CN115056964A - Built-in electro-hydraulic servo drive flap mechanism for aerospace vehicle - Google Patents
Built-in electro-hydraulic servo drive flap mechanism for aerospace vehicle Download PDFInfo
- Publication number
- CN115056964A CN115056964A CN202210258779.1A CN202210258779A CN115056964A CN 115056964 A CN115056964 A CN 115056964A CN 202210258779 A CN202210258779 A CN 202210258779A CN 115056964 A CN115056964 A CN 115056964A
- Authority
- CN
- China
- Prior art keywords
- cylindrical cam
- electro
- servo
- fixed
- built
- 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.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 32
- 230000000712 assembly Effects 0.000 claims abstract description 12
- 238000000429 assembly Methods 0.000 claims abstract description 12
- 238000006073 displacement reaction Methods 0.000 claims description 2
- 230000001360 synchronised effect Effects 0.000 claims description 2
- 230000005611 electricity Effects 0.000 claims 1
- 239000007788 liquid Substances 0.000 claims 1
- 230000033001 locomotion Effects 0.000 abstract description 7
- 230000005540 biological transmission Effects 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 2
- 239000000969 carrier Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a built-in electro-hydraulic servo drive flap mechanism for an aerospace vehicle, which comprises a cylindrical cam, a positioning supporting seat, a folding wing, a fixed wing, two rotating assemblies and two servo hydraulic cylinders, wherein the positioning supporting seat is fixed on the top surface of the fixed wing, and the bottom surface of the fixed wing is fixed on a shell of the aerospace vehicle. The electro-hydraulic servo system controls the servo hydraulic cylinder to drive the cylindrical cam to move axially, linear motion of the cylindrical cam is converted into rotary motion through the two rotating assemblies, and rotation of the folding wings around the fixed wings is achieved. The invention has small overall radial size and compact structure; by adopting electro-hydraulic servo drive and cylindrical cam reverse transmission, the aerospace vehicle can fold, unfold and maintain the folding wings at any angle within a certain range in the flying process, and unnecessary impact vibration is reduced by utilizing electro-hydraulic servo control.
Description
Technical Field
The invention belongs to the field of aviation structure design, and particularly relates to a built-in electro-hydraulic servo drive flap mechanism for an aerospace vehicle.
Background
The folding wing technology can be traced back to 30 years in the last century, is very common in some tactical weapons such as missiles and is very important for aircraft carriers. The folding and unfolding of the wings can improve the aerodynamic characteristics of the aircraft in flight and can also reduce the storage space of the aircraft. The existing folding wings are all low-altitude aircrafts, and most of the existing folding wings are unmanned aerial vehicles. It is characterized in that: the load is small, the driving moment is small, the folding and unfolding are mostly carried out under the static state, and the space occupied by the driving mechanism is larger. For example, the folding wing of chinese patent with publication number CN110001944A has a small load and is directly driven by a rotor motor. The folding wing of chinese patent publication CN113650782A has a large load, so it is connected and driven by a wheel train mechanism, which is exposed on the outer surface of the wing and occupies a large space. Chinese patent publication No. CN113830284A is directed to folding because a folding wing has a large folding rate and is focused on folding, and thus there is no specific driving mechanism. Chinese patent publication No. CN113734421A discloses a flexible wing for a wing, which is hinged and driven by a servo motor. The chinese patent publication CN113581446A adopts telescopic folding wings, and installs the ailerons inside the main wing by using guide rails, which has a large requirement on the thickness of the wings. Chinese patent publication No. CN113665793A adopts a spring driving device, which needs to be manually restored and has a small load. In order to reduce the influence on the aerodynamic characteristics, the folding and unfolding mechanism of the wing can be completely built in the hinge between the fixed wing and the folding wing of the aircraft, and the surface continuity of the wing is not influenced. The thickness of the hinge is only a few centimeters, and the installation and arrangement of the flap mechanism in the hinge is difficult.
Disclosure of Invention
The invention aims to provide a built-in electro-hydraulic servo drive flap mechanism for an aerospace craft, which realizes the arrangement of the flap mechanism of the aerospace craft in a narrow hinge space of a fixed wing and a folding wing, and realizes the folding, unfolding and locking of any angle in a certain range of wings under the condition of larger flap torque in the flying process.
The technical solution for realizing the purpose of the invention is as follows: a built-in electro-hydraulic servo drive flap mechanism for an aerospace vehicle comprises a cylindrical cam, a positioning support seat, a folding wing, a fixed wing, two rotating assemblies and two servo hydraulic cylinders, wherein the positioning support seat is fixed on the top surface of the fixed wing, the bottom surface of the fixed wing is fixed on a shell of the aerospace vehicle, four mounting grooves are formed in the positioning support seat at intervals, two mounting grooves in two ends are first mounting grooves, two mounting grooves in the middle are second mounting grooves, the four mounting grooves are communicated through a through hole, one servo hydraulic cylinder is fixed in each first mounting groove, the cylindrical cam is positioned in the two second mounting grooves, and output shafts of the two servo hydraulic cylinders extend into the two ends of the cylindrical cam and are fixedly connected with the cylindrical cam; two rotating assemblies are respectively connected with the cylindrical cam in a rotating mode, only one rotating assembly is arranged in each second mounting groove, the two rotating assemblies are fixedly connected with the folding wings, the two servo hydraulic cylinders are driven synchronously, the cylindrical cam moves along the axial direction, and the rotating assemblies on the cylindrical cam drive the folding wings to rotate around the fixed wings.
Compared with the prior art, the invention has the remarkable advantages that:
(1) the overall structure is refined, the radial dimension can be limited below 60mm, and the installation arrangement in narrow radial space can be adapted.
(2) The hinge space between the fixed wing and the folding wing is completely arranged in, and the continuity of the surface of the wing is not influenced.
(3) By adopting electro-hydraulic servo control, folding, unfolding and locking of an accurate angle are realized while a larger flap torque is provided.
(4) The cylindrical cam is adopted for inverse transmission to convert linear motion into rotary motion, and the mechanism has high operation efficiency.
Drawings
FIG. 1 is a schematic overall structure diagram of a built-in electro-hydraulic servo drive flap mechanism for an aerospace vehicle.
FIG. 2 is a schematic diagram of an electro-hydraulic servo drive of a built-in electro-hydraulic servo drive flap mechanism for an aerospace vehicle.
FIG. 3 is a schematic structural diagram of a cylindrical cam of the built-in electro-hydraulic servo drive flap mechanism for the aerospace vehicle.
FIG. 4 is a schematic diagram of the reverse transmission of the cylindrical cam of the built-in electro-hydraulic servo drive flap mechanism for the aerospace vehicle.
FIG. 5 is a schematic view of a sliding key arrangement of the built-in electro-hydraulic servo driven flap mechanism for the aerospace vehicle.
FIG. 6 is a schematic diagram of a positioning support structure of the built-in electro-hydraulic servo drive flap mechanism for the aerospace vehicle.
Detailed Description
The present invention is described in further detail below with reference to the attached drawing figures.
With reference to fig. 1 to 6, a built-in electro-hydraulic servo drive flap mechanism for an aerospace craft comprises a cylindrical cam 4, a positioning support seat 1, a folding wing 5, a fixed wing 7, two rotating assemblies and two servo hydraulic cylinders 2, wherein the positioning support seat 1 is fixed on the top surface of the fixed wing 7, the bottom surface of the fixed wing 7 is fixed on a shell of the aerospace craft, four mounting grooves are formed in the positioning support seat 1 at intervals, two mounting grooves at two ends are first mounting grooves, two mounting grooves in the middle are second mounting grooves, the four mounting grooves are communicated through a through hole, one servo hydraulic cylinder 2 is fixed in each first mounting groove, the cylindrical cam 4 is located in the two second mounting grooves, and output shafts of the two servo hydraulic cylinders 2 extend into the two ends of the cylindrical cam 4 and are fixedly connected with the cylindrical cam 4. Two runner assemblies rotate with cylindrical cam 4 respectively and are connected, and have and only have a runner assembly in every second mounting groove, and two runner assemblies all link firmly with folding wing 5, and 2 synchronous drives of two servo hydraulic cylinders for cylindrical cam 4 is along axial displacement, and then makes runner assembly above that drive folding wing 5 and rotate around stationary vane 7. The whole mechanism is in double-layer fit, the limitation of the radial size of the drive is controlled within 60mm, and the linear motion of the power source can be efficiently converted into the rotary motion.
The rotating assembly comprises a cylindrical sleeve 3 and a plurality of cam followers 6, the cylindrical sleeve 3 is sleeved on the outer side of the cylindrical cam 4, one end of each cam follower 6 is fixed on the inner wall of the cylindrical sleeve 3, and the other end of each cam follower rolls along a curve groove of the cylindrical cam 4.
The built-in electro-hydraulic servo drive flap mechanism for the aerospace craft further comprises a sliding key 8, key grooves are formed in the upper end and the lower end of the middle of the outer circumferential wall of the cylindrical cam 4 and the upper end and the lower end of the middle of the positioning support seat 1 respectively, the sliding key 8 is arranged in each key groove and can move axially along with the cylindrical cam 4 in the key groove of the positioning support seat, the function of limiting the rotation of the cylindrical cam 4 is achieved, and accurate transmission is guaranteed.
The built-in electro-hydraulic servo drive flap mechanism for the aerospace craft further comprises two thrust needle roller combined bearings 9, the thrust needle roller combined bearings 9 are arranged in the through hole of the positioning support seat 1 between the first mounting groove and the second mounting groove, one end of each thrust needle roller combined bearing 9 abuts against the end face of the cylindrical sleeve 3, and the output shaft of the servo hydraulic cylinder 2 penetrates through the thrust needle roller combined bearings 9 and then is fixedly connected with the cylindrical cam 4. The thrust needle roller combination bearing 9 has the effects of limiting the axial movement of the cylindrical sleeve 3, reducing the friction of the cylindrical sleeve 3 relative to the positioning support seat 1 during rotation and improving the transmission efficiency.
When the output shaft of the servo hydraulic cylinder 2 is not matched with the thrust needle roller combination bearing 9, the matching of the output shaft and the thrust needle roller combination bearing is realized through the shaft sleeve 10.
When the aerospace craft is provided with a plurality of groups of folding wings, each group of folding wings is controlled by a set of built-in electrohydraulic servo driving flap mechanisms, a servo hydraulic cylinder 2 in each set of built-in electrohydraulic servo driving flap mechanism is connected to the same set of electrohydraulic servo system, the locking of any position of the mechanism in an effective stroke is realized by using the locking function of the electrohydraulic servo system, and further the locking of any angle of the folding wings 5 in a certain range is realized. The working process is as follows: the oil supply of an external electro-hydraulic servo system is realized, two servo hydraulic cylinders 2 synchronously drive the cylindrical cam 4 to axially move, the cylindrical sleeve 3 is driven to rotate by the cam follower 6 uniformly arranged in the groove of the cylindrical cam 4, and finally, the torque is transmitted to the folding wings 5, so that the folding wings 5 rotate around the fixed wings 7. And the control of the driving direction and speed of the servo hydraulic cylinder 2 is realized through an electro-hydraulic servo control system. The locking function of the electro-hydraulic servo system is utilized to realize the locking of the mechanism at any position in the effective stroke, and further realize the locking of the folding wing 5 at any angle in a certain range.
Claims (5)
1. The utility model provides a be used for built-in electricity liquid servo drive flap mechanism of aerospace vehicle which characterized in that: the device comprises a cylindrical cam (4), a positioning support seat (1), folding wings (5), fixed wings (7), two rotating assemblies and two servo hydraulic cylinders (2), wherein the positioning support seat (1) is fixed on the top surface of the fixed wings (7), the bottom surfaces of the fixed wings (7) are fixed on a shell of an aerospace vehicle, four mounting grooves are formed in the positioning support seat (1) at intervals, two mounting grooves at two ends are first mounting grooves, two mounting grooves in the middle are second mounting grooves, the four mounting grooves are communicated through a through hole, one servo hydraulic cylinder (2) is fixed in each first mounting groove, the cylindrical cam (4) is positioned in the two second mounting grooves, and output shafts of the two servo hydraulic cylinders (2) extend into the two ends of the cylindrical cam (4) and are fixedly connected with the cylindrical cam (4); two rotating assemblies rotate with cylindrical cam (4) respectively and are connected, and have and only one rotating assembly in every second mounting groove, two rotating assemblies all link firmly with folding wing (5), two servo hydraulic cylinder (2) synchronous drive for cylindrical cam (4) are along axial displacement, and then make rotating assembly above that drive folding wing (5) and rotate around stationary vane (7).
2. The built-in electro-hydraulic servo drive flap mechanism for aerospace vehicles of claim 1, wherein: the rotating assembly comprises a cylindrical sleeve (3) and a plurality of cam followers (6), the cylindrical sleeve (3) is sleeved on the outer side of the cylindrical cam (4), one end of each cam follower (6) is fixed on the inner wall of the cylindrical sleeve (3), and the other end of each cam follower rolls along a curved groove of the cylindrical cam (4).
3. The built-in electro-hydraulic servo drive flap mechanism for aerospace vehicles of claim 2, wherein: the positioning support is characterized by further comprising two sliding keys (8), key grooves are formed in the upper end and the lower end of the middle part of the outer wall of the circumference of the cylindrical cam (4) and the upper end and the lower end of the middle part of the positioning support seat respectively, and the sliding keys (8) are arranged in the key grooves.
4. The built-in electro-hydraulic servo drive flap mechanism for aerospace vehicles of claim 3, wherein: the servo hydraulic cylinder is characterized by further comprising two thrust needle roller combination bearings (9), wherein the thrust needle roller combination bearings (9) are arranged in a through hole of the positioning support seat (1) between the first mounting groove and the second mounting groove, one end of the thrust ball bearing portion of each thrust needle roller combination bearing is in contact with one end of the cylindrical sleeve (3), and an output shaft of the servo hydraulic cylinder (2) penetrates through the thrust needle roller combination bearings (9) and then is fixedly connected with the cylindrical cam (4).
5. The built-in electro-hydraulic servo drive flap mechanism for aerospace vehicles of claim 4, wherein: the servo hydraulic cylinder is characterized by further comprising two shaft sleeves (10), and when the output shaft of the servo hydraulic cylinder (2) is not matched with the thrust needle roller combined bearing (9), the shaft sleeves (10) are matched with each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210258779.1A CN115056964B (en) | 2022-03-16 | 2022-03-16 | Built-in electrohydraulic servo driving flap mechanism for aerospace vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210258779.1A CN115056964B (en) | 2022-03-16 | 2022-03-16 | Built-in electrohydraulic servo driving flap mechanism for aerospace vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115056964A true CN115056964A (en) | 2022-09-16 |
| CN115056964B CN115056964B (en) | 2024-04-12 |
Family
ID=83196563
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210258779.1A Active CN115056964B (en) | 2022-03-16 | 2022-03-16 | Built-in electrohydraulic servo driving flap mechanism for aerospace vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115056964B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3247907A (en) * | 1963-09-18 | 1966-04-26 | Boeing Co | Blade folding mechanism for rotary wing aircraft |
| CN107933881A (en) * | 2017-11-15 | 2018-04-20 | 安徽工程大学 | A kind of outer wing folding and unfolding mechanism of aircraft |
| CN108033004A (en) * | 2017-12-20 | 2018-05-15 | 长安大学 | One kind rotary wings machine that inclines verts system |
| CN112109879A (en) * | 2020-10-16 | 2020-12-22 | 西安羚控电子科技有限公司 | Folding wing unfolding rotating shaft mechanism |
-
2022
- 2022-03-16 CN CN202210258779.1A patent/CN115056964B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3247907A (en) * | 1963-09-18 | 1966-04-26 | Boeing Co | Blade folding mechanism for rotary wing aircraft |
| CN107933881A (en) * | 2017-11-15 | 2018-04-20 | 安徽工程大学 | A kind of outer wing folding and unfolding mechanism of aircraft |
| CN108033004A (en) * | 2017-12-20 | 2018-05-15 | 长安大学 | One kind rotary wings machine that inclines verts system |
| CN112109879A (en) * | 2020-10-16 | 2020-12-22 | 西安羚控电子科技有限公司 | Folding wing unfolding rotating shaft mechanism |
Non-Patent Citations (1)
| Title |
|---|
| 胡明;黎德蓓;陈文华;张苗苗;钱萍;: "空间凸轮-螺旋组合式折叠翼面展开机构设计及其运动特性分析", 中国机械工程, no. 12, pages 1475 - 1478 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115056964B (en) | 2024-04-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2589683C (en) | Compact tiltrotor pylon-conversion actuation system | |
| CN102582832B (en) | Flapping-wing aircraft | |
| CN101380999B (en) | Wind tunnel model folding deformable wing | |
| US9376202B2 (en) | Pitch control of contra-rotating airfoil blades | |
| CN112109878B (en) | Folding mechanism suitable for folding morphing wing | |
| CN111332462B (en) | Portable small-sized cylinder type coaxial reverse-propeller three-blade rotor type unmanned aerial vehicle | |
| CN103434640B (en) | High-altitude unmanned plane equipped with Magnus effect propulsion system | |
| CN108945420A (en) | A kind of four axis tilting rotor mechanisms and method of verting based on unmanned plane | |
| CN101984331A (en) | Dynamics comprehensive test bed for half-unfolding gas bomb with long tilting rotor wing | |
| CN115056964A (en) | Built-in electro-hydraulic servo drive flap mechanism for aerospace vehicle | |
| CN208855867U (en) | A kind of four axis tilting rotor mechanisms based on unmanned plane | |
| CN111470030A (en) | Wing leading edge bending mechanism based on gear five-bar mechanism driving | |
| SU612062A1 (en) | Wind motor | |
| US11124287B2 (en) | Fan module with variable-pitch blades for a turbomachine | |
| CN109878711A (en) | Double paddle power devices and its mobile devices | |
| CN114857232A (en) | Spiral force-applying device and power transmission system | |
| CN107878775B (en) | Airplane wheel driving system for airplane ground taxiing | |
| CN104682655A (en) | Power component and transmission mechanism integrated servo mechanism | |
| CN110901893B (en) | Method for improving motion synchronism of two adjacent control surfaces | |
| CN211223840U (en) | Synchronizer for keeping motion synchronism of two adjacent control surfaces | |
| CN209875372U (en) | Novel variable-pitch decoupling structure | |
| CN105258905B (en) | A kind of pulp distance varying mechanism suitable for low-speed wind tunnel | |
| CN212305001U (en) | Compact electromechanical actuator | |
| CN211174694U (en) | Electric contra-rotating ducted fan | |
| CN216916275U (en) | Top direct-drive rotor wing device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Fan Yuanxun Inventor after: Zhong Tao Inventor after: Zhu Can Inventor after: Zhang Yingzhao Inventor before: Zhong Tao Inventor before: Zhu Can Inventor before: Zhang Yingzhao Inventor before: Fan Yuanxun |
|
| CB03 | Change of inventor or designer information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |