CN117985250B - Quick parachute removing system and aircraft - Google Patents
Quick parachute removing system and aircraft Download PDFInfo
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- CN117985250B CN117985250B CN202410405459.3A CN202410405459A CN117985250B CN 117985250 B CN117985250 B CN 117985250B CN 202410405459 A CN202410405459 A CN 202410405459A CN 117985250 B CN117985250 B CN 117985250B
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- 230000000670 limiting effect Effects 0.000 claims abstract description 122
- 238000009434 installation Methods 0.000 claims abstract description 38
- 238000000926 separation method Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 6
- 230000007423 decrease Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
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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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Hooks, Suction Cups, And Attachment By Adhesive Means (AREA)
Abstract
The invention discloses a rapid parachute removing system and an aircraft, and relates to the technical field of carrier rocket parachute removing, wherein the system comprises: the bearing assembly is provided with an installation space, and one side of the bearing assembly is provided with a rope hanging hook which is used for being connected with an aircraft body; two unhooking hooks are arranged on the other side of the installation space and are used for being connected with a parachute hanging rope of the drogue; the limiting mechanism is arranged in the installation space; the limiting mechanism is provided with two limiting parts which are arranged in one-to-one correspondence with the moving ends of the two unhooking hooks; when the limiting mechanism is in a first working state, the limiting part is contacted with the moving end surface of the corresponding unhooking hook, so that the clamping ends of the two unhooking hooks are contacted, and the unhooking hook is connected with an umbrella hanging rope of the drogue; when the limiting mechanism is in the second working state, the limiting part is completely separated from the corresponding movable end of the unhooking hook, so that the clamping ends of the two unhooking hooks are far away from each other, and the unhooking hook and the parachute hanging rope of the drogue are separated. The invention realizes the purpose of quick and stable separation of the aircraft and the drogue.
Description
Technical Field
The invention relates to the technical field of parachute removing of carrier rockets, in particular to a rapid parachute removing system and an aircraft.
Background
The parachute is widely applied to the landing process of the aircraft, and the parachute throwing device is arranged in the parachute cabin of the parachute device by being carried on the parachute device of the aircraft, and pulls out the parachute in the parachute cabin from the parachute cabin after being electrified and detonated, so that the parachute of the parachute is opened.
However, when an aircraft lands, the drogue is still generally connected to the aircraft, the drogue bears a large resistance to assist the speed of the aircraft to decrease, the resistance to which the drogue bears gradually decreases as the aircraft slides on the ground, and when the force of the aircraft itself can stop the aircraft smoothly, the drogue and the aircraft need to be separated, and if not separated, the aircraft is easily damaged or turned over. At present, the scheme for separating the drogue from the aircraft is not mature enough. Therefore, we propose a quick parachute-releasing system and an aircraft for solving the above problems.
Disclosure of Invention
In view of the foregoing drawbacks or shortcomings of the prior art, it is desirable to provide a quick parachute system and an aircraft that are efficient in separating the parachute from the aircraft, simple in construction and easy to implement.
In a first aspect, the present invention provides a quick-release system comprising:
the bearing assembly is provided with an installation space, one side of the installation space is provided with a rope hanging hook, and the rope hanging hook is used for being connected with an aircraft body; two matched unhooking hooks are arranged on the other side of the installation space and are used for being connected with a parachute hanging rope of the drogue;
the limiting mechanism is arranged in the installation space; the limiting mechanism is provided with two limiting parts, and the two limiting parts are arranged in one-to-one correspondence with the moving ends of the two unhooking hooks; the limiting mechanism is provided with a first working state and a second working state;
when the limiting mechanism is in a first working state, the limiting part is contacted with the moving end face of the corresponding unhooking hook, so that the clamping ends of the two unhooking hooks are contacted, and the unhooking hook is connected with an umbrella hanging rope of the drogue;
when the limiting mechanism is in the second working state, the limiting part is completely separated from the corresponding movable end of the unhooking hook, so that the clamping ends of the two unhooking hooks are far away from each other, and the unhooking hook and the parachute hanging rope of the drogue are separated.
According to the technical scheme provided by the embodiment of the invention, the bearing assembly comprises:
the first bearing plate and the second bearing plate are arranged in parallel, and the installation space is formed between the first bearing plate and the second bearing plate;
The rope hanging hook is connected with the first bearing plate and the second bearing plate through bolts, and the unhooking hook is connected with the first bearing plate and the second bearing plate through bolts.
According to the technical scheme provided by the embodiment of the invention, the limiting mechanism comprises:
The limiting shell is arranged on the wall surfaces of the first bearing plate and the second bearing plate, which are far away from each other, an installation cavity is formed between the limiting shell and the first bearing plate and between the limiting shell and the second bearing plate, a first opening communicated with the installation space is formed in the first bearing plate, a second opening communicated with the installation space is formed in the second bearing plate, and the installation cavity is communicated with the first opening and the second opening;
the limiting block is arranged in the installation space; the limiting parts are respectively formed on the two side walls, close to the two unhooking hooks, of the limiting block; the limiting block is provided with a limiting groove which is arranged corresponding to the second opening; the limiting block is also provided with a limiting protrusion extending into the mounting cavity from the first opening;
The driving assembly is arranged in the mounting cavity and is provided with a driving part, and the driving part is used for driving the limiting ball to move between the second opening and the limiting groove so as to control the limiting ball to be clamped with or separated from the limiting groove;
the first elastic element is arranged in the mounting cavity, one side of the first elastic element is connected with the limiting protrusion, and the other side of the first elastic element is connected with the side wall of the mounting cavity;
When the driving part drives the limiting ball to move to the second opening, the acting force of the first elastic element acts on the limiting protrusion, so that the limiting block is assisted to move to one side far away from the unhooking hook, and the unhooking hook is separated from the parachute hanging rope of the drogue.
According to the technical scheme provided by the embodiment of the invention, the limit shell comprises:
the first limiting cover is arranged on the first bearing plate; a first subchamber is formed between the first limit cover and the first bearing plate;
The second limiting cover is arranged on the second bearing plate; a second subchamber is formed between the second limiting cover and the second bearing plate;
the first subchamber and the second subchamber together form the mounting chamber.
According to the technical scheme provided by the embodiment of the invention, the driving assembly comprises:
the driving piece is arranged in the second subchamber; a limit stop is arranged on the driving shaft of the driving piece;
When the driving shaft of the driving piece drives the limit stop to move along the length direction of the second force bearing plate to the side far away from the unhooking hook, the limit ball is separated from the limit groove, so that the limit block moves to the side far away from the unhooking hook.
According to the technical scheme provided by the embodiment of the invention, the driving assembly further comprises:
the second elastic element is positioned on one side of the limit stop, which is far away from the driving piece, and one end of the second elastic element is connected with the limit stop, and the other end of the second elastic element is connected with the side wall of the second subchamber;
When the driving shaft of the driving piece drives the limit stop block to move along the length direction of the second force bearing plate to a side far away from the unhooking hook, the acting force of the second elastic element is applied to the limit stop block so as to assist the limit stop block to move stably.
According to the technical scheme provided by the embodiment of the invention, the method further comprises the following steps:
The protection cover is sleeved outside the first bearing plate, the second bearing plate and the limiting shell.
According to the technical scheme provided by the embodiment of the invention, the method further comprises the following steps:
The bearing columns penetrate through the pin holes in the first bearing plate, the pin holes in the second bearing plate, the rope hanging hooks and the unhooking hooks and are connected through locking nuts and locking screws.
In a second aspect, the present invention provides an aircraft comprising: the quick parachute-removing system is characterized by comprising a main body and a main body.
In summary, the present invention provides a specific structure of a quick parachute-removing system. The invention designs a bearing assembly which is provided with an installation space, wherein one side of the bearing assembly is provided with a rope hanging hook for being connected with an aircraft body; the other side of the installation space is provided with two unhooking hooks which are matched for use and are used for being connected with a parachute hanging rope of the drogue; a limiting mechanism is arranged in the installation space and is provided with two limiting parts which are arranged in one-to-one correspondence with the moving ends of the two unhooking hooks; the limiting mechanism is provided with a first working state and a second working state; when the limiting mechanism is in a first working state, the limiting part is contacted with the moving end surface of the corresponding unhooking hook, so that the clamping ends of the two unhooking hooks are contacted, and the unhooking hook is connected with an umbrella hanging rope of the drogue; when the limiting mechanism is in the second working state, the limiting part is completely separated from the corresponding movable end of the unhooking hook, so that the clamping ends of the two unhooking hooks are far away from each other, and the unhooking hook and the parachute hanging rope of the drogue are separated.
The invention uses the limiting mechanism to be in different working states, so that the unhooking hook and the parachute hanging rope of the drogue parachute are connected or separated, and further whether the aircraft body is unhooked or not is controlled, namely, the purpose of rapidly and stably separating the aircraft from the drogue parachute can be realized.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments made with reference to the following drawings.
FIG. 1 is a cross-sectional view of a quick-release system.
Fig. 2 is a schematic structural diagram of the force bearing assembly.
Fig. 3 is a schematic structural view of the limiting housing.
Fig. 4 is a schematic structural view of the stopper.
Fig. 5 is a schematic view of the structure of the stopper and unhooking hook.
Reference numerals in the drawings: 1. a rope hook; 2. a first force bearing plate; 3. a protective cover; 4. a lock nut; 5. a locking screw; 6. a limiting block; 7. a first elastic element; 8. a first limit cover; 9. unhooking; 10. a second force bearing plate; 11. the second limit cover; 12. a second elastic element; 13. a limit stop; 14. a limit ball; 15. a driving member; 16. a force bearing column; 17. a limit part; 18. a limit groove; 19. and a limit protrusion.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the invention are shown in the drawings.
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
The traditional aircraft body is provided with the drogue device, when the aircraft lands, the drogue is opened and bears larger resistance to assist the speed of the aircraft to gradually decrease, when the acting force of the aircraft can make the aircraft stably stop, the drogue and the aircraft are required to be quickly separated, and in order to prevent the acting force of the drogue from damaging the aircraft or causing side turning, the invention designs a quick drogue system.
Example 1
Referring to fig. 1, a schematic structural diagram of a quick parachute-removing system according to the present invention is shown, the system includes:
The bearing assembly is provided with an installation space, one side of the installation space is provided with a rope hanging hook 1, and the rope hanging hook 1 is used for being connected with an aircraft body; two matched unhooking hooks 9 are arranged on the other side of the installation space, and the two unhooking hooks 9 are used for being connected with a parachute hanging rope of the drogue;
Specifically, as shown in fig. 2, the force bearing assembly includes:
the first bearing plate 2 and the second bearing plate 10 which are arranged in parallel form an installation space therebetween; here, the first and second load bearing plates 2 and 10 are of the same plate-like structure, and the terms "first" and "second" are merely intended to distinguish between these two members, and are not limited to any particular type.
The rope hanging hook 1 is connected with the first bearing plate 2 and the second bearing plate 10 through bolts, and the unhooking hook 9 is connected with the first bearing plate 2 and the second bearing plate 10 through bolts.
Here, the bolt connection mode is, for example, to open holes on the rope hanging hook 1 and the unhooking hook 9, and the first bearing plate 2 and the second bearing plate 10 are provided with pin holes, the corresponding holes and pin holes are penetrated by the bearing column 16, then the corresponding two ends of the bearing column 16 are fixed by the cooperation of the locking nut 4 and the locking screw 5, the locking nut 4 and the pin holes can be concentrically arranged and fixed around the corresponding pin holes, the two ends of the bearing column are connected with the locking nut 4, the pin holes and the bearing column 16 are penetrated by the locking screw 5, and then the rope hanging hook 1, the unhooking hook 9, the first bearing plate 2 and the second bearing plate 10 are connected.
The limiting mechanism is arranged in the installation space; the limiting mechanism is provided with two limiting parts 17, and the two limiting parts 17 are arranged in one-to-one correspondence with the moving ends of the two unhooking hooks 9; the limiting mechanism is provided with a first working state and a second working state;
When the limiting mechanism is in a first working state, the limiting part 17 is contacted with the moving end surfaces of the corresponding unhooking hooks 9, so that the clamping ends of the two unhooking hooks 9 are contacted, and the unhooking hooks 9 are connected with the parachute hanging ropes of the drogue;
When the limiting mechanism is in the second working state, the limiting part 17 is completely separated from the corresponding movable end of the unhooking hook 9, so that the clamping ends of the two unhooking hooks 9 are far away from each other, and the unhooking hook 9 and the parachute hanging rope of the drogue are separated.
Specifically, as shown in fig. 1, the limiting mechanism includes:
The limiting shell is arranged on the wall surfaces, far away from each other, of the first bearing plate 2 and the second bearing plate 10, an installation cavity is formed between the limiting shell and the first bearing plate 2 and between the limiting shell and the second bearing plate 10, a first opening communicated with the installation space is formed in the first bearing plate 2, a second opening communicated with the installation space is formed in the second bearing plate 10, and the installation cavity is communicated with the first opening and the second opening;
Wherein, as shown in fig. 3, the limit housing includes:
The first limiting cover 8 is arranged on the first bearing plate 2; a first subchamber is formed between the first limit cover 8 and the first bearing plate 2; the first subchamber is intended to receive and mount the first resilient element 7.
The second limiting cover 11 is arranged on the second bearing plate 10; a second subchamber is formed between the second limit cover 11 and the second bearing plate 10; the second subchamber is used to house and mount the drive assembly.
The first subchamber and the second subchamber together form a mounting chamber.
The first and second stopper covers 8 and 11 have the same cover structure, and the terms "first" and "second" are merely intended to distinguish between these two members, and are not limited to any particular one.
The limiting block 6 is arranged in the installation space; as shown in fig. 4, two side walls of the limiting block 6, which are close to the two unhooking hooks 9, respectively form limiting parts 17; the limiting block 6 is provided with the limiting groove 18 which is arranged corresponding to the second opening, and the longitudinal section of the limiting groove 18 is semicircular, so that when the limiting groove 18 is clamped with the limiting ball 14, the inner wall of the limiting groove 18 can be completely contacted with the surface of the limiting ball 14, and the optimal limiting effect is achieved; the limiting block 6 is further provided with a limiting protrusion 19 extending from the first opening into the mounting cavity, the limiting protrusion 19 is used for being connected with the first elastic element 7, and the limiting protrusion 19 extends from the first opening into the mounting cavity, so that the distance that the limiting block 6 can move in the direction parallel to the length of the first bearing plate 2 is equal to the diameter of the first opening, namely, the limiting protrusion 19 has a limiting effect on the movement of the limiting block 6.
The driving assembly is arranged in the mounting cavity and is provided with a driving part, and the driving part is used for driving the limiting ball 14 to move between the second opening and the limiting groove 18 so as to control the limiting ball 14 and the limiting groove 18 to be clamped or separated;
Specifically, as shown in fig. 1, the driving assembly includes:
a driving member 15, the driving member 15 being disposed within the second subchamber; a limit stop 13 is arranged on the driving shaft of the driving piece 15; here, the driving member 15 is of a type such as an electric cylinder.
When the driving shaft of the driving member 15 drives the limit stop 13 to move along the length direction of the second bearing plate 10 to a side far away from the unhooking hook 9, the limit ball 14 and the limit groove 18 are separated, so that the limit block 6 moves to a side far away from the unhooking hook 9.
In addition, as shown in fig. 1, the driving assembly further includes:
a second elastic element 12, wherein the second elastic element 12 is positioned at one side of the limit stop 13 away from the driving piece 15, one end of the second elastic element 12 is connected with the limit stop 13, and the other end is connected with the side wall of the second subchamber; here, the second elastic element 12 is of the type, for example, a spring.
When the driving shaft of the driving member 15 drives the limit stop 13 to move along the length direction of the second force bearing plate 10 to the side far away from the unhooking hook 9, the acting force of the second elastic element 12 is applied to the limit stop 13 to assist the smooth movement of the limit stop 13.
As shown in fig. 1, the first elastic element 7 is arranged in the installation cavity, one side of the first elastic element 7 is connected with the limit protrusion 19, and the other side is connected with the side wall of the installation cavity; here, the first elastic element 7 is of the type, for example, a spring.
When the driving part drives the limiting ball 14 to move to the second opening, the acting force of the first elastic element 7 acts on the limiting protrusion 19, so that the limiting block 6 is assisted to move to one side far away from the unhooking hook 9, and the unhooking hook 9 is separated from the parachute hanging rope of the drogue.
Further, as shown in fig. 2, the method further includes:
The protection cover 3, the protection cover 3 cover is established in the outside of first load-bearing plate 2, second load-bearing plate 10 and spacing casing. The protection cover 3 plays a role in protecting the first bearing plate 2, the second bearing plate 10 and the limiting shell.
The specific working process of the quick parachute-removing system is as follows:
In the landing and sliding process of the aircraft, the drogue is opened, and at this time, the state of the quick parachute-removing system is as follows: the rope hook 1 is connected with an aircraft body, the driving piece 15 drives the limit stop 13 to move and extrude the second elastic element 12, the limit stop 13 butts against the limit ball 14, the limit ball 14 protrudes from the second opening and is clamped with the limit groove 18, at the moment, the first elastic element 7 is extruded, two limit parts 17 of the limit block 6 are respectively contacted with the moving end faces of the corresponding unhooking hooks 9, as shown in fig. 5, the clamping ends of the two unhooking hooks 9 are contacted, so that the unhooking hooks 9 can be connected with the hanging rope of the dropouts, and the force bearing assembly and the limit mechanism bear the acting force of the aircraft and the dropouts together.
When the aircraft can rest by means of self acting force, the control system of the aircraft and the driving piece 15 can be used for communication connection, the control system sends a starting instruction to the driving piece 15, the driving piece 15 starts to run after acquiring a starting signal in the starting instruction, the driving shaft of the driving piece 15 drives the limit stop 13 to move to one side far away from the unhooking hook 9, at the moment, the acting force of the second elastic element 12 is applied to the limit stop 13 so as to assist the limit stop 13 to stably move, at the moment, the limit ball 14 loses the acting force of the limit stop 13, the limit ball 14 can retract to a second opening position, namely the limit ball 14 is separated from the limit groove 18, the limit block 6 does not obstruct, and moves to one side far away from the unhooking hook 9 under the acting force of the first elastic element 7 and the dropouts, so that the clamping ends of the two unhooking hooks 9 are separated, and the parachute ropes of the unhooking hook 9 are separated, and finally the aircraft achieves the purpose of rapidly and stably unhooking.
Here, the type of control system is for example an STM32 series microcontroller.
Example 2
An aircraft, comprising: a quick-release umbrella system as described in embodiment 1; the corresponding aircraft has the functions and advantages of a quick parachute-removing system, and the description is omitted here.
The above description is only illustrative of the preferred embodiments of the present invention and of the principles of the technology employed. It will be appreciated by persons skilled in the art that the scope of the invention referred to in the present invention is not limited to the specific combinations of the technical features described above, but also covers other technical features formed by any combination of the technical features described above or their equivalents without departing from the inventive concept. Such as the above-mentioned features and the technical features disclosed in the present invention (but not limited to) having similar functions are replaced with each other.
Claims (7)
1. A quick-release umbrella system, comprising:
The bearing assembly is provided with an installation space, one side of the installation space is provided with a rope hanging hook (1), and the rope hanging hook (1) is used for being connected with an aircraft body; two unhooking hooks (9) which are matched with each other are arranged on the other side of the installation space, and the two unhooking hooks (9) are used for being connected with a parachute hanging rope of the drogue;
The limiting mechanism is arranged in the installation space; the limiting mechanism is provided with two limiting parts (17), and the two limiting parts (17) are arranged in one-to-one correspondence with the moving ends of the two unhooking hooks (9); the limiting mechanism is provided with a first working state and a second working state;
When the limiting mechanism is in a first working state, the limiting part (17) is contacted with the moving end surfaces of the corresponding unhooking hooks (9), so that the clamping ends of the two unhooking hooks (9) are contacted, and the unhooking hooks (9) are connected with the parachute hanging ropes of the drogue;
When the limiting mechanism is in a second working state, the limiting part (17) is completely separated from the moving ends of the corresponding unhooking hooks (9), so that the clamping ends of the two unhooking hooks (9) are far away from each other, and the unhooking hooks (9) are separated from the parachute hanging ropes of the drogue;
The force bearing assembly comprises:
The first bearing plate (2) and the second bearing plate (10) are arranged in parallel, and the installation space is formed between the first bearing plate and the second bearing plate;
the rope hanging hook (1) is connected with the first bearing plate (2) and the second bearing plate (10) through bolts, and the unhooking hook (9) is connected with the first bearing plate (2) and the second bearing plate (10) through bolts;
The limit mechanism comprises:
The limiting shell is arranged on the wall surfaces, away from each other, of the first bearing plate (2) and the second bearing plate (10), an installation cavity is formed between the limiting shell and the first bearing plate (2) and between the limiting shell and the second bearing plate (10), a first opening communicated with the installation space is formed in the first bearing plate (2), a second opening communicated with the installation space is formed in the second bearing plate (10), and the installation cavity is communicated with the first opening and the second opening;
the limiting block (6) is arranged in the installation space; the limiting parts (17) are respectively formed on two side walls, close to the two unhooking hooks (9), of the limiting block (6); a limiting groove (18) which is arranged corresponding to the second opening is formed in the limiting block (6); a limiting protrusion (19) extending into the mounting cavity from the first opening is further arranged on the limiting block (6);
The driving assembly is arranged in the mounting cavity and is provided with a driving part, and the driving part is used for driving the limiting ball (14) to move between the second opening and the limiting groove (18) so as to control the limiting ball (14) to be clamped with or separated from the limiting groove (18);
The first elastic element (7) is arranged in the mounting cavity, one side of the first elastic element (7) is connected with the limit protrusion (19), and the other side of the first elastic element is connected with the side wall of the mounting cavity;
When the driving part drives the limiting ball (14) to move to the second opening, the acting force of the first elastic element (7) acts on the limiting protrusion (19), so that the limiting block (6) is assisted to move to one side far away from the unhooking hook (9), and the unhooking hook (9) is separated from the parachute hanging rope of the drogue.
2. The quick release system of claim 1, wherein the limit housing comprises:
The first limiting cover (8) is arranged on the first bearing plate (2); a first subchamber is formed between the first limit cover (8) and the first bearing plate (2);
the second limiting cover (11) is arranged on the second bearing plate (10); a second subchamber is formed between the second limit cover (11) and the second bearing plate (10);
the first subchamber and the second subchamber together form the mounting chamber.
3. A quick parachute system according to claim 2, wherein the drive assembly comprises:
-a driving member (15), the driving member (15) being arranged within the second subchamber; a limit stop (13) is arranged on the driving shaft of the driving piece (15);
When the driving shaft of the driving piece (15) drives the limit stop (13) to move along the length direction of the second force bearing plate (10) to a side far away from the unhooking hook (9), the limit ball (14) is separated from the limit groove (18), so that the limit block (6) moves to a side far away from the unhooking hook (9).
4. A quick parachute system according to claim 3, wherein the drive assembly further comprises:
a second elastic element (12), wherein the second elastic element (12) is positioned at one side of the limit stop (13) away from the driving piece (15), one end of the second elastic element (12) is connected with the limit stop (13), and the other end of the second elastic element is connected with the side wall of the second subchamber;
when the driving shaft of the driving piece (15) drives the limit stop (13) to move to the side far away from the unhooking hook (9) along the length direction of the second force bearing plate (10), the acting force of the second elastic element (12) is applied to the limit stop (13) so as to assist the limit stop (13) to move stably.
5. A quick parachute system according to claim 1, further comprising:
the protection cover (3), the protection cover (3) is sleeved with the first bearing plate (2), the second bearing plate (10) and the outside of the limiting shell.
6. A quick parachute system according to claim 1, further comprising:
The bearing columns (16) penetrate through pin holes in the first bearing plate (2), pin holes in the second bearing plate (10), the rope hanging hooks (1) and the unhooking hooks (9) and are connected through locking nuts (4) and locking screws (5).
7. An aircraft, comprising: a quick parachute system according to any one of claims 1 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410405459.3A CN117985250B (en) | 2024-04-07 | 2024-04-07 | Quick parachute removing system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410405459.3A CN117985250B (en) | 2024-04-07 | 2024-04-07 | Quick parachute removing system and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117985250A CN117985250A (en) | 2024-05-07 |
| CN117985250B true CN117985250B (en) | 2024-07-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410405459.3A Active CN117985250B (en) | 2024-04-07 | 2024-04-07 | Quick parachute removing system and aircraft |
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| CN (1) | CN117985250B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118665716A (en) * | 2024-08-23 | 2024-09-20 | 四川凌空天行科技有限公司 | Electromagnetic separating mechanism for aircraft and parachute |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012045929A1 (en) * | 2010-10-08 | 2012-04-12 | ÉTAT FRANÇAIS représenté par LE DÉLÉGUÉ GÉNÉRAL POUR L'ARMEMENT | Securing/releasing device, and related airdrop device |
| WO2020243451A1 (en) * | 2019-05-29 | 2020-12-03 | P.D. Of Miami, Inc. | Release mechanism device, parachute systems and parachute stabilization |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB798482A (en) * | 1955-06-06 | 1958-07-23 | Short Brothers & Harland Ltd | Improvements relating to parachute and like release mechanism |
| FR1272993A (en) * | 1960-08-23 | 1961-10-06 | Auto-release coupling device | |
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