CN107933975B - High-temperature-resistant firer catapult - Google Patents
High-temperature-resistant firer catapult Download PDFInfo
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- CN107933975B CN107933975B CN201711116287.4A CN201711116287A CN107933975B CN 107933975 B CN107933975 B CN 107933975B CN 201711116287 A CN201711116287 A CN 201711116287A CN 107933975 B CN107933975 B CN 107933975B
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- cylinder
- medicine box
- diameter
- component
- inner cylinder
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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
Abstract
The invention relates to a high-temperature-resistant firer catapult which comprises an inner cylinder component, an outer cylinder component, a medicine box component and a shearing pin, wherein the inner cylinder component and the outer cylinder component are fixed through the shearing pin, and the outer cylinder component is connected with the medicine box component; the outer aircraft protective cover is connected with the inner barrel assembly, and the outer aircraft is connected with the outer barrel assembly. The catapult has axial bearing capacity, can bear external 560 ℃ high temperature for 1500s and then is normally catapulted and separated, the catapult speed is high, and the piston of the catapult is flush with the end face of the outer cylinder after separation, so that the aerodynamic appearance of the aircraft is ensured. The invention can be used for connecting and separating the protective cover and the supersonic aircraft.
Description
Technical Field
The invention belongs to the field of initiating explosive devices, and relates to a high-temperature-resistant initiating explosive device catapult capable of separating a supersonic aircraft protective cover from a supersonic aircraft.
Background
The catapult is widely applied to the fields of spacecrafts, satellites, carrier rockets, unmanned aerial vehicles and the like, is mainly used for connecting and separating structures, provides speed for reliable separation of objects, is generally used for locking and separating a cabin cover and a protective cover with lighter weight, belongs to the key technology of a separation catapulting system, determines success or failure of the catapulting and separating system, and has more and more prominent importance in the field of aerospace.
With the upgrading of the requirement of spacecraft tasks and the higher requirement of supersonic aircrafts on thermal environment, the catapult as a key action execution component also faces new research subjects. According to the report of high-temperature protection characteristic research of catapults for supersonic aircraft protective covers in journal of aerospace Return and remote sensing, the use temperature of the catapults matched with the existing star ships and aircrafts is mostly in the range of minus 60 ℃ to plus 90 ℃, and the tolerance temperature of main charges used by most of the catapults is about 100 ℃. In the flight process of the supersonic aircraft, the temperature of the head of the aircraft reaches more than hundreds of degrees due to the influence of great aerodynamic resistance, the ejector is rigidly connected with the protective cover and directly bears the surface heat flow of the aircraft, and the structure is rapidly heated. The prior catapult has the following problems:
(1) if the main charge with high temperature resistance is selected, the main charge is more insensitive and has influence on ignition reliability under the condition of limited ignition current.
(2) The existing ejector shear pin is generally made of aluminum alloy and structural steel, the shear strength is reduced rapidly under the high-temperature condition, and the speed and the thrust of the ejector are influenced.
(3) In order to ensure the stability of the motion of the piston, the contact between the piston and the sliding rod is generally surface contact, but the heat conduction speed is increased.
Therefore, the ejector can be optimized only from the structural design under the condition of using the existing main charge with mature application, the speed of structural heat conduction is reduced, and the temperature of the main charge position and the igniter position can meet the use requirement.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, the firer catapult is provided, the firer catapult has high catapulting speed and works normally at high temperature, the piston of the separated catapult is flush with the end face of the outer cylinder, and the aerodynamic appearance of an aircraft is guaranteed.
The technical solution of the invention is as follows:
a high-temperature-resistant firer catapult comprises an inner cylinder component, an outer cylinder component, a medicine box component and a shearing pin, wherein the inner cylinder component and the outer cylinder component are fixed through the shearing pin, and the outer cylinder component is connected with the medicine box component; the outer aircraft protective cover is connected with the inner barrel assembly, and the outer aircraft is connected with the outer barrel assembly.
The inner cylinder component comprises an inner cylinder and a sliding rod; one end of the inner cylinder is provided with a flange, the flange end is provided with internal threads, the other end of the inner cylinder is provided with a unthreaded hole, and a round hole is formed in the portion, close to the flange, of the unthreaded hole in the circumferential direction; the sliding rod is a cylinder, one end of the sliding rod is a ball head, the other end of the sliding rod is a plane, the outer diameter of the sliding rod is in clearance fit with the inner diameter of the through hole of the inner cylinder, and the sliding rod is inserted into the unthreaded hole of the inner cylinder.
The outer barrel component comprises a nut, an outer barrel and a piston; the outer cylinder is a cylinder, one end of the outer cylinder is provided with an external thread, a stepped hole is formed in the outer cylinder, the aperture of a unthreaded hole close to one end of the external thread is larger than that of the other end of the outer cylinder, an internal thread through hole is formed in the circumferential direction of the outer cylinder wall at one end of the unthreaded hole with a small aperture, and a boss is distributed on the outer wall of the outer cylinder; the nut is a cylinder, the inside of the nut is divided into a thread section and a unthreaded hole section, the small diameter of the internal thread is larger than the diameter of the unthreaded hole, the diameter of the unthreaded hole is larger than the outer diameter of the outer cylinder and smaller than the outer diameter of a boss of the outer cylinder, and the nut is arranged at the boss from one end of the external thread of the outer cylinder and clamped; the piston is a cylinder, the cylinder is divided into a thick section and a thin section, the piston is installed from one end of the external thread of the outer cylinder, and the end face of the thin section is in point contact with one end point of the spherical surface of the sliding rod.
One end of the shearing pin is an external thread, the other end of the shearing pin is a cylinder, and the external thread is matched with the internal thread of the outer cylinder.
The medicine box component comprises a medicine box base, a heat insulation gasket, a medicine box and an igniter; the medicine box base is an L-shaped cavity, a tapered hole is arranged in the middle section of the inner cavity, the end face, facing the large end of the tapered hole, of the two end faces of the medicine box base is used as a first end face, the other end of the tapered hole is a second end face, and the two end faces are both provided with internal threads; the heat insulation gasket is adhered to the conical hole of the medicine box base through an adhesive; the medicine box is filled with main medicine, and the medicine box is plugged into the heat-insulating gasket; the igniter is connected with the internal thread of the first end surface of the medicine box base through the external thread.
The specific mode that inner tube subassembly and urceolus subassembly are fixed through the shear pin does: the two shearing pins are oppositely screwed into the internal thread of the outer cylinder through the external threads of the shearing pins, and the cylindrical ends of the shearing pins are inserted into the round holes of the inner cylinder.
The specific mode that urceolus subassembly and medicine box subassembly are connected does: the second end surface of the medicine box base of the medicine box component is connected with the outer barrel of the outer barrel component through threads.
The external aircraft protective cover is in threaded connection with the inner cylinder of the inner cylinder assembly;
and the external aircraft is in threaded connection with a nut of the outer barrel assembly through threads of the stud.
The thickness of the inner cylinder flange is smaller than the length of the thread segment, and the major diameter of the internal thread is smaller than the aperture of the inner cylinder unthreaded hole; the inner diameter of a unthreaded hole with a small aperture of the outer cylinder is in clearance fit with the outer diameter of the inner cylinder, and the outer diameter of the outer cylinder is equal to the outer diameter of the flange of the inner cylinder; the outer diameter of the thick section is in clearance fit with the aperture of a unthreaded hole with a large aperture of the outer cylinder; the outer diameter of the thin section of the piston is in clearance fit with the inner diameter of the unthreaded hole with a small diameter of the outer cylinder.
The shearing pin is made of 1Cr18Ni9Ti stainless steel, the diameter of the cylinder of the shearing pin is smaller than the major diameter of the external thread of the shearing pin, and the length of the cylinder is not larger than the wall thickness of the inner cylinder; the material of the sliding rod is TA 15; the binder is DG-4 high temperature resistant glue.
The invention has the advantages over the prior art that:
(1) the shearing pin is made of 1Cr18Ni9Ti stainless steel, the shearing strength of the shearing pin can be kept unchanged at high temperature and normal temperature, the speed and the thrust of the ejector are kept consistent, and the ejector can work reliably and stably.
(2) The length of the sliding rod and the length of the outer cylinder are increased, so that the heat transfer path is increased, the heat transfer speed is reduced, the ejection speed of the ejector can be increased, and the requirements of different ejection speeds are met.
(3) The end of the sliding rod, which is in contact with the piston, is of a ball head structure, and is in point contact with the piston, so that the contact area is reduced, and the heat transfer speed is reduced. Meanwhile, the bulb can deform after the piston impacts the sliding rod, partial energy is absorbed, and impact of the ejector during working is reduced.
(4) The heat insulation gasket made of the non-metal material is added between the charge and the base, and the non-metal material is low in heat conductivity and used for reducing the temperature rising speed of the main charge.
Drawings
FIG. 1 is a structural diagram of a high temperature fire-resistant ejector according to the present invention;
FIG. 2 is a schematic view of the nut of the present invention;
FIG. 3 is a schematic diagram of the separation operation of the high temperature resistant firer catapult of the present invention.
Detailed Description
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
As shown in fig. 1, the high temperature resistant firer catapult of the present invention comprises an inner cylinder component, an outer cylinder component, a cartridge component and a shear pin 2, wherein the inner cylinder component and the outer cylinder component are fixed by the shear pin 2, and the outer cylinder component is connected with the cartridge component; the outer aircraft protective cover is connected with the inner barrel assembly, and the outer aircraft is connected with the outer barrel assembly.
The inner cylinder component comprises an inner cylinder 1 and a sliding rod 3; the material of the inner cylinder 1 is TA15, one end of the inner cylinder 1 is a flange, the flange end is provided with internal threads, the thickness of the flange is smaller than the length of the threaded section, the other end of the inner cylinder 1 is a unthreaded hole, the aperture of the unthreaded hole is larger than the major diameter of the internal threads of the inner cylinder 1, and a circular hole is formed in the portion, close to the flange, of the unthreaded hole in the circumferential direction; the slide bar 3 is a cylinder made of TA15, one end of the slide bar 3 is a ball head, the other end of the slide bar 3 is a plane, the outer diameter of the slide bar 3 is in clearance fit with the inner diameter of the through hole of the inner cylinder 1, and the slide bar 3 is inserted into the unthreaded hole of the inner cylinder 1. The inner cylinder 1 is connected to the protective cover of the aircraft by means of screws M6.
The outer cylinder component comprises a screw cap 4, an outer cylinder 5 and a piston 6; the outer cylinder 5 is a cylinder made of TA15, one end of the outer cylinder 5 is provided with an external thread, a stepped hole is formed in the outer cylinder 5, the aperture of a unthreaded hole close to one end of the external thread is larger than that of the other end of the external thread, an internal thread through hole is formed in the circumferential direction of the wall of the outer cylinder 5 at one end of the unthreaded hole with a small aperture, a boss is distributed on the outer wall of the outer cylinder 5, the outer diameter of the outer cylinder 5 is equal to the outer diameter of a flange of the inner cylinder 1, and the inner; as shown in fig. 2, the nut 4 is a cylinder made of TA15, the inside of the cylinder is divided into a threaded section and a unthreaded hole section, the small diameter of the internal thread is larger than the diameter of the unthreaded hole, the diameter of the unthreaded hole is larger than the outer diameter of the outer cylinder 5 and smaller than the outer diameter of a boss of the outer cylinder 5, and the nut 4 is installed and clamped at the boss from one end of the external thread of the outer cylinder 5; the piston 6 is a cylinder, the cylinder is divided into a thick section and a thin section, the outer diameter of the thick section is in clearance fit with the aperture of the unthreaded hole with the large aperture of the outer cylinder 5, the outer diameter of the thin section is in clearance fit with the inner diameter of the unthreaded hole with the small aperture of the outer cylinder 5, the piston 6 is installed from one end of the external thread of the outer cylinder 5, and the end surface of the thin section is in point contact with one end point of the spherical surface of. The nut 4 of the outer barrel assembly is in threaded connection with a stud of an external aircraft.
The one end of shearing round pin 2 is the external screw thread, and the other end is the cylinder, and the diameter of cylinder is less than the major diameter of external screw thread, and the external screw thread cooperates with the internal thread of urceolus 5, and the length of cylinder is not more than the wall thickness of inner tube 1. The two shearing pins 2 are oppositely screwed into the internal thread of the outer cylinder 5 through the external threads of the shearing pins 2, and the cylindrical ends of the shearing pins 2 are inserted into the circular holes of the inner cylinder 1. The material of the shear pin 2 is 1Cr18Ni9Ti stainless steel.
The medicine box component comprises a medicine box base 7, a heat insulation gasket 8, a medicine box 9 and an igniter 10; the medicine box base 7 is an L-shaped cavity made of TC4R, a tapered hole is arranged in the middle section of an inner cavity of the medicine box base 7, the end face, facing the large end of the tapered hole, of the two end faces of the medicine box base 7 serves as a first end face, the other end of the tapered hole serves as a second end face, and the two end faces are both provided with internal threads; the material of the heat insulation gasket 8 is an epoxy resin glass cloth rod 3840, and the heat insulation gasket 8 is connected to a tapered hole of the medicine box base 7 through a DG-4 high-temperature-resistant adhesive to play a role in heat insulation; the medicine box 9 is filled with main medicine, and the medicine box 9 is plugged into the heat-insulating gasket 8; the igniter 10 is connected with the internal thread of the first end face of the medicine box base 7 through the M14 multiplied by 1-6H external thread, and DG-4 high-temperature-resistant adhesive is coated at the thread position for preventing looseness. The medicine box base 7 of the medicine box component is connected with the outer cylinder 5 through M20 multiplied by 1-6H threads, and DG-4 high temperature resistant adhesive is coated at the threads for preventing looseness.
The operating principle of the ejector is as follows:
the basic working process of the catapult is shown in figure 3, and the whole process is divided into 3 steps:
1) sending a signal to an igniter 10, so that the igniter 10 ignites the main charge to generate high-temperature and high-pressure gas, the gas pushes the piston 6 and the sliding rod 3 to move, the shearing pin 2 is sheared, and the constraint between the inner cylinder 1 and the outer cylinder 5 is removed;
2) the piston 6 continues to push the inner cylinder assembly to continue to move forwards, the piston 6 is clamped in the outer cylinder 5, and the front end of the piston 6 is flush with the front end of the outer cylinder 5;
3) the inner cylinder component continues to push the protective cover to move forward, and finally the protective cover and the aircraft are separated.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (3)
1. The utility model provides a high temperature resistant firer catapult which characterized in that: the medicine box comprises an inner barrel component, an outer barrel component, a medicine box component and a shearing pin (2), wherein the inner barrel component and the outer barrel component are fixed through the shearing pin (2), and the outer barrel component is connected with the medicine box component; the outer aircraft protective cover is connected with the inner cylinder component, and the outer aircraft is connected with the outer cylinder component;
the inner cylinder component comprises an inner cylinder (1) and a sliding rod (3); one end of the inner cylinder (1) is a flange, the flange end is provided with internal threads, the other end of the inner cylinder (1) is a unthreaded hole, and a circular hole is formed in the portion, close to the flange, of the unthreaded hole in the circumferential direction; the sliding rod (3) is a cylinder, one end of the sliding rod is a ball head, the other end of the sliding rod is a plane, the outer diameter of the sliding rod (3) is in clearance fit with the inner diameter of the unthreaded hole of the inner cylinder (1), and the sliding rod (3) is inserted into the unthreaded hole of the inner cylinder (1);
the medicine box component comprises a medicine box base (7), a heat insulation gasket (8), a medicine box (9) and an igniter (10); the medicine box base (7) is an L-shaped cavity, a tapered hole is arranged in the middle section of the inner cavity, the end face, facing the large end of the tapered hole, of the two end faces of the medicine box base (7) serves as a first end face, the other end face is a second end face, and the two end faces are both provided with internal threads; the heat insulation gasket (8) is adhered to the conical hole of the medicine box base (7) through an adhesive; the medicine box (9) is filled with main medicine, and the medicine box (9) is plugged into the heat-insulating gasket (8); the igniter (10) is connected with the internal thread of the first end surface of the medicine box base (7) through the external thread;
the outer cylinder component comprises a screw cap (4), an outer cylinder (5) and a piston (6); the outer barrel (5) is a cylinder, one end of the outer barrel is provided with an external thread, a stepped hole is formed in the outer barrel (5), the aperture of a unthreaded hole close to one end of the external thread is larger than that of the other end of the outer barrel, an internal thread through hole is formed in the circumferential direction of the wall of the outer barrel (5) at one end of the unthreaded hole with a small aperture, and a boss is distributed on the outer wall of the outer barrel (5; the nut (4) is a cylinder, the inside of the nut is divided into a thread section and a unthreaded hole section, the small diameter of the internal thread is larger than the diameter of the unthreaded hole, the diameter of the unthreaded hole is larger than the outer diameter of the outer barrel (5) and smaller than the outer diameter of a boss of the outer barrel (5), and the nut (4) is installed and clamped at the boss from one end of the external thread of the outer barrel (5); the piston (6) is a cylinder, the cylinder is divided into a thick section and a thin section, the piston (6) is installed from one end of the external thread of the outer cylinder (5), and the end surface of the thin section is in point contact with one end point of the spherical surface of the sliding rod (3);
one end of the shear pin (2) is provided with an external thread, the other end of the shear pin is provided with a cylinder, and the external thread is matched with the internal thread of the outer cylinder (5);
the concrete mode that inner tube subassembly and urceolus subassembly are fixed through shear pin (2) does: the two shearing pins (2) are oppositely screwed into the internal threads of the outer cylinder (5) through the external threads of the shearing pins (2), and the cylinders of the shearing pins (2) are inserted into the round holes of the inner cylinder (1);
the specific mode that urceolus subassembly and medicine box subassembly are connected does: the second end surface of a medicine box base (7) of the medicine box component is connected with an outer cylinder (5) of the outer cylinder component through threads;
the external aircraft protective cover is in threaded connection with an inner cylinder (1) of the inner cylinder assembly;
the external aircraft is in threaded connection with a nut (4) of the outer barrel assembly through threads of the stud;
the outer diameter of the thick section of the piston (6) is in clearance fit with the aperture of the unthreaded hole with the large aperture of the outer cylinder (5); the outer diameter of the thin section of the piston (6) is in clearance fit with the inner diameter of the unthreaded hole with a small aperture of the outer cylinder (5);
after separation, the piston (6) is flush with the end surface of the outer cylinder (5);
the diameter of the cylinder of the shear pin (2) is smaller than the major diameter of the external thread of the shear pin (2), and the length of the cylinder is not larger than the wall thickness of the inner cylinder (1).
2. The high temperature resistant firer catapult as recited in claim 1, wherein: the thickness of the flange of the inner cylinder (1) is smaller than the length of the thread segment, and the major diameter of the internal thread is smaller than the aperture of the unthreaded hole of the inner cylinder (1); the inner diameter of the unthreaded hole with small aperture of the outer cylinder (5) is in clearance fit with the outer diameter of the inner cylinder (1), and the outer diameter of the outer cylinder (5) is equal to the outer diameter of the flange of the inner cylinder (1).
3. A high temperature fire-resistant aircraft ejector as claimed in any one of claims 1-2, wherein: the shear pin (2) is made of 1Cr18Ni9Ti stainless steel, and the slide bar (3) is made of TA 15; the binder is DG-4 high temperature resistant glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711116287.4A CN107933975B (en) | 2017-11-13 | 2017-11-13 | High-temperature-resistant firer catapult |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711116287.4A CN107933975B (en) | 2017-11-13 | 2017-11-13 | High-temperature-resistant firer catapult |
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| Publication Number | Publication Date |
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| CN107933975A CN107933975A (en) | 2018-04-20 |
| CN107933975B true CN107933975B (en) | 2019-12-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711116287.4A Active CN107933975B (en) | 2017-11-13 | 2017-11-13 | High-temperature-resistant firer catapult |
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| CN (1) | CN107933975B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109373811B (en) * | 2018-09-27 | 2021-02-09 | 北京空间机电研究所 | Multi-stage actuating ejection device adopting follow-up charging |
| CN112660908A (en) * | 2020-11-20 | 2021-04-16 | 南京理工大学 | Space rope releasing mechanism with adjustable damping |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105474793B (en) * | 2007-07-31 | 2011-10-05 | 上海宇航系统工程研究所 | aircraft component separation nut |
| CN101875404B (en) * | 2009-12-17 | 2012-10-24 | 北京理工大学 | Sealed small low-impact release screw bolt |
| RU2426676C1 (en) * | 2010-04-23 | 2011-08-20 | Федеральное государственное унитарное предприятие "Конструкторское бюро "Арсенал" имени М.Ф. Фрунзе" | Structural element connector/disconnector |
| KR101708768B1 (en) * | 2015-07-10 | 2017-02-21 | 국방과학연구소 | Pressure cartridge including pressure-resistant component |
| CN106628272B (en) * | 2016-11-15 | 2018-11-02 | 北京空间机电研究所 | A kind of firer's tripper with two-way bearing function |
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