Low-impact structure of spaceflight point type separation initiating explosive device

Abstract

The invention relates to the technical field of aerospace, and discloses a low-impact structure of an aerospace point type separation initiating explosive device, which comprises a shell, one end of the shell is in threaded plug-in connection with a connector, a fixed seat is arranged in the shell, two screws are in threaded plug-in connection between the bottom end of the fixed seat and one end of the shell, and the outer wall of the fixed seat is slidably sleeved with a constraint piston. The outer wall of the restraining piston is sleeved with a positioning spring, a bolt is inserted into one end of the fixing base in a sliding mode, an ejection spring is arranged at one end of the fixing base and one end of the bolt, a groove is formed in the outer wall of the bolt, and a plurality of steel balls are connected into the groove in a rolling mode. High-temperature and high-pressure gas generated by the igniter enters the inner cavity and then flows into the constraint piston through the ejection cavity, so that the constraint piston is pushed to move, constraint of the constraint piston on the steel ball is relieved, the steel ball moves outwards in the radial hole, meanwhile, the ejection spring plays a role to push the bolt to be separated, and the bolt is released and unlocked.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, specifically to a low-impact structure for aerospace point-type separation pyrotechnics. Background Art

[0002] Separation devices are widely used in many fields, especially in the aerospace field. In the early days of the aerospace field, the reliability of separation was the first goal. If the separation bolts failed to unlock, the entire mission would also face failure. With the improvement of separation bolts, the reliability problem has been gradually solved, and the focus has shifted to reducing the impact response of the surrounding structure during separation.

[0003] Currently, when the existing pyrotechnics are separated, the anti-impact effect is poor. The quality of the separation performance directly affects whether the spacecraft can accurately complete the expected mission. And with the gradual maturity of missiles and various spacecraft, the requirements for the separation system are getting higher and higher, and the development requirements for the supporting pyrotechnic separation devices are becoming more and more urgent. Summary of the Invention

[0004] (I) Technical Problems to be Solved

[0005] Aiming at the deficiencies of the prior art, the present invention provides a low-impact structure for aerospace point-type separation pyrotechnics, mainly to solve the problem of poor anti-impact effect when the existing pyrotechnics are separated.

[0006] (II) Technical Solutions

[0007] To achieve the above object, the present invention provides the following technical solutions:

[0008] A low-impact structure for aerospace point-type separation pyrotechnics, including a housing. One end of the housing is threadedly inserted with a connector. A fixed seat is arranged inside the housing. Two screws are threadedly inserted between the bottom end of the fixed seat and one end of the housing. A restraint piston is slidably sleeved on the outer wall of the fixed seat. A positioning spring is sleeved on the outer wall of the restraint piston. One end of the fixed seat is slidably inserted with a bolt. A top spring is arranged between the fixed seat and one end of the bolt. A groove is arranged on the outer wall of the bolt. A plurality of steel balls are rotatably connected in the groove. Radial holes are arranged on the circumference of the fixed seat. The steel balls can move in the radial holes. An inner cavity is arranged inside the connector. A top cavity is arranged between the connector and the fixed seat. The inner cavity is communicated with the top cavity. The top cavity is communicated with the restraint piston. An energy-absorbing pad is clamped inside the connector. One end of the restraint piston can contact the energy-absorbing pad.

[0009] Further, a first O-ring is clamped between the connector and the housing.

[0010] On the basis of the foregoing solution, second O-rings are clamped between the connector and the restraint piston and between the fixed seat and the restraint piston.

[0011] As a further solution of the present invention, a rubber pad is provided between the restraint piston and the fixed seat.

[0012] Further, a detonator is clamped at one end of the connector, and the detonator is communicated with the inner cavity.

[0013] On the basis of the foregoing solution, a plurality of mounting holes are provided at one end of the housing, and fixing bolts are inserted into the mounting holes.

[0014] As a further solution of the present invention, a perforation is provided at one end of the housing, and the bolt passes through the perforation.

[0015] (III) Beneficial effects

[0016] Compared with the prior art, the present invention provides a low-impact structure for aerospace point-type separation pyrotechnics, having the following beneficial effects:

[0017] 1. High-temperature and high-pressure gas is generated by the detonator and enters the inner cavity, and then flows into the restraint piston through the ejection cavity, thereby pushing the restraint piston to move, and further releasing the restraint of the restraint piston on the steel ball, so that the steel ball moves outward in the radial hole. At the same time, the ejection spring plays a role in pushing the bolt to separate, achieving the release and unlocking of the bolt.

[0018] 2. Through the setting of the energy-absorbing pad, the restraint piston impacts on the energy-absorbing pad to absorb the remaining kinetic energy of the restraint piston, so as to reduce the impact.

[0019] 3. Through the setting of the first O-ring and the second O-ring, a sealed cavity is formed between the housing and the connector, which is convenient for the gas generated by the detonator to build pressure in the cavity. Description of the drawings

[0020] Figure 1 It is a three-dimensional structure schematic diagram of the low-impact structure of the aerospace point-type separation pyrotechnics proposed by the present invention;

[0021] Figure 2 It is a side view structure schematic diagram of the low-impact structure of the aerospace point-type separation pyrotechnics proposed by the present invention;

[0022] Figure 3 It is a sectional structure schematic diagram of the low-impact structure of the aerospace point-type separation pyrotechnics proposed by the present invention;

[0023] Figure 4 It is an enlarged structure schematic diagram at A of the low-impact structure of the aerospace point-type separation pyrotechnics proposed by the present invention;

[0024] Figure 5 It is an enlarged structure schematic diagram at B of the low-impact structure of the aerospace point-type separation pyrotechnics proposed by the present invention.

[0025] In the figure: 1. housing; 2. connector; 3. fixing seat; 4. screw; 5. restraint piston; 6. positioning spring; 7. bolt; 8. ejecting spring; 9. groove; 10. steel ball; 11. radial hole; 12. inner cavity body; 13. ejecting cavity; 14. first O-ring; 15. second O-ring; 16. rubber pad; 17. igniter; 18. mounting hole; 19. energy-absorbing pad. Detailed implementation mode

[0026] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present invention.

[0027] Refer to Figures 1-5 , the low-impact structure of the aerospace point-type separation pyrotechnic device includes a housing 1. One end of the housing 1 is threadedly inserted with a connector 2. A fixing seat 3 is arranged inside the housing 1. Two screws 4 are threadedly inserted between the bottom end of the fixing seat 3 and one end of the housing 1. The outer wall of the fixing seat 3 is slidably sleeved with a restraint piston 5. The outer wall of the restraint piston 5 is sleeved with a positioning spring 6. The positioning spring 6 is installed between the connector 2 and the restraint piston 5 to determine the initial position of the ejecting spring 8 and ensure that the bolt 7 will not be accidentally unlocked due to overload during transportation and connection. One end of the fixing seat 3 is slidably inserted with a bolt 7. An ejecting spring 8 is arranged between the fixing seat 3 and one end of the bolt 7. A groove 9 is arranged on the outer wall of the bolt 7. A plurality of steel balls 10 are rollingly embedded in the groove 9. Radial holes 11 are arranged on the circumference of the fixing seat 3. The steel balls 10 can move in the radial holes 11. An inner cavity body 12 is arranged inside the connector 2. An ejecting cavity 13 is arranged between the connector 2 and the fixing seat 3. The inner cavity body 12 is communicated with the ejecting cavity 13. The ejecting cavity 13 is communicated with the restraint piston 5. One end of the connector 2 is clamped with an igniter 17. The igniter 17 generates high-temperature and high-pressure gas and enters the inner cavity body 12, and then flows into the restraint piston 5 through the ejecting cavity 13, thereby pushing the restraint piston 5 to move, and further releasing the restraint of the restraint piston 5 on the steel balls 10, so that the steel balls 10 move outwards in the radial holes 11. At the same time, the ejecting spring 8 plays a role in pushing the bolt 7 to separate, achieving the release and unlocking of the bolt 7. An energy-absorbing pad 19 is clamped inside the connector 2. One end of the restraint piston 5 can contact the energy-absorbing pad 19. The restraint piston 5 impacts on the energy-absorbing pad 19 to absorb the remaining kinetic energy of the restraint piston 5 to reduce the impact.

[0028] A first O-ring 14 is clamped between the connector 2 and the housing 1 to seal between the connector 2 and the housing 1. Second O-rings 15 are clamped between the connector 2 and the restraint piston 5 and between the fixed seat 3 and the restraint piston 5 to seal between the connector 2 and the restraint piston 5 and between the fixed seat 3 and the restraint piston 5. A rubber pad 16 is provided between the restraint piston 5 and the fixed seat 3. The igniter 17 communicates with the inner cavity 12. One end of the housing 1 is provided with a plurality of mounting holes 18 to facilitate the fixed installation of the device. Fixing bolts are inserted into the mounting holes 18. One end of the housing 1 is provided with a through hole, and the bolt 7 passes through the through hole.

[0029] Working principle of this embodiment: During use, the igniter 17 generates high-temperature and high-pressure gas that enters the inner cavity 12 and then flows into the restraint piston 5 through the ejection cavity 13, thereby pushing the restraint piston 5 to move, and then releasing the restraint of the restraint piston 5 on the steel ball 10, so that the steel ball 10 moves outward in the radial hole 11. At the same time, the ejection spring 8 plays a role in pushing the bolt 7 to separate, achieving the release and unlocking of the bolt 7. Then, the restraint piston 5 impacts on the energy-absorbing pad 19 to absorb the remaining kinetic energy of the restraint piston 5 to reduce the impact.

[0030] All the electrical components mentioned in this article are electrically connected to the external main controller and 220V mains, and the main controller can be a conventional known device such as a computer for control.

[0031] In the description of this article, it should be noted that unless otherwise clearly specified and limited, the terms "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a direct connection, or an indirect connection through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0032] In the description of this article, it should be noted that relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprising", "including" or any other variation thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such process, method, article or device.

[0033] Although embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A low-impact structure for aerospace point-separation pyrotechnics, comprising a housing (1), characterized in that: One end of the housing (1) is threadedly connected with a connector (2), a fixing seat (3) is provided inside the housing (1), two screws (4) are threadedly connected between the bottom end of the fixing seat (3) and one end of the housing (1), a restraining piston (5) is slidably sleeved on the outer wall of the fixing seat (3), a positioning spring (6) is sleeved on the outer wall of the restraining piston (5), a bolt (7) is slidably inserted at one end of the fixing seat (3), an ejection spring (8) is provided at one end of the fixing seat (3) and the bolt (7), a groove (9) is provided on the outer wall of the bolt (7), and the groove ( 9) are connected in a rolling manner, a plurality of steel balls (10) are provided in the circumference of the fixing seat (3), and the steel balls (10) can move in the radial holes (11), an inner cavity (12) is provided inside the connecting head (2), an ejection cavity (13) is provided between the connecting head (2) and the fixing seat (3), the inner cavity (12) is communicated with the ejection cavity (13), and the ejection cavity (13) is communicated with the restraining piston (5), an energy absorbing pad (19) is clamped in the connecting head (2), and one end of the restraining piston (5) can contact the energy absorbing pad (19).

2. The low impact structure of aerospace point separation pyrotechnics according to claim 1 is characterized in that: A first O-ring (14) is clamped between the connector (2) and the housing (1).

3. The low impact structure of aerospace point separation pyrotechnics according to claim 1 is characterized in that: A second O-ring (15) is clamped between the connecting head (2) and the restraining piston (5) and between the fixing seat (3) and the restraining piston (5).

4. The low impact structure of aerospace point separation pyrotechnics according to claim 1 is characterized in that: A rubber pad (16) is provided between the restraining piston (5) and the fixing seat (3).

5. The low impact structure of aerospace point separation pyrotechnics according to claim 1 is characterized in that: One end of the connector (2) is clamped with an igniter (17), and the igniter (17) is in communication with the inner cavity (12).

6. The low impact structure of aerospace point separation pyrotechnics according to claim 1, characterized in that: One end of the housing (1) is provided with a plurality of mounting holes (18), and fixing bolts are inserted into the mounting holes (18).

7. The low impact structure of aerospace point separation pyrotechnics according to claim 1, characterized in that: One end of the housing (1) is provided with a through hole, and the bolt (7) passes through the through hole.

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