CN210083565U - Fixed wing unmanned aerial vehicle - Google Patents
Fixed wing unmanned aerial vehicle Download PDFInfo
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- CN210083565U CN210083565U CN201920797762.7U CN201920797762U CN210083565U CN 210083565 U CN210083565 U CN 210083565U CN 201920797762 U CN201920797762 U CN 201920797762U CN 210083565 U CN210083565 U CN 210083565U
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Abstract
The utility model is suitable for an aircraft technical field provides a fixed wing unmanned aerial vehicle, and the foam fuselage is equipped with horizontal loading board in it can strengthen the bulk strength, and then can guarantee intensity performance when lightening the quality, and 4 lateral walls departments that horizontal loading board extends to the parachute cabin form and hold the piece perpendicularly, and the equipartition has a plurality of fixed buckles on holding the piece inner wall perpendicularly, and then the parachute can be fixed on fixed buckle through the parachute cord; when this fixed wing unmanned aerial vehicle descends, the parachute expandes the back, and its effort of applying for the umbrella rope bears jointly on distributing to vertical load bearing spare and horizontal loading board through fixed the knot, can avoid local atress too big the condition of damage that appears. And, the top of every fixed knot still is equipped with at least one and is used for the guide of umbrella rope to pass to detain, and then every umbrella rope of fixing on fixed knot can pass the guide earlier and detain to by the guide knot guide, can avoid appearing the umbrella rope winding condition of twining each other, the fail safe nature is high.
Description
Technical Field
The utility model belongs to the technical field of the aircraft, concretely relates to fixed wing unmanned aerial vehicle.
Background
Unmanned aerial vehicle has can adapt to complicated adverse circumstances, does not need personnel to drive, can not cause the huge advantage of personnel's loss, has consequently obtained more and more extensive application. At present, unmanned aerial vehicle technology is used in the fields of remote sensing and measurement, aerial surveying and mapping, environmental reconnaissance and the like. Along with the increase of application, unmanned aerial vehicle technique is more and more hot, and unmanned type of aircraft tends to diversify.
Wherein fixed wing unmanned aerial vehicle occupies very big proportion in the unmanned aerial vehicle field, and fixed wing unmanned aerial vehicle has that flight distance is far away, the journey is big, flight advantage such as steady, safety.
Parachute landing recovery, as one of the common recovery modes of the fixed-wing unmanned aerial vehicle, is a recovery mode of controlling the fixed-wing unmanned aerial vehicle to fly above a recovery area, opening a parachute in the recovery area, decelerating and landing the parachute in a designated area. This recovery mode easy operation safety, middle-size and small-size fixed wing unmanned aerial vehicle is retrieved to mainly used.
Among the current fixed wing unmanned aerial vehicle, the parachute setting is in the parachute cabin, and the parachute is fixed at the local position of fuselage through the parachute line usually, and then opens the back when the parachute, and this local position bears great power easily and damages, especially when the fuselage adopts the material that intensity is not high to make.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome not enough among the above-mentioned prior art, provide a fixed wing unmanned aerial vehicle.
The utility model discloses a realize like this: fixed wing unmanned aerial vehicle, it includes:
a foam fuselage;
the parachute assembly comprises a parachute cabin, a parachute cabin cover and a parachute, wherein the parachute cabin cover is constructed on the foam machine body, one end of the parachute cabin cover is hinged with the machine body, the other end of the parachute cabin cover is matched with a steering engine arranged on the foam machine body, and the parachute cabin is square;
wherein, still be constructed horizontal loading board in the foam fuselage, horizontal loading spare extends to 4 lateral walls departments in umbrella cabin form and hold the piece perpendicularly, the equipartition has a plurality of fixed knots on the perpendicular loading spare inner wall, the parachute pass through the parachute cord with fixed knot is connected, every the top of fixed knot still is equipped with at least one and is used for the guide that the parachute cord passed is detained.
As a preferable aspect of the present invention, the vertical supporting member includes 4 side wall portions, and the inner wall of each side wall portion is provided with one of the fixing buckles.
As an optimal scheme of the utility model, the material of horizontal loading board is metal material.
As a preferred aspect of the present invention, the fixing buckle is welded to the vertical bearing member or formed integrally therewith.
As a preferred embodiment of the present invention, the guiding buckle is welded to the vertical bearing member or formed integrally therewith.
As a preferred scheme of the utility model, be constructed with airspeed head on the foam fuselage.
As a preferred scheme of the utility model, the lower extreme of foam fuselage is equipped with the guard plate.
As a preferred scheme of the utility model, still include horizontal fin, horizontal fin's material is foam, be equipped with horizontal strengthening rod in the horizontal fin.
As a preferred scheme of the utility model, still include vertical fin, vertical fin's material is foam, be equipped with perpendicular anchor strut in the vertical fin.
As a preferred scheme of the utility model, horizontal anchor strut with perpendicular anchor strut is metal pole or carbon pole.
The utility model provides a pair of fixed wing unmanned aerial vehicle, for prior art, it can strengthen bulk strength to be equipped with horizontal loading board in the foam fuselage, and then can guarantee intensity performance when lightening the quality, and 4 lateral walls departments that horizontal loading board extends to the parachute cabin form and hold the carrier perpendicularly, the equipartition has a plurality of fixed knots on the perpendicular carrier inner wall that holds, and then the parachute can be fixed on fixed knot through the parachute cord, when this fixed wing unmanned aerial vehicle descends, steering wheel work, open the parachute cabin lid, make the parachute extend to outside in the parachute cabin with launching this fixed wing unmanned aerial vehicle of slowly descending, wherein, the parachute expandes the back, its effort of applying for the parachute cord, the fixed knot of accessible distributes and holds jointly to bearing on perpendicular carrier and the horizontal loading board, can avoid local atress to appear the damage condition excessively. And, every still be equipped with at least one above the fixed knot and be used for the umbrella rope passes the guide is detained, and then every umbrella rope of fixing on the fixed knot can pass the guide knot earlier to by the guide knot guide, can avoid appearing the umbrella rope winding condition of twining each other, safe and reliable is high.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
The drawings are only intended to illustrate and explain the present invention and do not limit the scope of the invention.
Fig. 1 is a schematic structural diagram of a fixed-wing drone provided by an embodiment of the present invention;
fig. 2 is a schematic structural cross-sectional view of a fixed-wing drone provided by an embodiment of the present invention;
some of the reference numerals describe:
1. a foam fuselage;
11. an umbrella cabin; 12. an umbrella canopy; 13. a steering engine; 14. a horizontal bearing plate; 15. a vertical carrier; 151. a fixing buckle; 152. a guide buckle; 16. a protection plate;
2. a horizontal rear wing;
3. a vertical tail;
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Examples
Referring to fig. 1-2, the present embodiment provides a fixed wing drone, which includes:
a foam fuselage 1;
the parachute assembly comprises a parachute cabin 11, a parachute cabin cover 12 and a parachute, wherein the parachute cabin cover 11 is constructed on the foam fuselage 1, one end of the parachute cabin cover 12 is hinged with the foam fuselage 1, the other end of the parachute cabin cover is matched with a steering engine 13 arranged on the fuselage 1, and the parachute cabin 11 is square;
wherein, still construct horizontal loading board 14 in the foam fuselage 1, horizontal loading board 14 extends to 4 lateral walls departments of umbrella cabin 11 form and hold the thing 15 perpendicularly, the equipartition has a plurality of fixed knots 151 on the perpendicular thing 15 inner wall that holds, the parachute pass through the parachute cord with fixed knot 151 is connected, every the top of fixed knot 151 still is equipped with at least one and is used for the guide that the parachute cord passed is detained 152.
In the fixed wing unmanned aerial vehicle, in order to reduce the overall mass, the foam body 1, the horizontal tail wing 2 and the vertical tail wing 3 are made of foam;
furthermore, be equipped with horizontal loading board 14 in foam fuselage 1 and can strengthen the bulk strength, and then can guarantee the intensity performance when lightening the quality, and 4 lateral walls departments that horizontal loading board 14 extends to parachute bay 11 form vertical load bearing spare 15, the equipartition has a plurality of fixed buckles 151 on vertical load bearing spare 15 inner wall, and then the parachute can be fixed on fixed buckle 151 through the parachute cord, when this fixed wing unmanned aerial vehicle descends, steering wheel 13 work, open parachute bay lid 12, make the parachute extend to outside in parachute bay 11 with the expansion slowly descend this fixed wing unmanned aerial vehicle, wherein, after the parachute expandes, its effort of applying for the parachute cord, accessible fixed buckle 151 distributes and bears jointly on vertical load bearing spare 15 and horizontal loading board 14, can avoid local atress to appear the damage condition too greatly.
And, each said fixed buckle 151 is equipped with at least one guide buckle 152 used for the said umbrella rope to pass above, and then each umbrella rope fixed on fixed buckle 151 can pass the guide buckle 152 first, in order to be guided by the guide buckle 152, can avoid the umbrella rope to twine the situation intertwined, safe and reliable is high.
As a preferred embodiment of the present invention, the vertical supporting member 15 includes 4 side wall portions 15a, and the inner wall of each side wall portion 15a is provided with one of the fixing buckles 151.
In the above, specifically, each side wall portion 15a is provided with one fixing buckle 151, so that after the parachute is opened, each parachute line is stressed uniformly.
As a preferred embodiment of the present invention, the material of the horizontal bearing plate 14 is a metal material.
Specifically, the horizontal carrier plate 14 made of a metal material has high strength and the like, specifically, the horizontal carrier plate 14 may be made of a light material such as an aluminum material, and the horizontal carrier plate 14 may be manufactured by embedding the foam body 1 in a mold in advance when the mold is formed.
As a preferred embodiment of the present invention, the fixing buckle 151 and the vertical bearing member 15 are welded or integrally formed.
As a preferred embodiment of the present invention, the guiding buckle 152 is welded or integrally formed with the vertical supporting member 15.
In the foregoing, the welding connection mode is more reliable, the cost is lower, the integrated forming is relatively simple in production process, the production efficiency is higher, and the concrete situation can be determined according to the actual production situation.
As a preferred scheme of the utility model, be constructed with airspeed tube on the foam fuselage 1.
In the above, the pitot tube is also called pitot tube, total pressure tube, total-static pressure tube. The device senses the total pressure (also called full pressure) and static pressure of the airflow and transmits the measured pressure data to an atmospheric data computer and an aerometer. Mainly used for measuring the flying speed and simultaneously has other multiple functions.
As a preferred scheme of the utility model, the lower extreme of foam fuselage 1 is equipped with guard plate 16.
In the aforesaid, it is concrete, guard plate 16 can play the guard action, and especially this fixed wing unmanned aerial vehicle can avoid foam fuselage 1 directly to land and cause the damage when descending, and is concrete, and guard plate 16 can adopt the plastic material to make, and then guard plate 16 can be the lower extreme through adhesive connection at foam fuselage 1.
As a preferred scheme of the utility model, still include horizontal fin, horizontal fin 2's material is foam, be equipped with horizontal strengthening rod in the horizontal fin 2.
As a preferred scheme of the utility model, still include vertical fin, vertical fin 3's material is foam, be equipped with perpendicular anchor strut in the vertical fin 3.
As a preferred scheme of the utility model, horizontal anchor strut with perpendicular anchor strut is metal pole or carbon pole.
In the foregoing, concrete, the material of horizontal tail 2 and vertical tail 3 adopts foam, can reduce this fixed wing unmanned aerial vehicle's whole quality relatively, and then sets up horizontal strengthening rod and vertical strengthening rod in it, can increase its intensity, and then can guarantee its intensity performance when reducing the quality, and is concrete, horizontal strengthening rod and vertical strengthening rod can be buried underground in the mould in advance when horizontal tail 2 and vertical tail 3 mould shaping and form in order to make.
In conclusion, the fixed wing unmanned aerial vehicle that this embodiment provided, be equipped with horizontal loading board 14 in the foam fuselage 1 and can strengthen the bulk strength, and then can guarantee the intensity performance when lightening the quality, and 4 lateral walls departments that horizontal loading board 14 extends to parachute cabin 11 form and hold a 15 perpendicularly, the equipartition has a plurality of fixed buckles 151 on the perpendicular 15 inner walls that hold a ware, and then the parachute can be fixed on fixed buckle 151 through the parachute cord, when this fixed wing unmanned aerial vehicle descends, steering wheel 13 work, open parachute cabin lid 12, make the parachute extend to outside in the parachute cabin 11 in order to expand this fixed wing unmanned aerial vehicle that slowly descends, wherein, after the parachute expandes, its effort of applying for the parachute cord, accessible fixed buckle 151 distributes and holds jointly on perpendicular loading board 15 and horizontal loading board 14, can avoid local atress too big emergence damage condition. And, each said fixed buckle 151 is equipped with at least one guide buckle 152 used for the said umbrella rope to pass above, and then each umbrella rope fixed on fixed buckle 151 can pass the guide buckle 152 first, in order to be guided by the guide buckle 152, can avoid the umbrella rope to twine the situation intertwined, safe and reliable is high.
Unless defined otherwise, technical or scientific terms used herein shall have the ordinary meaning as understood by those of ordinary skill in the art to which the invention belongs. The use of "first," "second," and similar terms in the description herein do not denote any order, quantity, or importance, but rather the terms are used to distinguish one element from another. Also, the use of the terms "a," "an," or "the" and similar referents do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprising" or "comprises", and the like, means that the element or item listed before the word covers the element or item listed after the word and its equivalents, but does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.
The geometric position relations of the horizontal, vertical, concentric and the like in the utility model are only limited under ideal conditions, and the deviation of 5 percent in the field is allowable in consideration of multiple actual conditions of technology, processing precision, cost and technical effect, and is also the actual condition of limiting the geometric position relations of the invention.
Meanwhile, the following points need to be explained:
(1) unless otherwise defined, in the embodiments and drawings of the present invention, the same reference numerals represent the same meanings.
(2) In the drawings of the embodiments of the present invention, only the structures related to the embodiments of the present invention are referred to, and other structures may refer to general designs.
(3) In the drawings, which are used to describe embodiments of the invention, the thickness of layers or regions are exaggerated for clarity. It will be understood that when an element such as a layer, film, region, or substrate is referred to as being "on" or "under" another element, it can be "directly on" or "under" the other element or intervening elements may be present.
(4) Features of the present invention may be combined with each other in the same embodiment and in different embodiments without conflict.
The above description is only exemplary of the present invention and should not be construed as limiting the present invention, and any modification, equivalent replacement or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. Fixed wing unmanned aerial vehicle, its characterized in that includes:
a foam fuselage;
the parachute assembly comprises a parachute cabin, a parachute cabin cover and a parachute, wherein the parachute cabin cover is constructed on the foam machine body, one end of the parachute cabin cover is hinged with the machine body, the other end of the parachute cabin cover is matched with a steering engine arranged on the foam machine body, and the parachute cabin is square;
wherein, still be constructed horizontal loading board in the foam fuselage, horizontal loading spare extends to 4 lateral walls departments in umbrella cabin form and hold the piece perpendicularly, the equipartition has a plurality of fixed knots on the perpendicular loading spare inner wall, the parachute pass through the parachute cord with fixed knot is connected, every the top of fixed knot still is equipped with at least one and is used for the guide that the parachute cord passed is detained.
2. A fixed wing drone according to claim 1, wherein the vertical carrier comprises 4 side walls, one of the retaining buckles being provided on the inner wall of each side wall.
3. The fixed-wing drone of claim 2, wherein the horizontal carrier plate is made of a metallic material.
4. The fixed-wing drone of claim 3, wherein the retaining buckle is welded or integrally formed with the vertical carrier.
5. The fixed-wing drone of claim 3, wherein the guide buckles are welded or integrally formed with the vertical carrier.
6. The fixed wing drone of claim 1, wherein the foam fuselage is constructed with a pitot tube thereon.
7. The fixed wing drone of claim 1, wherein the lower end of the foam fuselage is provided with a protective plate.
8. The fixed-wing drone of claim 1, further comprising a horizontal tail, the horizontal tail being made of foam, the horizontal tail having horizontal reinforcing rods therein.
9. The fixed-wing drone of claim 8, further comprising a vertical tail, the vertical tail being made of foam, the vertical tail having vertical reinforcing rods disposed therein.
10. The fixed-wing drone of claim 9, wherein the horizontal and vertical reinforcing rods are metal or carbon rods.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920797762.7U CN210083565U (en) | 2019-05-29 | 2019-05-29 | Fixed wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920797762.7U CN210083565U (en) | 2019-05-29 | 2019-05-29 | Fixed wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210083565U true CN210083565U (en) | 2020-02-18 |
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ID=69480898
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920797762.7U Active CN210083565U (en) | 2019-05-29 | 2019-05-29 | Fixed wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210083565U (en) |
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2019
- 2019-05-29 CN CN201920797762.7U patent/CN210083565U/en active Active
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