Composite near space separation triggering mechanism and carrier rocket

Abstract

The invention relates to the technical field of carrier rockets, and provides a combined type near space separation triggering mechanism and a carrier rocket, the combined type near space separation triggering mechanism comprises a rocket cabin body, an aircraft, two hoops and explosive bolts, and the two hoops are oppositely arranged; the explosive bolt comprises a screw rod, a pyrotechnic separation head, a nut and a sleeve; the screw rod is arranged between the two hoops in a penetrating manner; the pyrotechnic separating head is fixedly arranged at one end of the screw rod; the nut is connected to the other end of the screw in a threaded fit mode. And the sleeve penetrates through and is fixed in the hoop far away from the nut, and a lubricating groove is formed in the sleeve. According to the explosive bolt, the casing pipe is arranged in the explosive bolt, the casing pipe is fixed in the hoop close to the pyrotechnic separation head, and the lubricating groove is formed in the casing pipe, so that impact damage to the hoop when the pyrotechnic separation head is detonated can be reduced, and the separation efficiency of the screw and the hoop can be improved; therefore, the accuracy of the separation time of the aircraft and the rocket cabin is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of carrier rockets, in particular to a composite near-space separation trigger mechanism and a carrier rocket. BACKGROUND

[0002] As the main transportation tool for human beings to enter space, the successful completion of the task of a carrier rocket depends on the coordinated work of multiple systems, and the separation system is a crucial link. When a carrier rocket performs a near-space carrying task, the carrier vehicle and other carried equipment need to be separated from the carrier rocket in the near space, and these separation actions are completed by a separation trigger mechanism.

[0003] A carrier rocket usually uses a mechanical trigger mechanism to achieve separation actions, and such a mechanism is usually based on mechanical transmission and timing devices to trigger the separation device after reaching a preset mechanical stroke or time.

[0004] As disclosed in the invention patent with the publication number CN116853535A, a satellite-rocket separation device and a carrier rocket are provided with a support leg between the carrier rocket and the satellite, and the support leg is connected with the mounting plate through an explosive bolt. However, the explosion impact of the explosive bolt is not easy to control. When the explosive bolt is started, not only is it easy to produce splashes to damage the rocket and its carried equipment, but also there is a problem that the explosive residues hinder the separation of the connecting mechanism, resulting in that the carried equipment cannot be separated from the carrier rocket on time. SUMMARY

[0005] Therefore, the present application provides a composite near-space separation trigger mechanism and a carrier rocket, which can ensure the rapid separation of the carrier vehicle and the rocket cabin and improve the accuracy of the separation time of the carrier vehicle.

[0006] The technical scheme of the present application is implemented as follows: on the one hand, the present application provides a composite near-space separation trigger mechanism and a carrier rocket, which comprises a rocket cabin, a carrier vehicle, two clamps and an explosive bolt, wherein, The two clamps are oppositely arranged, and the rocket cabin and the carrier vehicle are clamped between the two clamps; The explosive bolt comprises a screw rod, an explosive separation head, a nut and a sleeve. The screw rod is arranged through the two clamps. The explosive separation head is fixedly arranged at one end of the screw rod. The nut is connected at the other end of the screw rod through thread cooperation and abuts against one of the clamps. The sleeve is fixedly arranged in the clamp away from the nut and abuts against the explosive separation head. The sleeve is sleeved on the screw rod, and a lubricating groove is arranged in the sleeve.

[0007] On the basis of the above technical scheme, preferably, a sliding groove is formed at the end of the screw rod away from the nut, a ball hole is formed in the sliding groove, and the ball hole penetrates the screw rod; The explosive separation head comprises a cap, a piston, a spring and a ball, the cap is sleeved on the end of the screw rod away from the nut and abuts against the sleeve, the piston has a structure with thin middle part and thick both ends, the both ends of the piston are slidably arranged in the cap and the sliding groove respectively, the spring is arranged between the screw rod and the piston and abuts against the end of the piston close to the nut, the ball is slidably arranged in the ball hole and abuts against the piston and the cap, and the end of the cap on the side away from the spring is used for filling gunpowder, when the gunpowder is ignited, the piston moves towards the nut, so that the ball is separated from the cap.

[0008] Further preferably, the end of the cap abutting against the sleeve is located outside the sleeve.

[0009] Further preferably, a plurality of lubricating grooves are arranged, and at least one of the lubricating grooves corresponds to the ball. The distance between the circumferential side of the end of the piston close to the spring and the inner wall of the lubricating groove corresponding to the ball is not less than the outer diameter of the ball.

[0010] On the basis of the above technical scheme, preferably, the sleeve comprises a sleeve body, a first limiting ring and a second limiting ring, wherein, The sleeve body is sleeved on the screw rod and abuts against the explosive separation head, the circumferential side of the sleeve body is provided with an expansion joint, and the lubricating groove is formed in the sleeve body; The first limiting ring is fixedly arranged on the sleeve body and abuts against the clamp away from the nut; The second limiting ring is sleeved on the screw rod and abuts against the clamp close to the nut and away from the explosive separation head.

[0011] Further preferably, the outer diameter of the end of the screw rod away from the nut is smaller than the outer diameter of the end of the screw rod close to the nut.

[0012] Further preferably, the cross section of the end of the screw rod away from the nut is circular, and the cross section of the end of the screw rod close to the nut is oblong. The second limiting ring is slidably arranged on the screw rod and can be rotationally connected with the end of the screw rod away from the nut.

[0013] On the basis of the above technical scheme, preferably, the clamp comprises a clamping belt and a clamping block, wherein, The clamping band is in a semicircular shape, and both ends of the clamping band are provided with connecting portions, the connecting portions on the two clamping bands correspond to each other, and the connecting portions are connected by the explosive bolt. The clamping blocks are arranged on the clamping band, a plurality of clamping blocks are arranged on each clamping band, the clamping blocks are arranged at intervals, and the clamping band is clamped with at least one of the clamping blocks.

[0014] Further preferably, one side of the connecting portion, which abuts against the nut, is inclined to the center line of the screw rod, and the width of the connecting portion gradually increases from the end close to the center of the clamping band to the end away from the center of the clamping band. The explosive bolt further comprises a wedge-shaped gasket, which is arranged between the connecting portion and the nut and is sleeved on the screw rod.

[0015] In the second aspect, the application provides a carrier rocket comprising the composite near-space separation trigger mechanism.

[0016] The composite near-space separation trigger mechanism and the carrier rocket of the application have the following beneficial effects compared with the prior art: (1) By arranging the sleeve in the explosive bolt, fixing the sleeve in the clamp close to the pyrotechnic separation head, and arranging the lubricating groove in the sleeve, the impact damage of the clamp caused by the detonation of the pyrotechnic separation head can be reduced, and the separation efficiency of the screw rod and the clamp can be improved, thereby improving the accuracy of the separation time of the spacecraft and the rocket cabin. (2) By arranging the pyrotechnic separation head to include a cap, a piston, a spring and a ball, the explosive impact force required for the explosive bolt to disintegrate can be reduced, and by arranging the pyrotechnic separation head at one end of the screw rod and outside the clamp, the damage to the spacecraft and the rocket cabin caused by the disintegration of the explosive bolt can be reduced. (3) By arranging the clamp to include a clamping band and a plurality of clamping blocks, when the two clamps are separated, the clamping blocks can be quickly separated from the rocket cabin and the spacecraft, and by clamping the clamping band with at least one of the clamping blocks, the connection firmness of the clamp to the rocket cabin and the spacecraft can be improved. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are only some embodiments of the application, and for those skilled in the art, other drawings can also be obtained without creative labor based on these drawings.

[0018] Figure 1 It is a front view of the composite near-space separation trigger mechanism and the carrier rocket of the application. Figure 2 It is a perspective view of a composite near space separation trigger mechanism and a carrier rocket middle clamp for the application; Figure 3 It is an explosion view of a composite near space separation trigger mechanism and an explosion bolt in a carrier rocket for the application; Figure 4 It is a sectional view of a composite near space separation trigger mechanism and an explosion bolt in a carrier rocket for the application; Figure 5 It is a sectional view of a composite near space separation trigger mechanism and a pyrotechnic separation head in a carrier rocket for the application; Figure 6 It is a sectional view of a composite near space separation trigger mechanism and a ball bearing in a carrier rocket for the application; Figure 7 It is a sectional view of a composite near space separation trigger mechanism and a cap and tube connection in a carrier rocket for the application; Figure 8 It is a perspective view of a composite near space separation trigger mechanism and a sleeve in a carrier rocket for the application; Figure 9 It is a sectional view of a composite near space separation trigger mechanism and a sleeve in a carrier rocket for the application; Figure 10 It is a sectional view of a composite near space separation trigger mechanism and a nut in a carrier rocket for the application; Figure 11 It is a perspective view of a composite near space separation trigger mechanism and a clamp block in a carrier rocket for the application.

[0019] 1, rocket cabin body; 2, aircraft; 3, clamp; 31, clamp belt; 32, clamp block; 301, connection part; 4, explosion bolt; 41, screw rod; 42, pyrotechnic separation head; 421, cap; 422, piston; 423, spring; 424, ball bearing; 43, nut; 44, sleeve; 441, tube; 442, first limiting ring; 443, second limiting ring; 45, wedge-shaped gasket; 401, lubrication groove; 402, sliding groove; 403, ball hole; 404, expansion joint. DETAILED DESCRIPTION

[0020] The technical solutions in the application will be described clearly and completely below in combination with the specific embodiments of the application. Obviously, the described embodiments are only some of the embodiments of the application, but not all the embodiments. Based on the embodiments in the application, all the other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the application.

[0021] With the continuous progress of aviation technology, the aircraft 2 has been widely used in many fields such as military reconnaissance, geographic mapping, environmental monitoring, disaster relief, etc. Especially in the operation of the near space between 20 to 100 kilometers above sea level, the aircraft 2 has a wider field of view due to its height in the near space, can cover a larger reconnaissance or monitoring range, reduce the blind area and improve the efficiency.

[0022] Some near space aircraft 2 do not have the ability to take off directly from the ground, they usually use the way of transportation by carrier rocket to enter the near space to perform tasks such as weather monitoring, geographic mapping, etc. Since the transportation by carrier rocket is more efficient, it can deliver the aircraft 2 to the designated location in a short time, reducing the flight time and energy consumption of the aircraft 2, thereby improving the timeliness and accuracy of task execution.

[0023] The carrier rocket of the present application comprises a separation trigger mechanism for carrying the aircraft 2 performing tasks to take off and separate from the aircraft 2 when reaching the task location in the near space to realize the delivery of the aircraft 2.

[0024] As shown in Figure 1 , the separation trigger mechanism comprises a rocket cabin body 1, an aircraft 2, two clamps 3 and an explosive bolt 4, the rocket cabin body 1 and the aircraft 2 are provided with connecting bases, and the connecting base of the rocket cabin body 1 abuts against the connecting base of the aircraft 2, the two clamps 3 are oppositely arranged and connected and fixed by the explosive bolt 4, and the connecting base of the rocket cabin body 1 and the connecting base of the aircraft 2 are clamped between the two clamps 3, so as to fix the aircraft 2 on the rocket cabin body 1; when the carrier rocket flies to the task location in the near space, the explosive bolt 4 is detonated and disintegrated, so that the two clamps 3 fall off, to realize the separation of the aircraft 2 from the rocket cabin body 1, and make the aircraft 2 perform tasks.

[0025] As shown in Figure 11 , the clamp 3 comprises a clamping belt 31 and a clamping block 32, the clamping belt 31 is a semicircular structure, and both ends of the clamping belt 31 are provided with connecting parts 301, as shown in Figure 2 , the connecting parts 301 on the two clamping belts 31 correspond one by one and are connected by the explosive bolt 4 to form a circular ring structure, and the clamping block 32 is abuttingly arranged on the clamping belt 31, and the side of the clamping block 32 away from the clamping belt 31 abuts against the connecting base of the rocket cabin body 1 or the connecting base of the aircraft 2, so as to realize the connection and fixation of the rocket cabin body 1 and the aircraft 2.

[0026] In order to ensure the fixed firmness of the clamping block 32 and the connecting bases of the rocket cabin body 1 and the aircraft 2, the clamping block 32 should be a rigid structure, however, the rigid structure of the clamping block 32 will affect the separation efficiency of the clamping block 32 and the connecting bases of the rocket cabin body 1 and the aircraft 2, therefore, as shown inFigure 11 As shown, a plurality of clamping blocks 32 are arranged on each clamping band 31, and the plurality of clamping blocks 32 are arranged at intervals, so that when the explosive bolt 4 is exploded and disintegrated, the plurality of clamping blocks 32 can be quickly scattered, thereby improving the separation efficiency of the spacecraft 2 and the rocket cabin body 1. Of course, in order to ensure the fixing firmness of the rocket cabin body 1 and the spacecraft 2, it is preferred that the clamping band 31 is clamped with at least one of the clamping blocks 32, so as to prevent the clamping band 31 from being separated from the clamping block 32 during normal use.

[0027] The explosive bolt 4 penetrates the connecting portion 301 and abuts against the connecting portion 301. It is preferred that the side of the connecting portion 301 abutting against the nut 43 is inclined to the center line of the screw rod 41, so that the width of the connecting portion 301 gradually increases from the end close to the center of the clamping band 31 to the end away from the center of the clamping band 31. Figure 4 As shown, the right side of the right connecting portion 301 is inclined, and the right side is inclined to the right from top to bottom. When the explosive bolt 4 is locked, the nut 43 abuts against the inclined surface, which not only ensures the tensioning degree of the two connecting portions 301, but also allows the connecting portion 301 to slide away from the connecting base of the rocket cabin body 1 and the spacecraft 2, so that the connecting portion 301 is as far away from the connecting base of the rocket cabin body 1 and the spacecraft 2 as possible, the space between the connecting portion 301 and the connecting base of the rocket cabin body 1 and the spacecraft 2 is enlarged, and the plurality of clamping blocks 32 are more easily scattered when the explosive bolt 4 is disintegrated.

[0028] When the conventional explosive bolt 4 is initiated, strong impact load is generated, and the stability of equipment in the aerospace field is extremely high. Such impact may cause damage to surrounding sensitive equipment and structures. Meanwhile, the explosive bolt 4 is essentially a pyrotechnic device, which is filled with explosives and other flammable and explosive substances. During production, transportation, storage and use, there are certain safety hazards. If improper operation or external factors are affected, an accidental explosion may occur, causing serious harm and loss to personnel and equipment. In addition, after completing a separation operation, the internal explosive of the conventional explosive bolt 4 has exploded, the structure is damaged, and the explosive bolt 4 cannot be used again, which means that a new explosive bolt 4 needs to be replaced each time a separation operation is performed, increasing the use cost. Especially for some systems that need to be separated for multiple times or perform tasks for a long time, frequent replacement of the explosive bolt 4 will bring high economic burden.

[0029] The explosive bolt 4 includes a screw rod 41, a pyrotechnic separation head 42, a nut 43, a sleeve 44 and a wedge-shaped gasket 45, as shown in Figure 3 and Figure 4As shown, the screw rod 41 is arranged through the two clamps 3, the pyrotechnic separation head 42 is fixedly arranged at one end of the screw rod 41, the nut 43 is connected at the other end of the screw rod 41 through threaded cooperation, the sleeve 44 is fixedly arranged in the clamp 3 away from the nut 43, the sleeve 44 is sleeved at one end of the screw rod 41, and the sleeve 44 abuts against the pyrotechnic separation head 42, the nut 43 abuts against the clamp 3 away from the pyrotechnic separation head 42, the hardness of the sleeve 44 is much higher than the hardness of the clamps 3 and the screw rod 41 and the like, when the pyrotechnic separation head 42 explodes and disintegrates, the support of the sleeve 44 to the clamp 3 can avoid the deformation of the clamp 3, so that the screw rod 41 can smoothly separate from the clamp 3, thereby improving the separation efficiency of the separation trigger mechanism and ensuring the accuracy of the separation time of the aircraft 2; at the same time, the lubrication groove 401 is preferably arranged in the sleeve 44, the contact area of the sleeve 44 and the screw rod 41 is reduced, thereby reducing the friction between the sleeve 44 and the screw rod 41, and further improving the separation efficiency of the screw rod 41 and the sleeve 44.

[0030] The wedge-shaped gasket 45 is arranged between the connecting portion 301 and the nut 43 and is sleeved on the screw rod 41, one side of the wedge-shaped gasket 45 abutting against the connecting portion 301 is in a beveled shape, and the other side abutting against the nut 43 is in a planar shape, which not only can maintain the above technical effects, but also fills the gap between the nut 43 and the connecting portion 301, and is beneficial to ensuring the fastening stability of the explosive bolt 4.

[0031] As shown in Figure 5 , the screw rod 41 is arranged through the two clamps 3, the pyrotechnic separation head 42 is fixedly arranged at one end of the screw rod 41, the nut 43 is connected at the other end of the screw rod 41 through threaded cooperation, the sleeve 44 is fixedly arranged in the clamp 3 away from the nut 43, the sleeve 44 is sleeved at one end of the screw rod 41, and the sleeve 44 abuts against the pyrotechnic separation head 42, the nut 43 abuts against the clamp 3 away from the pyrotechnic separation head 42, the hardness of the sleeve 44 is much higher than the hardness of the clamps 3 and the screw rod 41 and the like, when the pyrotechnic separation head 42 explodes and disintegrates, the support of the sleeve 44 to the clamp 3 can avoid the deformation of the clamp 3, so that the screw rod 41 can smoothly separate from the clamp 3, thereby improving the separation efficiency of the separation trigger mechanism and ensuring the accuracy of the separation time of the aircraft 2; at the same time, the lubrication groove 401 is preferably arranged in the sleeve 44, the contact area of the sleeve 44 and the screw rod 41 is reduced, thereby reducing the friction between the sleeve 44 and the screw rod 41, and further improving the separation efficiency of the screw rod 41 and the sleeve 44.

[0032] As shown in Figure 5 and Figure 6As shown, in order to improve the resistance of the ball 424 and the cap 421, preferably in the cap 421 also set corresponding ball groove, when the piston 422 resistance ball 424, let the ball 424 resistance in the ball groove; Similarly, also should be set a plurality of ball 424 and a plurality of ball hole 403, and let a plurality of ball 424 and a plurality of ball hole 403 around the center line of the screw 41 circumferential array, so as to keep the cap 421 and the screw 41 connection stability and firmness.

[0033] The cap 421 is fixed through the ignition device, and the ignition device is connected with the ignition control device. The cap 421 is filled with gunpowder on the side away from the spring 423. When the ignition control device controls the ignition device to ignite the gunpowder, as shown in Figure 6 As shown, the explosion impact force moves the piston 422 towards the nut 43, so that the piston 422 is not in contact with the ball 424, and the ball 424 is separated from the cap 421. At the same time, the explosion impact force pushes the cap 421 to slide relative to the screw 41, so that the cap 421 is separated from the screw 41, so that the screw 41 can slide out of the sleeve 44 and the clamp 3, so that the two clamps 3 are separated, and the aircraft 2 and the rocket cabin 1 are separated.

[0034] When the amount of gunpowder filled in the cap 421 is large, the cap 421 will be deformed by the impact, causing the cap 421 to be stuck on the outer wall of the screw 41, affecting the separation of the aircraft 2 and the rocket cabin 1. Therefore, as shown in Figure 7 As shown, the inner side of the right end of the cap 421 and the outer side of the left end of the sleeve 44 are provided with clamping grooves, so that the end of the cap 421 in contact with the sleeve 44 is located on the outer side of the sleeve 44. When the gunpowder explodes and causes a large impact force on the cap 421, the deformed cap 421 is clamped on the sleeve 44, not on the screw 41, so that the screw 41 can smoothly separate from the sleeve 44 and the clamp 3.

[0035] The explosion bolt 4 of the present application belongs to a separation type explosion bolt. By optimizing the distribution and initiation mode of the explosive, the energy is released more uniformly, reducing the impact on the surrounding equipment and structure. This is crucial for systems sensitive to impact, which can improve the reliability and stability of the equipment. At the same time, after completing a separation action, only simple inspection and maintenance and replacement of some vulnerable parts are needed to put it into use again. This not only greatly reduces the use cost, but also improves the utilization rate of resources, in line with the concept of sustainable development.

[0036] As shown in Figure 8As shown, a plurality of lubrication grooves 401 are provided, and the plurality of lubrication grooves 401 are arranged in a circular array around the center line of the sleeve 44, so that the screw 41 and the sleeve 44 can be in uniform contact, and the sleeve 44 can apply force to the screw 41 evenly, thereby preventing the screw 41 from being deflected due to uneven force when it is separated from the sleeve 44, thereby affecting the separation of the screw 41 and the sleeve 44.

[0037] After the cap 421 is separated from the screw 41, part of the ball 424 may not be separated from the ball hole 403, and the spring 423 will push the piston 422 to resist the ball 424, so that part of the ball 424 protrudes from the side of the screw 41. In order to allow the screw 41 and the ball 424 to be smoothly separated from the sleeve 44 under this working condition, Figure 7 As shown, at least one lubrication groove 401 corresponds to the ball 424, and the distance x between the circumferential side of the piston 422 close to one end of the spring 423 and the inner wall of the lubrication groove 401 corresponding to the ball 424 is not less than the outer diameter of the ball 424; at the same time, the lubrication groove 401 is preferably set to have an arc-shaped cross section to reduce the opening range of the lubrication groove 401 and ensure the structural strength of the sleeve 44.

[0038] like Figure 3 、 Figure 4 and Figure 8 As shown, the sleeve 44 includes a tube body 441, a first limiting ring 442 and a second limiting ring 443. The tube body 441 is sleeved on the screw 41 and is abutted against the pyrotechnic separation head 42. An expansion joint 404 is provided on the peripheral side of the tube body 441, and a lubrication groove 401 is provided in the tube body 441 and passes through the tube body 441. The first limiting ring 442 is fixedly set on the tube body 441 and is abutted against the clamp 3 away from the nut 43. The second limiting ring 443 is sleeved on the screw 41 and is abutted against the clamp 3 of the tube body 441 away from the pyrotechnic separation head 42 and close to the nut 43. When the screw 41 is tightened by the nut 43, the first limiting ring 442 and the second limiting ring 443 are abutted against the two clamps 3, so that the two ends of the tube body 441 are squeezed at the same time, and the inside of the tube body 441 bulges outward and abuts against the clamp 3, thereby realizing a fixed connection between the sleeve 44 and the clamp 3.

[0039] like Figure 8 As shown, in order to allow the middle position of the tube body 441 to protrude in the direction away from the center line of the tube body 441 rather than protrude in the direction close to the center line of the tube body 441, it is preferred to open a corresponding annular groove in the tube body 441; in order to ensure the pressure expansion effect of the tube body 441, it is preferred to set a plurality of expansion joints 404, and let the plurality of expansion joints 404 be arranged in a circular array about the center line of the tube body 441.

[0040] In order to improve the efficiency of the screw 41 being separated from the two clamps 3, the outer diameter of the screw 41 can also be improved so that the outer diameter of the end of the screw 41 away from the nut 43 is smaller than the outer diameter of the end close to the nut 43. Specifically, Figure 3 As shown, the cross section of the end of the screw rod 41 away from the nut 43 is circular, and the cross section of the end of the screw rod 41 close to the nut 43 is oblong.

[0041] The second limiting ring 443 is preferably provided with an oblong hole inside so that the inner diameter of the second limiting ring 443 is the same as the outer diameter of the end of the screw 41 close to the nut 43, so that the second limiting ring 443 is slidably arranged on the screw 41 and can be rotatably connected to the end of the screw 41 away from the nut 43. Figure 4 As shown, when assembling the explosive bolt 4, by rotating the second limiting ring 443, the second limiting ring 443 between the two clamps 3 can be pressed against the screw rod 41, thereby making it easier to install the nut 43.

[0042] The wedge-shaped washer 45 also has an oblong hole formed therein, so that the inner diameter of the wedge-shaped washer 45 is the same as the outer diameter of the end of the screw 41 near the nut 43. Figure 10 As described above, the circumferential side of the wedge-shaped gasket 45 abuts against the connecting portion 301, so that the wedge-shaped gasket 45 can limit the screw 41 and prevent the screw 41 from rotating when the nut 43 is tightened. This not only helps to improve the assembly convenience of the explosive bolt 4, but also protects the pyrotechnic separation head 42.

[0043] like Figure 4 As shown, the upper portion of the wedge-shaped gasket 45 does not abut against the card belt 31 , thereby preventing the wedge-shaped gasket 45 from affecting the deformation of the card belt 31 and preventing the card blocks 32 from falling off.

[0044] The working principles of the composite near-space separation trigger mechanism and carrier rocket of the present invention are as follows: When the carrier rocket brings the aircraft 2 to the mission location in near space, the ignition device is used to ignite the gunpowder in the explosive bolt 4, and the explosive impact force of the gunpowder is used to drive the piston 422 to slide in the direction close to the nut 43, so that the ball 424 does not resist the piston 422, thereby realizing the separation of the piston 422 and the screw 41. Subsequently, the screw 41 will successively detach from the two clamps 3 and the sleeve 44, thereby releasing the fixation of the two clips 31, allowing multiple blocks 32 to scatter, thereby realizing the separation of the aircraft 2 connection base and the rocket cabin 1 connection base; during this period, in order to prevent the scattered blocks 32 and clips 31 from colliding with the aircraft 2, it is preferably provided with tension springs on the blocks 32 and clips 31 to allow the blocks 32 and clips 31 to scatter in a specified direction.

[0045] The composite near-space separation trigger mechanism and launch vehicle of the present invention have the following beneficial effects compared with the prior art: By setting the sleeve in the explosive bolt, fixing the sleeve in the clamp close to the pyrotechnic separation head, and setting the lubricating groove in the sleeve, not only the impact damage of the clamp caused by the pyrotechnic separation head can be reduced when the pyrotechnic separation head is exploded, but also the separation efficiency of the screw rod and the clamp can be accelerated, so that the accuracy of the separation time of the aircraft and the rocket cabin body is improved; by setting the pyrotechnic separation head to include the cap, the piston, the spring and the ball, the explosive impact force required for the explosive bolt to disintegrate can be reduced, by setting the pyrotechnic separation head at one end of the screw rod and outside the clamp, the damage caused to the aircraft and the rocket cabin body when the explosive bolt disintegrates can be reduced; by setting the clamp to include the clamping belt and a plurality of clamping blocks, when the two clamps are separated, the clamping blocks can be quickly separated from the rocket cabin body and the aircraft, by clamping the clamping belt with at least one of the clamping blocks, the connection firmness of the clamp to the rocket cabin body and the aircraft can be improved.

[0046] The above only describes the preferred embodiments of the present application and is not intended to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A composite near-space separation trigger mechanism, characterized by: It comprises a rocket cabin (1), an aircraft (2), two clamps (3) and an explosive bolt (4), wherein: The two clamps (3) are arranged opposite to each other, and the rocket cabin (1) and the aircraft (2) are clamped and arranged between the two clamps (3); The explosive bolt (4) comprises a screw (41), a pyrotechnic separation head (42), a nut (43) and a sleeve (44); the screw (41) is arranged between the two clamps (3); the pyrotechnic separation head (42) is fixedly arranged at one end of the screw (41); the nut (43) is connected to the other end of the screw (41) through threaded engagement, and is held against one of the clamps (3); the sleeve (44) is fixed in the clamp (3) away from the nut (43), and is held against the pyrotechnic separation head (42); the sleeve (44) is sleeved on the screw (41), and a lubrication groove (401) is provided inside the sleeve.

2. The composite near-space separation trigger mechanism according to claim 1, characterized in that: A sliding groove (402) is provided at one end of the screw rod (41) away from the nut (43), a ball hole (403) is provided in the sliding groove (402), and the ball hole (403) passes through the screw rod (41); The pyrotechnic separation head (42) includes a cap (421), a piston (422), a spring (423) and a ball (424). The cap (421) is sleeved on the end of the screw (41) away from the nut (43) and abuts against the sleeve (44); the piston (422) is thin in the middle and thick at both ends, and its two ends are respectively slidably arranged in the cap (421) and the slide groove (402); the spring (423) is abutted between the screw (41) and the piston (422), and the spring (423) abuts against one end of the piston (422) close to the nut (43); the ball (424) is slidably arranged in the ball hole (403) and abutted between the piston (422) and the cap (421); the cap (421) is located on the side of the piston (422) away from the spring (423) for filling gunpowder. When the gunpowder is ignited, the piston (422) moves in a direction close to the nut (43), so that the ball (424) is separated from the cap (421).

3. The composite near-space separation trigger mechanism according to claim 2, characterized in that: The end of the cap (421) that abuts against the sleeve (44) is located outside the sleeve (44).

4. The composite near-space separation trigger mechanism according to claim 3, characterized in that: A plurality of lubrication grooves (401) are provided, and at least one lubrication groove (401) corresponds to the ball (424); The distance between the circumferential side of the piston (422) close to one end of the spring (423) and the inner wall of the lubrication groove (401) corresponding to the ball (424) is not less than the outer diameter of the ball (424).

5. The composite near-space separation trigger mechanism according to claim 1, characterized in that: The sleeve (44) comprises a tube body (441), a first limiting ring (442) and a second limiting ring (443), wherein: The tube body (441) is sleeved on the screw rod (41) and abuts against the pyrotechnic separation head (42); an expansion joint (404) is provided on the circumference of the tube body (441); and the lubrication groove (401) is provided in the tube body (441); The first limiting ring (442) is fixedly arranged on the tube body (441) and abuts against the clamp (3) away from the nut (43); The second limiting ring (443) is sleeved on the screw rod (41) and abuts against the clamp (3) of the tube body (441) away from the pyrotechnic separation head (42) and close to the nut (43).

6. The composite near-space separation trigger mechanism according to claim 5, characterized in that: The outer diameter of the end of the screw (41) away from the nut (43) is smaller than the outer diameter of the end of the screw (41) close to the nut (43).

7. The composite near-space separation trigger mechanism according to claim 6, characterized in that: The cross section of the end of the screw (41) away from the nut (43) is circular, and the cross section of the end of the screw (41) close to the nut (43) is oblong; The second limiting ring (443) is slidably arranged on the screw rod (41) and is rotatably connected to an end of the screw rod (41) away from the nut (43).

8. The composite near-space separation trigger mechanism according to claim 1, characterized in that: The clamp (3) comprises a clamping belt (31) and a clamping block (32), wherein: The cassette (31) is a semicircular structure, and both ends thereof are provided with connecting portions (301), the connecting portions (301) on the two cassettes (31) correspond to each other and are connected by the explosive bolts (4); The clamping block (32) is arranged to abut against the clamping belt (31), and each clamping belt (31) is provided with a plurality of the clamping blocks (32). The plurality of the clamping blocks (32) are arranged at intervals, and the clamping belt (31) is clamped with at least one of the clamping blocks (32).

9. The composite near-space separation trigger mechanism according to claim 8, characterized in that: The side of the connecting portion (301) that contacts the nut (43) is inclined to the center line of the screw (41), and the width of the connecting portion (301) gradually increases from the end close to the center of the cassette (31) to the end away from the center of the cassette (31); The explosive bolt (4) further comprises a wedge-shaped washer (45), which is disposed between the connecting portion (301) and the nut (43) and is sleeved on the screw rod (41).

10. A launch vehicle, characterized in that: It comprises the composite near-space separation trigger mechanism as described in any one of claims 1-9.

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