CN113955082A - Light control surface and hinge structure suitable for solar unmanned aerial vehicle - Google Patents
Light control surface and hinge structure suitable for solar unmanned aerial vehicle Download PDFInfo
- Publication number
- CN113955082A CN113955082A CN202111459715.XA CN202111459715A CN113955082A CN 113955082 A CN113955082 A CN 113955082A CN 202111459715 A CN202111459715 A CN 202111459715A CN 113955082 A CN113955082 A CN 113955082A
- Authority
- CN
- China
- Prior art keywords
- control surface
- main beam
- wing
- rib
- hinge
- 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
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a light control surface and hinge structure suitable for a solar unmanned aerial vehicle, belongs to the field of aircraft design, and comprises a composite material light control surface, an adjustable hinge mechanism and the like. The main beam, the front edge, the wing ribs and the rear edge of the control surface are all made of carbon fiber-PMI foam composite materials, and compared with the traditional control surface, the control surface has lighter structural weight. The control surface bears bending and twisting through the composite material main beam with the square section, and the appearance is maintained by adopting the flexible skin, so that the extra weight caused by the rigid skin is saved; under the action of the adjustable hinge mechanism, the control surface can smoothly rotate around the rotating shaft within the range of +/-45 degrees, and the designed adjustable hinge mechanism can eliminate the size error caused by processing of composite materials and meet the coaxiality requirement of a plurality of hinge rotating shafts of the control surface with a large aspect ratio; a maintenance opening cover of the control surface is omitted, and the control surface is quickly assembled and disassembled through bolts perpendicular to the control surface.
Description
Technical Field
The invention belongs to the field of aircraft design, and relates to a light control surface and hinge structure suitable for a solar unmanned aerial vehicle.
Background
The sensitivity of the feasibility of the overall scheme of the solar unmanned aerial vehicle to the weight of the structure is high, and the closed loop of the scheme can be realized only by controlling the weight coefficient of the structure within 35%. Due to the requirements of reducing cruise power consumption and increasing the light receiving area, the load of the solar unmanned aerial vehicle is usually 2.4-6.3 kg/m2, and the wing area of the solar unmanned aerial vehicle is larger than that of a traditional unmanned aerial vehicle with the same takeoff mass. In addition, for reducing the structure quality, solar energy unmanned aerial vehicle adopts combined material airfoil structure usually, and its solidification process that is heated, size precision and straightness accuracy error are great, and the installation accuracy is difficult to guarantee. The traditional unmanned aerial vehicle control surface structural framework mainly adopts a solid carbon fiber structure, so that the structural mass is large; the skin is made of rigid materials to ensure the structural rigidity under high wing load, and has high surface density and high maintenance cost; the hinge is usually a hidden structure, has small rotation amplitude and large disassembly and assembly difficulty, and is difficult to adjust the distance between the control surface and the airfoil surface. This kind of control surface and hinge structure not only are unfavorable for the reduction of structure quality, require high to combined material machining precision moreover, maintain comparatively difficultly, consequently are unfavorable for the promotion of solar energy unmanned aerial vehicle performance and processing technology.
Disclosure of Invention
In order to overcome the defects of the existing control surface and hinge structure of the unmanned aerial vehicle, the invention provides the light control surface and hinge structure suitable for the solar unmanned aerial vehicle.
The invention is suitable for a light control surface and a hinge structure of a solar unmanned aerial vehicle, wherein the control surface is provided with a main beam, a wing rib, a front edge, a rear edge and a skin; the main beam is provided with a wing rib along the spanwise direction; the front end and the rear end of each wing rib are respectively fixed on the front edge and the rear edge; and covering skins are laid on the outer surface of the integral control surface.
The control surface is connected with the airfoil surface through a hinge; the main beam, the front edge and the rear edge of the control surface are all designed into a composite material interlayer structure, PMI foam material is arranged inside the control surface, and a carbon fiber layer is wrapped outside the control surface; the wing rib of the control surface is of a composite material enveloping structure, the outer layer is a carbon fiber layer, and the inner part is PMI foam material.
The hinge is designed as an omnidirectional adjusting hinge and comprises a supporting plate nut, a rotating arm seat and an adjusting plate. The supporting plate nut is fixed at the mounting position of the omnidirectional adjusting hinge on the main beam; the rear end of the rotating arm is fixedly connected with the nut of the supporting plate through threads; the front end of the rotating arm is connected with the rotating arm base through a spreading screw to form a rotating pair; the connecting hole formed in the front end of the rotating arm seat is matched with a strip-shaped hole formed in the connecting platform in the middle of the back side of the adjusting plate, the connecting hole is connected with the adjusting plate through a normal bolt, and the rotating of the rotating arm seat is limited through baffles on two sides of the connecting platform; the adjusting plate is used for connecting a rear beam of the airfoil.
The rotating arm adjusts the position of the rotating shaft along the chord direction through relative rotation between the rotating arm and the supporting plate nut, and the coaxiality error of the omni-directional adjusting hinge caused by processing and assembling of composite materials is eliminated; by loosening the normal bolts in all the omnidirectional adjusting hinges, the rotating arm base moves along the strip-shaped hole, and the adjustment of the distance between the control surface and the airfoil surface is realized.
The invention has the advantages that:
1. the light control surface structure provided by the invention adopts the composite material interlayer type main beam, the composite material wrapped wing ribs, the composite material front edge and the composite material rear edge which are all formed by carbon fibers and PMI foam, so that the structural strength and rigidity can be ensured, and the structural weight can be reduced;
2. the light control surface provided by the invention adopts a polyimide flexible skin structure, so that on one hand, the weight is greatly reduced while the tearing-resistant performance of the skin is ensured, on the other hand, the skin can be damaged and replaced at any time when the structure is maintained, the maintenance difficulty is small, and the cost is low;
3. according to the composite material interlayer type main beam structure in the light control surface, the torque is borne through the +/-45-degree paving layer, the rigidity of the flexible skin control surface can be ensured, the inclined strut structure is omitted, and the structural weight is saved;
4. the composite material enveloping type wing rib in the light control surface is of a separated structure, wherein the front half section is connected with the composite material sandwich type main beam in a mortise and tenon mode, so that the connection precision is improved, and the structural integrity of the main beam is ensured;
5. the hinge structure provided by the invention adjusts the coaxiality of a plurality of hinges by adjusting the screwing distance of the rotating arm on the supporting plate nut and the mounting position of the rotating arm seat on the mounting plate, and is also used for adjusting the gap between the control surface and the airfoil surface;
6. the light control surface provided by the invention is connected with the airfoil through the normal bolt vertical to the airfoil, and the operation hole is reserved on the control surface, so that the control surface can be quickly assembled and disassembled, and the maintenance is simple;
7. the light control surface provided by the invention can smoothly rotate within +/-45 degrees with the airfoil surface, and the requirement of large rudder deflection angle under the limit working condition is met.
Drawings
Fig. 1 is a diagram showing the assembly relationship between a control surface and an airfoil surface in a light control surface and hinge structure suitable for a solar unmanned aerial vehicle.
Fig. 2 is a structure diagram of a light rudder surface and a rudder surface in a hinge structure suitable for a solar unmanned aerial vehicle.
Fig. 3 is a structural diagram of an omnidirectional adjusting hinge in a light control surface and hinge structure suitable for a solar unmanned aerial vehicle.
Fig. 4 is a schematic diagram of an actuation system of a light control surface and a control surface in a hinge structure suitable for a solar unmanned aerial vehicle.
Fig. 5 is a structural diagram of a light control surface and a main beam in a hinge structure suitable for a solar unmanned aerial vehicle.
Fig. 6 is a structural view of a wing rib in a light control surface and hinge structure suitable for a solar unmanned aerial vehicle.
Fig. 7 is a front edge structure diagram in a light rudder surface and hinge structure suitable for a solar unmanned aerial vehicle of the present invention.
Fig. 8 is a relative relationship diagram of the light control surface and hinge structure control surface and hinge of the solar unmanned aerial vehicle in different rudder deflection states.
In the figure:
1-control surface 2-omnidirectional adjustment hinge 3-wing surface
4-actuation System 101-girder 102-Rib
103-leading edge 104-trailing edge 105-skin
201-supporting plate nut 202-rotating arm 203-rotating arm seat
204-adjustment plate 205-span bolt 206-normal bolt
401-steering engine 402-actuating pull rod 403-control surface rocker
1011-rectangular hole 1012-circular hole 1021-rib front section
1022-rib rear section 1031-leading edge foam layer 1032-leading edge carbon fiber layer
Detailed Description
The invention is further described below with reference to the accompanying drawings.
The invention is suitable for a light control surface and hinge structure of a solar unmanned aerial vehicle, and is provided with a composite material light control surface 1 and an omnidirectional adjusting hinge 2 for connecting the control surface and an airfoil surface 3, wherein the omnidirectional adjusting hinge 2 is used for realizing the rotation relation of a rotating shaft formed by the composite material light control surface 1 and the airfoil surface 3 along the spanwise direction, as shown in figure 1.
The composite material lightweight rudder surface 1 comprises a girder 101, a wing rib 102, a leading edge 103, a trailing edge 104 and a skin 105, as shown in fig. 2.
The longitudinal section of the main beam 101 is rectangular and is designed into a composite material interlayer structure; inside it is a PMI foam. The outer layer of the PMI foam material is wrapped with a +/-45-degree carbon fiber layer for bearing torsional moment; and 0-degree carbon fiber layers are arranged between the top surface of the PMI foam material and the +/-45-degree carbon fiber layers and between the bottom surface of the PMI foam material and the +/-45-degree carbon fiber layers and are used for bearing shearing force and bending moment.
Grooves are formed in the middle of the end faces of the left end and the right end of the main beam 101, and two protruding plugs are formed at the two ends of each groove and serve as connecting positions of end wing ribs; circular through holes 1012 are arranged on the main beam 101 at equal intervals along the length direction of the main beam and are used as the connecting positions of the omnidirectional adjusting hinges 2; rectangular holes 1011 are formed in the symmetrical positions of two sides of each circular through hole 1012, and meanwhile, the rectangular holes 1011 are formed in the middle point of the central connecting line of two adjacent circular through holes 1012; the rectangular hole 1011 serves as a mid-rib connection location.
The wing ribs 102 are of a composite material enveloping structure, the overall configuration of the wing ribs is consistent with that of the rear part of the wing profile adopted by the wing surface 3, as shown in fig. 4, the wing ribs comprise front section wing ribs 1021 and rear section wing ribs 1022, both the two sections of wing ribs are of the composite material enveloping structure, the outer layer is a 0-degree/90-degree carbon fiber layer, the inner part is PMI foam, and the rigidity can be guaranteed on the premise of reducing the weight of the wing ribs. Wherein, the front end of the rear wing rib 1022 is designed with a wedge-shaped groove; the front end of the front section wing rib 1021 is designed to be a circular arc shape so as to reduce the aerodynamic resistance of the control surface 1 in a deflection state; the rear end of the front section rib 1021 is provided with a plug, the front part of the plug is a wedge-shaped part 1023, and the rear part of the plug is a rectangular section 1024 with upper and lower parallel planes; therefore, the front wedge-shaped part 1023 of the plug of the front rib 1021 is matched with the wedge-shaped slot of the rear rib 1022, so that the front rib 1021 and the rear rib 1022 are spliced and fixed by low-temperature epoxy resin; the contact surface at the plugging position is increased by a plugging mode of a wedge-shaped structure. Meanwhile, after the front rib 1021 and the rear rib 1022 are spliced, the upper plane and the lower plane of the rectangular section 1024 at the tail end of the plug, the front end face of the front rib 1021 and the rear end face of the rear rib 1022 are matched, so that two rectangular grooves are reserved at the corresponding positions of the upper part and the lower part of the integral rib 102 and are used for matching with the spliced girder 101.
When the rib 102 and the main beam 101 are installed, at the connecting position of the rib at the end of the main beam 101, the rib 102 is respectively matched and inserted with two plugs at the end of the main beam 101 through the upper and lower grooves, and is adhered and fixed by low-temperature epoxy resin. At the middle rib connection position of the main beam 101, the rib 102 is respectively matched with the rectangular hole 1011 through the upper and lower position grooves and is adhered and fixed by low-temperature epoxy resin. During assembly, the front rib 1021 is inserted into the rectangular hole 1011 of the main beam 101 from the front side of the main beam, and then the rear rib 1022 is inserted into the front rib 1021.
The front edge 103 is of a composite material sandwich structure, the outer side of the front edge is a 0/90-degree carbon fiber layer 1032, and the inner side of the front edge is a layer of PMI foam structure 1031 with equal thickness; the leading edge 103 is fixed to the front arc of the front rib 1021 in the rib 102 by low temperature epoxy bonding. As shown in fig. 7, the leading edge 103 adopts a multi-section structure, a section of leading edge 103 is arranged between the rib 102 at the end of the main beam 101 and the rib 102 adjacent to the main beam, and the two ends of the leading edge 103 are fixed positions of the ribs 102; the rib between two adjacent omnidirectional adjustment hinge connection positions is fixed with a section of leading edge 103, and the positions of two ends and the middle position of the leading edge 103 are rib fixing positions. At the fixed position between the front edge 103 and the rib 102, only the carbon fiber layer is kept, and the PMI foam structure is not arranged, so that the bonding strength is enhanced.
The trailing edge 104 is of a composite material sandwich type structure, the longitudinal section of the trailing edge is triangular, the shape of the trailing edge is consistent with that of an airfoil trailing edge adopted by the airfoil 3, the outer side of the trailing edge is a 0/90-degree carbon fiber layer, and PMI foam is arranged inside the trailing edge. On the trailing edge 104, only the upper and lower carbon fiber layers are remained at the positions corresponding to the positions of the ribs 102 without PMI foam, rib insertion positions are formed, the ribs 102 are respectively inserted into the trailing edge 104 at the positions corresponding to the rib insertion positions on the trailing edge 104, and then the ribs 102 and the upper and lower carbon fiber layers are bonded and fixed through low-temperature epoxy resin.
The skin 105 is a polyimide flexible skin and circumferentially covers the outer surface of the control surface 1 of the structure. The covering 105 contains radial and weft-wise glass fiber yarns, so that the strength of the covering can be enhanced on one hand, and on the other hand, the covering can be prevented from being torn in a large scale when local damage occurs to the covering in the flight process during long endurance.
The omnidirectional adjustment hinge 2 comprises a supporting plate nut 201, a rotating arm 202, a rotating arm seat 203 and an adjustment plate 204, as shown in fig. 6. The supporting plate nut 201 is fixed with the composite material interlayer type main beam 101 through screw holes arranged at opposite positions of two sides of the center and matched with bolts, and when the supporting plate nut 201 is fixed, the cylindrical connecting part designed in the middle of the supporting plate nut 201 is matched with a circular hole 1012 arranged on the main beam so as to ensure the positioning precision between the supporting plate nut and the main beam. The rear end of the rotating arm 202 is fixedly connected with the internal thread of the connecting part of the middle cylinder of the supporting plate nut 201 through external threads; the front end of the rotating arm 202 is designed with a through hole for connecting with the rotating arm seat 203. Two sides of the rear end of the rotating arm seat 203 are provided with lugs which are parallel to each other, and through holes are formed at the opposite positions of the two lugs; the front end of the rotating arm 202 is inserted between the two lugs, and through holes on the three lugs are coaxially arranged; after a spanwise bolt 205 arranged along a spanwise direction through an axis passes through the two lugs and the through hole at the front end of the rotating arm 202 from one side, the two lugs of the rotating arm seat 203 clamp the rotating arm 202 in a matched nut screwing mode, and the degrees of freedom of the rotation of the two lugs around the axis of the spanwise bolt 205 are reserved. The front end of the rotating arm seat 203 is provided with a longitudinal connecting hole for connecting the adjusting plate 204. The adjusting plate 204 is a rectangular plate, a connecting platform is designed in the middle of the back side, a strip-shaped hole is formed in the middle of the connecting platform, and after a normal bolt 206 along the normal direction passes through the connecting hole in the front end of the rotating arm seat 203 and the strip-shaped hole in the connecting platform from one side through an axis, a nut is matched to screw down, so that the rotating arm seat 203 and the adjusting plate 204 are fixedly connected. Meanwhile, parallel baffles are designed on two sides of the connecting platform, so that the front end of the rotating arm seat 203 is positioned between the two baffles, the two sides of the rotating arm seat are attached to the two baffles, and the rotation of the rotating arm seat 203 is limited by the two baffles, as shown in fig. 3. Round holes are designed at four corners of the adjusting plate 204, and bolts penetrate through the round holes to be connected with a back beam of the airfoil 3, so that the adjusting plate and the airfoil 3 are fixed. Therefore, after the omni-directional adjusting hinges 2 on the main beam 101 are connected with the airfoil 3 in the above mode, the connection between the control surface 1 and the airfoil 3 is realized.
The rotating arm 202 can adjust the position of the rotating shaft along the chord direction through relative rotation with the supporting plate nut 201, so that the coaxiality error of the omnidirectional adjusting hinge 2 caused by processing and assembling of composite materials is eliminated. By loosening the normal bolts 206 in the omnidirectional adjusting hinges 1, the rotating arm seat 203 can be moved along the strip-shaped hole, so that the distance between the control surface 1 and the airfoil surface 3 can be adjusted, and after the distance between the control surface 1 and the airfoil surface 3 is adjusted, the normal bolts 206 are screwed to fix the current position of the control surface 1.
The relative rotation between the light control surface 1 and the airfoil 3 is realized by an actuating system 4, and the actuating system 4 comprises a steering engine 401, an actuating pull rod 402 and a control surface rocker 403, as shown in fig. 7.
The rudder face rocker 403 has two side rods parallel to each other and a connecting rod between the two side rods. The upper parts of the two side rods are respectively fixed on wing ribs 3 at two sides of an omnidirectional adjusting hinge 2 in the middle of the control surface 1 through bolts, so that asymmetric force during operation is eliminated, and the omnidirectional adjusting hinge 2 in the middle of the control surface 1 is positioned between the two side rods. The bottom end of one side rod is connected with a fisheye bearing at one end of the actuating pull rod 402 through a bolt. The fisheye bearing at the other end of the actuating pull rod 402 is connected with the rocker arm of the steering engine 401 through a bolt to form an actuating relation. The ratio of the length of the rocker arm of the steering engine 401 to the length of the control surface rocker arm 403 is 1:1, so that the transmission ratio of the actuating system 4 is 1: 1. Therefore, the steering engine 401 drives the actuating pull rod 402 and the control surface rocker 403 to move, so that the control surface 3 can be driven to actuate within a range of +/-45 degrees, and the positions and hinge states of the control surface in different rudder deflection states are shown in fig. 8.
Taking a small-sized ultra-long solar unmanned aerial vehicle for navigation as an example, when a control surface made of traditional composite materials and a traditional hinge are adopted, the mass of an elevator (including the hinge mechanism) with the length of 2m and the width of 0.22m is 340g, and the rotation range of the control surface is +/-35 degrees. After the invention is applied, the mass of the control surface is reduced to 260g, and the rotation range of the control surface can be increased to +/-45 degrees.
Claims (9)
1. A light control surface and hinge structure suitable for a solar unmanned aerial vehicle is provided, wherein the control surface is provided with a main beam, wing ribs, a front edge, a rear edge and a skin; wherein, the main beam is provided with a wing rib along the spanwise direction; the front end and the rear end of each wing rib are respectively fixed on the front edge and the rear edge; laying a skin on the outer surface of the integral control surface; the control surface is connected with the airfoil surface through a hinge; the method is characterized in that:
the main beam, the front edge and the rear edge of the control surface are all designed into a composite material interlayer structure, PMI foam material is arranged inside the control surface, and a carbon fiber layer is wrapped outside the control surface; the wing ribs of the control surface are of a composite material enveloping structure, the outer layer is a carbon fiber layer, and the interior is PMI foam material;
the hinge is designed as an omnidirectional adjusting hinge and comprises a supporting plate nut, a rotating arm seat and an adjusting plate. The supporting plate nut is fixed at the mounting position of the omnidirectional adjusting hinge on the main beam; the rear end of the rotating arm is fixedly connected with the nut of the supporting plate through threads; the front end of the rotating arm is connected with the rotating arm base through a spreading screw to form a rotating pair; the connecting hole formed in the front end of the rotating arm seat is matched with a strip-shaped hole formed in the connecting platform in the middle of the back side of the adjusting plate, the connecting hole is connected with the adjusting plate through a normal bolt, and the rotating of the rotating arm seat is limited through baffles on two sides of the connecting platform; the adjusting plate is used for connecting a rear beam of the airfoil;
the rotating arm adjusts the position of the rotating shaft along the chord direction through relative rotation between the rotating arm and the supporting plate nut, and the coaxiality error of the omni-directional adjusting hinge caused by processing and assembling of composite materials is eliminated; by loosening the normal bolts in all the omnidirectional adjusting hinges, the rotating arm base moves along the strip-shaped hole, and the adjustment of the distance between the control surface and the airfoil surface is realized.
2. The light control surface and hinge structure suitable for solar unmanned aerial vehicle of claim 1, characterized in that: the outer layer of the PMI foam material of the main beam is wrapped with a +/-45-degree carbon fiber layer, and 0-degree carbon fiber layers are arranged between the top surface of the PMI foam material and the +/-45-degree carbon fiber layers and between the bottom surface of the PMI foam material and the +/-45-degree carbon fiber layers; the outer layers of the wing ribs, the front edges and the rear edges are all 0 degree/90 degree carbon fiber layers.
3. The light control surface and hinge structure suitable for solar unmanned aerial vehicle of claim 1, characterized in that: circular through holes are formed in the main beam in the unfolding direction at equal intervals and serve as mounting positions of the omnidirectional adjusting hinge, rectangular holes are formed in symmetrical positions of two sides of each circular through hole, and meanwhile, a rectangular hole is formed in the middle point position of the central connecting line of every two adjacent circular holes and serves as a rib connecting position of the main beam in the unfolding direction.
4. The light control surface and hinge structure suitable for solar unmanned aerial vehicle of claim 1, characterized in that:
firstly, designing a longitudinal section of a main beam to be rectangular; grooves are formed in the middle of the end faces of the left end and the right end of the main beam, and two protruding plugs are formed at the two ends of each groove and used for connecting wing ribs located at the end parts of the main beam;
secondly, designing wing ribs comprising front section wing ribs and rear section wing ribs; wherein, the front end of the rear wing rib is provided with a wedge-shaped groove; the front end of the front section rib is designed into an arc shape, the rear end of the front section rib is designed with a plug, the front part of the plug is a wedge-shaped part, and the rear part of the plug is a rectangular section with upper and lower parallel planes; the front wedge-shaped part of the plug of the front wing rib is matched with the wedge-shaped slot of the rear wing rib, so that the front wing rib and the rear wing rib are fixedly inserted; after the front section wing rib and the rear section wing rib are spliced, the upper plane and the lower plane of the rectangular section at the tail end of the plug, the front end surface of the front section wing rib and the rear end surface of the rear section wing rib are matched, so that two rectangular grooves are reserved at the upper and lower corresponding positions of the integral wing rib;
when the wing ribs and the main beam are installed, the wing ribs at the end part of the main beam are respectively matched, spliced and fixed with the two plugs at the end part of the main beam through the grooves at the upper and lower positions; the wing ribs in the unfolding direction of the main beam are respectively matched and fixed with the rectangular holes at the installation positions of the wing ribs through the grooves at the upper and lower positions; during assembly, the front section wing ribs are inserted into the rectangular holes in the main beam from the front side of the main beam, and then the rear section wing ribs and the front section wing ribs are in plug fit.
5. The light control surface and hinge structure suitable for solar unmanned aerial vehicle of claim 1, characterized in that: the front edge adopts a multi-section structure, and a section of front edge is arranged between the wing rib at the end part of the main beam and the wing rib adjacent to the main beam; the wing rib between the connecting positions of two adjacent omnidirectional adjusting hinges is fixed with a section of the front edge; the fixed position between the front edge and the wing rib only keeps the carbon fiber laying layer and has no PMI foam structure.
6. The light control surface and hinge structure suitable for solar unmanned aerial vehicle of claim 1, characterized in that: the positions of the rear edges corresponding to the wing ribs are not provided with PMI foam parts, and only the upper carbon fiber layer and the lower carbon fiber layer are reserved to form the insertion positions of the wing ribs.
7. The light control surface and hinge structure suitable for solar unmanned aerial vehicle of claim 1, characterized in that: the covering adopts the flexible covering of polyimide, and inside contains radial and latitudinal direction glass silk.
8. The light control surface and hinge structure suitable for solar unmanned aerial vehicle of claim 1, characterized in that: the relative rotation between the control surface and the airfoil surface is realized through an actuating system, and the actuating system comprises a steering engine, an actuating pull rod and a control surface rocker arm;
the control surface rocker arm is provided with two side rods which are parallel to each other and a connecting rod between the two side rods; the upper parts of the two side rods are respectively fixed on wing ribs on two sides of an omnidirectional adjusting hinge in the middle of the control surface through bolts, and the omnidirectional adjusting hinge in the middle of the control surface is positioned between the two side rods; the bottom end of one side rod is connected with a fisheye bearing at one end of the actuating pull rod through a bolt; the fisheye bearing at the other end of the actuating pull rod is connected with the rocker arm of the steering engine through a bolt to form an actuating relation; the steering engine drives the actuating pull rod and the control surface rocker arm to move, and the control surface is driven to actuate within a +/-45-degree range.
9. The light rudder face and hinge structure suitable for a solar unmanned aerial vehicle of claim 8, wherein: the ratio of the length of the rocker arm of the steering engine to the length of the rocker arm of the control surface is 1:1, so that the transmission ratio of the actuating system 4 is 1: 1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111459715.XA CN113955082B (en) | 2021-12-02 | 2021-12-02 | Light control surface and hinge structure suitable for solar unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111459715.XA CN113955082B (en) | 2021-12-02 | 2021-12-02 | Light control surface and hinge structure suitable for solar unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113955082A true CN113955082A (en) | 2022-01-21 |
| CN113955082B CN113955082B (en) | 2022-04-19 |
Family
ID=79472763
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111459715.XA Active CN113955082B (en) | 2021-12-02 | 2021-12-02 | Light control surface and hinge structure suitable for solar unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113955082B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476015A (en) * | 2022-03-28 | 2022-05-13 | 沃飞长空科技(成都)有限公司 | Unmanned aerial vehicle part quick detach mechanism and unmanned aerial vehicle |
| CN114750931A (en) * | 2022-04-14 | 2022-07-15 | 中国空气动力研究与发展中心空天技术研究所 | Front flap rudder surface structure of unmanned aerial vehicle |
| CN115571325A (en) * | 2022-09-29 | 2023-01-06 | 中国航天空气动力技术研究院 | Double-freedom-degree composite material hinge and preparation method thereof |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102014102283A1 (en) * | 2014-02-21 | 2015-08-27 | Airbus Operations Gmbh | An adjustment system for moving a flap on a wing of an aircraft, a method of moving a flap on a wing of an aircraft, and an aircraft having a wing and at least one flap movably disposed thereon |
| CN107444617A (en) * | 2017-07-13 | 2017-12-08 | 北京航空航天大学 | A kind of variable adaptive wing structure of camber |
| CN107512384A (en) * | 2017-08-01 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of elevator |
| CN109353489A (en) * | 2018-11-08 | 2019-02-19 | 浙江南洋科技股份有限公司 | A kind of multi-functional flap configurations of unmanned plane |
| CN110641696A (en) * | 2019-10-30 | 2020-01-03 | 南开大学 | Control mechanism of bionic hummingbird flapping wing unmanned aerial vehicle based on wing deformation |
| CN210592407U (en) * | 2019-08-19 | 2020-05-22 | 浙江大学 | Empennage device of ornithopter |
| CN112357058A (en) * | 2020-11-19 | 2021-02-12 | 航天彩虹无人机股份有限公司 | Steering engine mounting structure of unmanned aerial vehicle, unmanned aerial vehicle and mounting method of steering engine |
| CN113716027A (en) * | 2021-08-30 | 2021-11-30 | 北京航空航天大学 | Simple and easy undercarriage structure of photovoltaic aircraft light |
-
2021
- 2021-12-02 CN CN202111459715.XA patent/CN113955082B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102014102283A1 (en) * | 2014-02-21 | 2015-08-27 | Airbus Operations Gmbh | An adjustment system for moving a flap on a wing of an aircraft, a method of moving a flap on a wing of an aircraft, and an aircraft having a wing and at least one flap movably disposed thereon |
| CN107444617A (en) * | 2017-07-13 | 2017-12-08 | 北京航空航天大学 | A kind of variable adaptive wing structure of camber |
| CN107512384A (en) * | 2017-08-01 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of elevator |
| CN109353489A (en) * | 2018-11-08 | 2019-02-19 | 浙江南洋科技股份有限公司 | A kind of multi-functional flap configurations of unmanned plane |
| CN210592407U (en) * | 2019-08-19 | 2020-05-22 | 浙江大学 | Empennage device of ornithopter |
| CN110641696A (en) * | 2019-10-30 | 2020-01-03 | 南开大学 | Control mechanism of bionic hummingbird flapping wing unmanned aerial vehicle based on wing deformation |
| CN112357058A (en) * | 2020-11-19 | 2021-02-12 | 航天彩虹无人机股份有限公司 | Steering engine mounting structure of unmanned aerial vehicle, unmanned aerial vehicle and mounting method of steering engine |
| CN113716027A (en) * | 2021-08-30 | 2021-11-30 | 北京航空航天大学 | Simple and easy undercarriage structure of photovoltaic aircraft light |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476015A (en) * | 2022-03-28 | 2022-05-13 | 沃飞长空科技(成都)有限公司 | Unmanned aerial vehicle part quick detach mechanism and unmanned aerial vehicle |
| CN114476015B (en) * | 2022-03-28 | 2022-08-16 | 沃飞长空科技(成都)有限公司 | Unmanned aerial vehicle part quick detach mechanism and unmanned aerial vehicle |
| CN114750931A (en) * | 2022-04-14 | 2022-07-15 | 中国空气动力研究与发展中心空天技术研究所 | Front flap rudder surface structure of unmanned aerial vehicle |
| CN115571325A (en) * | 2022-09-29 | 2023-01-06 | 中国航天空气动力技术研究院 | Double-freedom-degree composite material hinge and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113955082B (en) | 2022-04-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113955082B (en) | Light control surface and hinge structure suitable for solar unmanned aerial vehicle | |
| CN105416565B (en) | Solar airplane | |
| US10640221B2 (en) | Wing airfoil stiffening for solar powered aircraft | |
| JP5230413B2 (en) | Integrated wingtip extension for jet transport aircraft and other types of aircraft | |
| US7913947B2 (en) | Compact tiltrotor pylon-conversion actuation system | |
| US10005541B2 (en) | Methods for providing a durable solar powered aircraft with a variable geometry wing | |
| CN101863306B (en) | Omnidirectional vectored thrust cycloidal propeller | |
| US10618632B2 (en) | Foldable rotor blade assembly | |
| CN102627146A (en) | Tilt rotor aircraft with fixed engine arrangement | |
| CN113371175A (en) | Fixed wing scouting and hitting integrated unmanned aerial vehicle model and design method thereof | |
| EP2886450B1 (en) | Aircraft control surface | |
| CN102849210A (en) | Spherical small unmanned aircraft | |
| CN109823514B (en) | Quick detachable fin structure of adjustable installation angle | |
| CN110654530A (en) | Variable camber wing structure with deformation feedback | |
| US11643196B1 (en) | Teetering propulsor assembly of an electric vertical takeoff and landing aircraft | |
| RU140499U1 (en) | UNMANNED AERIAL VEHICLE | |
| CN107097936B (en) | Unmanned aerial vehicle aileron driving structure | |
| US20100001121A1 (en) | System for tilting a power unit | |
| CN202481313U (en) | Flying wing aircraft with cycloidal rotor thrusters installed | |
| CN112009680A (en) | Double-duct fan vertical take-off and landing aircraft | |
| US8474747B2 (en) | Pivoting stabilising surface for aircraft | |
| CN221068457U (en) | Integrated power-landing gear nacelle for fixed-wing aircraft | |
| CN219029788U (en) | Light elevator | |
| CN115610640B (en) | Flapping wing folding mechanism for flapping wing aircraft | |
| CN112141317A (en) | Unmanned aerial vehicle and wing thereof |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |