Pneumatic separation lock for carrier rocket

Abstract

The invention relates to the technical field of pneumatic locks, in particular to a carrier rocket pneumatic separation lock. Comprising a lock cylinder which is provided with an air inlet pipe capable of supplying air into a cylinder body and limiting and fixing pieces oppositely arranged at the two ends of the lock cylinder; the number of the buckling modules is two, and the two buckling modules are oppositely and coaxially arranged at the two ends of the lock cylinder in a sliding mode; the fastening module is provided with a fastening piece capable of being locked with the limiting piece, a driving piece capable of driving the fastening piece to move to a first stroke, and a resetting piece capable of driving the fastening piece to move to a second stroke; the number of the connecting pieces is two, the two connecting pieces are coaxially and fixedly arranged at the far ends of the two buckling modules correspondingly, when the buckling pieces are located at the first stroke position, the connecting pieces are fixedly connected with the lock cylinder, and when the buckling pieces are located at the second stroke position, the connecting pieces are separated from the lock cylinder; the sealing device is quick in response and reliable in sealing and has double locking.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of pneumatic lock, in particular to a pneumatic separation lock of a launch vehicle. BACKGROUND

[0002] With the continuous development of modern aerospace technology, launch vehicles are gradually evolving towards reusability, high reliability and low cost. In the separation of each stage, fairing separation and recovery system of traditional one-off launch vehicles, explosive separation devices (such as explosive bolts or separation nuts) are usually used to achieve connection release. This kind of separation device relies on high-pressure gas generated by explosive combustion to release mechanical connection instantaneously, which has the advantages of simple structure and short response time, but also has the problems of large separation impact, non-reusability, harsh storage and transportation conditions, and the risk of dud.

[0003] In recent years, pneumatic drive separation technology has gradually become an important development direction of rocket separation mechanism. Pneumatic separation technology uses compressed gas to drive piston mechanism to achieve mechanical unlocking, which can realize controllable release of separation action by controlling gas pressure and flow, and has the advantages of small separation impact (controllable within 200g), repeatable action, adjustable response time and high safety. At the same time, this technology does not need to use explosive, avoiding the management and storage restrictions of explosive, which can significantly improve the safety level of the system.

[0004] However, the existing pneumatic separation device still has some technical bottlenecks. For example: 1. The sealing holding force is insufficient, and micro-leakage may occur under long-time high-pressure gas storage state, resulting in insufficient driving gas pressure; 2. Poor separation synchronization, in multi-point separation conditions, there is a large error (usually more than 10ms) in the action time of multiple pneumatic execution units, affecting the attitude stability of stage separation; 3. Complex structure, large volume, not conducive to lightweight design and rocket system integration; 4. Lack of self-locking and safety redundancy design, there are problems that cannot be reliably locked or cannot be completely unlocked in some working conditions. SUMMARY

[0005] In view of the above problems, a launch vehicle pneumatic separation lock is provided, which proposes a compact structure, fast response, reliable sealing, and double insurance pneumatic separation lock, thereby solving the technical problems of insufficient sealing force retention, complex structure, large volume and lack of self-locking and safety redundancy design of the existing pneumatic separation device.

[0006] To solve the prior art problems, the present application provides a kind of launch vehicle aerodynamic separation lock, comprising: lock cylinder is equipped with the air inlet pipe that can supply gas to the cylinder body and opposite setting in the locking member of the both ends of the lock cylinder, the lock cylinder is hollow and the both ends open cylindrical pipe body;Two buckle modules are provided, and two buckle modules are coaxially slidably arranged at the both ends of the lock cylinder;The buckle module is equipped with the buckle piece that can be locked with the locking member and the driving piece that can drive the buckle piece to displace to the first stroke and the reset piece that can drive the buckle piece to displace to the second stroke;Two connecting pieces are provided, and two connecting pieces are coaxially fixedly arranged at the distal end of two buckle modules respectively, when the buckle piece is located at the first stroke, the connecting piece is fixedly connected with the lock cylinder, when the buckle piece is located at the second stroke, the connecting piece is disconnected with the lock cylinder.

[0007] Preferably, the buckle module further includes a limiting sleeve capable of guiding the axial sliding of the driving piece, the limiting sleeve is further radially provided with a guide groove capable of guiding the radial sliding of the buckle piece and a limiting rod capable of radially limiting the buckle piece and detachably arranged in the guide groove;The connecting piece is coaxially fixedly arranged at the distal end of the limiting sleeve;The limiting sleeve is coaxially slidably arranged in the locking member;The guide groove is provided with a plurality of guide grooves along the axial direction of the limiting sleeve.

[0008] Preferably, the driving piece is composed of a guide ring, a piston push rod and a driving rod which are coaxially fixedly connected in sequence;The guide ring is further embeddedly mounted with a sealing ring outside;The diameter of the driving rod is greater than that of the piston push rod, and the connection between the driving rod and the piston push rod is further provided with a second chamfer capable of obliquely pushing the buckle piece;The driving rod and the limiting sleeve are clearance fit.

[0009] Preferably, the distal end of the driving rod is further coaxially fixedly provided with a buckle convex ring capable of being buckled in the limiting sleeve;The reset piece is coaxially arranged in the limiting sleeve and abuts against the inner wall of the limiting sleeve and the buckle convex ring at both ends respectively.

[0010] Preferably, the side of the guide ring away from the piston push rod is further provided with a groove for the air source to enter.

[0011] Preferably, two first pistons and second pistons capable of axially limiting the axial sliding positions of two buckle modules are further respectively arranged in the lock cylinder;The first piston and the second piston are oppositely arranged on both sides of the air inlet pipe.

[0012] Preferably, the buckle piece is a rectangular slide block and an internal through hole is provided with a sliding groove matched with the limiting rod for sliding;The top of the buckle piece is further provided with a third chamfer matched with the first chamfer.

[0013] Preferably, the reset member is specifically a spring.

[0014] The beneficial effects of the present application compared with the prior art are:

[0015] 1. The double buckle fixing module structure is arranged in the lock cylinder, the fixing member and the disengaging member of the rocket are symmetrically locked by two buckle fixing modules and limiting members in the non-separation state, the separation force is evenly distributed, the structure deviation or local instability caused by single-point stress is avoided, and therefore the locking stability and assembly precision are improved.

[0016] 2. When separation is needed, only an external high-pressure gas source needs to be connected, the gas is introduced into the inside of the lock cylinder through the gas inlet pipe, the axial sliding of the driving member is driven by the gas pressure difference, the buckle fixing member is driven to retract radially, the quick and synchronous unlocking action is realized, the rocket stage separation response time can be significantly shortened, and the immediacy and synchronism of the separation action are improved. Meanwhile, the pneumatic driving replaces the traditional explosion or electromagnetic release mechanism, the influence of unstable factors such as high temperature and high impact is avoided, and higher safety and reusability are achieved.

[0017] 3. The guiding ring and the groove gas storage cavity are arranged, the gas flow thrust area is formed by the gas pressure, the gas source is efficiently used on the driving member in the limited space, the quick starting force is concentrated and transmitted, the maximum extension stroke of the buckle fixing module is axially limited by the double convex ring limiting structure, the mutual interference and airflow disturbance between the modules are prevented, and the stability and repeated consistency of the separation and locking action are ensured. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is a perspective view of a pneumatic separation lock of a launch vehicle.

[0019] Figure 2 It is a side view of a pneumatic separation lock of a launch vehicle.

[0020] Figure 3 It is Figure 2 the A-A cross-sectional view of.

[0021] Figure 4 It is Figure 3 the B local enlarged view of.

[0022] Figure 5 It is a top view of a pneumatic separation lock of a launch vehicle.

[0023] Figure 6 It is Figure 5 the C-C cross-sectional view of.

[0024] Figure 7 It is an exploded perspective view of the buckle fixing module part structure of a pneumatic separation lock of a launch vehicle Figure 1 .

[0025] Figure 8 It is a kind of carrying rocket aerodynamic separation lock buckle fixed module part structure exploded perspective Figure 2 .

[0026] The figure mark is:

[0027] 1, lock cylinder;11, air inlet pipe;12, limiting part;121, first chamfer;13, first piston;14, second piston;

[0028] 2, buckle fixed module;21, buckle;211, sliding groove;212, third chamfer;22, driving part;221, guide ring;2211, sealing ring;2212, groove;222, piston push rod;223, driving rod;224, second chamfer;225, buckle convex ring;23, reset part;24, limiting sleeve;241, guide slot;242, limiting rod;

[0029] 3, connecting piece. Specific embodiments

[0030] In order to further understand the features, technical means and specific purposes and functions of the present application, the present application will be described in detail below in combination with the drawings and specific embodiments.

[0031] Referring to Figures 1 to 8 As shown: a kind of carrying rocket aerodynamic separation lock, comprising: lock cylinder 1, is equipped with the air inlet pipe 11 of being able to supply air to cylinder body and the limiting part 12 of being oppositely arranged at the both ends of the lock cylinder 1, the lock cylinder 1 is hollow and the cylindrical pipe body of both ends opening;Buckle fixed module 2, is equipped with two, two buckle fixed modules 2 are oppositely coaxially arranged at the both ends of the lock cylinder 1;The buckle fixed module 2 is equipped with the buckle 21 of being able to be locked with the limiting part 12 and the driving part 22 of being able to drive the buckle 21 displacement to first stroke and the reset part 23 of being able to drive the buckle 21 displacement to second stroke;Connecting piece 3, is equipped with two, two the connecting piece 3 is coaxially fixedly arranged at the distal end of two the buckle fixed module 2 respectively, when the buckle 21 is located at first stroke, the connecting piece 3 is fixedly connected with the lock cylinder 1, when the buckle 21 is located at second stroke, the connecting piece 3 and the lock cylinder 1 are disconnected.

[0032] The connecting end of two the connecting piece 3 is fixedly connected with the fixing part and the separation part of rocket respectively.

[0033] The limiting part 12 is the cylinder body that is arranged in the form of circular ring, and the inner wall of the cylinder body is further provided with the first chamfer 121 for inclining to guide the buckle 21.

[0034] When the fixed part and the separation part of the rocket are in the locked state and have not been separated, the two buckle modules 2 are buckled by the buckle 21 arranged therein and the limiting buckle 12 arranged at both ends of the lock cylinder 1, so that a reliable mechanical connection is formed between the fixed part and the separation part, thereby ensuring the stability of the connection under the action of the flight load.

[0035] When it is necessary to automatically separate the fixed part and the separation part, first, the external high-pressure gas source is connected, and the lock cylinder 1 is filled with compressed gas through the gas inlet pipe 11. The cavity thrust generated by the gas in the lock cylinder 1 drives the driving part 22 to produce axial displacement. Then, the driving part 22 is axially contracted towards the connecting part 3, so that the driving part 22 is displaced relative to the buckle 21, thereby releasing the buckling fit between the buckle 21 and the limiting buckle 12. After the buckling is released, the continuous gas pressure pushes the corresponding buckle module 2 and the connecting part 3 out of the lock cylinder 1, thereby separating the fixed part and the separation part.

[0036] The device is provided with two independent buckle modules 2, and the two modules are connected with the two ends of the lock cylinder 1 correspondingly. In the case that the gas source drives any side buckle module 2 to be buckled, the constraint link of the whole device is broken, and the separation of the fixed part and the separation part is triggered, thereby realizing the redundant buckling function that the separation can be completed by unilateral triggering. In the case that the reliability needs to be improved, the two side buckle modules 2 can be triggered at the same time to ensure the synchronization of separation and attitude control.

[0037] Meanwhile, the cooperation of the driving part 22, the lock cylinder 1 and the guide ring 221 in the embodiment makes the pushing force and the displacement in the separation process controllable by the gas source pressure and the throttle parameter, so that the separation impact is controlled within the designed range. With the double-module redundancy and controllable pneumatic drive, the repeatable separation, low-impact and easy-maintenance separation function can be completed without the need of a pyrotechnic product.

[0038] Through the above structure and cooperative matching, the reliable locking under the flight load and the controllable, repeatable, low-impact and redundant buckling capability of the automatic separation of the rocket stages or the fairing are realized, so that the separation reliability is ensured, the maintenance cost is reduced, and the system safety is improved.

[0039] Referring to Figure 7 and Figure 8As shown: the buckle module 2 further comprises a limiting sleeve 24 capable of guiding the axial sliding of the driving member 22, the limiting sleeve 24 is radially provided with a guide groove 241 capable of guiding the radial sliding of the buckle member 21 and a limiting rod 242 detachably arranged in the guide groove 241 and capable of radially limiting the buckle member 21; the connecting member 3 is coaxially fixedly arranged at the distal end of the limiting sleeve 24; the limiting sleeve 24 is coaxially slidably arranged in the limiting member 12; the guide groove 241 is circumferentially arranged along the axial direction of the limiting sleeve 24.

[0040] The limiting sleeve 24 is a long circular cylindrical body arranged in a ring shape and has an outer diameter in clearance fit with the limiting member 12.

[0041] The buckle member 21 is circumferentially arranged along the lock cylinder 1 and has a plurality of buckle members 21 arranged one by one corresponding to the guide groove 241, for realizing multi-point balanced locking of the limiting member 12.

[0042] In the non-disengagement state, the driving member 22 is axially away from the connecting member 3 under the axial support of the reset member 23; at this time, the driving member 22 radially supports each buckle member 21 from inside to outside through the inclined pressure surface on the outer periphery of the driving member 22, so that each buckle member 21 radially extends out of the outer side of the limiting sleeve 24 and forms a reliable buckle connection with the limiting member 12.

[0043] In this state, the buckle module 2 and the lock cylinder 1 form a ring force closed structure, thereby realizing high-strength locking between the rocket fixing member and the disengagement member, and ensuring that the connection state remains stable when bearing axial and radial loads during launching and flying.

[0044] When the high-pressure gas is introduced into the inside of the lock cylinder 1 through the gas inlet channel, the gas pressure drives the driving member 22 to slide axially towards the connecting member 3 and compresses the reset member 23, so that the pressure surface of the driving member 22 is disengaged from each buckle member 21. At this time, each buckle member 21 loses radial support and constraint and is automatically recovered towards the center of the lock cylinder 1 under the guidance of the limiting groove, thereby releasing the buckle with the limiting member 12. With all the buckle members 21 exiting the limiting state, the locking relationship between the buckle module 2 and the lock cylinder 1 is completely released, and finally the pneumatic separation of the rocket fixing member and the disengagement member is realized.

[0045] By arranging a plurality of buckle members 21 one by one corresponding to the guide groove 241 and using the radial support of the driving member 22 and the high-pressure gas driving and unlocking structure, the synergistic effect of multi-point ring balanced locking, pneumatic quick unlocking and low-impact separation is realized; in the locked state, the connection is stable and reliable, in the separation state, the response is rapid and the action is synchronous, which can significantly improve the safety, reusability and pneumatic control accuracy of the separation lock.

[0046] See Figure 7 and Figure 8 As shown: The driving component 22 is composed of a guide ring 221, a piston push rod 222 and a driving rod 223 that are coaxially fixedly connected in sequence; a sealing ring 2211 is also embedded in the guide ring 221; the diameter of the driving rod 223 is larger than that of the piston push rod 222, and the connection between the driving rod 223 and the piston push rod 222 is provided with a second chamfer 224 that can tilt and push the fastener 21; the driving rod 223 and the limiting sleeve 24 are in clearance fit.

[0047] The guide ring 221 and the inner wall of the lock cylinder 1 are in clearance fit and are sealed to the inner wall of the lock cylinder 1 by the sealing ring.

[0048] When an external high-pressure air source is introduced into the lock cylinder 1 through the air inlet channel, under the action of air pressure, the drive rod 223, under the synchronous constraint and guidance of the guide ring 221, slides smoothly along the axial direction of the lock cylinder 1 toward the connecting member 3. As the drive rod 223 moves axially away from its original top support position, an annular gap is formed inside the limiting sleeve 24, providing space for the radial inward movement of the fastener 21.

[0049] During this process, the fastener 21, which was originally supported by the outer periphery of the drive rod 223, loses its radial support force and retracts towards the center of the locking cylinder 1 under its own weight, thereby releasing the mechanical fastening relationship with the limiting component 12. When all the fasteners 21 have completely retracted into the limiting sleeve 24, the locking connection between the locking cylinder 1 and the fastening module 2 is completely released; at this time, the high-pressure gas continues to release thrust, causing the fastening module 2 to be completely pushed out of the locking cylinder 1 under the action of pneumatic thrust, thereby realizing the automatic separation action between the rocket fixing component and the release component.

[0050] Through the clearance fit design between the drive rod 223 and the limiting sleeve 24, and the synergistic guiding effect of the guide ring 221, the controllability and smoothness of the fastener 21's release process are achieved, effectively avoiding separation failure caused by structural interference or frictional obstruction. At the same time, the continuous drive of high-pressure gas is used to complete the separation release, making the release action more stable, synchronous, and with controllable impact, significantly improving the reliable separation performance and reusability stability of the pneumatic release lock under high load conditions.

[0051] See Figure 4 and Figure 8 As shown: The end of the drive rod 223 is also coaxially fixed with a fastening protrusion 225 that can be fastened to the inside of the limiting sleeve 24; the reset member 23 is coaxially disposed inside the limiting sleeve 24 and its two ends abut against the inner wall of the limiting sleeve 24 and the fastening protrusion 225 respectively.

[0052] In the assembled state, the guide ring 221 can slide within a preset range along the axial direction of the locking cylinder 1. When it is in the non-disengaged state, the guide ring 221 is held in the initial position by the elastic support of the reset member 23, and its axial travel is effectively constrained by the fastening protrusion ring 225, thereby preventing the guide ring 221 from moving too far forward under static or micro-vibration conditions and avoiding its end from passing the inlet of the air intake pipe 11.

[0053] When external high-pressure gas is introduced into the lock cylinder 1 through the air inlet pipe 11, the high-pressure gas source can directly act on the pressure-bearing surface of the guide ring 221, causing it to generate directional thrust and slide smoothly along the axial direction, thereby driving the drive rod 223 and the fastening assembly connected to it to complete the release action. Because the fastening protrusion 225 precisely limits the sliding range of the guide ring 221, it ensures that the high-pressure gas continuously and concentratedly acts on the effective force-bearing surface area after entering the lock cylinder 1, avoiding airflow dispersion or leakage due to sliding exceeding the limit, thereby improving pneumatic drive efficiency and control accuracy.

[0054] By setting a fastening protrusion 225 to physically limit the axial sliding stroke of the guide ring 221, the over-positioning of the guide ring 221 and the mis-entry of high-pressure airflow in the non-disengaged state are effectively prevented, ensuring the stable position of the air source and the accurate pressure transmission path, thereby achieving high reliability of the pneumatic drive process.

[0055] See Figure 3 and Figure 7 As shown: The guide ring 221 is also provided with a groove 2212 for the air supply source to enter on the side away from the piston push rod 222.

[0056] The guide ring 221 has a groove 2212 on the side away from the piston push rod 222. The groove 2212 and the inner cavity of the lock cylinder 1 together form a closed air storage cavity.

[0057] When external compressed gas is introduced into the lock cylinder 1 through the air inlet pipe 11, the airflow first enters the air storage chamber and is temporarily stored under pressure. After the air pressure reaches the set value, the high-pressure gas in the air storage chamber acts on the pressure-bearing surface of the guide ring 221, generating a directional thrust, thereby driving the guide ring 221 to slide rapidly along the axis of the lock cylinder 1 towards the piston push rod 222. This sliding motion further drives the drive component 22 connected to the guide ring 221 to move synchronously, realizing the pneumatic drive release of the fastener 21.

[0058] Through the above structure, the air storage cavity formed by the groove 2212 plays the role of energy buffering and secondary pressurization in the pneumatic separation process: it can not only avoid damage caused by the instantaneous airflow directly impacting the sealing components, but also provide a stable and continuous driving force in a very short time to complete the rapid separation action.

[0059] SeeFigure 3 As shown: The locking cylinder 1 is also provided with two first pistons 13 and second pistons 14, which can respectively limit the axial sliding position of the two fastening modules 2; the first pistons 13 and second pistons 14 are arranged opposite to each other on both sides of the air inlet pipe 11.

[0060] By using two first pistons 13 and second pistons 14 relatively disposed on the inner wall of the lock cylinder 1, the maximum extension stroke of the two fastening modules 2 can be axially limited respectively; thereby avoiding the maximum extension stroke of the two fastening modules 2, which are placed in the lock cylinder 1 in a non-separated state, being stopped by the first pistons 13 and second pistons 14 respectively, and preventing the two fastening modules 2 from interfering with each other and affecting the normal introduction of external high-pressure air source into the lock cylinder 1 through the air inlet pipe 11 and ultimately acting on the fastening modules 2.

[0061] The inner wall of the locking cylinder 1 is provided with a first piston 13 and a second piston 14 spaced apart along the axial direction. The two convex rings are located on both sides of the middle part of the locking cylinder 1 and are symmetrically distributed to limit the axial sliding stroke of the two fastening modules 2.

[0062] In the assembled state, the two fastening modules 2 are located at both ends of the locking cylinder 1, and their ends can extend and retract axially to a limited extent between the first piston 13 and the second piston 14. When in the non-separated state, the two fastening modules 2 are held in the locked position by the elastic pre-tightening action of the reset member 23, and their end faces abut against the limiting surfaces of the corresponding first piston 13 or second piston 14, thereby limiting their maximum extension stroke and ensuring that the fastening modules 2 are always in a stable locked posture. This effectively prevents interference or collision when the two fastening modules 2 move towards each other inside the locking cylinder 1, ensuring that the two fastening modules 2 operate independently during the force application and reset process.

[0063] In addition, the distance between the first piston 13 and the second piston 14 is precisely designed so that when the external high-pressure gas source is introduced into the lock cylinder 1 through the air inlet pipe 11, the lock cylinder 1 cavity still retains sufficient gas flow channels and pressure distribution space, thereby ensuring that the high-pressure gas can be smoothly transmitted to the force-bearing surfaces of each fastening module 2, achieving a uniform pneumatic drive effect, and preventing airflow blockage or pressure unevenness caused by the maximum extension and retraction position of the fastening module 2.

[0064] By symmetrically arranging the first piston 13 and the second piston 14 on the inner wall of the locking cylinder 1 and limiting the maximum extension stroke of the fastening module 2, a bidirectional stroke limit and structural anti-interference design are achieved. This not only ensures the stable locking and independent movement of the fastening module 2 in the non-separated state, but also ensures that the high-pressure gas can be smoothly introduced and evenly applied to each fastening module 2 during the separation stage.

[0065] See Figure 7 and Figure 8 As shown: the fastener 21 is a rectangular slider with a through groove 211 that slides and engages with the limiting rod 242; the top of the fastener 21 is also provided with a third chamfer 212 that abuts against the first chamfer 121.

[0066] In the non-disengaged state, the fastener 21, under the radial pressing action of the drive rod 223, is pushed against the inner wall of the limiting sleeve 24 and extends radially outward, with its outer end protruding through the outer surface of the limiting sleeve 24. At this time, the third chamfer 212 of the fastener 21 and the first chamfer 121 of the limiting member 12 fit together to form a wedge engagement, thereby achieving stable locking between the fastening module 2 and the locking cylinder 1. In this state, the drive rod 223 maintains radial support under the pre-tightening force of the reset member 23, keeping the fastener 21 continuously in the extended position, thereby ensuring a reliable connection between the rocket's fixing and disengaging components.

[0067] When an external air source is introduced into the locking cylinder 1 through the air inlet pipe 11 and acts on the driving component 22, the driving component 22 slides axially toward the connecting component 3 under the impact of the high-pressure airflow and generates a contraction stroke. As the driving component 22 contracts axially, the driving rod 223, which was originally in contact with the bottom of the fastener 21, gradually disengages, and the piston push rod 222 replaces the driving rod 223 to form a guiding contact with the bottom of the fastener 21, thereby creating a radial clearance space between the fastener 21 and the limiting sleeve 24, allowing the fastener 21 to retract radially and release the fastening between it and the limiting component 12. As all the fasteners 21 have completed their radial retraction, the fastening module 2 disengages from the locking cylinder 1 under the thrust of the high-pressure air source, realizing the rapid separation of the rocket fixing component and the disengagement component.

[0068] In addition, the limiting rod 242 is disposed inside the limiting sleeve 24 to constrain the radial sliding stroke of the fastener 21. During the radial extension or retraction of the fastener 21, the limiting rod 242 provides limiting support to its sliding end face to prevent the fastener 21 from detaching from the limiting sleeve 24 due to excessive sliding, thereby ensuring the structural stability and repeatability of the fastening mechanism in multiple action cycles.

[0069] Through the above structure, the radial extension and self-locking control mechanism of the fastener 21 under the coordinated action of the drive rod 223 and the piston push rod 222 is realized. It can ensure stable locking in the non-disengaged state and achieve rapid unlocking and automatic separation in the pneumatic drive state.

[0070] See Figure 4 and Figure 8 As shown: The reset element 23 is specifically a spring.

[0071] By configuring the reset member 23 as a spring structure, with one end abutting against the drive member 22 and the other end fixedly connected to the connector 3, a stable axial elastic support force can be applied to the drive member 22 in the non-disengaged state. This elastic support force ensures that the drive member 22 and the connector 3 maintain a continuous axial abutment state during operation, thereby providing a constant radial support force to the fastener 21, ensuring that the fastener 21 remains firmly fastened to the retainer 12. This not only guarantees reliable force and real-time abutment effect of the fastener 21 in the locked state, but also automatically compensates for minute gap changes under aerodynamic impact or vibration environments, preventing loosening or displacement of the fastener.

[0072] This invention not only has a fast response and reliable sealing, but also features double locking.

[0073] The above embodiments only illustrate one or more implementations of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of the present invention should be determined by the appended claims.

Claims

1. A pneumatic separation lock for a launch vehicle, characterized in that, include: The lock cylinder is provided with an air inlet pipe that can supply air into the cylinder and limiting fasteners that are disposed opposite to each other at both ends of the lock cylinder. The lock cylinder is a hollow cylindrical tube with open ends. The fastening module is provided in two parts, which are slidably disposed coaxially at both ends of the lock cylinder; the fastening module is provided with a fastener that can be locked with the limiting fastener, a driving member that can drive the fastener to a first stroke position, and a reset member that can drive the fastener to a second stroke position. Two connectors are provided, and the two connectors are coaxially fixedly disposed at the far ends of the two fastening modules. When the fastening module is located at the first stroke, the connector is fixedly connected to the locking cylinder. When the fastening module is located at the second stroke, the connector is disengaged from the locking cylinder.

2. The pneumatic separation lock for a launch vehicle according to claim 1, characterized in that, The fastening module also includes a limiting sleeve that can guide the axial sliding of the driving component. The limiting sleeve is also radially provided with a guide groove that guides the radial sliding of the fastener and a limiting rod that can be detachably disposed in the guide groove to radially limit the fastener. The connector is coaxially fixedly disposed at the far end of the limiting sleeve; The limiting sleeve is coaxially and slidably disposed within the limiting component; Multiple guide grooves are provided along the axial and circumferential direction of the limiting sleeve.

3. A pneumatic separation lock for a launch vehicle according to claim 2, characterized in that, The driving component consists of a guide ring, a piston rod, and a driving rod that are coaxially and fixedly connected in sequence. A sealing ring is also embedded outside the guide ring; The diameter of the drive rod is larger than that of the piston push rod, and the connection between the drive rod and the piston push rod is provided with a second chamfer that can tilt and push the fastener; the drive rod and the limiting sleeve are in clearance fit.

4. A pneumatic separation lock for a launch vehicle according to claim 3, characterized in that, The end of the drive rod is also coaxially fixed with a fastening protrusion that can fasten to the inside of the limiting sleeve; The reset component is coaxially disposed inside the limiting sleeve, and its two ends abut against the inner wall of the limiting sleeve and the fastening protrusion, respectively.

5. A pneumatic separation lock for a launch vehicle according to claim 3, characterized in that, The guide ring also has a groove on the side away from the piston rod for the air supply to enter.

6. A pneumatic separation lock for a launch vehicle according to claim 1, characterized in that, The lock cylinder is also equipped with two first pistons and a second piston, which can respectively limit the axial sliding position of the two fastening modules; The first piston and the second piston are disposed opposite each other on both sides of the intake pipe.

7. A pneumatic separation lock for a launch vehicle according to claim 2, characterized in that, The fastener is a rectangular slider with a through groove that slides through it to engage with the limiting rod. The top of the fastener is also provided with a third chamfer that abuts against the first chamfer.

8. A pneumatic separation lock for a launch vehicle according to claim 1, characterized in that, The reset element is specifically a spring.

Images