CN113264193A - Parachute assembly, structure and system for unmanned aerial vehicle and control method of parachute assembly, structure and system - Google Patents
Parachute assembly, structure and system for unmanned aerial vehicle and control method of parachute assembly, structure and system Download PDFInfo
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- CN113264193A CN113264193A CN202110540748.0A CN202110540748A CN113264193A CN 113264193 A CN113264193 A CN 113264193A CN 202110540748 A CN202110540748 A CN 202110540748A CN 113264193 A CN113264193 A CN 113264193A
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- 230000005484 gravity Effects 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
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- 230000001965 increasing effect Effects 0.000 claims description 3
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- 229910001008 7075 aluminium alloy Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/22—Load suspension
- B64D17/24—Rigging lines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/62—Deployment
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- 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
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- Engineering & Computer Science (AREA)
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- Mechanical Engineering (AREA)
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Abstract
The invention discloses a parachute assembly for an unmanned aerial vehicle, which comprises a supporting mechanism, a suspension mechanism and a parachute, wherein the supporting mechanism comprises: the first support of a set of vertical opposition with arrange on horizontal with the second support of first support grafting, first support and second support constitute U type accommodation space, the parachute is arranged in the U type accommodation space, hang the mechanism for connect parachute and unmanned aerial vehicle. Still disclose an unmanned aerial vehicle's parachuting structure, including organism, parachute cabin, hatch door and foretell parachute assembly, the parachute assembly splice in the parachute cabin, the hatch door sets up in unmanned aerial vehicle organism bottom for the lid closes the opening part. In addition, the parachute landing system and the control method based on the parachute landing structure of the unmanned aerial vehicle are further disclosed. The technical scheme of the invention optimizes the structural strength of the parachute assembly suspension mechanism and can be repeatedly utilized; the provided control method is easy to operate, has low requirements on users and is easy to popularize and use.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle parachuting, in particular to a parachuting assembly, a structure and a system for an unmanned aerial vehicle and a control method thereof.
Background
Unmanned aerial vehicle's type is various, and the function is more and more, and service environment is more and more wide, plays more and more important effect in aerial photography, agricultural plant protection, resource exploration, survey and drawing, electric power patrol and examine, especially to the resource exploration in open-air remote area, is limited to not having environments such as airport, needs unmanned aerial vehicle to take off and land in the field, provides special requirement to unmanned aerial vehicle take off and land.
The unmanned aerial vehicle adopting the parachuting recovery mode has low requirement on the field, does not need a runway, and is suitable for field conditions. Therefore, parachutes have been widely used in unmanned aerial vehicle recovery. The landing of unmanned aerial vehicle is related to the safety performance and the cost height problem of unmanned aerial vehicle, along with unmanned aerial vehicle is in the wide use in many fields, has proposed the requirement to the reliability of parachuting structure on the one hand, and on the other hand has also proposed higher requirement to the cost of parachuting system and user's operating skill.
Disclosure of Invention
In view of the above problems in the prior art, an object of the present invention is to provide a parachute assembly, a structure, a system for a drone and a control method thereof. According to the technical scheme, on one hand, the structural strength of the parachute assembly suspension mechanism is optimized, and the parachute assembly suspension mechanism can be repeatedly utilized for multiple times; on the other hand, the control method of the unmanned aerial vehicle parachuting system is easy to operate, low in requirement on users and easy to popularize and use.
Therefore, in order to solve the technical problem, the specific technical scheme of the invention is as follows:
in one aspect, the present invention provides a parachuting assembly for an unmanned aerial vehicle, comprising: a supporting mechanism, a hanging mechanism and a parachute;
the support mechanism includes: the device comprises a group of vertically opposite first brackets and a second bracket which is arranged in a transverse direction and is spliced with the first brackets; the first support and the second support form a U-shaped accommodating space;
the parachute is arranged in the U-shaped accommodating space;
the suspension mechanism includes: the parachute rope supports are arranged on the supporting mechanism, and the parachute ropes are arranged on the parachutes and used for connecting the parachutes with the unmanned aerial vehicle;
the top surface of the umbrella rope support is used for being glued with the unmanned aerial vehicle, and one side surface and the bottom surface of the umbrella rope support are respectively glued with the first support and the second support;
one end of the umbrella rope is connected with the parachute, and the other end of the umbrella rope is connected with the umbrella rope support;
an umbrella rope through hole is further formed in the second support and used for penetrating through the umbrella rope.
Preferably, the upper end of the first bracket is provided with a slotted hole for being inserted into the second bracket; the web plate of the first bracket is also provided with a plurality of lightening holes; the umbrella rope support is arranged at four corners of the edge where the second support is spliced with the first support.
Preferably, the bottom surface and the top surface of the umbrella rope support are both provided with a plurality of small holes, and the small holes are used for increasing the glue joint area, so that the structural strength of the glue joint surface is improved.
Further, the umbrella rope support comprises a support body and a stud; the end part of the stud is provided with threads, the support body is correspondingly provided with a connecting hole, and the connecting hole is provided with internal threads for being in threaded connection with the stud; the umbrella rope is arranged on the stud.
Further, in order to reduce the weight of the assembly, the support mechanism is made of a carbon fiber composite material.
In a second aspect, based on the above parachute assembly for the unmanned aerial vehicle, the present invention further provides a parachute structure for the unmanned aerial vehicle, comprising: the parachute bay comprises a body, a parachute bay, a bay door and any one of the parachute landing assemblies;
the umbrella cabin is a cavity structure formed by an upper skin and a lower skin of the machine body;
the lower covering is provided with an opening, and the opening is larger than an outer envelope of the folded parachute;
the parachute assembly is glued in the parachute cabin;
the hatch door sets up in unmanned aerial vehicle organism bottom for the lid closes the opening part.
Furthermore, the parachute cabin is internally provided with the parachute landing assembly and the cabin door lock; one end of the cabin door is hinged with the machine body, and the other end opposite to one end of the cabin door is provided with the cabin door lock for opening or closing the cabin door.
In a third aspect, based on the parachute landing structure of the unmanned aerial vehicle, the invention further provides a parachute landing system of the unmanned aerial vehicle, which comprises a flight control computer, the parachute landing structure of any one of the unmanned aerial vehicles, and an electric control component, wherein the electric control component is used for controlling the opening of the cabin door.
Optionally, the electronic control component is an actuator for electrical connection with the flight control computer; the flight control computer is used for sending a command for controlling the opening or closing of the cabin door lock; the actuator is arranged in the umbrella chamber and used for receiving the opening or closing instruction of the chamber door lock and controlling the opening or closing of the chamber door lock.
In a fourth aspect, based on any one of the above parachuting control systems for an unmanned aerial vehicle, the present invention further provides a method for controlling parachuting of an unmanned aerial vehicle, including:
s1, stopping the unmanned aerial vehicle power by the flight control computer;
s2, the flight control computer sends an instruction for controlling the opening of the cabin door lock to the electric control component;
s3, the electric control component receives the instruction of opening the control cabin door lock, and the control cabin door lock is opened to make the cabin door break away from the fuselage under the action of gravity, form a certain opening, and then the cabin door continues to rotate around one end and open under the action of wind resistance and the gravity of parachute, makes the parachute fall out by the cabin door, and the parachute is opened under the action of air, and then makes unmanned aerial vehicle hang under the parachute until safe landing.
By adopting the technical scheme, the parachute assembly structure, the parachute system and the parachute control method for the unmanned aerial vehicle have the following beneficial effects:
1. according to the parachute assembly for the unmanned aerial vehicle, the suspension mechanism is arranged at the corner where the three parts are intersected, so that the tension force in the landing process of the unmanned aerial vehicle can be effectively dispersed, and the reliability of the structure is improved.
2. According to the parachute landing structure of the unmanned aerial vehicle, the small holes are formed in the gluing surfaces of the parachute landing component and the upper skin, the gluing area is increased, and the reliability of the combination of the parachute landing structure and the body of the unmanned aerial vehicle is further improved.
3. The unmanned aerial vehicle parachute landing system can be repeatedly used, is simple in structure, can meet production requirements without complex processes, and greatly reduces cost.
4. The control method of the unmanned aerial vehicle parachuting system is easy to operate, has low requirements on users and is beneficial to popularization and use.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the description of the embodiment or the prior art will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic structural diagram of a parachute assembly for an unmanned aerial vehicle according to the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1;
FIG. 3 is an exploded view of the cord support of FIG. 1;
fig. 4 is a schematic view of a parachute landing structure of the unmanned aerial vehicle according to an embodiment of the present invention;
FIG. 5 is a schematic view of a door according to an embodiment of the present invention;
FIG. 6 is a schematic view of a door lock mounting arrangement provided in the present invention;
in the figure: 1-upper covering, 2-umbrella cabin, 3-lower covering, 4-cabin door, 20-parachute landing assembly, 21-umbrella rope support, 210-small hole, 211-support body, 212-stud, 22-first support, 221-lightening hole, 222-slotted hole, 23-second support, 231-umbrella rope through hole, 24-parachute, 242-umbrella rope, 41-electric control component, 42-hinge component and 43-cabin door lock.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, apparatus, article, or device that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or device.
Example 1
This embodiment provides a parachuting subassembly for unmanned aerial vehicle, through will hanging the mechanism setting in the crossing corner of three part, can effectively disperse the pulling force of unmanned aerial vehicle descending in-process, improved the reliability of subassembly structure.
Referring specifically to fig. 1, it includes a support mechanism consisting of a first support 22 and a second support 23, a suspension mechanism consisting of a parachute line support 21 and a parachute line 242, and a parachute 24. Wherein,
a support mechanism comprising: a group of vertically opposite first brackets 22 and second brackets 23 which are arranged in a transverse direction and are inserted with the first brackets 22, and a parachute 24 is placed in an inverted U-shaped accommodating space formed by the first brackets 22 and the second brackets 23.
Hang the mechanism for connect parachute 24 and unmanned aerial vehicle include: 4 parachute line holders 21 provided on the support mechanism and 4 parachute lines 242 provided on the parachute 24.
The top surface of the umbrella rope support 21 is bonded with the unmanned aerial vehicle by an adhesive, and one side surface and the bottom surface are bonded with the first support 22 and the second support 23 by the adhesive respectively.
The parachute line 242 has one end connected to the parachute 24 and the other end connected to the parachute line support 21.
An umbrella rope through hole 231 is further formed in the second support 23, and the umbrella rope 242 penetrates through the umbrella rope through hole 231 and then is connected with the umbrella rope support 21.
In order to more clearly illustrate the structure and beneficial effects of the parachute assembly 20 for the unmanned aerial vehicle provided by the embodiment, the following description is specifically provided in conjunction with fig. 2 and 3:
the umbrella rope support 21 is arranged at four corners of the edge of the second bracket 23 which is spliced with the first bracket 22. The bottom surface passes through the adhesive bonding with the upper surface of second support 23, simultaneously, also bonds to first support 22 through the adhesive with the side of first support 22 contact on, the top surface of reservation is used for gluing with unmanned aerial vehicle. Therefore, the suspension mechanism is simultaneously combined with the three parts, the stress can be quickly distributed to the three parts, the installation is firm, and the safety is high.
The structure in which the upper end of the first bracket 22 is provided with the slot 222 and the two opposite sides of the second bracket 23 are respectively inserted into the slot 222 is easy to assemble, and those skilled in the art will understand that the slot 222 needs to be specifically adjusted based on the thickness of the assembled components and the required strength, and this embodiment is given only as an illustrative example.
On the other hand, in order to reduce the weight of the assembly, the web of the first bracket 22 of the present embodiment is further provided with a plurality of lightening holes 221, and it should be noted that the lightening holes 221 can weaken the strength of the supporting structure to some extent, and need to be reasonably arranged based on the use condition.
Further, the embodiment provides an example for further enhancing the structural strength of the adhesive surface of the suspension mechanism, specifically, a plurality of small holes 210 are uniformly arranged on the top surface and the bottom surface of the umbrella rope support 21, and the small holes 210 can increase the area of the adhesive surface and further improve the adhesive strength.
As a preferred embodiment, the present embodiment further provides a specific structure of a non-limiting suspension mechanism, which can meet the production and manufacturing requirements through a conventional process, and has strong practicability, specifically including: referring to fig. 2, the top, bottom and side surfaces of the support body 211 in this example are the top, bottom and side surfaces of the above-mentioned parachute line support 21.
The end of the stud 212 is provided with a thread, the support body 211 is correspondingly provided with a connecting hole, the connecting hole is provided with an internal thread for screwing with the stud 212, and the umbrella rope 242 is installed on the stud 212.
The stud 212 may be made of standard parts to reduce cost.
The holder body 211 is a metal machined part, preferably 7075 aluminum alloy, and preferably has a heat treated state of T7351.
Based on the suspension mechanism of the above structure, during assembly, the umbrella rope 242 firstly passes through the umbrella rope through hole 231 on the second bracket 23, then the threaded end of the stud 212 is inserted into the inlet end of the connecting hole, the umbrella rope 242 is provided with a knot sleeved with the stud 212, the stud 212 is sleeved on the column body in the process of pushing the stud 212 into the connecting hole, and then the threaded end of the stud 212 is in threaded connection with the internal thread, so that the assembly is completed.
In some embodiments, the supporting mechanism of the embodiment can be made of carbon fiber composite materials, so that the weight of the assembly can be effectively reduced, and the application requirements of more scenes can be met.
Example 2
The invention further provides a parachute landing structure of an unmanned aerial vehicle, which comprises a machine body, a parachute bay 2, a bay door 4 and a parachute assembly 20 in any one of embodiments 1, and the specific components are as follows, with reference to fig. 4 and 5:
the umbrella cabin 2 is a cavity structure formed by an upper skin 1 and a lower skin 3 of the machine body;
the lower covering 3 is provided with an opening 331, and the opening 331 is larger than the outer envelope of the folded parachute 24;
the parachute landing assembly 20 is arranged in the parachute bay 2 and is glued with the upper skin 1.
It should be noted that the opening 331 needs to be larger than the outer envelope of the folded parachute 24, so that the hatch 4 can be freely taken out of the parachute bay 2 after being opened. The preferred size is that the single edge of the opening 331 is 20mm larger than the folded outer envelope of the parachute 24. On the basis of the above, the person skilled in the art can further set the opening size to be smaller than the outer envelope size of the above-mentioned support member, so as to ensure that the above-mentioned parachute assembly 20 can be always confined in the parachute bay 2 without risk of falling, further improving safety.
Optionally, the upper skin 1 and the lower skin 3 adopt a carbon fiber composite sandwich structure, and the middle parts of the upper skin and the lower skin are bonded with each other by an adhesive to form a cavity of the unmanned aerial vehicle.
Example 3
The present embodiment further provides an example of a mounting structure of a door 4 that can be used in the above-mentioned parachuting system, specifically: one end of the cabin door 4 is connected with the machine body through a hinge 42, the other end opposite to one end of the cabin door 4 is provided with a cabin door lock 43 for opening or closing the cabin door 4, the cabin door 4 is unlocked under the control of the cabin door lock 43, and can rotate around the shaft of the hinge 42 to open under the action of gravity.
The parachute landing structure of the unmanned aerial vehicle provided by the embodiment can realize the parachute opening and the parachute landing of the parachute 24 without an ejection device, and the complexity of the system is reduced while the requirements are met. It should be understood by those skilled in the art that, in the parachute landing structure of the unmanned aerial vehicle, the parachute 24 does not protrude outside the body inside the body, so that the air resistance is low when the unmanned aerial vehicle flies, and the range of the unmanned aerial vehicle is also improved to a certain extent.
When the unmanned aerial vehicle is used, whether the parachute 24 can be effectively opened or not directly influences whether the unmanned aerial vehicle can safely land or not, and therefore a reliable control system is needed to achieve the synergistic effect. Based on the parachute landing structure of the unmanned aerial vehicle, the embodiment also provides a parachute landing system of the unmanned aerial vehicle, which can be controlled in real time, and comprises a flight control computer, the parachute landing structure of the unmanned aerial vehicle and an electric control component 41;
an electrical control unit 41 is electrically connected to the flight control computer for controlling the opening of the door 4.
Referring to fig. 3 and 4, the embodiment provides a structure of a parachute system including an electric control part 41, wherein the electric control part 41 is disposed above a door lock 43 and is installed in the parachute bay 2 by a fixing member. The cabin door lock 43 may be a locking structure having a safety pin and a safety pin hole, and the electric control component 41 may drive the transmission device through a coil, and the transmission device may drive the safety pin to move, and further pull out from the safety pin hole, thereby completing the opening operation of the cabin door 4.
In some embodiments, the door lock 43 may also be configured as an electromagnetic locking structure, and the opening and closing of the door 4 is realized by controlling the on and off of the current in the electromagnetic component through the flight control computer.
The electric control component 41 of this embodiment is an actuator, and the actuator can be first mounted on the mounting plate, and then mounted on the lower portion of the first bracket 22 through the fixing member, so as to ensure the stability of the actuator. The preferred setting is that the actuator is provided with a rocker arm, the cabin door lock 43 is provided with a stop pin, and after the actuator receives an unlocking instruction, the rocker arm is driven to rotate to drive the stop pin to act, so that the opening action of the cabin door 4 is completed.
The electric control component 41 may further be provided with a sensor for detecting the position of the cabin door 4, when the cabin door 4 is located at the closed position, the electric control component 41 feeds back the closed state of the cabin door 4 to the flight control computer, and the flight control computer sends out an instruction for locking the cabin door 4 to drive the cabin door lock 43 to complete the closing action of the cabin door 4.
Example 4
The invention further provides a parachute landing control method of the unmanned aerial vehicle, which is based on the unmanned aerial vehicle parachute landing system.
The method specifically comprises the following steps:
s1, stopping the unmanned aerial vehicle power by the flight control computer;
s2, the flight control computer sends an instruction for controlling the opening of the cabin door lock to the electric control component;
s3, the electric control component receives an instruction for controlling the opening of the cabin door lock, and the cabin door lock is opened so that the cabin door falls under the action of gravity to form a certain opening, and then the cabin door continues to rotate around one end to be opened under the action of wind resistance and the gravity of the parachute, the parachute falls out of the cabin door, the parachute is opened under the action of air, and the unmanned aerial vehicle is hung under the parachute until safe landing.
By the method, the unmanned aerial vehicle control personnel can issue a recovery instruction to the flight control computer when completing the flight task of the unmanned aerial vehicle, and then the flight control computer completes the steps. Based on the control method, the unmanned aerial vehicle recovery task can be completed without complex control logic.
It will be appreciated by those skilled in the art that the power to shut down the drone is to take full advantage of the air resistance acting on the parachute to open it as quickly as possible, and on the other hand to help avoid damage to the parachute structure from the power plant. During the actual recovery process, a deceleration process can be added before the shutdown power is executed, or the flight control computer can determine when to issue a command of opening the cabin door lock to the electric control component through timing or detection of the flight speed. Those skilled in the art can specifically adjust the unmanned aerial vehicle based on actual use and use environment.
While the invention has been described with reference to specific embodiments, it will be appreciated by those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the invention can be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (10)
1. A parachute assembly for an unmanned aerial vehicle, comprising a support mechanism, a suspension mechanism and a parachute (24);
the support mechanism includes: a group of vertically opposite first brackets (22) and second brackets (23) which are arranged in a transverse direction and are inserted into the first brackets (22); the first support (22) and the second support (23) form a U-shaped accommodating space;
the parachute (24) is arranged in the U-shaped accommodating space;
the suspension mechanism includes: a plurality of parachute line supports (21) arranged on the supporting mechanism and a plurality of parachute lines (242) arranged on the parachute (24) and used for connecting the parachute (24) and the unmanned aerial vehicle;
the top surface of the umbrella rope support (21) is used for being glued with the unmanned aerial vehicle, and one side surface and the bottom surface are respectively glued with the first support (22) and the second support (23);
one end of the umbrella rope (242) is connected with the parachute (24), and the other end of the umbrella rope is connected with the umbrella rope support (21);
an umbrella rope through hole (231) is further formed in the second support (23) and used for penetrating through the umbrella rope (242).
2. The parachuting assembly for unmanned aerial vehicles of claim 1, wherein the first bracket (22) is provided with a slot hole (222) at an upper end thereof for being plugged with the second bracket (23);
a plurality of lightening holes (221) are further formed in the web plate of the first bracket (22);
the umbrella rope support (21) is arranged at four corners of the edge where the second support (23) is connected with the first support (22) in an inserting mode.
3. The parachuting assembly for unmanned aerial vehicles of claim 1, wherein the bottom surface and the top surface of the parachute line support (21) are provided with a plurality of small holes (210) for increasing the bonding area.
4. A parachute assembly for a drone according to claim 1, wherein the parachute line mount (21) comprises: a holder body (211) and a stud (212);
the end part of the stud (212) is provided with threads, the support body (211) is correspondingly provided with a connecting hole, and the connecting hole is provided with internal threads for being in threaded connection with the stud (212);
the umbrella rope (242) is mounted on the stud (212).
5. A parachuting assembly for unmanned aerial vehicles according to claim 1, wherein the support mechanism is made of carbon fiber composite material.
6. An unmanned aerial vehicle parachute landing structure, comprising a body, a parachute bay (2), a bay door (4) and a parachute assembly (20) according to any one of claims 1 to 5;
the umbrella cabin (2) is a cavity structure formed by an upper skin (1) and a lower skin (3) of the machine body;
an opening (331) is formed in the lower skin (3), and the opening (331) is larger than an outer envelope of the folded parachute (24);
the parachute assembly (20) is glued with the upper skin (1);
hatch door (4) set up in unmanned aerial vehicle organism bottom for the lid closes opening (331).
7. The parachuting structure of an unmanned aerial vehicle of claim 6,
the parachute cabin (2) is internally provided with the parachute landing assembly (20) and the cabin door lock (43);
one end of the cabin door (4) is connected with the machine body through a hinge element (42), and the other end opposite to one end of the cabin door (4) is provided with the cabin door lock (43) for opening or closing the cabin door (4).
8. An unmanned aerial vehicle parachuting system comprising a flight control computer and the unmanned aerial vehicle parachuting structure of claim 6 or 7, further comprising an electronic control component (41);
the electric control component (41) is electrically connected with the flight control computer and is used for controlling the opening of the cabin door (4).
9. An unmanned aerial vehicle parachuting system as claimed in claim 8, wherein the electrical control component (41) is an actuator;
the flight control computer is used for sending an instruction for controlling the cabin door lock (43) to be opened or closed;
the actuator is arranged in the umbrella cabin (4) and used for receiving the opening or closing instruction of the cabin door lock (43) and controlling the cabin door lock (43) to open or close.
10. A method for controlling parachuting of an unmanned aerial vehicle, the method being based on the unmanned aerial vehicle parachuting system of claim 8 or 9, comprising:
s1, stopping the unmanned aerial vehicle power by the flight control computer;
s2, the flight control computer sends an instruction for controlling the opening of the cabin door lock to the electric control component;
s3, the electric control component receives an instruction for controlling the opening of the cabin door lock, and the cabin door lock is opened so that the cabin door falls under the action of gravity to form a certain opening, and then the cabin door continues to rotate around one end to be opened under the action of wind resistance and the gravity of the parachute, the parachute falls out of the cabin door, the parachute is opened under the action of air, and the unmanned aerial vehicle is hung under the parachute until safe landing.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114750955A (en) * | 2022-06-16 | 2022-07-15 | 沃飞长空科技(成都)有限公司 | Double-point throwing mechanism, aircraft and throwing method |
Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3221537A1 (en) * | 1981-07-14 | 1983-02-03 | VEB Bekleidungswerke Seifhennersdorf, Betrieb des VEB TKC, DDR 8812 Seifhennersdorf | Release device for parachute jumpers, having a replaceable belt ring as the main closing part |
| US20030222178A1 (en) * | 2002-05-29 | 2003-12-04 | Jack Chen | Apparatus for slowly and safely descending from a high-rise building |
| US20080191098A1 (en) * | 2007-01-25 | 2008-08-14 | Milan Babovka | Life parachute especially for ultra-lightweight aircrafts |
| JP2008302856A (en) * | 2007-06-08 | 2008-12-18 | Fujikura Parachute Co Ltd | Leafing device of parachute |
| CN101602405A (en) * | 2008-06-11 | 2009-12-16 | 李晓亮 | Low-altitude parachute for airplane |
| CN101857089A (en) * | 2009-04-07 | 2010-10-13 | 陈昌志 | Plane parachute |
| JP2010280330A (en) * | 2009-06-05 | 2010-12-16 | Yoshio Usui | Soft landing parachute drop equipment |
| CN102020018A (en) * | 2009-09-11 | 2011-04-20 | 朱步成 | Aviation safety system |
| CN102152851A (en) * | 2008-07-28 | 2011-08-17 | 李晓亮 | Self-driven power parachute |
| CN202609086U (en) * | 2012-05-03 | 2012-12-19 | 西安大地测绘工程有限责任公司 | Downwards-throwing popup type parachute opening device of unmanned plane |
| EP3233632A1 (en) * | 2014-12-19 | 2017-10-25 | Dae | Drone and associated airborne intervention equipment |
| CN206634193U (en) * | 2017-03-14 | 2017-11-14 | 陕西爱维森航空工程有限责任公司 | A kind of aircraft parachute jumping personnel use parachute jumping supplementary structure |
| US9981749B1 (en) * | 2017-10-13 | 2018-05-29 | Kitty Hawk Corporation | Parachute deployment system using decoupled tow and release lines |
| CN108945478A (en) * | 2018-08-14 | 2018-12-07 | 中国科学院工程热物理研究所 | The parachute opener of unmanned plane |
| CN109665110A (en) * | 2018-12-24 | 2019-04-23 | 东汉太阳能无人机技术有限公司 | Umbrella cabin device and its unmanned plane |
| US20190168882A1 (en) * | 2016-08-08 | 2019-06-06 | Heli-Tech | Rotary-wing aerodyne with parachute |
| CN110884655A (en) * | 2018-10-24 | 2020-03-17 | 航天时代飞鸿技术有限公司 | Unmanned aerial vehicle umbrella mounting and unfolding method |
| US20200407068A1 (en) * | 2018-02-28 | 2020-12-31 | Safran Aerosystems | Device for unlocking a system for closing a container by means of a tie and container provided with such an unlocking device |
| CN212580150U (en) * | 2020-06-19 | 2021-02-23 | 四川傲势科技有限公司 | External hanging type parachute transport cabin of small-sized fixed wing unmanned aerial vehicle |
-
2021
- 2021-05-18 CN CN202110540748.0A patent/CN113264193B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3221537A1 (en) * | 1981-07-14 | 1983-02-03 | VEB Bekleidungswerke Seifhennersdorf, Betrieb des VEB TKC, DDR 8812 Seifhennersdorf | Release device for parachute jumpers, having a replaceable belt ring as the main closing part |
| US20030222178A1 (en) * | 2002-05-29 | 2003-12-04 | Jack Chen | Apparatus for slowly and safely descending from a high-rise building |
| US20080191098A1 (en) * | 2007-01-25 | 2008-08-14 | Milan Babovka | Life parachute especially for ultra-lightweight aircrafts |
| JP2008302856A (en) * | 2007-06-08 | 2008-12-18 | Fujikura Parachute Co Ltd | Leafing device of parachute |
| CN101602405A (en) * | 2008-06-11 | 2009-12-16 | 李晓亮 | Low-altitude parachute for airplane |
| CN102152851A (en) * | 2008-07-28 | 2011-08-17 | 李晓亮 | Self-driven power parachute |
| CN101857089A (en) * | 2009-04-07 | 2010-10-13 | 陈昌志 | Plane parachute |
| JP2010280330A (en) * | 2009-06-05 | 2010-12-16 | Yoshio Usui | Soft landing parachute drop equipment |
| CN102020018A (en) * | 2009-09-11 | 2011-04-20 | 朱步成 | Aviation safety system |
| CN202609086U (en) * | 2012-05-03 | 2012-12-19 | 西安大地测绘工程有限责任公司 | Downwards-throwing popup type parachute opening device of unmanned plane |
| EP3233632A1 (en) * | 2014-12-19 | 2017-10-25 | Dae | Drone and associated airborne intervention equipment |
| US20190168882A1 (en) * | 2016-08-08 | 2019-06-06 | Heli-Tech | Rotary-wing aerodyne with parachute |
| CN206634193U (en) * | 2017-03-14 | 2017-11-14 | 陕西爱维森航空工程有限责任公司 | A kind of aircraft parachute jumping personnel use parachute jumping supplementary structure |
| US9981749B1 (en) * | 2017-10-13 | 2018-05-29 | Kitty Hawk Corporation | Parachute deployment system using decoupled tow and release lines |
| US20200407068A1 (en) * | 2018-02-28 | 2020-12-31 | Safran Aerosystems | Device for unlocking a system for closing a container by means of a tie and container provided with such an unlocking device |
| CN108945478A (en) * | 2018-08-14 | 2018-12-07 | 中国科学院工程热物理研究所 | The parachute opener of unmanned plane |
| CN110884655A (en) * | 2018-10-24 | 2020-03-17 | 航天时代飞鸿技术有限公司 | Unmanned aerial vehicle umbrella mounting and unfolding method |
| CN109665110A (en) * | 2018-12-24 | 2019-04-23 | 东汉太阳能无人机技术有限公司 | Umbrella cabin device and its unmanned plane |
| CN212580150U (en) * | 2020-06-19 | 2021-02-23 | 四川傲势科技有限公司 | External hanging type parachute transport cabin of small-sized fixed wing unmanned aerial vehicle |
Non-Patent Citations (2)
| Title |
|---|
| 余莉等: "降落伞技术的研究进展及展望", 《世界科技研究与发展》 * |
| 荣海春等: "某型无人机伞降回收系统设计", 《西安航空学院学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114750955A (en) * | 2022-06-16 | 2022-07-15 | 沃飞长空科技(成都)有限公司 | Double-point throwing mechanism, aircraft and throwing method |
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