CN110481754B - Simple covering cap structure for flexible covering opening of solar unmanned aerial vehicle - Google Patents
Simple covering cap structure for flexible covering opening of solar unmanned aerial vehicle Download PDFInfo
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- CN110481754B CN110481754B CN201910779830.1A CN201910779830A CN110481754B CN 110481754 B CN110481754 B CN 110481754B CN 201910779830 A CN201910779830 A CN 201910779830A CN 110481754 B CN110481754 B CN 110481754B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
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Abstract
The invention discloses a simple cover cap structure for a flexible skin opening of a solar unmanned aerial vehicle, which is designed aiming at the characteristic that the solar unmanned aerial vehicle in an adjacent space adopts a flexible film as a film covering material, and has an upper layer of carbon sheets, a middle layer of carbon sheets and a lower layer of carbon sheets, wherein the three layers of carbon sheets are bonded and fixed; the three layers of carbon sheets are provided with holes, the holes in the middle layer are designed to be slightly larger, and gaps are formed between the upper layer of carbon sheet and the lower layer of carbon sheet. Further through the trompil department that design flap inserted the intermediate level, through the quick assembly disassembly to the simple push-and-pull of flap, rotation operation completion flap, the flap that designs can not only be perfect with flexible skin laminating and the quality is extremely light. The simple opening cover structure for the opening of the flexible skin of the solar unmanned aerial vehicle can be widely applied to the simple opening structure of the flexible skin.
Description
Technical Field
The invention belongs to the field of aircraft design, and relates to a simple covering cap structure for a flexible covering opening of a solar unmanned aerial vehicle, in particular to a simple covering cap structure capable of meeting the requirement of a wing opening of a flexible covering.
Background
Most of airplanes have opening covers designed at the positions where equipment such as steering engines and the like are arranged on skins, so that the equipment is convenient to replace and maintain. Because the skin is generally a rigid material, the designed flap is also rigid, and can be disassembled and assembled through screws. But to near space solar energy unmanned aerial vehicle, in order to lighten structure weight, conveniently arrange solar cell panel as far as possible, can only adopt flexible film as covering material. Conventional rigid flaps are too bulky for such flexible skin aircraft and cannot be screwed to the skin. Conventional rigid flap structures cannot be used anymore for the opening of flexible-skin wings such as solar drones. There is a need to propose new flap structures suitable for use in lightweight flexible skin wings.
Disclosure of Invention
In order to solve the problem that the existing cover cap structure is not suitable for a light flexible skin wing, the invention provides a simple cover cap structure for a flexible skin opening of a solar unmanned aerial vehicle, the cover cap can be quickly assembled and disassembled through simple push-pull rotation operation, the cover cap can be perfectly attached to the flexible skin, and the weight is extremely light.
The invention discloses a simple covering cap structure for a flexible covering opening of a solar unmanned aerial vehicle.
The cover base comprises a lower-layer substrate, an intermediate-layer lap joint piece and an upper-layer clamping groove piece, and is arranged and fixed in a stacked mode from bottom to top and formed by curing one layer of carbon cloth brush glue.
The lower layer substrate and the upper layer clamping groove sheet are respectively provided with a lower layer round hole and an upper layer round hole with equal diameters; the middle layer lap joint sheet is provided with a middle layer hole which consists of a middle rectangle and semicircles at the left side and the right side of the rectangle; and the diameter of the semicircle at the two sides is larger than that of the lower layer round hole and the upper layer round hole, so that a clearance layer exists between the lower layer substrate and the upper layer clamping groove sheet. The upper layer circular hole is also provided with a clamping groove in the circumferential direction.
The detachable opening cover is circular, the diameter of the detachable opening cover is equal to the diameter of the semicircle at the two sides of the middle-layer hole, and the detachable opening cover is formed by adopting two layers of carbon cloth brushing glue for curing. The detachable cover is provided with a boss in the circumferential direction. After the detachable opening cover is inserted into the gap of the opening cover base, the detachable opening cover is rotated, and the boss and the clamping groove are matched to realize the fixed installation of the opening cover.
According to the invention, the cover cap base is bonded on the skin, one side of the detachable cover cap penetrates into the gap layer from the clamping groove, and then the detachable cover cap is horizontally pushed towards the penetrating side and inserted into the gap layer; the detachable cover cap is pressed downwards, so that the detachable cover cap is integrally arranged on one side of the gap layer and is horizontally pushed reversely, the other side of the detachable cover cap is inserted into the other side of the gap layer, the detachable cover cap is coaxial with the upper round hole, and the detachable cover cap is integrally and completely inserted into the gap layer; and finally, rotating the detachable opening cover to enable the boss to be clamped into the clamping groove, and completing the installation of the detachable opening cover.
The invention has the advantages that:
(1) the simple covering cap structure for the opening of the flexible skin of the solar unmanned aerial vehicle can finish quick assembly and disassembly of the covering cap through simple push-pull rotation operation, can be perfectly attached to the flexible skin, and is extremely light in weight.
(2) The simple covering cap structure for the opening of the flexible covering of the solar unmanned aerial vehicle is made of carbon fibers, the upper layer, the middle layer and the lower layer are respectively made of only one layer of carbon cloth, the detachable covering cap is made of only two layers of carbon cloth, the weight is extremely light, the flexibility is good, the flexible covering cap can be perfectly attached to the curved flexible covering, and the strength of the covering after the opening can be ensured. The solar unmanned plane is particularly suitable for the ultra-light airplanes such as the solar unmanned plane.
(3) The simple covering cap structure for the opening of the flexible covering of the solar unmanned aerial vehicle can be widely applied to the opening requirement of the flexible covering, and has great significance for realizing equipment maintainability of the solar unmanned aerial vehicle with strict weight control requirement.
Drawings
FIG. 1 is a schematic view of a simple flap structure for a flexible skin opening of a solar unmanned aerial vehicle according to the present invention;
FIG. 2 is a schematic structural view of a simple flap structure flap base for a flexible skin opening of a solar unmanned aerial vehicle according to the present invention;
FIG. 3 is a schematic plan view of the lower base of the flap;
FIG. 4 is a schematic plan view of the upper layer of the flap base with a notch;
FIG. 5 is a schematic plan view of the intermediate layer strap of the flap base;
FIG. 6 is a schematic view of the gap layer area in the base of the flap;
FIG. 7 is a schematic view of a detachable flap in a simple flap structure for a flexible skin opening of a solar unmanned aerial vehicle according to the present invention;
FIG. 8 is a schematic plan view of a detachable flap in the simple flap structure for a flexible skin opening of a solar unmanned aerial vehicle according to the present invention;
fig. 9 is a schematic view of the operation flow of the simple cover structure for covering and uncovering the flexible skin opening of the solar unmanned aerial vehicle.
In the figure:
1-flap base 2-removable flap 101-lower base
102-middle layer overlapping plate 103-upper layer clamping groove plate 101 a-lower layer round hole
102 a-middle hole 103 a-upper round hole 103 b-clamping groove A
103C-card slot B103 d-card slot C201-rib
202-convex platform
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The invention discloses a simple covering cap structure for a flexible covering opening of a solar unmanned aerial vehicle, which comprises a covering cap base 1 and a detachable covering cap 2, and is shown in figure 1.
As shown in fig. 2, the flap base 1 includes a lower substrate 101, an intermediate layer overlapping plate 102 and an upper layer slot plate 103, which are formed by curing a layer of carbon cloth brush glue, and have the same outer contour and are all similar to a playground shape, that is, an approximate ellipse is formed by a middle rectangle and semi-circles on the left and right sides of the rectangle; the diameter of the semicircle at the two sides of the rectangle at the middle part is 140mm, and the distance between the centers of the two semicircles is 20 mm. The lower-layer substrate 101, the middle-layer lap joint sheet 102 and the upper-layer slot sheet 103 are arranged from bottom to top, and the outer contour projections of the lower-layer substrate, the middle-layer lap joint sheet and the upper-layer slot sheet are overlapped on the horizontal plane.
As shown in fig. 3, 4 and 5, a lower circular hole 101a is formed in the lower substrate 101, and a circle center of the lower circular hole 101a is coaxial with a circle center of a right semicircle of the lower substrate 101 and has a diameter of 110 mm. The upper layer slot sheet 103 is provided with an upper layer round hole 103a which is coaxial with the lower layer round hole 101a and has the same diameter. The middle layer overlapping plate 102 is provided with a middle layer hole 102a, the shape of the middle layer hole 102a is the same as that of the middle layer overlapping plate 2, and the middle layer hole 102a is an approximately elliptical hole formed by a middle rectangle and semicircles on the left side and the right side of the rectangle; the diameter of the semicircle of the middle layer hole 102a is 125mm, and the distance between the centers of the semicircle on the left side and the right side is 20 mm; and the semi-circles on the left and right sides are coaxial with the semi-circles on the left and right sides of the shape of the interlayer overlapping sheet 102, respectively. On the upper layer slot sheet 103, 3 slots with a width of 6mm and a depth of 5mm are designed on the upper layer round hole 103a in the circumferential direction, namely a slot a103B, a slot B103C and a slot C103 d; draw-in groove A103B, draw-in groove B103C divide into with draw-in groove C103d and lie in upper round hole 103a circumference 0 degree, -90 degree, -180 degree position, 3 draw-in grooves lie in the front and back and the right side of upper round hole 103a respectively promptly, interval 90.
The upper surface and the lower surface of the middle layer lapping plate 102 with the structure are evenly coated with glue, and the lower layer substrate 101, the middle layer lapping plate 102 and the upper layer clamping groove plate 103 are fixedly bonded to form an integral cover base. Since the shape of the opening on the intermediate layer strap 102 is different from the shape of the opening on the lower layer substrate 101 and the upper layer card slot piece 103, a clearance layer is formed between the lower layer substrate 101 and the upper layer card slot piece 103, as shown in fig. 6, namely, a certain clearance layer is still left in the overlapping area of the lower layer substrate 101 and the upper layer card slot piece 103 except for the contact with the intermediate layer strap carbon sheet 2, and the thickness of the clearance layer is equal to the thickness of the intermediate layer strap 102.
As shown in fig. 7 and 8, the detachable flap 2 is circular and has a diameter of 125 mm; the upper surface of the detachable flap 2 is designed with ribs 201 with a height of about 2.5mm along one diameter direction thereof, so that the detachable flap 2 can be pushed, pulled and rotated conveniently. The peripheral positions of the detachable flap 2 in the circumferential direction of 0 degree and 90 degrees are provided with bosses 202 with the height of 2mm, the width of 6mm and the length of 4mm, namely, the two bosses 202 are respectively positioned at the right side and the front side of the detachable flap 2 at an interval of 90 degrees. The outer surfaces of the two bosses 202 are cambered surfaces and are used for being clamped into the two clamping grooves of the upper clamping groove sheet 103 so as to lock the detachable opening cover 2. Above-mentioned flap 2 that can dismantle adopts 2 layers of carbon cloth brush to glue the solidification and forms.
In the invention, the cover base is bonded on the skin, when the cover 2 is disassembled to cover, as shown in fig. 9, the left side of the disassembled cover 2 passes through the clamping groove A103B and the clamping groove C103d on the upper clamping groove piece 103, and the clamping groove B103C at the position of minus 90 degrees on the upper clamping groove piece 103 is ensured to be positioned on the perpendicular bisector of the connecting line of the two bosses 202 on the cover 4 when the left side of the disassembled cover 2 passes through the clamping groove A103B and the clamping; the detachable flap 2 is then pushed horizontally to the left, inserted into the left gap between the upper card slot sheet 103 and the lower base 101, and pushed into the end of the left gap, and most of the detachable flap is completely inserted into the gap between the upper card slot sheet 103 and the left end of the lower base 101. Immediately will dismantle flap 2 and push down slightly, make and to dismantle flap 2 and wholly arrange in between upper card slot piece 103 and lower floor's basement 101, and the flat push right, make two boss 202 that can dismantle on flap 2 insert upper card slot piece 103 and lower floor's basement 101 right side space in situ, it is coaxial with the round hole on upper card slot piece 103 and lower floor's basement 101 to dismantle flap 2 this moment, can dismantle that flap 2 is whole and two boss 202 on it has been filled in the space in between upper card slot piece 103 and lower floor's basement 101 completely.
Because the upper layer slot piece 103 has certain flexibility, and the height of the two bosses 202 on the detachable flap 2 is greater than the thickness of the gap layer between the upper layer slot piece 103 and the lower layer base 101, when the detachable flap 2 rotates 45 degrees anticlockwise, the two bosses 202 on the detachable flap 2 are ejected out from the gap layer and are respectively clamped into the slot A103B and the slot B103c on the upper layer slot piece 103, and the detachable flap 2 is fixed with the flap base at the moment, so that the upper cover operation is completed. After the upper cover is completed, the direction of the upper surface gluten strips 201 on the detachable cover 2 is designed to be the downwind direction, so that the aerodynamic performance of the wing cannot be influenced, and even the airflow separation can be favorably inhibited.
When the cover is taken, the detachable cover cap 2 is slightly pressed down and rotates clockwise by 45 degrees by utilizing the flexible deformation of the carbon sheet and the skin, so that two bosses on the detachable cover cap 2 are separated from the clamping grooves A103B and B103C on the upper clamping groove sheet 103 respectively and rotate into a gap layer between the upper clamping groove sheet 103 and the lower base 101, then the detachable cover cap 2 is horizontally pushed leftwards into the left side of the gap layer between the upper clamping groove sheet 103 and the lower base 101, at the moment, two bosses 202 on the detachable cover cap 2 already exit from the right side of the gap layer between the upper clamping groove sheet 103 and the lower base 101, then the right side of the detachable cover cap 2 is slightly upwards from the clamping grooves A103B and C103d on the upper clamping groove sheet 103, so that the right side of the detachable cover cap 2 is positioned above the upper clamping groove sheet 103, at the moment, the cover cap 4 is pulled rightwards, and the cover.
Claims (8)
1. The utility model provides a be used for flexible skin open-ended simple and easy flap structure of solar energy unmanned aerial vehicle, its characterized in that: comprises a cover pedestal and a detachable cover;
the cover base comprises a lower layer substrate, an intermediate layer lap joint piece and an upper layer clamping groove piece, and the lower layer substrate, the intermediate layer lap joint piece and the upper layer clamping groove piece are arranged in a stacked mode from bottom to top and are fixed; the lower layer substrate and the upper layer clamping groove sheet are respectively provided with a lower layer round hole and an upper layer round hole with equal diameters; the middle layer lap joint sheet is provided with a middle layer hole which consists of a middle rectangle and semicircles at the left side and the right side of the rectangle; the semicircular diameters of the two sides are larger than those of the lower layer circular hole and the upper layer circular hole, so that a clearance layer is formed between the lower layer substrate and the upper layer clamping groove sheet; the upper layer of round holes are circumferentially provided with clamping grooves; the lower layer round hole is coaxial with the upper layer round hole, and the lower layer round hole, the upper layer round hole are coaxial with a semicircle on one side of the middle layer hole;
the detachable opening cover is circular, and the diameter of the detachable opening cover is equal to the diameter of the semicircle at the two sides of the middle-layer hole; bosses are arranged on the periphery of the detachable opening cover; after the detachable opening cover is inserted into the gap of the opening cover base, the detachable opening cover is rotated, and the boss and the clamping groove are matched to realize the fixed installation of the opening cover.
2. The simple flap structure for a flexible skin opening of a solar drone according to claim 1, characterized in that: the lower-layer substrate, the middle-layer lap joint sheet and the upper-layer clamping groove sheet are formed by adopting a layer of carbon cloth brushing glue for curing; the detachable opening cover is formed by adopting two layers of carbon cloth brushing glue for curing.
3. The simple flap structure for a flexible skin opening of a solar drone according to claim 1, characterized in that: the diameters of the lower layer circular hole and the upper layer circular hole are both 110 mm; the diameter of the semicircle of the middle layer hole is 125mm, and the distance between the centers of the left and right semicircle is 20 mm.
4. The simple flap structure for a flexible skin opening of a solar drone according to claim 1, characterized in that: ribs are designed on the upper surface of the detachable opening cover along the diameter direction.
5. The simple flap structure for a flexible skin opening of a solar drone according to claim 1, characterized in that: the number of the clamping grooves is 3, and the clamping grooves are respectively positioned at the positions of 0 degree, 90 degrees and 180 degrees in the circumferential direction of the upper layer circular hole; the bosses are two and are respectively positioned at 0 degree and 90 degrees in the circumferential direction of the detachable cover cap.
6. The simple flap structure for a flexible skin opening of a solar drone according to claim 1, characterized in that: the width of the clamping groove is 6mm, and the depth of the clamping groove is 5 mm; the boss is 2mm high, wide 6mm, long 4mm, and the surface is the cambered surface.
7. The simple flap structure for the flexible skin opening of the solar unmanned aerial vehicle as claimed in claim 1, wherein: the cover cap base is adhered to the skin, one side of the detachable cover cap penetrates into the gap layer from the clamping groove, and then the detachable cover cap is horizontally pushed towards the penetrating side and inserted into the gap layer; the detachable cover cap is pressed downwards, so that the detachable cover cap is integrally arranged on one side of the gap layer and is horizontally pushed reversely, the other side of the detachable cover cap is inserted into the other side of the gap layer, the detachable cover cap is coaxial with the upper round hole, and the detachable cover cap is integrally and completely inserted into the gap layer; and finally, rotating the detachable opening cover to enable the boss to be clamped into the clamping groove, and completing the installation of the detachable opening cover.
8. The installation method of the simple flap structure for the flexible skin opening of the solar unmanned aerial vehicle as claimed in claim 7, is characterized in that: the direction of the detachable opening cover mounting opening and the ribs is the direction along the air flow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910779830.1A CN110481754B (en) | 2019-08-22 | 2019-08-22 | Simple covering cap structure for flexible covering opening of solar unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910779830.1A CN110481754B (en) | 2019-08-22 | 2019-08-22 | Simple covering cap structure for flexible covering opening of solar unmanned aerial vehicle |
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| CN110481754A CN110481754A (en) | 2019-11-22 |
| CN110481754B true CN110481754B (en) | 2021-04-09 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017186B (en) * | 2019-12-10 | 2023-03-24 | 中国特种飞行器研究所 | Flexible wing surface structure maintenance opening cover |
| CN114715376B (en) * | 2022-05-24 | 2022-09-06 | 北京航空航天大学 | Maintenance flap suitable for flexible skin wing |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6877695B2 (en) * | 2002-12-13 | 2005-04-12 | The Boeing Company | Hinge cover integration into door seal edges |
| US7661626B2 (en) * | 2005-10-28 | 2010-02-16 | The Boeing Company | Window assembly retaining system |
| CN206358346U (en) * | 2016-12-06 | 2017-07-28 | 成都飞机设计研究所制造中心 | A kind of microlight-type quick-release lid |
| CN108583842B (en) * | 2018-03-09 | 2020-07-14 | 彩虹无人机科技有限公司 | Composite material light cover mechanism for film skin |
| CN109533273B (en) * | 2018-11-28 | 2022-03-15 | 中国特种飞行器研究所 | Simple quick-release opening cover |
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