CN112109926B - Explosive cutting and separating device for rapid cabin opening of aircraft - Google Patents
Explosive cutting and separating device for rapid cabin opening of aircraft Download PDFInfo
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- CN112109926B CN112109926B CN202010897722.7A CN202010897722A CN112109926B CN 112109926 B CN112109926 B CN 112109926B CN 202010897722 A CN202010897722 A CN 202010897722A CN 112109926 B CN112109926 B CN 112109926B
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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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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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
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- Aviation & Aerospace Engineering (AREA)
- Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
Abstract
The invention discloses an explosive cutting and separating device for rapid cabin opening of an aircraft, which comprises an energy-gathering cutting rope, a buffering protection strip, a protection cover, a base and a baffle. Gather can the cutting cable and be the annular and arrange to set up along the parting face inner wall of aircraft casing, buffering protection strip outer wall is equipped with the first recess of round, gather and to cut the cable embedding and fly first recess, safety cover laminating aircraft shells inner wall, it has the second recess to open on the outer wall of safety cover, buffering protection strip embedding second recess, safety cover one end is opened to second recess direction has a third recess, between base embedding third recess and the aircraft casing main part. The other end of the protective cover is provided with a fourth groove towards the direction of the second groove, one end of the baffle is embedded between the fourth groove and the aircraft shell and is abutted against the protective cover, and the other end of the baffle is positioned outside the fourth groove and is fixedly connected with the cutting separation part of the aircraft shell. The invention has the advantages of high cutting speed, large cutting surface and high cutting power when the aircraft is opened.
Description
Technical Field
The invention belongs to the field of explosive cutting, and particularly relates to an explosive cutting and separating device for rapid cabin opening of an aircraft.
Background
In recent years, China has attracted attention in the aerospace field, and the development of aerospace industry drives a series of scientific and technological progress. The government of China highly pays attention to the development of the aircraft industry, and the aircraft industry is used as a strategic emerging industry and a high-technology industry with preferential development. The aircraft structure is usually made of materials with the characteristics of small specific gravity, high specific strength, large specific modulus, convenient processing and forming, high and low temperature resistance, strong aging resistance and corrosion resistance and the like. In the field of aerospace, the aluminum alloy material has the unique advantage of high material requirements of aircrafts, so that the aluminum alloy material is effectively applied to aerospace technology and military.
At present, the aluminum alloy material becomes a high-performance aerospace material which is vigorously developed at home and abroad, and the structural member of the aircraft cabin equipment is manufactured, so that the cost of the material is greatly reduced while the performance of the aircraft equipment is ensured, and the quality of the equipment is greatly reduced. The application of the aluminum alloy material effectively solves the requirements of aircraft structure integration and light weight, but for the conventional aircraft, a key problem is how to rapidly open the cabin and realize effective cutting separation.
At present, because aircraft opening has some technical difficulties, explosive cutting separation usually causes damage and destruction of an aircraft shell, often causes phenomena of uneven separation surfaces, material delamination, tearing and the like, and even causes damage to other structural components. Therefore, the cutting and separating device with reasonable structure is the key for realizing the rapid cabin opening technology of the aircraft and is a novel direction for the development of the existing cabin opening technology of the aircraft.
Therefore, a cutting and separating device which is reasonable in design, simple in structure and capable of being widely applied to rapid cabin opening of the aircraft needs to be developed. Form comprehensive light integration with the aircraft, solve the not enough of current aircraft technique of opening the cabin, be difficult to realize cutting validity and ageing's problem.
Disclosure of Invention
The invention aims to provide an explosive cutting and separating device for rapid cabin opening of an aircraft, which effectively solves the design contradiction between the connection strength and the effective separation of a main body part and a cutting and separating part, ensures the sufficient connection strength, ensures the effective separation of the cutting and separating part and the main body part, and has good application prospect.
The technical solution for realizing the purpose of the invention is as follows: the utility model provides an explosion cutting separator for aircraft is fast opened cabin, sets up in the aircraft casing, including gathering can cutting cable, buffering protective strip, safety cover, base, baffle, detonator. The aircraft casing includes main part and cutting part of separation (aircraft division of cabin region), gather and cut the cable and include two hoop cables and two vertical cables, two hoop cables and two vertical cables are the inner wall of the casing that the aircraft division of cabin region was laid to the quadrilateral form, overlap joint position seam department is equipped with the detonator, buffering protection strip outer wall is equipped with the first recess of round, gather and cut the first recess of cable embedding, first recess and gather and cut the cable and closely cooperate, the outer wall of buffering protection strip is circular-arc to the indent, can effective absorption detonation energy. The safety cover is arch, and safety cover laminating aircraft shells inner wall opens on the outer wall of safety cover has the second recess, and buffering protection strip embedding second recess, and safety cover one end is opened to second recess direction has a third recess, and the base imbeds between third recess and the aircraft casing main part to link firmly through first bolt. The other end of the protective cover is provided with a fourth groove towards the direction of the second groove, one end of the baffle is embedded between the fourth groove and the aircraft shell to abut against the protective cover, and the other end of the baffle is positioned outside the fourth groove and is fixedly connected with the cutting separation part of the aircraft shell through a second bolt.
Compared with the prior art, the invention has the remarkable advantages that:
(1) the device disclosed by the invention is simple and reasonable in structural design, realizes comprehensive light integration with the aircraft, can achieve a good separation effect while ensuring the connection strength of the cutting separation part and the main body part of the aircraft cabin body, effectively solves the problem of complete structure and no deformation after separation, and can be widely applied to rapid cabin opening of the aircraft.
(2) The invention adopts the energy-gathering cutting cable to rapidly cut and separate the aircraft cabin body, the cabin opening area fracture consists of two parts of jet penetration and detonation bursting, but the ratio of the jet penetration thickness to the detonation bursting thickness is different when different structural devices cut and separate.
(3) According to the invention, by controlling the preset explosion height of the energy-gathered cutting rope, the reasonable distribution of the detonation energy generated by the energy-gathered cutting rope in the structure is realized, so that the cutting surface can achieve the effects of being neat, free of layering and free of tearing.
Drawings
Fig. 1 is a schematic partial cross-sectional view of an explosive cutting and separating device for rapid aircraft opening according to the invention.
FIG. 2 is a general schematic view of the explosive cutting and separating device for rapid aircraft cabin opening according to the present invention
Fig. 3 is a partially enlarged schematic view of the explosive cutting and separating device for the rapid cabin opening of the aircraft.
Detailed Description
The invention is further described with reference to the following figures and examples.
With reference to fig. 1, 2 and 3, the invention discloses an explosive cutting and separating device 10 for aircraft fast cabin opening, which is arranged in an aircraft shell 7 and comprises an energy-gathering cutting rope 1, a buffering protective strip 2, a protective cover 3, a base 4, a baffle 5 and a plurality of detonators 11. Aircraft casing 7 includes main part and cutting separation part (aircraft division of cabin region), gather ability cutting cable 1 and include two hoop cables and two vertical cables, two hoop cables and two vertical cables are the inner wall of the housing that the aircraft division of cabin region was laid to the quadrilateral, overlap joint position seam crossing all is equipped with detonator 11, 2 outer walls of buffering protection strip are equipped with the first recess of round, gather and to cut the first recess of 1 embedding of cable, first recess and gather and to cut the cable 1 and closely cooperate, the outer wall of buffering protection strip 2 is circular-arc to the indent, can effectively absorb the detonation energy. The cross-section of safety cover 3 is the arch, and 3 laminating aircraft shells 7 inner walls of safety cover, it has the second recess to open on the outer wall of safety cover 3, and buffering protection strip 2 imbeds the second recess, and 3 one ends of safety cover are opened to second recess direction has a third recess, and base 4 imbeds between third recess and the 7 main parts of aircraft shell to link firmly through first bolt 8. The other end of the protective cover 3 is provided with a fourth groove towards the direction of the second groove, one end of the baffle 5 is embedded between the fourth groove and the aircraft shell 7 to abut against the protective cover 3, and the other end of the baffle is positioned outside the fourth groove and is fixedly connected with the cutting separation part of the aircraft shell 7 through a second bolt 9.
The explosion cutting and separating device for the rapid cabin opening of the aircraft further comprises a sealing ring 6, and the space between the baffle 5 and the protective cover 3 is sealed through the sealing ring 6, so that the generated air flow is prevented from overflowing to cause damage to other structural members; the aircraft shell 7 is cut by the energy-gathered jet flow generated by the energy-gathered cutting rope 1 at the preset separation surface to realize the separation of the cutting separation part and the main body part, and the cutting separation part is separated from the main body part under the action of external pressure to realize the cabin opening.
The aircraft shell 7 is made of an aluminum alloy material represented by an aerospace material. The thickness of the aircraft shell 7 is determined according to the load bearing requirements of the structure, and the smaller the separation thickness is, the more beneficial the cutting separation is on the premise of meeting the load bearing.
When the energy-collecting cutting rope 1 is selected to be explosive, the energy-collecting jet flow is required to be formed and converged before reaching the shell 7 of the aircraft to be cut.
The buffering protective strip 2 is a rubber sheath or a polyurethane foam sheath, and the sectional area of the buffering protective strip is not less than 6 times of the charging sectional area of the energy-gathering cutting rope 1. The buffering protection strip 2 plays a role in absorbing detonation energy in the structure, and the material and the volume of the buffering protection strip 2 are main factors influencing the energy absorption effect. Different types of energy-gathering cutting ropes generate different detonation energies, and correspondingly, the required materials and the required volumes of the buffer sheaths 2 are different. By controlling the preset explosion height of the energy-gathering cutting rope 1, the detonation energy generated by the energy-gathering cutting rope 1 is reasonably distributed in the structure, so that the effect of neatly cutting the aircraft shell 7 is realized. Therefore, the cutting surface is ensured to be neat without layering and tearing.
The protective cover 3 is made of aluminum alloy material and is used for realizing effective utilization and release ratio of detonation energy, the structure is complete after separation, and the protective cover 3 has no large deformation.
The base 4 can be made of an aluminum alloy material or a carbon fiber resin composite material, a threaded hole connected with the protective cover 3 is formed in the base 4, the base 4 is connected with a third groove of the protective cover 3 and a main body of the aircraft shell 7 through a first bolt 8, the protective cover 3 can be fixed on the one hand, and the base 4 can keep rigidity of a structure fixed with the protective cover after separation on the other hand.
The baffle 5 can be made of aluminum alloy materials or carbon fiber resin composite materials, the baffle 5 is connected to the cutting separation part of the aircraft shell through the second bolt 9, the protective cover 3 can be controlled, and deformation of the protective cover is prevented.
In the present invention, where the cutting cord 1 is provided, the protective cover 3, the base 4, and the baffle 5 are inevitably provided.
While the invention has been described with reference to specific embodiments, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the following claims. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (6)
1. An explosive cutting and separating device for rapid aircraft opening, an aircraft shell (7) comprises a main body part and a cutting and separating part, and the cutting and separating part is an aircraft opening area and is characterized in that: comprises the steps of (a) preparing a mixture of a plurality of raw materials,
the energy-gathering cutting rope (1) is in a quadrilateral shape and is arranged along the inner wall of the separation surface of the aircraft shell (7) to generate energy-gathering jet flow, so that the aircraft cabin opening area is cut, and the separation of the cutting separation part and the main body part is realized; when the energy-gathering cutting rope (1) is selected to be high, the energy-gathering jet flow is required to be formed and gathered before reaching the shell (7) of the aircraft to be cut;
the outer wall of the buffering protection strip (2) is provided with a circle of first grooves, the energy-gathering cutting rope (1) is embedded into the first grooves, and the energy-gathering cutting rope and the first grooves are tightly matched to play a role in absorbing detonation energy; the outer wall surface of the buffering protective strip (2) is an inward-concave arc, so that detonation energy is effectively absorbed;
the section of the protective cover (3) is arched, the protective cover (3) is tightly attached to the inner wall of the aircraft shell (7), a second groove is formed in the outer wall of the protective cover (3), the buffering protective strip (2) is embedded into the second groove, a third groove is formed in one end of the protective cover (3) in the direction of the second groove, and a fourth groove is formed in the other end of the protective cover (3) in the direction of the second groove;
the base (4) is embedded between the third groove and the main body part of the aircraft shell (7) and fixedly connected with the third groove and the main body part; the base (4) is used for fixing the protective cover (3) on one hand and can keep the rigidity of a structure fixed with the protective cover after being separated on the other hand;
one end of the baffle (5) is embedded between the fourth groove and the aircraft shell (7) and props against the protective cover (3), and the other end of the baffle is positioned outside the fourth groove and fixedly connected with the cutting separation part of the aircraft shell (7) and used for controlling the protective cover (3) and preventing the protective cover from deforming;
and the exploder (11) is arranged on the energy-gathered cutting rope (1) and is used for exploding the energy-gathered cutting rope (1).
2. The explosive cutting and separating device for rapid aircraft opening according to claim 1, wherein: the buffering protective strip (2) adopts a rubber sheath or a polyurethane foam sheath.
3. The explosive cutting and separating device for rapid aircraft opening according to claim 1, wherein: the protective cover (3) is made of aluminum alloy materials and is used for realizing effective utilization and release ratio of detonation energy, the structure is complete after separation, and the protective cover (3) has no large deformation.
4. The explosive cutting and separating device for rapid aircraft opening according to claim 1, wherein: the base (4) is made of an aluminum alloy material or a carbon fiber resin composite material.
5. The explosive cutting and separating device for rapid aircraft opening according to claim 1, wherein: the baffle (5) is made of aluminum alloy material or carbon fiber resin composite material.
6. The explosive cutting and separating device for rapid aircraft opening according to claim 1, wherein: the protective cover is characterized by further comprising a sealing ring (6), and the sealing ring (6) is used for sealing between the baffle plate (5) and the protective cover (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010897722.7A CN112109926B (en) | 2020-08-31 | 2020-08-31 | Explosive cutting and separating device for rapid cabin opening of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010897722.7A CN112109926B (en) | 2020-08-31 | 2020-08-31 | Explosive cutting and separating device for rapid cabin opening of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112109926A CN112109926A (en) | 2020-12-22 |
| CN112109926B true CN112109926B (en) | 2022-05-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010897722.7A Active CN112109926B (en) | 2020-08-31 | 2020-08-31 | Explosive cutting and separating device for rapid cabin opening of aircraft |
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Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3135163A (en) * | 1962-05-08 | 1964-06-02 | Jr George F Mechlin | Self-rupturing diaphragm assembly |
| US4648227A (en) * | 1985-09-23 | 1987-03-10 | The Boeing Company | Low shock explosive joint systems |
| CN203461147U (en) * | 2013-08-19 | 2014-03-05 | 北京宇航系统工程研究所 | Interstage separating device for aircraft |
| CN203615839U (en) * | 2013-11-29 | 2014-05-28 | 北京宇航系统工程研究所 | Interstage separating device |
| CN107031871B (en) * | 2016-10-14 | 2019-11-29 | 北京宇航系统工程研究所 | A kind of cutting separator of fiber-reinforced composite materials structures |
| CN110965045A (en) * | 2018-09-29 | 2020-04-07 | 南京理工大学 | Method for protecting thin-wall energy-gathered cutting rope by utilizing Parylene micro-nano film |
| CN213873999U (en) * | 2021-04-25 | 2021-08-03 | 中国科学院力学研究所 | Carrier rocket |
| CN113525726B (en) * | 2021-06-23 | 2023-03-07 | 北京宇航系统工程研究所 | Large-thickness weak groove-free, stress-concentration-free and protective cover-free separation structure |
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- 2020-08-31 CN CN202010897722.7A patent/CN112109926B/en active Active
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