CN116986036A - Recovery system of fixed wing unmanned aerial vehicle - Google Patents
Recovery system of fixed wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN116986036A CN116986036A CN202311258204.0A CN202311258204A CN116986036A CN 116986036 A CN116986036 A CN 116986036A CN 202311258204 A CN202311258204 A CN 202311258204A CN 116986036 A CN116986036 A CN 116986036A
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- wing
- air bag
- bearing
- belt
- fixed
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- 238000011084 recovery Methods 0.000 title claims abstract description 34
- 238000004804 winding Methods 0.000 claims description 10
- 238000013016 damping Methods 0.000 claims description 5
- 238000005096 rolling process Methods 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 2
- 230000001012 protector Effects 0.000 claims 1
- 238000013461 design Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003814 drug Substances 0.000 description 1
- 229940079593 drug Drugs 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
- B64U70/83—Vertical take-off or landing, e.g. using rockets using parachutes, balloons or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
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- 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
Abstract
The application discloses a recovery system of a fixed-wing unmanned aerial vehicle, which comprises a fuselage, wings, a bearing belt, a parachute, an air bag and an air bag locking and unlocking structure, wherein the fuselage is provided with a first locking mechanism and a second locking mechanism; the wing is arranged in the middle of the fuselage; the upper part of the front end of the machine body is provided with an umbrella bin, an opening of the umbrella bin is covered by an umbrella bin cover plate, the umbrella bin is arranged in front of the wing, the machine body is provided with two bearing areas, one bearing area is arranged in the umbrella bin, the other bearing area is arranged at the rear of the wing, one end of the bearing belt is connected with one bearing area, the other end of the bearing belt is connected with the other bearing area, the parachute is arranged in the umbrella bin, and the parachute is connected with the bearing belt; the lower part of the machine body is provided with two air bag cabins which are arranged at intervals from front to back, the opening of each air bag cabin is covered by an air bag cabin cover plate, and the air bags are arranged in the air bag cabins. The application can realize automatic opening of the air bag cabin cover plate by matching the bearing belt and the air bag locking and unlocking structure without independently arranging an electric control cabin opening mechanism for opening the air bag, and has smart whole structure, low cost and good reliability.
Description
Technical Field
The application relates to the field of aircrafts, in particular to a recovery system of a fixed wing unmanned aerial vehicle.
Background
The fixed wing drone take-off mode is usually launched by a rocket, which is not provided with landing gear means, and therefore is usually recovered by parachute and balloon cooperation at the time of recovery.
In the prior art, the opening of the parachute and the opening of the air bag cabin are mutually independent, the opening of the air bag cabin is controlled by an independent electric control structure, so that the cost is increased, and in addition, the fixed wing target aircraft is easy to touch the ground to cause damage when falling.
Disclosure of Invention
The application aims at the problems and overcomes at least one defect, and provides a recovery system of a fixed-wing unmanned aerial vehicle.
The technical scheme adopted by the application is as follows:
a recovery system of a fixed-wing unmanned aerial vehicle comprises a body, wings, a bearing belt, a parachute, an air bag and an air bag locking and unlocking structure;
the wing is arranged in the middle of the fuselage;
the upper part of the front end of the machine body is provided with an umbrella bin, an opening of the umbrella bin is covered by an umbrella bin cover plate, the umbrella bin is arranged in front of the wing, the machine body is provided with two bearing areas, one bearing area is arranged in the umbrella bin, the other bearing area is arranged at the rear of the wing, one end of the bearing belt is connected with one bearing area, the other end of the bearing belt is connected with the other bearing area, the parachute is arranged in the umbrella bin, and the parachute is connected with the bearing belt;
the lower part of the machine body is provided with two air bag cabins which are arranged at intervals in the front-back direction, the opening of each air bag cabin is covered by an air bag cabin cover plate, and the air bags are arranged in the air bag cabins;
the airbag locking and unlocking structure includes:
the convex block is positioned on the air bag cabin cover plate and is provided with an inserting hole;
the movable hole is positioned in the bearing area;
the connecting piece is arranged on the movable hole in an up-down movable mode, the lower end of the connecting piece is provided with a first limiting part, the first limiting part is located below the movable hole and used for limiting the maximum position of upward movement of the connecting piece, the upper end of the connecting piece is used for being connected with the bearing belt, and the connecting piece can be driven to move upwards through the bearing belt after the parachute is opened;
the fixed seat is fixed with the machine body;
the locking pin is slidably mounted on the fixed seat and provided with a first convex part, and the locking pin is used for extending into the jack to limit the air bag cabin cover plate;
the spring is sleeved on the locking pin, one end of the spring is in abutting joint with the fixing seat, and the other end of the spring is in abutting joint with the first convex part and is used for enabling the locking pin to keep a state of being inserted into the jack;
and one end of the pull rope is connected with the locking pin, the other end of the pull rope is connected with the connecting piece, and when the connecting piece moves upwards, the connecting piece drives the locking pin to be separated from the jack through the pull rope.
When the parachute is recovered, the force-bearing belt can be driven to move upwards after being unfolded, the force-bearing belt is connected with the connecting piece, namely the connecting piece can be driven to move upwards, the locking pin can be driven to be separated from the jack through the pull rope when the connecting piece moves upwards, and at the moment, the cover plate of the air bag cabin can be pushed open under the action of the elastic force of the air bag, so that the air bag can come out of the air bag cabin; the application can realize automatic opening of the air bag cabin cover plate by matching the bearing belt and the air bag locking and unlocking structure without independently arranging an electric control cabin opening mechanism for opening the air bag, and has smart whole structure, low cost and good reliability.
In practical use, the opening mode of the umbrella bin is not the application point of the application, and the existing design can be adopted according to the needs, such as the structure of patent document with the publication number of CN 116062173A of I department, and the like.
Each air bag bin is correspondingly provided with an air bag locking and unlocking structure, a connecting piece of one air bag locking and unlocking structure is connected with the first end of the bearing belt, and a connecting piece of the other air bag locking and unlocking structure is connected with the second end of the bearing belt.
In an embodiment of the application, the locking pin further has a second protrusion, and the first protrusion and the second protrusion are respectively located at two sides of the fixing seat.
The second protrusion is used for limiting the position of the locking pin and preventing the locking pin from being completely separated from the fixed seat.
In an embodiment of the application, the connecting piece further has a second limiting portion located at an upper end of the movable hole, and the second limiting portion is used for limiting a maximum position of the connecting piece moving downward.
In one embodiment of the present application, the upper part of the machine body has a groove into which the bearing belt is inserted.
In one embodiment of the application, after the airbag is inflated and deployed, the end portion of the airbag is provided with an upward turned wing protection portion, and the wing protection portion is used for being semi-covered at the outer end of the wing.
The fixed wing target aircraft is easy to touch the ground to cause damage when falling, and the air bags are provided with wing protection parts so as to protect the outer ends of the wings.
In one embodiment of the present application, the wing includes a first wing portion and a second wing portion, the first wing portion is fixed to the fuselage, the second wing portion is capable of sliding relative to the first wing portion, and the second wing portion has a retracted state in which the first wing portion is retracted and an operating state in which the second wing portion is extended.
The wing is unfolded in a large length, so that the wing is easy to collide with the ground and damage due to the inclination of the landing posture during recovery, and in addition, a larger air bag is required for forming the air bag into a wing protection part, so that the requirement on the space of a fuselage is high. The wing comprises the first wing part and the second wing part, and the second wing part can retract into the first wing part, so that the second wing part can retract into the first wing part during recovery, the length of the wing is effectively reduced, the collision probability of the wing and the ground is reduced, and the airbag with the wing protection part is convenient to set.
In one embodiment of the present application, the switching mechanism is further provided for switching the state of the second wing, and the switching mechanism includes two racks and a first rotating member, wherein one of the two racks is a first rack, and the other is a second rack;
the first racks are arranged on the machine body and one of the first wing parts in a sliding manner, driving teeth are arranged on one end side part of each first rack, and the first racks are fixed with one of the second wing parts;
the second racks are arranged on the machine body and the other first wing part in a sliding manner, driving teeth are arranged on one end side part of each second rack, the second racks are fixed with the other second wing part, and the driving teeth of the second racks are arranged opposite to the driving teeth of the first racks;
the first rotating part is arranged on the machine body in a rotating mode, the first transmission part is provided with a driving gear, the driving gear is meshed with the driving teeth of the first rack and the driving teeth of the second rack at the same time, and when the first rotating part rotates, the first rack and the second rack can be driven to be close to each other or far away from each other.
During practical use, the first rotating piece is driven to rotate so as to drive the two racks to be close to or far away from each other, and when the two racks are close to each other, the second wing part can be switched from the working state to the recovery state.
In one embodiment of the present application, the first rotating member further includes a first conical tooth coaxially disposed with the driving gear, the switching mechanism further includes a second rotating member and a driving belt, wherein,
the second rotating piece is rotatably arranged on the machine body and is provided with a second conical tooth and a rolling wheel which are coaxially arranged, the second conical tooth is meshed with the first conical tooth, and the rolling wheel can drive the driving gear to rotate through the meshing of the two conical teeth and the first conical tooth when rotating, so that the two racks are driven to move;
the driving belt is wound on the winding wheel, one end of the driving belt is connected with the middle of the bearing belt, the driving belt can be driven to move outwards through the bearing belt after the parachute is opened, the driving belt further drives the winding wheel to rotate, and finally the second wing part is switched to a recovery state.
The unmanned aerial vehicle has the weight of at least hundreds of kilograms, after the parachute is opened, the acting force applied to the bearing belt and the driving belt is very large, and the power for switching the second wing part to the retraction state can be completely improved.
In one embodiment of the present application, the rotation axis of the winding wheel is horizontally arranged;
the first wing part is internally provided with a track matched with the corresponding rack, and a damping structure is arranged between the track and the rack.
The provision of the damping structure prevents the second wing section from retracting into the first wing section in normal operating conditions.
In one embodiment of the application, the device further comprises an inflation mechanism positioned in the body for inflating the air bag.
The beneficial effects of the application are as follows: when the parachute is recovered, the force-bearing belt can be driven to move upwards after being unfolded, the force-bearing belt is connected with the connecting piece, namely the connecting piece can be driven to move upwards, the locking pin can be driven to be separated from the jack through the pull rope when the connecting piece moves upwards, and at the moment, the cover plate of the air bag cabin can be pushed open under the action of the elastic force of the air bag, so that the air bag can come out of the air bag cabin; the application can realize automatic opening of the air bag cabin cover plate by matching the bearing belt and the air bag locking and unlocking structure without independently arranging an electric control cabin opening mechanism for opening the air bag, and has smart whole structure, low cost and good reliability.
Drawings
FIG. 1 is a schematic view of a recovery system of a fixed wing drone;
FIG. 2 is a front view of the recovery system of the fixed wing drone after the parachute is opened;
FIG. 3 is a rear view of the recovery system of the fixed wing drone after the parachute is opened;
FIG. 4 is a partial schematic view of the recovery system of the fixed wing drone after the parachute is opened;
FIG. 5 is a schematic view of an airbag lock unlock configuration;
FIG. 6 is a schematic diagram of a switching mechanism;
fig. 7 is a schematic view of the switching mechanism after the drive belt is pulled upward.
The reference numerals in the drawings are as follows:
1. a body; 11. an umbrella bin; 12. an umbrella bin cover plate; 13. an airbag cabin cover plate; 131. a bump; 1311. a jack; 14. a groove; 2. a wing; 21. a first wing section; 22. a second wing section; 3. a force-bearing belt; 4. a parachute; 5. an air bag; 51. a wing protection part; 61. a force bearing area; 611. a movable hole; 62. a connecting piece; 621. a first limit part; 622. a second limit part; 63. a fixing seat; 64. a locking pin; 641. a first convex portion; 642. a second convex portion; 65. a spring; 66. a pull rope; 7. a switching mechanism; 71. a first rack; 711. a drive tooth; 72. a second rack; 73. a first rotating member; 731. a drive gear; 732. a first conical tooth; 74. a second rotating member; 741. a second conical tooth; 742. a winding wheel; 8. and driving the belt.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. It will be apparent that the described embodiments are some, but not all, embodiments of the application. The components of the embodiments of the present application generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
In the description of the present application, it should be noted that, the azimuth or positional relationship indicated by the terms "inner", "outer", etc. are based on the azimuth or positional relationship shown in the drawings, or the azimuth or positional relationship that is commonly put in use of the product of this application, are merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and therefore should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In the description of the present application, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed", "connected" and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected or integrally connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application will be understood in specific cases by those of ordinary skill in the art.
The present application will be described in detail with reference to the accompanying drawings.
As shown in fig. 1-5, a recovery system of a fixed-wing unmanned aerial vehicle comprises a machine body 1, wings 2, a bearing belt 3, a parachute 4, an air bag 5 and an air bag 5 locking and unlocking structure;
the wing 2 is arranged in the middle of the fuselage 1;
the upper part of the front end of the machine body 1 is provided with an umbrella bin 11, an opening of the umbrella bin 11 is covered by an umbrella bin cover plate 12, the umbrella bin 11 is arranged in front of the wing 2, the machine body 1 is provided with two bearing areas 61, one bearing area 61 is positioned in the umbrella bin 11, the other bearing area 61 is positioned behind the wing 2, one end of the bearing belt 3 is connected with one bearing area 61, the other end is connected with the other bearing area 61, the parachute 4 is positioned in the umbrella bin 11, and the parachute 4 is connected with the bearing belt 3;
the lower part of the machine body 1 is provided with two air bag cabins (the inner side of an air bag cabin cover plate 13 is omitted from the figure) which are arranged at intervals back and forth, the openings of the air bag cabins are covered by the air bag cabin cover plate 13, and the air bag 5 is arranged in the air bag cabin;
as shown in fig. 5, the airbag 5 locking and unlocking structure includes:
a projection 131 on the airbag housing cover 13, the projection 131 having a receptacle 1311;
a movable hole 611 located in the bearing area 61;
the connecting piece 62 is movably arranged on the movable hole 611 up and down, the lower end of the connecting piece 62 is provided with a first limiting part 621, the first limiting part 621 is positioned below the movable hole 611 and used for limiting the maximum upward movement position of the connecting piece 62, the upper end of the connecting piece 62 is used for being connected with the bearing belt 3, and the parachute 4 can drive the connecting piece 62 to move upward through the bearing belt 3 after being opened;
a fixing base 63 fixed to the body 1;
a locking pin 64 slidably mounted on the fixed seat 63, the locking pin 64 having a first protrusion 641, the locking pin 64 being adapted to extend into the receptacle 1311 to define the airbag cover 13;
a spring 65 which is sleeved on the locking pin 64, wherein one end of the spring 65 is abutted against the fixed seat 63, and the other end is abutted against the first convex part 641, so that the locking pin 64 is kept in a state of being inserted into the jack 1311;
and a pull cord 66, one end of which is connected to the locking pin 64, and the other end of which is connected to the connecting member 62, wherein when the connecting member 62 moves upward, the connecting member 62 drives the locking pin 64 to disengage from the insertion hole 1311 through the pull cord 66.
When the parachute 4 is recovered, the force-bearing belt 3 can be driven to move upwards after being unfolded, the force-bearing belt 3 is connected with the connecting piece 62, namely the connecting piece 62 can be driven to move upwards, the locking pin 64 can be driven to be separated from the jack 1311 through the pull rope 66 when the connecting piece 62 moves upwards, at the moment, the airbag cabin cover plate 13 can be pushed open under the action of the elastic force of the airbag 5, and therefore the airbag 5 can come out of the airbag cabin; according to the application, an electric control cabin opening mechanism for opening the air bag 5 is not required to be independently arranged, and the air bag cabin cover plate 13 can be automatically opened through the cooperation of the bearing belt 3 and the air bag 5 locking and unlocking structure, so that the whole structure is ingenious, the cost is low, and the reliability is good.
In practical use, the opening mode of the umbrella housing 11 is not an application point of the present application, and an existing design such as a structure of patent document with publication number CN 116062173A of my department can be adopted according to needs.
Each airbag cabin corresponds to an airbag 5 locking and unlocking structure, a connecting piece 62 of one airbag 5 locking and unlocking structure is connected with the first end of the bearing belt 3, and a connecting piece 62 of the other airbag 5 locking and unlocking structure is connected with the second end of the bearing belt 3.
As shown in fig. 5, in the present embodiment, the locking pin 64 further has a second protrusion 642, and the first protrusion 641 and the second protrusion 642 are respectively located at two sides of the fixing base 63. The second projection 642 serves to define a position of the locking pin 64, preventing the locking pin 64 from being completely separated from the fixing base 63.
As shown in fig. 5, in the present embodiment, the connecting member 62 further has a second limiting portion 622 located at an upper end of the movable hole 611, and the second limiting portion 622 is used to limit a maximum position of the downward movement of the connecting member 62.
As shown in fig. 1 and 4, in this embodiment, the upper part of the body 1 has a recess 14 into which the carrier tape 3 is inserted.
As shown in fig. 3 and 4, in the present embodiment, after the airbag 5 is inflated and deployed, the end of the airbag 5 has an upward turned wing protecting portion 51, and the wing protecting portion 51 is used to half-wrap at the outer end of the wing 2. The fixed wing drone is easy to touch the ground to cause damage when the wing 2 falls, and the airbag 5 is provided with the wing protection part 51 to protect the outer end of the wing 2.
As shown in fig. 1, 3 and 4, in the present embodiment, the wing 2 includes a first wing part 21 and a second wing part 22, the first wing part 21 is fixed to the fuselage 1, the second wing part 22 is capable of sliding relative to the first wing part 21, and the second wing part 22 has a retracted state in which the first wing part 21 is retracted and an operating state in which the first wing part 21 is extended.
The wing 2 is large in deployment length, is easily damaged by collision with the ground due to the inclination of the landing posture during recovery, and requires a larger airbag 5 to form the wing protecting portion 51, thereby requiring a large space for the fuselage 1. The wing 2 of the application comprises the first wing part 21 and the second wing part 22, and the second wing part 22 can retract into the first wing part 21, so that after the arrangement, the second wing part 22 can retract into the first wing part 21 during recovery, thereby effectively reducing the length of the wing 2, reducing the collision probability of the wing 2 and the ground, and facilitating the arrangement of the air bag 5 with the wing protection part 51.
As shown in fig. 6 and 7, in the present embodiment, the switching mechanism 7 for switching the state of the second wing 22 is further included, and the switching mechanism 7 includes two racks, one of which is a first rack 71 and the other of which is a second rack 72, and a first rotating member 73;
the first rack 71 is slidably arranged on the machine body 1 and one of the first wing parts 21, one end side part of the first rack 71 is provided with a driving tooth 711, and the first rack 71 is fixed with one of the second wing parts 22;
the second rack 72 is slidably arranged on the machine body 1 and the other first wing part 21, one end side part of the second rack 72 is provided with a driving tooth 711, the second rack 72 is fixed with the other second wing part 22, and the driving tooth 711 of the second rack 72 is opposite to the driving tooth 711 of the first rack 71;
the first rotating member 73 is rotatably provided on the main body 1, and the first transmitting member has a driving gear 731, and the driving gear 731 is simultaneously engaged with the driving teeth 711 of the first rack 71 and the driving teeth 711 of the second rack 72, and when the first rotating member 73 rotates, the first rack 71 and the second rack 72 can be driven to approach each other or to separate from each other.
In actual use, the first rotating member 73 is driven to rotate to drive the two racks to move closer to or away from each other, and when the two racks move closer to each other, the second wing 22 can be switched from the working state to the recovery state.
In other embodiments, the first rotating member 73 may be driven by a power mechanism to drive the belt 8, such as a hydraulic cylinder, a gear motor, or the like.
As shown in fig. 6 and 7, in the present embodiment, the first rotation member 73 further includes a first taper tooth 732 provided coaxially with the driving gear 731, and the switching mechanism 7 further includes a second rotation member 74 and a driving belt 8, wherein,
the second rotating member 74 is rotatably installed on the machine body 1, the second rotating member 74 is provided with a second conical tooth 741 and a winding wheel 742 which are coaxially arranged, the second conical tooth 741 is meshed with the first conical tooth 732, and when the winding wheel 742 rotates, the driving gear 731 can be driven to rotate by the meshing of the second conical tooth and the first conical tooth 732, so that the two racks are driven to move;
the driving belt 8 is wound on the winding wheel 742, one end of the driving belt 8 is connected with the middle part of the bearing belt 3, the driving belt 8 can be driven to move outwards through the bearing belt 3 after the parachute is opened, the driving belt 8 further drives the winding wheel 742 to rotate, and finally the second wing part 22 is switched to a recovery state.
The unmanned aerial vehicle has the weight of at least hundreds of kilograms, after the parachute 4 is opened, the acting force applied to the bearing belt 3 and the driving belt 8 is very large, the power for switching the second wing part 22 to the retracted state can be fully improved, and the application has the advantages of simple and reliable structure and can complete the switching without additional power equipment.
In this embodiment, the rotational axis of the reel 742 is disposed horizontally.
In actual use, the first wing portion 21 has a track (not shown) therein, which cooperates with a corresponding rack, and a damping structure is provided between the track and the rack. Providing a damping structure prevents the second wing part 22 from retracting into the first wing part 21 in normal operating conditions.
In actual use, the machine body 1 further comprises an inflation mechanism (not shown in the figure) which is positioned in the machine body 1 and is used for inflating the air bag 5, and in actual use, the inflation mechanism can be an inflation pump and other devices or a chemical drug reaction component.
In summary, the recovery system of the fixed wing unmanned aerial vehicle according to the present application can recover after the completion of the task, can decelerate by the parachute 4, can open the two air bag chambers and switch the second wing section 22 to the recovery state when the parachute 4 is opened, has a smart overall structure, effectively uses the force when the parachute 4 is opened, and can effectively protect the wing 2 by the retracted second wing section 22 and the wing protection section 51 of the air bag 5.
The foregoing description is only of the preferred embodiments of the present application, and is not intended to limit the scope of the application, but rather is intended to cover all equivalent structures as modifications within the scope of the application, either directly or indirectly, as may be contemplated by the present application.
Claims (10)
1. The recovery system of the fixed-wing unmanned aerial vehicle is characterized by comprising a machine body, wings, a bearing belt, a parachute, an air bag and an air bag locking and unlocking structure;
the wing is arranged in the middle of the fuselage;
the upper part of the front end of the machine body is provided with an umbrella bin, an opening of the umbrella bin is covered by an umbrella bin cover plate, the umbrella bin is arranged in front of the wing, the machine body is provided with two bearing areas, one bearing area is arranged in the umbrella bin, the other bearing area is arranged at the rear of the wing, one end of the bearing belt is connected with one bearing area, the other end of the bearing belt is connected with the other bearing area, the parachute is arranged in the umbrella bin, and the parachute is connected with the bearing belt;
the lower part of the machine body is provided with two air bag cabins which are arranged at intervals in the front-back direction, the opening of each air bag cabin is covered by an air bag cabin cover plate, and the air bags are arranged in the air bag cabins;
the airbag locking and unlocking structure includes:
the convex block is positioned on the air bag cabin cover plate and is provided with an inserting hole;
the movable hole is positioned in the bearing area;
the connecting piece is arranged on the movable hole in an up-down movable mode, the lower end of the connecting piece is provided with a first limiting part, the first limiting part is located below the movable hole and used for limiting the maximum position of upward movement of the connecting piece, the upper end of the connecting piece is used for being connected with the bearing belt, and the connecting piece can be driven to move upwards through the bearing belt after the parachute is opened;
the fixed seat is fixed with the machine body;
the locking pin is slidably mounted on the fixed seat and provided with a first convex part, and the locking pin is used for extending into the jack to limit the air bag cabin cover plate;
the spring is sleeved on the locking pin, one end of the spring is in abutting joint with the fixing seat, and the other end of the spring is in abutting joint with the first convex part and is used for enabling the locking pin to keep a state of being inserted into the jack;
and one end of the pull rope is connected with the locking pin, the other end of the pull rope is connected with the connecting piece, and when the connecting piece moves upwards, the connecting piece drives the locking pin to be separated from the jack through the pull rope.
2. The recovery system of the fixed wing unmanned aerial vehicle of claim 1, wherein the locking pin further comprises a second protrusion, and the first protrusion and the second protrusion are respectively located at two sides of the fixed seat.
3. The recovery system of a fixed wing unmanned aerial vehicle of claim 1, wherein the connector further has a second stop located at an upper end of the moveable aperture, the second stop being configured to define a maximum position for downward movement of the connector.
4. The recovery system of a fixed wing unmanned aerial vehicle of claim 1, wherein the upper portion of the fuselage has a recess into which the carrier strip is inserted.
5. The fixed wing unmanned aerial vehicle recovery system of claim 1, wherein the airbag has an upwardly turned wing protector at an end of the airbag for semi-wrapping at an outer end of the wing after inflation and deployment.
6. The recovery system of any one of claims 1-5, wherein the wing comprises a first wing portion and a second wing portion, the first wing portion is fixed to the fuselage, the second wing portion is capable of sliding relative to the first wing portion, and the second wing portion has a recovery state retracted into the first wing portion and an operating state extended out of the first wing portion.
7. The fixed wing unmanned aerial vehicle recovery system of claim 6, further comprising a switching mechanism for switching the state of the second wing section, the switching mechanism comprising two racks, one of the two racks being a first rack and the other being a second rack, and a first rotating member;
the first racks are arranged on the machine body and one of the first wing parts in a sliding manner, driving teeth are arranged on one end side part of each first rack, and the first racks are fixed with one of the second wing parts;
the second racks are arranged on the machine body and the other first wing part in a sliding manner, driving teeth are arranged on one end side part of each second rack, the second racks are fixed with the other second wing part, and the driving teeth of the second racks are arranged opposite to the driving teeth of the first racks;
the first rotating part is arranged on the machine body in a rotating mode, the first transmission part is provided with a driving gear, the driving gear is meshed with the driving teeth of the first rack and the driving teeth of the second rack at the same time, and when the first rotating part rotates, the first rack and the second rack can be driven to be close to each other or far away from each other.
8. The recovery system of a fixed wing unmanned aerial vehicle of claim 7, wherein the first rotating member further comprises a first conical tooth coaxially disposed with the drive gear, the switching mechanism further comprises a second rotating member and a drive belt, wherein,
the second rotating piece is rotatably arranged on the machine body and is provided with a second conical tooth and a rolling wheel which are coaxially arranged, the second conical tooth is meshed with the first conical tooth, and the rolling wheel can drive the driving gear to rotate through the meshing of the two conical teeth and the first conical tooth when rotating, so that the two racks are driven to move;
the driving belt is wound on the winding wheel, one end of the driving belt is connected with the middle of the bearing belt, the driving belt can be driven to move outwards through the bearing belt after the parachute is opened, the driving belt further drives the winding wheel to rotate, and finally the second wing part is switched to a recovery state.
9. The fixed wing unmanned aerial vehicle recovery system of claim 8, wherein the rotational axis of the take-up reel is disposed horizontally;
the first wing part is internally provided with a track matched with the corresponding rack, and a damping structure is arranged between the track and the rack.
10. The fixed wing unmanned aerial vehicle recovery system of claim 1, further comprising an inflation mechanism located within the fuselage for inflating the airbag.
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| CN202311258204.0A CN116986036B (en) | 2023-09-27 | 2023-09-27 | Recovery system of fixed wing unmanned aerial vehicle |
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Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5836544A (en) * | 1996-05-13 | 1998-11-17 | Gentile; Dino M. | Emergency soft-landing system for rotor-type aircraft |
| DE10300819A1 (en) * | 2003-01-10 | 2004-07-29 | Dietrich Pomeranz | Guard for protecting motorcycle driver, has brake parachute that opens before impact to carry driver from accident area, and airbag with inflatable hoses, in which brake parachute and airbag are connected to driver's clothing via tear line |
| CN203318683U (en) * | 2013-04-25 | 2013-12-04 | 王忠财 | Escape device |
| CN205931274U (en) * | 2016-08-30 | 2017-02-08 | 北方天途航空技术发展（北京）有限公司 | Light fixed wing uavs with parachute |
| CN205971884U (en) * | 2016-08-30 | 2017-02-22 | 北方天途航空技术发展（北京）有限公司 | Can protect light fixed wing uavs of carry equipment |
| CN207257995U (en) * | 2018-01-12 | 2018-04-20 | 黑龙江云顶航空科技有限公司 | The unmanned plane that fail-safe is crashed |
| CN108100265A (en) * | 2018-01-17 | 2018-06-01 | 安徽中骄智能科技有限公司 | A kind of band parachute-type unmanned plane |
| DE102021129574A1 (en) * | 2021-11-12 | 2023-05-17 | Esg Elektroniksystem- Und Logistik-Gesellschaft Mit Beschränkter Haftung | RESCUE SYSTEM FOR AN AIRCRAFT |
| CN116477055A (en) * | 2023-04-24 | 2023-07-25 | 中国商用飞机有限责任公司 | Recovery device, recovery system and recovery method for unmanned aerial vehicle |
| CN116552841A (en) * | 2023-05-22 | 2023-08-08 | 郑州亚柏智能科技有限公司 | Fixed wing unmanned aerial vehicle with stable landing |
| CN219770163U (en) * | 2023-08-28 | 2023-09-29 | 西咸新区云峰航控智能有限公司 | Hood subassembly and unmanned aerial vehicle |
| CN219790561U (en) * | 2023-03-09 | 2023-10-03 | 光子时空科技(山东)有限公司 | Waterproof unmanned aerial vehicle |
-
2023
- 2023-09-27 CN CN202311258204.0A patent/CN116986036B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5836544A (en) * | 1996-05-13 | 1998-11-17 | Gentile; Dino M. | Emergency soft-landing system for rotor-type aircraft |
| DE10300819A1 (en) * | 2003-01-10 | 2004-07-29 | Dietrich Pomeranz | Guard for protecting motorcycle driver, has brake parachute that opens before impact to carry driver from accident area, and airbag with inflatable hoses, in which brake parachute and airbag are connected to driver's clothing via tear line |
| CN203318683U (en) * | 2013-04-25 | 2013-12-04 | 王忠财 | Escape device |
| CN205931274U (en) * | 2016-08-30 | 2017-02-08 | 北方天途航空技术发展（北京）有限公司 | Light fixed wing uavs with parachute |
| CN205971884U (en) * | 2016-08-30 | 2017-02-22 | 北方天途航空技术发展（北京）有限公司 | Can protect light fixed wing uavs of carry equipment |
| CN207257995U (en) * | 2018-01-12 | 2018-04-20 | 黑龙江云顶航空科技有限公司 | The unmanned plane that fail-safe is crashed |
| CN108100265A (en) * | 2018-01-17 | 2018-06-01 | 安徽中骄智能科技有限公司 | A kind of band parachute-type unmanned plane |
| DE102021129574A1 (en) * | 2021-11-12 | 2023-05-17 | Esg Elektroniksystem- Und Logistik-Gesellschaft Mit Beschränkter Haftung | RESCUE SYSTEM FOR AN AIRCRAFT |
| CN219790561U (en) * | 2023-03-09 | 2023-10-03 | 光子时空科技(山东)有限公司 | Waterproof unmanned aerial vehicle |
| CN116477055A (en) * | 2023-04-24 | 2023-07-25 | 中国商用飞机有限责任公司 | Recovery device, recovery system and recovery method for unmanned aerial vehicle |
| CN116552841A (en) * | 2023-05-22 | 2023-08-08 | 郑州亚柏智能科技有限公司 | Fixed wing unmanned aerial vehicle with stable landing |
| CN219770163U (en) * | 2023-08-28 | 2023-09-29 | 西咸新区云峰航控智能有限公司 | Hood subassembly and unmanned aerial vehicle |
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|---|---|
| CN116986036B (en) | 2023-12-22 |
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