CN216734828U - Separation unlocking mechanism based on rotary electromagnet - Google Patents

Abstract

The utility model discloses a separation release mechanism based on rotary electromagnet, including last section of thick bamboo, lower, locking device, rotating device, thrust unit, drive arrangement, the spacer pin, loading nut and micro-gap switch, go up the cover on lower, rotating device installs on drive arrangement, and can rotate along with drive arrangement, locking device crosses last section of thick bamboo and lower and with the rotating device butt, with last section of thick bamboo and lower locking together, when drive arrangement received satellite separation signal, rotating device rotates to breaking away from the position by the butt position under drive arrangement's drive, remove rotating device and locking device's butt, locking device is deviate from by last section of thick bamboo, go up a section of thick bamboo and lower unblock, it is ejecting under thrust unit's effect to go up a section of thick bamboo, accomplish the separation of star arrow. The utility model provides a star rocket separating mechanism structure complicated, with high costs, envelope size big, the quality is heavy a difficult problem.

Description

Separation unlocking mechanism based on rotary electromagnet

Technical Field

The utility model relates to a star and arrow separation field, concretely relates to separation release mechanism based on rotary electromagnet.

Background

The separation of the satellite and the arrow is an important link in the satellite launching process, and the separation mechanism provides reliable connection before the satellite is released, unlocks in orbit and safely releases the satellite at a preset release speed.

In the prior art, the initiating explosive device separation mode usually adopts a belting mode, a point mode and the like, the non-initiating explosive device separation mode usually adopts a hot knife separation box type structure (P-POD), and the prior art has the following defects when used for separating stars and arrows: the separation of the initiating explosive devices can generate larger impact force, which is easy to damage and impact a single machine on the satellite, and brings certain damage to the satellite to be separated, especially the launching of the rocket-like multi-star can cause damage to other satellites; the explosive separation of initiating explosive devices inevitably generates redundancy, which is easy to pollute the single machine on the satellite, especially the optical single machines such as remote sensing load and the like; the initiating explosive device is a mature product, is disposable and can not be reused, has higher cost and is not beneficial to ground repeated tests; the instantaneous current is larger when the initiating explosive device is separated, and the requirement on carrying the instantaneous current is higher. The hot knife separation box type structure (P-POD) has the disadvantages of complex structure, large envelope size and heavy mass.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model provides a separation release mechanism based on rotary electromagnet has solved star and arrow separating mechanism structure complicacy, with high costs, envelope size is big, a difficult problem such as the quality is heavy.

The utility model provides a separation release mechanism based on rotary electromagnet, including last section of thick bamboo, lower section of thick bamboo, locking device, rotating device and drive arrangement, it is in to go up the cover barrel casing on the lower section of thick bamboo, rotating device installs drive arrangement is last, and can follow drive arrangement rotates together, locking device crosses go up a section of thick bamboo with lower section of thick bamboo and with the rotating device butt, will go up a section of thick bamboo with lower section of thick bamboo locking is in the same place, works as when drive arrangement receives satellite separation signal, rotating device is in drive arrangement's drive is down rotated to breaking away from the position by the butt position, removes rotating device with locking device's butt, locking device by deviate from in going up a section of thick bamboo, go up a section of thick bamboo with lower section of thick bamboo unblock.

The rotating device is arranged on the upper barrel and is used for rotating the lower barrel, the upper barrel is arranged on the lower barrel, the lower barrel is arranged on the lower barrel, the pushing device is arranged on the upper barrel, the lower barrel is arranged on the lower barrel, the pushing device is arranged in a compressed state when the upper barrel and the lower barrel are locked, the pushing device penetrates through the lower barrel and is contacted with the upper barrel, when the rotating device rotates to a separation position, the pushing device pushes the upper barrel to move upwards under the action of restoring force, and the upper barrel is separated from the lower barrel.

Furthermore, the upper barrel and the lower barrel are both of a barrel-shaped structure, first locking holes are uniformly distributed in the barrel wall of the upper barrel, second locking holes are uniformly distributed in the barrel wall of the lower barrel, and the locking device sequentially penetrates through the second locking holes and the first locking holes and then is abutted to the rotating device.

Furthermore, the rotating device comprises a rotating block and a bearing, the bearing is installed on the rotating block and located between the rotating block and the top surface of the lower barrel, the driving device comprises an electromagnet and a rotating shaft located in the middle of the electromagnet, and the rotating block is fixed on the rotating shaft and can rotate along with the rotating shaft.

Furthermore, the locking device comprises an unlocking spring, a first pressing cap, an inner retainer ring, an inner sliding sleeve, a locking shaft, an outer retainer ring, an outer sliding sleeve and a second pressing cap, the unlocking spring is sleeved outside the first pressing cap, the first pressing cap abuts against the rotating device after the locking shaft penetrates into the upper barrel and the lower barrel, the unlocking spring abuts against the inner barrel wall of the lower barrel, the second pressing cap is located outside the upper barrel and inserted into the first locking hole, the inner sliding sleeve is sleeved at one end, close to the first pressing cap, of the locking shaft and limits the position of the locking shaft through the inner retainer ring, the outer sliding sleeve is sleeved at one end, close to the second pressing cap, of the locking shaft and limits the position of the locking shaft through the outer retainer ring, and a molybdenum disulfide film is plated on the inner sliding sleeve and the outer sliding sleeve.

Furthermore, the rotating device further comprises a limiting pin, the limiting pin is fixed on the inner top surface of the lower barrel, the rotating block comprises a limiting lug protruding out of the rotating block along the radial direction, and the limiting lug is blocked by the limiting pin after the rotating device rotates to the disengaging position, so that the rotating block is prevented from over-rotating.

Further, the rotating block further comprises a locking lug which protrudes out of the rotating block along the radial direction, the locking lug is located below the limiting lug, when the rotating device is located at the abutting position, the locking lug abuts against the locking device, and when the rotating device rotates to the disengaging position, the locking device is located at the recessed position between the adjacent locking lugs.

Further, still include lower cover and satellite heat insulating mattress, lower section of thick bamboo and the electro-magnet is all installed on the lower cover, the lower cover is connected with the carrier rocket, the satellite heat insulating mattress is installed on the last section of thick bamboo, the satellite heat insulating mattress is connected with the satellite.

Furthermore, the pushing device comprises a separation acting ring, an acting ejector rod, a separation lower ring, a separation spring and a spring sleeve, one end of the spring sleeve is fixed on the separation lower ring, the other end of the spring sleeve is fixed on the lower cover, the separation spring is sleeved on the spring sleeve, when the upper barrel and the lower barrel are locked, the separation spring is in a compression state, the separation acting ring is located between the top surface of the upper barrel and the top surface of the lower barrel and can act on the upper barrel, the acting ejector rod is fixed between the separation acting ring and the separation lower ring and penetrates through a positioning hole in the lower barrel, and the separation acting ring and the acting ejector rod can be driven by the separation spring to slide upwards relative to the lower barrel.

Furthermore, the top surface of the upper cylinder is also provided with an anti-shearing taper hole, the top surface of the lower cylinder is provided with an anti-shearing taper pin which corresponds to the position of the upper cylinder and protrudes outwards, and tungsten carbide is plated on the anti-shearing taper pin.

The micro switch is fixed to the upper barrel, the pin is inserted into the micro switch and fixed to the top of the lower barrel, and when the upper barrel is separated from the lower barrel, the micro switch is separated from the pin and sends a signal to a control system to inform that the separation of the upper barrel and the lower barrel is completed.

Compared with the prior art, the utility model discloses following profitable technological effect has:

the utility model provides a pair of separation release mechanism and separation unblock method based on rotatory electro-magnet, adopt the modularized design, including locking module, rotation module and promotion module, reasonable make full use of space resource, compact structure, whole upper barrel and lower barrel all adopt 7075-T651 aluminum alloy material, thereby solve envelope size big, the quality is heavy scheduling problem, simultaneously can be according to the quality characteristics and the separation characteristic requirement of different satellites, select the locking device of different numbers, electro-magnet of different driving moment, the spring of different separation drive power, the separation demand of different satellites has been satisfied greatly, the adaptability of separating mechanism to different magnitude satellites has been increased; the rotary electromagnet is used as a unique driving source to replace initiating explosive devices, so that the problems of large impact, debris pollution, high cost, unrepeatability and the like are solved; the shifting fork principle is applied to design the locking device, so that the upper barrel and the lower barrel are locked and unlocked, 3 conical surface bosses are designed at the connecting surface of the upper barrel and the lower barrel, the bearing is arranged on the rotating device, the loading nut is arranged on the upper barrel, and the like, so that the rigidity of the whole structure is improved, the separating mechanism is guaranteed to bear axial load, longitudinal load, torque and bending moment in the launching stage, and the bearing capacity is high.

Drawings

Fig. 1 is a schematic external structural view of the present invention;

FIG. 2 is a schematic view of the internal structure of the present invention;

fig. 3 is a cross-sectional view of the present invention;

FIG. 4 is a schematic structural view of the pushing device of the present invention;

fig. 5 is a schematic structural view of the rotation device and the driving device of the present invention;

fig. 6 is a schematic structural view of a rotating block in the present invention;

FIG. 7 is a schematic structural view of the middle upper tube of the present invention;

FIG. 8 is a schematic structural view of the middle and lower tubes of the present invention;

fig. 9 is a schematic structural diagram of the locking device of the present invention.

Wherein: 10-upper cylinder; 11-a first locking hole; 12-anti-shearing taper holes; 13-separation of the action surface; 20-lower cylinder; 21-a second locking hole; 22-anti-shearing taper pin; 23-positioning holes; 30-a locking device; 31-an unlocking spring; 32-a first compression cap; 33-inner retainer ring; 34-an inner sliding sleeve; 35-locking the shaft; 36-outer retainer ring; 37-an outer sliding sleeve; 38-a second impaction cap; 40-a rotating device; 41-turning block; 411-limit ear; 412-locking ears; 414-bearing mounting part; 42-a bearing; 43-pin holes; 50-a drive device; 51-an electromagnet; 52-rotating shaft; 60-a pushing device; 61-separation loop; 62-acting a mandril; 63-separation of the lower ring; 64-a separation spring; 65-spring sleeve; 70-lower cover; 80-a limit pin; 90-loading a nut; 91-a fixed shaft; 92-locknut; 100-a microswitch; 101-a pin; 120-satellite insulation mat.

Detailed Description

The following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.

In the description of the present invention, it should be noted that the directions or positional relationships indicated in the present description are based on the directions or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, and do not indicate or imply that the indicated device or element must have a specific direction, be constructed and operated in a specific direction, and thus, should not be construed as limiting the present invention.

Referring to fig. 1-3, the present invention provides a separation unlocking mechanism based on a rotary electromagnet, including an upper barrel 10, a lower barrel 20, a locking device 30, a rotating device 40, a driving device 50, a pushing device 60, a lower cover 70, a limit pin 80, a loading nut 90, a micro switch 100 and a satellite heat insulation pad 120, wherein the lower barrel 20 and the driving device 50 are both mounted on the lower cover 70, the lower cover 70 is connected with a launch vehicle, the satellite heat insulation pad 120 is mounted on the upper barrel 10, the satellite heat insulation pad 120 is connected with a satellite, the loading nut 90 and the micro switch 100 are both mounted on the upper barrel 10, the upper barrel 10 is sleeved on the lower barrel 20, the rotating device 40 is mounted on the driving device 50, the driving device 50 is located inside the lower barrel 20, the pushing device 60 is in a compressed state and passes through the lower barrel 20 to be in contact with the upper barrel 10, the locking device 30 crosses the upper barrel 10 and the lower barrel 20 and is abutted against the rotating device 40 to lock the upper barrel 10 and the lower barrel 20 together, when the driving device 50 receives the satellite separation signal, the rotating device 40 rotates from the abutting position to the disengaging position under the driving of the driving device 50, the abutting of the rotating device 40 and the locking device 30 is released, the locking device 30 is separated from the upper barrel 10, the upper barrel 10 and the lower barrel 20 are unlocked, the pushing device 60 pushes the upper barrel 10 to move upwards under the action of restoring force to be separated from the lower barrel 20, and the satellite and arrow separation is completed.

Referring to fig. 7-8, the upper barrel 10 and the lower barrel 20 are both barrel-shaped structures, the upper barrel 10 and the lower barrel 20 both include barrel walls and top surfaces, first locking holes 11 are uniformly formed around the barrel wall of the upper barrel 10, corresponding second locking holes 21 are uniformly formed around the barrel wall of the lower barrel 20, and in this embodiment, the number of the first locking holes 11 and the number of the second locking holes 21 are 3. The locking means 30 in turn traverses the second locking hole 21 and the first locking hole 11 in abutment with the rotation means 40. The top surface of the upper barrel 10 is provided with an anti-shearing taper hole 12, the top surface of the lower barrel 20 is provided with an anti-shearing taper pin 22 which is correspondingly arranged and protrudes outwards, and the anti-shearing taper pin 22 penetrates through the anti-shearing taper hole 12. The cooperation of the anti-shear tapered hole 12 and the anti-shear tapered pin 22 can prevent the damage of the split locking mechanism caused by the transverse shear force, and meanwhile, the tungsten carbide is plated on the anti-shear tapered pin 22, so that the anti-shear effect is increased, and the cold welding is prevented. In the present embodiment, each of the shear-preventing taper holes 12 and the shear-preventing taper pins 22 is 3. The top surface of the upper barrel 10 is also provided with a separation acting surface 13, the top surface of the lower barrel 20 is also provided with a positioning hole 23, in the process of separating the star and the arrow, the thrust of the pushing device 60 acts on the separation acting surface 13 to further push the upper barrel 10 upwards, and the positioning hole 23 is arranged to limit the moving direction of the pushing device 60 and only can move up and down. In the present embodiment, the number of the positioning holes 23 is 3.

Referring to fig. 3, the upper tube 10 is connected to the satellite by screws through the satellite heat insulating mat 120, the lower tube 20 is fixed to the lower cover 70 by screws, and the lower cover 70 is connected to the launch vehicle, so that the satellite and the launch vehicle are separated after the upper tube 10 and the lower tube 20 are separated.

Further, a fixing shaft 91 is provided on an outer top surface of the upper barrel 10, a loading nut 90 is threadedly mounted on the fixing shaft 91, and a locknut 92 is threadedly mounted on the loading nut 90. The vertical pretension of the upper cylinder 10 can be further ensured by the tightness of the loading nut 90 and the locknut 92. The microswitch 100 further comprises a pin 101, the pin 101 penetrates through the top of the upper barrel 10 and is fixed to the top of the lower barrel 20, the microswitch 100 is fixed to the top of the upper barrel 10 and is internally provided with a spring, the microswitch 100 is in signal connection with a satellite and a carrier rocket, when the upper barrel 10 and the lower barrel 20 are locked together through the locking device 30, the microswitch 100 is abutted against the pin 101, the spring in the microswitch 100 is in a compression state, the signal is that the satellite and the rocket are not separated, after the upper barrel 10 is separated from the lower barrel 20, the spring in the microswitch 100 is restored, the signal is that the satellite and the rocket are separated, and the microswitch 100 sends a signal to a control system to inform that the upper barrel 10 and the lower barrel 20 are separated.

Referring to fig. 3 and 5-6, the rotating device 40 includes a rotating block 41 and a bearing 42, a bearing mounting portion 414 is disposed on a top portion of the rotating block 41, and the bearing 42 is fixed on the rotating block 41 through the bearing mounting portion 414 and is located between the rotating block 41 and the top surface of the lower cylinder 20. During the rotation of the bearing 42 with the rotation block 41, the rolling friction thereof can reduce the rotation resistance torque of the rotation block 41. The driving device 50 comprises an electromagnet 51 and a rotating shaft 52 positioned in the middle of the electromagnet 51, the rotating block 41 is sleeved on the rotating shaft 52, a pin hole 43 is formed in the middle of the rotating block 41, and the rotating block 41 is fixed with the rotating shaft 52 through a pin and the pin hole 43. The electromagnet 51 is fixed on the lower cover 70 by a screw, and the rotating shaft 52 can be rotated by electrifying the electromagnet 51, so as to drive the rotating device 40 to rotate. The turning block 41 further comprises locking lugs 412 and stop lugs 411 projecting radially out of the turning block 41, the locking lugs 412 being located below the stop lugs 411, the locking lugs 412 abutting the locking means 30 when the turning means 40 is in the abutting position, and the locking means 30 being located in the recessed position between adjacent locking lugs 412 when the turning means 40 is turned to the disengaged position. The inner top surface of the lower barrel 20 is provided with a limit pin 80, and the limit lug 411 can be blocked by the limit pin 80 in the rotating process to prevent the rotating block 41 from over-rotating. In the present embodiment, the number of the spacing lug 411, the locking lug 412 and the spacing pin 80 is 3.

Referring to fig. 3 and 9, the locking device 30 includes an unlocking spring 31, a first pressing cap 32, an inner retainer 33, an inner sliding sleeve 34, a locking shaft 35, an outer retainer 36, an outer sliding sleeve 37, and a second pressing cap 38, the first pressing cap 32 is located inside the lower barrel 20 and is in threaded connection with one end of the locking shaft 35, the unlocking spring 31 is sleeved outside the first pressing cap 32, the first pressing cap 32 abuts against the locking lug 412 to press the unlocking spring 31 on the inner wall of the lower barrel 20, the second pressing cap 38 is located outside the upper barrel 10 and is inserted into the first locking hole 11, and the second pressing cap 38 is connected with an optical hole at the other end of the locking shaft 35. The unlocking spring 31 is always in a compressed state under abutment of the locking lug 412, and the upper and lower cartridges 10 and 20 are locked. The inner sliding sleeve 34 is sleeved on one end of the locking shaft 35 close to the first compression cap 32 and is limited by the inner retainer ring 33, the outer sliding sleeve 37 is sleeved on one end of the locking shaft 35 close to the second compression cap 38 and is limited by the outer retainer ring 36, the sliding friction force between the locking device 30 and the first locking hole 11 and the second locking hole 21 is reduced by plating a molybdenum disulfide film on the inner sliding sleeve 34 and the outer sliding sleeve 37, cold welding is prevented, when the locking device 30 and the locking lug 412 lose abutting force, the unlocking spring 31 recovers elasticity, the locking shaft 35 can be rapidly driven to move towards the rotating device 40, and the upper barrel 10 and the lower barrel 20 are unlocked. In the present embodiment, the number of the locking devices 30 is 3.

Referring to fig. 3-4, the pushing device 60 includes a separating action ring 61, an action push rod 62, a separating lower ring 63, a separating spring 64 and a spring sleeve 65, one end of the spring sleeve 65 is mounted on the separating lower ring 63, the other end is fixed on the lower cover 70, the separating spring 64 is sleeved on the spring sleeve 65 and is in a compressed state under the action of a pre-tightening force, the action push rod 62 is fixed between the separating action ring 61 and the separating lower ring 63, the action push rod 62 penetrates through the positioning hole 23 of the lower barrel 20, and the separating action ring 61 is located between the top surfaces of the upper barrel 10 and the lower barrel 20. In the process of separating the satellite and the arrow, the locking device 30 loses the abutting force with the rotating device 40, the pushing device 60 loses the pretightening force after the upper barrel 10 is unlocked with the lower barrel 20, the separating spring 64 drives the acting mandril 62 to move upwards in the process of restoring the elastic force, and the acting mandril 62 drives the separating acting ring 61 to act on the separating acting surface 13 of the upper barrel 10 to eject the upper barrel 10.

Separation unlocking method based on separation unlocking mechanism of rotary electromagnet, specifically as follows:

step 1: receiving satellite and rocket separation signals;

step 2: after the driving device 50 receives the satellite and rocket separation signal, the electromagnet 51 starts to be electrified, the rotating shaft 52 starts to rotate and drives the limiting lug 411 and the locking lug 412 in the rotating device 40 to rotate;

and step 3: during the rotation process, the locking lug 412 in the rotating device 40 is separated from the first pressing cap 32 in the locking device 30 after the abutting force is lost, the locking shaft 35 moves towards the inside of the lower barrel 20, and the upper barrel 10 is unlocked from the lower barrel 20;

and 4, step 4: after the upper barrel 10 and the lower barrel 20 are unlocked, the separating spring 64 in the pushing device 60 loses the pretightening force, the elastic force is restored to move upwards, the acting mandril 62 moves upwards in the positioning hole 23, the separating acting ring 61 acts on the separating acting surface 13 of the upper barrel 10 to eject the upper barrel 10 upwards, and the upper barrel 10 is separated from the lower barrel 20;

and 5: the microswitch 100 sends out a signal for separating the star from the arrow, and the separation of the star from the arrow is finished.

According to the above description, the utility model provides a separating mechanism based on rotary electromagnet, adopt the modularized design, including locking module, rotation module and promotion module, reasonable make full use of space resource, compact structure, whole upper tube and lower tube all adopt 7075-T651 aluminum alloy material, thereby solve envelope size big, the quality is heavy scheduling problem, simultaneously can be according to the quality characteristics and the separation characteristic requirement of different satellites, select the locking device of different numbers, the electro-magnet of different driving moments, the spring of different separation drive power, the separation demand of different satellites has been satisfied greatly, the adaptability of separating mechanism to different magnitude satellites has been increased; the rotary electromagnet is used as a unique driving source to replace initiating explosive devices, so that the problems of large impact, debris pollution, high cost, unrepeatability and the like are solved; the shifting fork principle is applied to design the locking device, so that the upper barrel and the lower barrel are locked and unlocked, 3 conical surface bosses are designed at the connecting surface of the upper barrel and the lower barrel, the bearing is arranged on the rotating device, the loading nut is arranged on the upper barrel, and the like, so that the rigidity of the whole structure is improved, the separating mechanism is guaranteed to bear axial load, longitudinal load, torque and bending moment in the launching stage, and the bearing capacity is high.

The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the changes or substitutions within the technical scope of the present invention, and all should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims (11)

1. A separation unlocking mechanism based on a rotary electromagnet is characterized by comprising an upper barrel (10), a lower barrel (20), a locking device (30), a rotating device (40) and a driving device (50), wherein the upper barrel (10) is sleeved on the lower barrel (20), the rotating device (40) is installed on the driving device (50) and can rotate along with the driving device (50), the locking device (30) transversely penetrates through the upper barrel (10) and the lower barrel (20) and is abutted against the rotating device (40) to lock the upper barrel (10) and the lower barrel (20) together, when the driving device (50) receives a satellite separation signal, the rotating device (40) is driven by the driving device (50) to rotate from an abutting position to a disengaging position, and the abutting of the rotating device (40) and the locking device (30) is released, the locking device (30) is disengaged from the upper barrel (10), and the upper barrel (10) and the lower barrel (20) are unlocked.

2. The separation unlocking mechanism based on a rotary electromagnet according to claim 1, further comprising a pushing means (60), wherein the pushing means (60) is in a compressed state when the upper cylinder (10) and the lower cylinder (20) are locked and contacts with the upper cylinder (10) through the lower cylinder (20), and when the rotating means (40) is rotated to the disengaged position, the pushing means (60) pushes the upper cylinder (10) to move upward by a restoring force, and the upper cylinder (10) is separated from the lower cylinder (20).

3. The separating and unlocking mechanism based on the rotary electromagnet as claimed in claim 1, wherein the upper cylinder (10) and the lower cylinder (20) are both of a cylindrical structure, first locking holes (11) are uniformly distributed on the cylinder wall of the upper cylinder (10), second locking holes (21) are uniformly distributed on the cylinder wall of the lower cylinder (20), and the locking device (30) sequentially traverses the second locking holes (21) and the first locking holes (11) and then abuts against the rotating device (40).

4. A rotary electromagnet based separation unlocking mechanism according to claim 2, characterized in that the rotating means (40) includes a rotating block (41) and a bearing (42), the bearing (42) is mounted on the rotating block (41) and is located between the rotating block (41) and the top surface of the lower cylinder (20), the driving means (50) includes an electromagnet (51) and a rotating shaft (52) located in the middle of the electromagnet (51), and the rotating block (41) is fixed on the rotating shaft (52) to be rotatable together with the rotating shaft (52).

5. The separation unlocking mechanism based on the rotary electromagnet as claimed in claim 1, characterized in that the locking device (30) comprises an unlocking spring (31), a first pressing cap (32), an inner retainer ring (33), an inner sliding sleeve (34), a locking shaft (35), an outer retainer ring (36), an outer sliding sleeve (37) and a second pressing cap (38), the first pressing cap (32) is arranged at one end of the locking shaft (35), the unlocking spring (31) is sleeved outside the first pressing cap (32), the first pressing cap (32) abuts against the rotating device (40) after the locking shaft (35) penetrates into the upper barrel (10) and the lower barrel (20), the unlocking spring (31) abuts against the inner barrel wall of the lower barrel (20), and the second pressing cap (38) is arranged outside the upper barrel (10) and inserted into the first locking hole (11), interior sliding sleeve (34) cover is established locking shaft (35) is gone up and is close to the first one end that compresses tightly cap (32), and pass through interior retaining ring (33) carry on spacingly, outer sliding sleeve (37) cover is established locking shaft (35) is gone up and is close to the second compresses tightly the one end of cap (38), and pass through outer retaining ring (36) carry on spacingly, interior sliding sleeve (34) with the molybdenum disulfide membrane has been plated on outer sliding sleeve (37).

6. The separation unlocking mechanism based on a rotary electromagnet according to claim 4, characterized by further comprising a stopper pin (80), wherein the stopper pin (80) is fixed on the inner top surface of the lower cylinder (20), the rotary block (41) comprises a stopper lug (411) radially protruding out of the rotary block (41), and the stopper lug (411) is stopped by the stopper pin (80) after the rotary device (40) is rotated to the disengaging position, so as to prevent the rotary block (41) from being over-rotated.

7. A split unlocking mechanism based on a rotary electromagnet according to claim 6, characterized in that the turning block (41) further comprises locking lugs (412) projecting radially out of the turning block (41), the locking lugs (412) being located below the limit lugs (411), the locking lugs (412) abutting the locking means (30) when the turning means (40) is in the abutting position, the locking means (30) being located in the recessed position between adjacent locking lugs (412) when the turning means (40) is turned to the disengaged position.

8. A rotary electromagnet based release mechanism according to claim 4, further comprising a lower cover (70) and a satellite insulating mat (120), the lower drum (20) and the electromagnet (51) being mounted on the lower cover (70), the lower cover (70) being connected to a launch vehicle, the satellite insulating mat (120) being mounted on the upper drum (10), the satellite insulating mat (120) being connected to a satellite.

9. The separating and unlocking mechanism based on the rotary electromagnet according to claim 8, wherein the pushing device (60) includes a separating action ring (61), an action ejector pin (62), a separating lower ring (63), a separating spring (64) and a spring sleeve (65), one end of the spring sleeve (65) is fixed on the separating lower ring (63), the other end is fixed on the lower cover (70), the separating spring (64) is sleeved on the spring sleeve (65), when the upper barrel (10) and the lower barrel (20) are locked, the separating spring (64) is in a compressed state, the separating action ring (61) is positioned between the top surfaces of the upper barrel (10) and the lower barrel (20) and can act on the upper barrel (10), the action ejector pin (62) is fixed between the separating action ring (61) and the separating lower ring (63) and penetrates through the positioning hole (23) on the lower barrel (20), the separating action ring (61) and the action mandril (62) can slide upwards relative to the lower barrel (20) under the driving of the separating spring (64).

10. A separating and unlocking mechanism based on a rotary electromagnet as claimed in claim 3, characterized in that the top surface of the upper cylinder (10) is further provided with a shear-proof taper hole (12), the top surface of the lower cylinder (20) is provided with a corresponding position of a shear-proof taper pin (22) which protrudes outwards, and the shear-proof taper pin (22) is plated with tungsten carbide.

11. The separation unlocking mechanism based on the rotary electromagnet as claimed in claim 1, further comprising a micro switch (100) and a pin (101), wherein the micro switch (100) is fixed on the upper cylinder (10), the pin (101) is inserted into the micro switch (100) and fixed on the top of the lower cylinder (20), when the upper cylinder (10) is separated from the lower cylinder (20), the micro switch (100) is disengaged from the pin (101) and sends a signal to a control system, so as to inform that the upper cylinder (10) and the lower cylinder (20) are separated.

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