CN108482686B - Heavy helicopter catapulting escape device - Google Patents
Heavy helicopter catapulting escape device Download PDFInfo
- Publication number
- CN108482686B CN108482686B CN201810509760.3A CN201810509760A CN108482686B CN 108482686 B CN108482686 B CN 108482686B CN 201810509760 A CN201810509760 A CN 201810509760A CN 108482686 B CN108482686 B CN 108482686B
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- ejection
- machine body
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- connecting plate
- wheels
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- 239000002360 explosive Substances 0.000 claims abstract description 20
- 238000004880 explosion Methods 0.000 claims description 4
- 238000005516 engineering process Methods 0.000 description 10
- 238000004146 energy storage Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
Classifications
-
- 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
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/12—Ejectable capsules
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- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Motorcycle And Bicycle Frame (AREA)
Abstract
The invention discloses an ejection escape device of a heavy helicopter, which comprises a body, a connecting device, a control module, a power module and an ejection cabin, wherein the body is provided with a first power supply and a second power supply; the machine body is hollow, the ejection bin is arranged in the machine body, and a rear cabin door for the ejection bin to eject is arranged at the tail part of the machine body; at least 4 power wheels driven by an engine are arranged at the bottom of the ejection bin, and auxiliary wheels are arranged at the top and two sides of the ejection bin; the head of the ejection bin is connected with the machine body through a connecting device. The connecting device comprises a connecting plate, a pressing plate, a right-angle limiting block and an explosive cable. The control module is connected with each engine and the connecting device and is used for controlling the connecting device to break after receiving the ejection command, enabling each engine to work and ejecting the ejection bin from the rear cabin door of the machine body. The invention ensures that the personnel escape when the helicopter is in accident has higher initiative and improves the escape probability.
Description
Technical Field
The invention relates to a life-saving ejection mechanism of a heavy helicopter, in particular to an ejection escape device of the heavy helicopter.
Background
The rapid development of the current motor and battery energy storage technology provides the possibility for this new active escape device. By the aid of the device, when the helicopter is in accident, personnel on the helicopter can more actively perform escape ejection, and if the device is matched with a parachute, an inflatable air bag and the like, the casualties rate of the helicopter when the helicopter is in accident can be greatly reduced.
From the development status of domestic electric automobiles, china is already in the world advanced level in the fields of motors and battery energy storage, so that the scheme has a good prospect. At present, there is no technology of helicopter ejection in China temporarily, and only Russian card-52 has cabin ejection technology abroad, but the technology applied by the helicopter needs to break a rotor firstly and then eject a seat from the upper part by rocket propulsion, so that the helicopter has great danger.
At present, when a helicopter is dangerous, the helicopter is generally prevented from casualties by means of the helicopter rotor wing autorotation landing and anti-crash structure, the helicopter is very passive, and the helicopter can directly fall when encountering rotor wing damage, so that the helicopter almost cannot achieve a protection effect. The ejection device well solves the problem that the active escape can not be realized.
Disclosure of Invention
The invention aims to solve the technical problem of providing a heavy helicopter ejection escape device aiming at the defects related to the background technology.
The invention adopts the following technical scheme for solving the technical problems:
the heavy helicopter catapulting escape device comprises a body, a connecting device, a control module, a power module and an catapulting bin;
the machine body is hollow, the ejection bin is arranged in the machine body, and a rear cabin door for the ejection bin to eject is arranged at the tail part of the machine body;
the ejection bin comprises a shell, N power wheels, N motors and 3M auxiliary wheels, wherein N is a natural number greater than or equal to 4, and M is a natural number greater than or equal to 1;
the head of the shell is connected with the inner wall of the machine body through a connecting device;
the N power wheels are uniformly arranged at the bottom of the ejection bin;
the N motors are arranged on the ejection bin and are in one-to-one correspondence with the N power wheels and are used for driving the N power wheels to rotate;
the 3M auxiliary wheels are divided into 3 groups, each group of M auxiliary wheels is respectively arranged on the top and two side walls of the ejection bin, and each group of auxiliary wheels is on the same straight line;
three grooves extending from the head of the machine body to the rear cabin door are formed in the inner wall of the machine body, the three grooves correspond to the 3 groups of auxiliary wheels one by one, and the 3 groups of auxiliary wheels rotate in the corresponding machine body grooves when the ejection cabin ejects out;
the connecting device comprises a connecting plate, a pressing plate, a right-angle limiting block and an explosive cable;
one end of the connecting plate is fixedly connected with the machine body, and the other end of the connecting plate is fixedly connected with the ejection bin;
a groove for placing the explosive cable is formed in the middle of the pressing plate, and one end of the pressing plate is fixedly connected with the connecting plate;
the right-angle limiting block is fixedly connected with the connecting plate, and the other end of the pressing plate is fixed on the connecting plate;
the explosive cable is used for breaking the connecting plate along the groove of the pressing plate after triggering explosion, and at the moment, one end of the pressing plate, which is close to the right-angle limiting block, is separated from the right-angle limiting block;
the power supply module is arranged on the ejection bin and is respectively and electrically connected with the control module and the N motors for supplying power;
the control module is respectively and electrically connected with the N motors and the explosive cable and is used for controlling the explosive cable to explode after receiving the ejecting instruction, so that the connecting plate is broken, the ejection bin is separated from the machine body, and simultaneously, the N motors are controlled to work, so that the ejection bin is ejected out from the rear cabin door.
As a further optimization scheme of the heavy helicopter ejection escape device, M=3 and N=6, at the moment, six driving wheels are uniformly distributed in two rows and three columns along the direction of the ejection bin.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
1. by adopting the technology, people can escape when the helicopter is in accident, the higher initiative is realized, and the escape probability is improved.
2. The technology adopted by the scheme is most of the current mature technology, such as a motor, electric energy storage and the like, so that the technology is reliable.
3. Compared with the escape scheme of the K-52 helicopter, the escape scheme does not need to generate explosion, so that the safety is higher.
4. The helicopter body is slightly changed by the scheme, so that the application range is wider.
Drawings
FIG. 1 is a schematic general construction of the present invention;
fig. 2 is a schematic structural view of the connecting device in the present invention.
In the figure, the machine body 1-, the auxiliary wheels at the top of the ejection bin 2-, the ejection bin 3-, the auxiliary wheels at the two sides of the ejection bin 4-, the power wheel 5-, the explosive rope 6-, the pressing plate 7-, the connecting plate 8-and the right-angle limiting block 9-are arranged.
Detailed Description
The technical scheme of the invention is further described in detail below with reference to the accompanying drawings:
this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, the components are exaggerated for clarity.
As shown in fig. 1, the invention discloses a heavy helicopter ejection escape device, which comprises a body, a connecting device, a control module, a power module and an ejection cabin;
the machine body is hollow, the ejection bin is arranged in the machine body, and a rear cabin door for the ejection bin to eject is arranged at the tail part of the machine body;
the ejection bin comprises a shell, N power wheels, N motors and 3M auxiliary wheels, wherein N is a natural number greater than or equal to 4, and M is a natural number greater than or equal to 1;
the head of the shell is connected with the inner wall of the machine body through a connecting device;
the N power wheels are uniformly arranged at the bottom of the ejection bin;
the N motors are arranged on the ejection bin and are in one-to-one correspondence with the N power wheels and are used for driving the N power wheels to rotate;
the 3M auxiliary wheels are divided into 3 groups, each group of M auxiliary wheels is respectively arranged on the top and two side walls of the ejection bin, and each group of auxiliary wheels is on the same straight line;
the inner wall of the machine body is provided with three grooves extending from the head of the machine body to the rear cabin door, the three grooves correspond to the 3 groups of auxiliary wheels one by one, and the 3 groups of auxiliary wheels rotate in the corresponding machine body grooves respectively when the ejection cabin ejects.
As shown in fig. 2, the connecting device comprises a connecting plate, a pressing plate, a right-angle limiting block and an explosive cable;
one end of the connecting plate is fixedly connected with the machine body, and the other end of the connecting plate is fixedly connected with the ejection bin;
a groove for placing the explosive cable is formed in the middle of the pressing plate, and one end of the pressing plate is fixedly connected with the connecting plate;
the right-angle limiting block is fixedly connected with the connecting plate, and the other end of the pressing plate is fixed on the connecting plate;
the explosive cable is used for breaking the connecting plate along the groove of the pressing plate after triggering explosion, and at the moment, one end of the pressing plate, which is close to the right-angle limiting block, is separated from the right-angle limiting block.
The power supply module is arranged on the ejection bin and is respectively and electrically connected with the control module and the N motors for supplying power;
the control module is respectively and electrically connected with the N motors and the explosive cable and is used for controlling the explosive cable to explode after receiving the ejecting instruction, so that the connecting plate is broken, the ejection bin is separated from the machine body, and simultaneously, the N motors are controlled to work, so that the ejection bin is ejected out from the rear cabin door.
One preferred application is that M is 3 and N is 6, and at this time, six driving wheels are uniformly distributed in two rows and three columns along the direction of the magazine of the ejection magazine.
The explosive cable is an elongated metal hose filled with explosive, is arranged in a groove with a U-shaped section along a separation surface, and is used for unlocking two separated bodies by directionally exploding the explosive and cutting a connecting plate during separation. The connecting and unlocking device can ensure that no prefabricated separating surface exists between two separated bodies, so that the structure quality is smaller, the connecting rigidity is easy to ensure, the separating synchronism is good, and the reliability is higher.
The ejection device is called automobile type ejection, the invention uses the motor to drive the driving wheel on the ejection cabin body to move so as to accelerate the ejection cabin to a proper speed, the energy required for carrying out the ejection for one time is less than 1kWh, and the weight of the battery can be limited within 50 kg. Considering that such transmission has been used for a long time in the aspect of automobiles, the technology is mature, and can be directly applied to ejection.
It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
While the foregoing is directed to embodiments of the present invention, other and further details of the invention may be had by the present invention, it should be understood that the foregoing description is merely illustrative of the present invention and that no limitations are intended to the scope of the invention, except insofar as modifications, equivalents, improvements or modifications are within the spirit and principles of the invention.
Claims (2)
1. The ejection escape device of the heavy helicopter is characterized by comprising a machine body, a connecting device, a control module, a power supply module and an ejection cabin;
the machine body is hollow, the ejection bin is arranged in the machine body, and a rear cabin door for the ejection bin to eject is arranged at the tail part of the machine body;
the ejection bin comprises a shell, N power wheels, N motors and 3M auxiliary wheels, wherein N is a natural number greater than or equal to 4, and M is a natural number greater than or equal to 1;
the head of the shell is connected with the inner wall of the machine body through a connecting device;
the N power wheels are uniformly arranged at the bottom of the ejection bin;
the N motors are arranged on the ejection bin and are in one-to-one correspondence with the N power wheels and are used for driving the N power wheels to rotate;
the 3M auxiliary wheels are divided into 3 groups, each group of M auxiliary wheels is respectively arranged on the top and two side walls of the ejection bin, and each group of auxiliary wheels is on the same straight line;
three grooves extending from the head of the machine body to the rear cabin door are formed in the inner wall of the machine body, the three grooves correspond to the 3 groups of auxiliary wheels one by one, and the 3 groups of auxiliary wheels rotate in the corresponding machine body grooves when the ejection cabin ejects out;
the connecting device comprises a connecting plate, a pressing plate, a right-angle limiting block and an explosive cable;
one end of the connecting plate is fixedly connected with the machine body, and the other end of the connecting plate is fixedly connected with the ejection bin;
a groove for placing the explosive cable is formed in the middle of the pressing plate, and one end of the pressing plate is fixedly connected with the connecting plate;
the right-angle limiting block is fixedly connected with the connecting plate, and the other end of the pressing plate is fixed on the connecting plate;
the explosive cable is used for breaking the connecting plate along the groove of the pressing plate after triggering explosion, and at the moment, one end of the pressing plate, which is close to the right-angle limiting block, is separated from the right-angle limiting block;
the power supply module is arranged on the ejection bin and is respectively and electrically connected with the control module and the N motors for supplying power;
the control module is respectively and electrically connected with the N motors and the explosive cable and is used for controlling the explosive cable to explode after receiving the ejecting instruction, so that the connecting plate is broken, the ejection bin is separated from the machine body, and simultaneously, the N motors are controlled to work, so that the ejection bin is ejected out from the rear cabin door.
2. The heavy helicopter ejection escape device according to claim 1, wherein m=3 and n=6, and the six driving wheels are uniformly distributed in two rows and three columns along the direction of the ejection cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810509760.3A CN108482686B (en) | 2018-05-24 | 2018-05-24 | Heavy helicopter catapulting escape device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810509760.3A CN108482686B (en) | 2018-05-24 | 2018-05-24 | Heavy helicopter catapulting escape device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108482686A CN108482686A (en) | 2018-09-04 |
| CN108482686B true CN108482686B (en) | 2023-09-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810509760.3A Active CN108482686B (en) | 2018-05-24 | 2018-05-24 | Heavy helicopter catapulting escape device |
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| Country | Link |
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| CN (1) | CN108482686B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109305372A (en) * | 2018-09-10 | 2019-02-05 | 南京航空航天大学 | Heavy helicopter and its catapult technique with separable crew module |
| CN109747806A (en) * | 2018-12-10 | 2019-05-14 | 储锋 | A kind of airplane catapult system |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3525490A (en) * | 1968-04-11 | 1970-08-25 | Stencel Aero Eng Corp | Aircraft ejection seat system |
| CN1473739A (en) * | 2002-08-08 | 2004-02-11 | 孙则阳 | Gun type ejection life-saving system for civil air plane |
| CN200967565Y (en) * | 2006-11-10 | 2007-10-31 | 闫波 | Safe cabin |
| CN202314999U (en) * | 2011-09-28 | 2012-07-11 | 王剑刚 | Ejection type high-rise life saving dropping system |
| CN104941088A (en) * | 2015-06-11 | 2015-09-30 | 华北科技学院 | Escape capsule |
| CN208377076U (en) * | 2018-05-24 | 2019-01-15 | 南京航空航天大学 | A kind of heavy helicopter ejection escape device |
-
2018
- 2018-05-24 CN CN201810509760.3A patent/CN108482686B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3525490A (en) * | 1968-04-11 | 1970-08-25 | Stencel Aero Eng Corp | Aircraft ejection seat system |
| CN1473739A (en) * | 2002-08-08 | 2004-02-11 | 孙则阳 | Gun type ejection life-saving system for civil air plane |
| CN200967565Y (en) * | 2006-11-10 | 2007-10-31 | 闫波 | Safe cabin |
| CN202314999U (en) * | 2011-09-28 | 2012-07-11 | 王剑刚 | Ejection type high-rise life saving dropping system |
| CN104941088A (en) * | 2015-06-11 | 2015-09-30 | 华北科技学院 | Escape capsule |
| CN208377076U (en) * | 2018-05-24 | 2019-01-15 | 南京航空航天大学 | A kind of heavy helicopter ejection escape device |
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| Publication number | Publication date |
|---|---|
| CN108482686A (en) | 2018-09-04 |
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