Rapid locking and unlocking mechanism for rocket recovery supporting mechanism
By designing a quick locking and unlocking mechanism for rocket recovery support mechanism, the problem of insufficient structural stability and sealing performance in the existing technology in extremely low temperatures and harsh environments is solved, and the efficiency, reliability and sustainability of rocket recovery is achieved.
Patent Information
- Application Number
- CN202421673937.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-16
- Publication Date
- 2025-04-15
- Estimated Expiration
- 2034-07-16
AI Technical Summary
The existing rocket recovery devices face the harsh environmental impacts of thermal expansion, cooling, damp heat, mold and other bacteria caused by temperature changes, as well as insufficient structural stability and sealing performance under extremely low temperature conditions.
A quick locking and unlocking mechanism for rocket recovery support mechanism is designed, and the adjustment mechanism and locking components are composed of locking hooks, piston rods, pressure reset chambers, lock keys, rollers, guide plates, mounting plates, valve bodies, lock hook return springs, lock key return springs, joint bearings, gas valves, etc. The piston rod is pushed by high-pressure gas to achieve rapid unlocking, and the joint bearings are automatically adjusted to adapt to deformation caused by temperature changes.
The stable operation of the rocket recovery support mechanism in extremely low temperature environments has been achieved, the stability and sealing performance of the structure have been improved, economic costs have been reduced, and the reliability and sustainability of rocket recycling have been enhanced.
Smart Images
Figure CN222761501U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of rocket recovery, in particular to a quick locking and unlocking mechanism for a rocket recovery support mechanism. Background Art
[0002] In the current rocket recovery technology, the commonly used disposable punch-off pin structure can complete its basic recovery mission, but its one-time use limits its economy and sustainability. After each rocket launch, these parts need to be replaced, which not only increases the economic burden, but also increases the complexity of maintenance work.
[0003] At present, existing technologies have limitations in dealing with the environmental challenges encountered by rockets during launch and recovery. When a rocket experiences temperature changes, it will expand and contract, and existing devices do not perform well in adapting to such changes. In harsh environments such as humidity, heat, and mold, the performance and durability of existing devices will also be affected. Especially in extreme low temperature conditions, the structural stability and sealing performance of existing devices are often difficult to meet the requirements, which not only affects the long-term operational reliability of the device, but also increases the difficulty and cost of operation and maintenance.
[0004] In order to overcome these problems, we need to develop a quick locking and unlocking mechanism for the rocket recovery support mechanism. This device must not only meet the requirements of quick locking and unlocking, but also be reusable to reduce economic costs. Utility Model Content
[0005] The purpose of this section is to summarize some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this section and the abstract of the specification and the name of the utility model to avoid blurring the purpose of this section, the abstract of the specification and the name of the utility model, and such simplifications or omissions cannot be used to limit the scope of the utility model.
[0006] Therefore, the purpose of the utility model is to provide a quick locking and unlocking mechanism for a rocket recovery support mechanism, which can solve the problems of insufficient structural stability and sealing performance of existing rocket recovery devices when facing harsh environmental influences such as thermal expansion and contraction caused by temperature changes, humidity, heat, mildew, and extreme low temperature conditions.
[0007] In order to solve the above technical problems, the utility model provides a rapid locking and unlocking mechanism for a rocket recovery support mechanism, which adopts the following technical solution: comprising an adjustment mechanism and a locking assembly, wherein the locking assembly is arranged in the middle of the adjustment mechanism, the adjustment mechanism comprises a valve body, guide plates are arranged on both sides of the valve body, and a mounting plate is connected to the top of the valve body;
[0008] The locking assembly comprises a locking hook, and a roller is arranged at one end of the locking hook.
[0009] By adopting the above technical scheme, the quick locking and unlocking mechanism designed in this scheme is mainly used for the support mechanism of recoverable rockets. It is locked before the rocket is launched and quickly unlocked during the recovery process to open the folded support mechanism, thereby achieving a smooth landing of the rocket. The core of the locking and unlocking mechanism is an adjustment mechanism and a locking assembly, including a lock hook, a piston rod, a pressure reset chamber, a lock key, a roller, a guide plate, a mounting plate, a valve body, a lock hook reset spring, a lock key reset spring, a joint bearing, an air valve, etc. In the locked state, the lock hook moves upward under the guidance of the roller. When moving to the specified position, the lock hook is locked by the lock key to achieve the locking of the rocket recovery support mechanism. When unlocking, high-pressure gas is introduced into the valve body through the air valve to push the piston rod to move, so that the lock key rotates and disengages from the roller, thereby unlocking the lock hook and the rocket support mechanism can be deployed. In addition, the deformation of the support mechanism caused by temperature changes is corrected by the floating joint bearing to ensure the stability of the mechanism and the smoothness of unlocking during the launch and recovery process.
[0010] Optionally, a lock hook return spring is arranged at one end of the valve body, and a lock key is arranged at the bottom of one end of the valve body close to the lock hook return spring.
[0011] By adopting the above-mentioned technical scheme, the valve body in this scheme is equipped with a lock hook reset spring and a lock key, which constitutes the key part of the quick locking and unlocking mechanism, ensuring the rapid reset of the lock hook and the reliability of the locked state, and realizing the automation, efficiency and safety of the rocket recovery support mechanism in launch and recovery operations.
[0012] Optionally, the lock key matches the roller structure, and the lock key and the roller are snap-fitted.
[0013] By adopting the above-mentioned technical scheme, this scheme ensures the reliable fixation of the support mechanism in the locked state through the structural design of the snap-fit between the lock key and the roller, avoiding structural instability caused by temperature changes or external impacts. At the same time, during the unlocking process, the lock hook can be released quickly and effectively to ensure the smooth deployment of the support mechanism and the safe recovery of the rocket.
[0014] Optionally, an air valve is further provided on one side of the end of the valve body away from the lock hook return spring.
[0015] By adopting the above-mentioned technical scheme, the gas valve in this scheme is a key control component in the rapid locking and unlocking mechanism. It realizes the unlocking operation by providing high-pressure gas. Its setting improves the automation level, response speed and safety of the rapid locking and unlocking mechanism, ensuring the reliable deployment of the rocket recovery support mechanism at the critical stage of the mission, thereby ensuring the smooth landing and efficient recovery of the rocket.
[0016] Optionally, a lock hook shaft is connected between the lock hook and the two groups of guide plates.
[0017] By adopting the above technical solution, the lock hook in this solution moves between two sets of guide plates through the lock hook shaft. The two sets of guide plates provide a precise movement path for the lock hook to prevent it from having position errors due to deviation from the track during movement. Through this structure, the lock hook can move smoothly and without obstruction to the locked or unlocked position, ensuring the reliability and smoothness of the operation.
[0018] Optionally, a lock key shaft is connected between the lock key and one end of the valve body, and a contact is also provided on the top of the lock key.
[0019] By adopting the above technical solution, the lock key shaft in this solution provides a rotation fulcrum and connection support for the lock key, so that the lock key can rotate stably, and the contact serves as a trigger point and force surface during the unlocking process, ensuring that the thrust of the piston connecting rod can be effectively transmitted to the lock key to complete the unlocking operation.
[0020] Optionally, a spherical bearing is connected between the mounting plate and the top of the valve body.
[0021] By adopting the above technical solution, the present solution connects the mounting plate to the top of the valve body through a spherical bearing, so that there is a certain degree of flexibility between the two components.
[0022] Optionally, a piston rod is connected to the interior of the valve body, one end of the piston rod is in contact with the contact, and a pressure return spring is sleeved on the exterior of the piston rod.
[0023] By adopting the above technical solution, this solution accurately transmits the power of high-pressure gas to the contact through the linear movement of the piston rod, triggers the rotation operation of the lock key, and completes unlocking. The contact and cooperation between the piston rod and the contact ensures the precise transmission of force and improves the reliability and accuracy of unlocking. The pressure return spring provides the necessary reverse elastic force during the movement of the piston rod, so that the piston rod can be quickly reset after each operation, maintaining the continuity and stability of the quick locking and unlocking mechanism.
[0024] In summary, the present invention has at least one of the following beneficial effects:
[0025] 1. The quick locking and unlocking mechanism of this patent has significantly improved the efficiency and reliability of the rocket recovery process through a series of innovative designs. First of all, the mechanism uses ultra-low temperature resistant titanium alloy materials and special sealing materials, so that it can maintain stable operation even in an extreme low temperature environment of -197°C, effectively solving the problem of performance degradation of traditional technologies at low temperatures and enhancing the stability of rocket recovery. Compared with the traditional disposable pin structure, the mechanism design of this patent allows for repeated use, which not only reduces the economic burden caused by component replacement, but also improves the economic benefits and sustainability of rocket launch and recovery, and promotes multiple recycling of rockets. In addition, the mechanism adopts a joint bearing structure, which can automatically adjust to adapt to the deformation of the support mechanism caused by temperature changes in the rocket, ensuring stability and smooth unlocking during the launch and recovery process, reducing the risk of mechanism damage and optimizing the operating experience;
[0026] 2. The unlocking mechanism in this scheme uses high-pressure gas to push the piston rod, achieving rapid response and synchronous unlocking, meeting the needs of unlocking multiple locks at the same time, and improving the safety and operational efficiency of the recovery process. At the same time, the mechanism exhibits excellent impact resistance and overload resistance, and can maintain normal operation even in harsh environments such as humidity, heat, mold, salt spray, rain and snow, ensuring long-term reliability and durability under changing climatic conditions. From the above, it can be seen that the rapid locking and unlocking mechanism of this patent not only improves the performance of the rocket recovery support mechanism through innovative material application and structural optimization, but also ensures its wide application in various harsh environments, achieving maximum cost-effectiveness, and has far-reaching practical value and economic significance. BRIEF DESCRIPTION OF THE DRAWINGS
[0027] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for describing the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.
[0028] Figure 1 This is a schematic diagram of the locking state of the utility model;
[0029] Figure 2 This is a schematic diagram of the valve body structure of the utility model;
[0030] Figure 3 This is a schematic diagram of the unlocked state of the utility model;
[0031] Figure 4 This is a schematic diagram of the lock hook structure of the utility model;
[0032] Figure 5 This is a schematic diagram of the piston rod structure of the utility model.
[0033] Explanation of the reference numerals: 100, adjusting mechanism; 101, valve body; 101a, piston rod; 101b, pressure return spring; 102, guide plate; 103, mounting plate; 103a, spherical bearing; 104, lock hook return spring; 105, lock key; 105a, lock key shaft; 105b, contact; 106, air valve; 200, locking assembly; 201, lock hook; 201a, lock hook shaft; 202, roller. DETAILED DESCRIPTION
[0034] The following is combined with Figure 1-5 The utility model is described in further detail.
[0035] Embodiment 1, refer to Figure 1-3 The utility model discloses a quick locking and unlocking mechanism for a rocket recovery support mechanism.
[0036] The valve body 101 includes an adjusting mechanism 100 and a locking assembly 200. The locking assembly 200 is arranged in the middle of the adjusting mechanism 100. The adjusting mechanism 100 includes a valve body 101. Guide plates 102 are arranged on both sides of the valve body 101. A mounting plate 103 is connected to the top of the valve body 101.
[0037] The locking assembly 200 includes a locking hook 201 , and a roller 202 is disposed at one end of the locking hook 201 .
[0038] A lock hook return spring 104 is provided at one end of the valve body 101, and a lock key 105 is provided at the bottom of the end of the valve body 101 close to the lock hook return spring 104. The valve body 101 in this scheme is equipped with a lock hook return spring 104 and a lock key 105, which constitute the key part of the quick locking and unlocking mechanism, ensuring the quick reset of the lock hook 201 and the reliability of the locked state, and realizing the automation, efficiency and safety of the rocket recovery support mechanism in launching and recovery operations.
[0039] Example 2, refer to Figure 3-5 In this embodiment, in order to solve the problem of insufficient structural stability and sealing performance of the existing rocket recovery device under the influence of thermal expansion and contraction, humidity, mold and other harsh environments caused by temperature changes and extreme low temperature conditions, based on the same concept as the above-mentioned embodiment 1, the rocket recovery support mechanism quick locking and unlocking mechanism also includes:
[0040] The lock key 105 matches the structure of the roller 202, and the lock key 105 and the roller 202 are snap-fitted. The snap-fitted structural design between the lock key 105 and the roller 202 ensures reliable fixation of the support mechanism in the locked state, avoiding structural instability caused by temperature changes or external impacts. At the same time, the lock hook 201 can be released quickly and effectively during the unlocking process, ensuring the smooth deployment of the support mechanism and the safe recovery of the rocket.
[0041] An air valve 106 is also provided on one side of the end of the valve body 101 away from the lock hook return spring 104. The air valve 106 in this scheme is a key control component in the rapid locking and unlocking mechanism. It realizes the unlocking operation by providing high-pressure gas. Its setting improves the automation level, response speed and safety of the rapid locking and unlocking mechanism, ensures the reliable deployment of the rocket recovery support mechanism at the critical stage of the mission, thereby ensuring the smooth landing and efficient recovery of the rocket.
[0042] A lock hook shaft 201a is connected between the lock hook 201 and the two groups of guide plates 102. The lock hook 201 in this solution moves between the two groups of guide plates 102 through the lock hook shaft 201a. The two groups of guide plates 102 provide a precise movement path for the lock hook 201 to prevent it from having position errors due to deviation from the track during movement. Through this structure, the lock hook 201 can move smoothly and without obstruction to the locked or unlocked position, ensuring the reliability and smoothness of the operation.
[0043] Example 3, refer to Figure 5 In this embodiment, in order to solve the problem of insufficient structural stability and sealing performance of the existing rocket recovery device under the influence of thermal expansion and contraction, humidity, mold and other harsh environments caused by temperature changes and extreme low temperature conditions, based on the same concept as the above-mentioned embodiment 1, the rocket recovery support mechanism quick locking and unlocking mechanism also includes:
[0044] A lock key shaft 105a is connected between the lock key 105 and one end of the valve body 101, and a contact 105b is also provided on the top of the lock key 105. The lock key shaft 105a in this scheme provides a rotation fulcrum and connection support for the lock key, so that the lock key can rotate stably, and the contact 105b serves as a trigger point and force surface during the unlocking process, ensuring that the thrust of the piston connecting rod can be effectively transmitted to the lock key to complete the unlocking operation.
[0045] A spherical bearing 103 a is connected between the mounting plate 103 and the top of the valve body 101 . The mounting plate 103 and the top of the valve body 101 are connected via the spherical bearing 103 a , so that there is a certain degree of flexibility between the two components.
[0046] The interior of the valve body 101 is connected to a piston rod 101a, and one end of the piston rod 101a is in contact with the contact 105b. A pressure return spring 101b is also sleeved on the outside of the piston rod 101a. Through the linear movement of the piston rod 101a, the power of the high-pressure gas is accurately transmitted to the contact 105b, triggering the rotation operation of the lock key 105 to complete the unlocking. The contact and cooperation between the piston rod 101a and the contact 105b ensures the precise transmission of force and improves the reliability and accuracy of unlocking. The pressure return spring 101b provides the necessary reverse elastic force during the movement of the piston rod 101a, so that the piston rod 101a can be quickly reset after each operation, thereby maintaining the continuity and stability of the quick locking and unlocking mechanism.
[0047] The above are all preferred embodiments of the present utility model, and are not intended to limit the protection scope of the present utility model. Therefore, any equivalent changes made based on the structure, shape, and principle of the present utility model should be included in the protection scope of the present utility model.
Claims
1. A quick locking and unlocking mechanism for a rocket recovery support mechanism, comprising an adjustment mechanism (100) and a locking assembly (200), wherein the locking assembly (200) is arranged in the middle of the adjustment mechanism (100), and is characterized in that: The regulating mechanism (100) comprises a valve body (101), guide plates (102) are arranged on both sides of the valve body (101), and a mounting plate (103) is connected to the top of the valve body (101); The locking assembly (200) comprises a locking hook (201), and a roller (202) is provided at one end of the locking hook (201).
2. A rapid locking and unlocking mechanism for a rocket recovery support mechanism according to claim 1, characterized in that: A lock hook return spring (104) is disposed at one end of the valve body (101), and a lock key (105) is disposed at the bottom of one end of the valve body (101) close to the lock hook return spring (104).
3. A rapid locking and unlocking mechanism for a rocket recovery support mechanism according to claim 2, characterized in that: The lock key (105) and the roller (202) are structurally matched, and the lock key (105) and the roller (202) are snap-fitted.
4. A rapid locking and unlocking mechanism for a rocket recovery support mechanism according to claim 3, characterized in that: An air valve (106) is also provided on one side of the end of the valve body (101) away from the lock hook return spring (104).
5. A rapid locking and unlocking mechanism for a rocket recovery support mechanism according to claim 4, characterized in that: A locking hook shaft (201a) is connected between the locking hook (201) and the two sets of guide plates (102).
6. A rapid locking and unlocking mechanism for a rocket recovery support mechanism according to claim 5, characterized in that: A lock key shaft (105a) is connected between the lock key (105) and one end of the valve body (101), and a contact (105b) is also provided on the top of the lock key (105).
7. A rapid locking and unlocking mechanism for a rocket recovery support mechanism according to claim 6, characterized in that: A spherical bearing (103a) is connected between the mounting plate (103) and the top of the valve body (101).
8. A rapid locking and unlocking mechanism for a rocket recovery support mechanism according to claim 7, characterized in that: The interior of the valve body (101) is connected to a piston rod (101a), one end of the piston rod (101a) is in contact with a contact (105b), and a pressure return spring (101b) is sleeved on the exterior of the piston rod (101a).