degree of freedom) tail wing and operating method |
-
2016
- 2016-11-14 CN CN201611024000.0A patent/CN106697261B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102717888A (en) * | 2012-06-20 | 2012-10-10 | 重庆大学 | Flap assembly of aircraft |
| CN202765290U (en) * | 2012-08-10 | 2013-03-06 | 南昌航空大学 | Airplane capable of achieving wing fixing and vertical take-off and landing based on three-shaft flight control board |
| EP2851288A1 (en) * | 2013-09-24 | 2015-03-25 | Embraer , S.A. | Aerodynamic surface drive mechanism |
| CN105752319A (en) * | 2016-02-01 | 2016-07-13 | 李苏杭 | Fixed wing aircraft adopting full-DOF (degree of freedom) tail wing and operating method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106697261A (en) | 2017-05-24 |
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