A near space aerial camera lock shaft assembly and camera lock

Abstract

The application discloses a near space aerial camera lock shaft assembly and a camera lock, relates to the technical field of near space equipment, and the near space aerial camera lock shaft assembly comprises a translation execution assembly, the translation execution assembly is provided with a bolt assembly, the bolt assembly reciprocates along the translation execution assembly; a driving assembly, the driving assembly comprises a brushless motor and a transmission assembly, the brushless motor realizes reciprocating movement of the bolt assembly through the transmission assembly, and the transmission assembly has a self-locking function; a shell assembly, the translation execution assembly and the driving assembly are installed in the interior of the shell assembly, the bolt assembly can extend from the shell assembly, and the exterior of the shell assembly is provided with a thermal control layer. The application can realize safe locking and unlocking of an aerial camera servo shaft system, and has high overall adaptability and high working stability.

Description

Technical Field

[0001] This application relates to the field of near-space equipment technology, and in particular to a near-space aerial camera locking axis assembly and camera lock. Background Technology

[0002] Compared to traditional aerial cameras, near-space aerial cameras typically operate at altitudes of 20km or higher, and their environments differ from traditional aviation environments.

[0003] 1. The temperature is even lower, down to about -85°C. Under such low temperature conditions, electronic devices (such as motors, encoders, etc.) will not be able to start working, and bearings will be cold-welded.

[0004] 2. Different parts of the camera components are continuously exposed to uneven solar radiation, causing uneven heating of the corresponding components, which in turn affects the working performance of the equipment.

[0005] 3. The air is thin and close to a vacuum. In addition to affecting heat transfer, the air is also prone to ionization. If a brushed motor is used, it will produce an "arcing" phenomenon, which poses a safety hazard to the equipment.

[0006] On the other hand, when a camera is not in use, its servo axis often needs to be rotated to a certain position and held in place for storage to protect the optical system.

[0007] Existing locking shaft assemblies can be broadly classified into two categories: non-powered locking shaft assemblies and powered locking shaft assemblies. Non-powered locking shaft assemblies are mostly elastic locking mechanisms with electromagnets or permanent magnets. This type of locking shaft assembly has low reliability in low-temperature environments, and the component structure may deform due to the thermal expansion and contraction of materials, resulting in problems such as "not being able to lock" or "not being able to open".

[0008] Powered locking shaft assemblies typically use brushed servo motors for direct drive. Brushed motors pose safety hazards in air-conditioning environments. Furthermore, direct drive often results in insufficient locking force, which can lead to "unopenable" problems when unbalanced torque is present. Summary of the Invention

[0009] In view of this, the purpose of this application is to provide a near-space aerial camera locking axis assembly and camera lock, which can realize the safe locking and unlocking of the aerial camera servo axis system, with strong overall adaptability and high working stability.

[0010] To achieve the above objectives, this application provides a near-space aerial camera locking assembly, comprising:

[0011] A translational actuation component, wherein a pin assembly is mounted on the translational actuation component, and the pin assembly reciprocates along the translational actuation component;

[0012] A drive assembly, comprising a brushless motor and a transmission assembly, wherein the output end of the brushless motor drives the reciprocating movement of the pin assembly via the transmission assembly, and the transmission assembly has a self-locking function.

[0013] The housing assembly has the translation actuator and the drive assembly installed inside it, the pin assembly extending out of it, and a thermal control layer on the outside of it.

[0014] Preferably, the housing assembly includes a base and a top cover, and the thermal control layer covers the outer surfaces of the housing and the top cover.

[0015] Preferably, the thermal control layer comprises, from the inside to the outside, a heating layer, a heat insulation layer, and a radiation shielding layer, attached to one side of the housing assembly.

[0016] Preferably, the brushless motor is connected to a reducer, one end of which is connected to the output shaft of the brushless motor, and the other end is connected to a first bevel gear. The brushless motor is fixed to the housing assembly by a motor mount, and the motor mount is provided with an adjustment pad.

[0017] Preferably, the transmission assembly includes a worm gear box assembly and a turbine gear box assembly.

[0018] Preferably, the worm gear box assembly includes a worm gear box body, a first worm, a second bevel gear, a first bearing, and a first pressure cap;

[0019] The first bearing is mounted on the first worm gear, and the first worm gear is rotatably mounted in the worm gear housing via the first bearing. The first pressure cap is used to press the first bearing in place. One end of the first worm gear extends out of the worm gear housing, and the second bevel gear is fixed to the end of the first worm gear that extends out of the worm gear housing.

[0020] Preferably, the adjusting pad has a reserved adjustment amount, which is used to make the rotation axis of the first bevel gear and the rotation axis of the second bevel gear coplanar.

[0021] Preferably, the turbine housing assembly includes a turbine housing, a rotating shaft, a first turbine, a second bearing, a second pressure cap, a rotary encoder, and a spur gear, wherein the spur gear is installed at the end of the rotating shaft, and the first turbine is installed in the middle of the rotating shaft;

[0022] The first turbine is installed in the middle of the rotating shaft, the rotating shaft is rotatably installed in the turbine housing through the second bearing and one end of the rotating shaft extends out of the turbine housing, the spur gear is installed at the end of the rotating shaft that extends out of the turbine housing, the second cover is used for pressing the second bearing, and the angle encoder is installed on the turbine housing and the rotating shaft.

[0023] Preferably, the translation actuation component further includes a guide rail base, a linear guide rail, and a rack;

[0024] The linear guide rail includes two spaced-apart rails, which are fixed to the housing assembly by the guide rail seat. The pin assembly is slidably mounted on the linear guide rail, and the rack is mounted on the pin assembly, meshing with the spur gear.

[0025] Preferably, the pin assembly includes a pin head and a pin sleeve, the pin sleeve being installed on the pin head, and the pin sleeve being a polytetrafluoroethylene (PTFE) component.

[0026] A near-space aerial camera lock includes a camera lock body, wherein any of the near-space aerial camera lock shaft assemblies is applied to the camera lock body.

[0027] Compared with the aforementioned background technology, the near-space aerial camera locking assembly provided in this application has the following advantages:

[0028] This invention is adapted to the complex environment of near space, characterized by low temperatures, vacuum, and uneven solar radiation. It avoids the safety hazards of potential arcing in near space by using a brushless motor, and uses a transmission component with a self-locking function to ensure the stable position of the pin assembly and output sufficient locking / unlocking torque. The housing assembly enables precise assembly and protection of each component, and the outer thermal control layer ensures the normal operation of internal components at ultra-low temperatures and avoids deformation due to uneven heating. At the same time, the translational actuator precisely constrains the movement trajectory of the pin assembly, realizing the safe locking and unlocking of the servo axis system of the aerial camera. The invention has strong overall adaptability and high operational stability. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0030] Figure 1 This is a front view of the near-space aerial camera locking assembly after the top cover is opened, according to an embodiment of this application.

[0031] Figure 2 This is a left cross-sectional view of the near-space aerial camera locking axis assembly according to an embodiment of this application.

[0032] Figure 3 This is a three-dimensional structural diagram of the near-space aerial camera locking assembly after the translation execution component and the pin assembly are assembled, according to an embodiment of this application.

[0033] Figure 4 This is a three-dimensional structural diagram illustrating the installation relationship between the translation actuator and the pin assembly in the near-space aerial camera locking assembly according to an embodiment of this application.

[0034] Figure 5 This is a schematic diagram of the drive component in the near-space aerial camera locking assembly according to an embodiment of this application.

[0035] Figure 6 This is a three-dimensional structural diagram of the worm gear box assembly and turbine box assembly in the near-space aerial camera locking shaft assembly according to an embodiment of this application.

[0036] Figure 7 This is a front cross-sectional view of the worm gear box assembly in the near-space aerial camera locking assembly according to an embodiment of this application.

[0037] Figure 8 This is a front cross-sectional view of the turbine box assembly in the near-space aerial camera locking assembly according to an embodiment of this application.

[0038] The components include: 1. Translation actuator; 2. Pin assembly; 3. Drive assembly; 4. Transmission assembly; 5. Housing assembly; 6. Thermal control layer; 11. Guide rail base; 12. Linear guide rail; 13. Rack; 21. Pin head; 22. Pin sleeve; 31. Brushless motor; 32. Reducer; 33. First bevel gear; 34. Motor base; 35. Adjusting pad; 41. Worm gearbox assembly; 411. Worm gearbox body; 412. First worm; 413. Second bevel gear; 414. First bearing; 415. First pressure cap; 42. Turbine gearbox assembly; 421. Turbine gearbox body; 422. Shaft; 423. First turbine; 424. Second bearing; 425. Second pressure cap; 426. Angle encoder; 427. Spur gear; 51. Base; 52. Top cover; 61. Heating layer; 62. Insulation layer; 63. Radiation protection layer. Detailed Implementation

[0039] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0040] To enable those skilled in the art to better understand the present application, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0041] It should be noted that the directional terms such as "upper end," "lower end," "left side," and "right side" used below are defined based on the accompanying drawings in the instruction manual.

[0042] Please refer to Figures 1 to 8 The near-space aerial camera locking assembly provided in this application mainly includes a translation execution assembly 1, a pin assembly 2, a drive assembly 3, and a housing assembly 5.

[0043] Translation actuator 1, with a pin assembly 2 installed on the translation actuator 1, the pin assembly 2 reciprocating along the translation actuator 1;

[0044] The drive component 3 includes a brushless motor 31 and a transmission component 4. The output end of the brushless motor 31 drives the reciprocating movement of the pin component 2 through the transmission component 4. The transmission component 4 has a self-locking function.

[0045] The housing assembly 5, the translation actuator 1 and the drive assembly 3 are installed inside the housing assembly 5, the pin assembly 2 can extend out from the housing assembly 5, and the housing assembly 5 is provided with a thermal control layer 6 on the outside.

[0046] Both the translation actuator 1 and the drive assembly 3 are installed inside the housing assembly 5, and the housing assembly 5 is covered with a thermal control layer 6. The translation actuator 1 is equipped with a pin assembly 2, which can move linearly back and forth along the translation actuator 1. The pin assembly 2 can extend from the preset opening of the housing assembly 5 to lock with the locking structure of the aerial camera servo axis, and can also retract into the housing assembly 5 to unlock.

[0047] The drive assembly 3 includes a brushless motor 31 and a transmission assembly 4 with a self-locking function. The brushless motor 31 provides power to the entire locking shaft assembly. The power is transmitted to the translation execution assembly 1 through the transmission assembly 4, which in turn drives the pin assembly 2 to complete the reciprocating movement. The self-locking function of the transmission assembly 4 can prevent the pin assembly 2 from being displaced due to random vibration after the locking shaft assembly is powered off, thus avoiding safety hazards to the aerial camera.

[0048] The housing assembly 5 serves as the mounting base for the overall structure. It is made of high-strength alloy material and has the ability to resist stress deformation in the air environment. It has reserved precise mounting positions for the translation actuator 1 and the drive assembly 3 inside to ensure the coaxiality and fitting accuracy of each component. The exterior has a pre-set protrusion opening that matches the pin assembly 2, while providing a stable mounting base for the thermal control layer 6.

[0049] The brushless motor 31 is a high-speed brushless motor, which is suitable for the near-vacuum air environment of the adjacent space. It avoids the "arcing" phenomenon caused by brushed motors in ionized air environment, eliminating the safety hazards of the equipment from the root. Its output end is precisely connected to the input end of the transmission component 4 to ensure the efficiency and stability of power transmission.

[0050] The transmission component 4 is a multi-stage reduction transmission structure, which not only reduces and amplifies the power of the brushless motor 31, enabling the pin assembly 2 to obtain sufficient locking and unlocking torque, effectively overcoming the frictional resistance of components and the unbalanced torque of the shaft system in the air environment, but also has the self-locking characteristics of a worm gear, meeting the locking and holding requirements of the locking shaft assembly.

[0051] The translation actuator 1 is a linear transmission structure that constrains the movement trajectory of the pin assembly 2, ensuring the straightness of the pin assembly 2 when it extends / retracts, ensuring the cooperation with the locking structure of the aviation camera servo axis, and avoiding locking failure or unlocking jamming caused by trajectory deviation.

[0052] The thermal control layer 6 completely covers the outer surface of the housing component 5, which can heat and keep the inside of the housing component 5 warm, while resisting uneven solar radiation in the nearby space, so that the internal temperature of the housing component 5 is stable above -40℃. This ensures that the brushless motor 31, transmission component 4, and other electronic and mechanical components can start and work normally in the ultra-low temperature environment, and avoids deformation of components due to uneven heating, which would affect the working performance of the locking shaft assembly.

[0053] This device is adaptable to the complex environment of near space, characterized by low temperatures, vacuum, and uneven solar radiation. It avoids the safety hazards of potential arcing in near space by using a brushless motor 31. The transmission component 4 with a self-locking function ensures the stable position of the pin component 2 and outputs sufficient locking / unlocking torque. The housing component 5 enables precise assembly and protection of each component. The outer thermal control layer 6 ensures the normal operation of internal components at ultra-low temperatures and prevents deformation due to uneven heating. At the same time, the translation execution component 1 precisely constrains the movement trajectory of the pin component 2, realizing the safe locking and unlocking of the flight camera servo axis system. The device has strong overall adaptability and high operational stability.

[0054] Based on any of the above embodiments, the housing assembly 5 includes a base 51 and a top cover 52, and a thermal control layer 6 covers the outer surfaces of the housing assembly 5 and the top cover 52.

[0055] The housing assembly 5 specifically includes a base 51 and a top cover 52 that cooperate with each other. The base 51 is the mounting base for each functional component of the locking shaft assembly. It has positioning mounting slots and connection holes for each component. The top cover 52 and the base 51 are detachably fixed together by fasteners. The two together form a closed mounting cavity, which encapsulates the translation execution component 1 and the drive component 3 in the cavity, thereby achieving dustproof and airborne environmental protection for the internal components.

[0056] The thermal control layer 6 is not segmented, but rather completely covers the entire outer surface of the base 51 and the top cover 52 without any blind spots. This ensures full-area protection for the housing assembly 5, keeping all components inside the cavity in a stable temperature working environment. It also prevents temperature differences caused by the absence of thermal control layer 6 in certain areas of the base 51 and top cover 52, which could lead to uneven heating and deformation of internal components. This further improves the reliability of the locking shaft assembly in near-space environments.

[0057] Based on any of the above embodiments, the thermal control layer 6, from the inside to the outside, includes a heating layer 61, a heat insulation layer 62, and a radiation shielding layer 63, attached to one side of the housing assembly 2.

[0058] The thermal control layer 6 adopts a three-layer composite structure design, consisting of a heating layer 61, an insulation layer 62, and a radiation protection layer 63 from the inside out. The three layers are tightly bonded together in sequence and are completely covered on the outer surfaces of the base 51 and the top cover 52 by adhesive bonding. The fixing method and functional division of each layer work together to achieve all-round thermal control protection.

[0059] The inner heating layer 61 is adhered to the outer surface of the base 51 and the top cover 52 with a special low-temperature resistant adhesive, and is tightly bonded to the housing assembly 5 to ensure efficient heat conduction. It can actively generate heat to provide heat to the inside of the housing assembly 5, maintaining the internal temperature above -40℃, and ensuring that each component can start and work normally in the ultra-low temperature environment. The middle insulation layer 62 is tightly adhered to the outside of the heating layer 61 with adhesive, which not only achieves a firm connection with the heating layer 61, but also reduces the heat loss of the heating layer 61 to the outside, while blocking the cold air from the external low temperature environment, improving the insulation efficiency of the thermal control layer 6, and reducing the energy consumption of the heating layer 61. The outer radiation protection layer 63 is fixed to the outside of the insulation layer 62 with adhesive by wrapping and pasting, without any dead corners. It can effectively resist the uneven solar radiation in the nearby space, prevent the housing assembly 5 from deforming due to uneven heating caused by local radiation, and prevent radiant heat from adversely affecting the working performance of internal components.

[0060] The three-layer structure is firmly fixed layer by layer with adhesive, forming an integrated structure with the shell component 5. Combined with the functional design of each layer, the thermal control layer 6 has multiple functions such as active heating, efficient heat preservation, and protection against solar radiation, further ensuring the working stability of the locking shaft assembly in the complex environment of the near space.

[0061] Based on any of the above embodiments, the brushless motor 31 is connected to a reducer 32. One end of the reducer 32 is connected to the output shaft of the brushless motor 31, and the other end is connected to a first bevel gear 33. The brushless motor 31 is fixed to the housing assembly 5 by a motor base 34, and the motor base 34 is provided with an adjustment pad 35.

[0062] Optionally, the reducer 32 is a planetary reducer 32.

[0063] The output end of the brushless motor 31 is connected to the reducer 32. The power input end of the reducer 32 is coaxially fixed to the output shaft of the brushless motor 31, and the power output end is fixedly connected to the first bevel gear 33 to realize the first-stage reduction and amplification of power and the reversal of direction. The brushless motor 31 is fixedly installed to the base 51 in the housing assembly 5 through the motor mount 34. An adjustment pad 35 is provided between the motor mount 34 and the base 51. The adjustment pad 35 is a metal pad, and its thickness can be flexibly adjusted according to the actual assembly requirements.

[0064] With the reducer 32, the power output by the brushless motor 31 is first amplified by a first-stage reduction before being transmitted to the subsequent transmission structure. This provides a larger torque reserve for the locking and unlocking actions of the pin assembly 2, effectively overcoming the frictional resistance of components and the unbalanced torque of the shaft system in the near-space environment. The adjustment pad 35 at the motor mount 34 allows for precise fine-tuning of the installation height and horizontal position of the brushless motor 31 and the first bevel gear 33, ensuring the meshing accuracy of the first bevel gear 33 with the gears in the subsequent transmission assembly 4. This avoids problems such as excessive meshing clearance, transmission jamming, or power loss caused by assembly deviations, thereby improving the stability and efficiency of power transmission in the drive assembly 3.

[0065] Based on any of the above embodiments, the transmission assembly 4 includes a worm gear box assembly 41 and a turbine gear box assembly 42.

[0066] The transmission assembly 4 is specifically composed of a worm gear box assembly 41 and a turbine gear box assembly 42 that mesh with each other. Together, they form a worm gear transmission structure, serving as the secondary reduction transmission mechanism following the drive assembly 3. It receives the power transmitted via the reducer 32 and the first bevel gear 33, further reducing and amplifying the power to increase the torque transmitted to the translational actuator 1, thus providing sufficient locking and unlocking power to the pin assembly 2. Simultaneously, the worm gear transmission structure formed by the worm gear box assembly 41 and the turbine gear box assembly 42 inherently possesses self-locking characteristics. This ensures that even after the locking shaft assembly is de-energized, the pin assembly 2 will not shift due to random vibrations in the surrounding space, always maintaining the preset locked or unlocked position, eliminating any safety hazards to the aerial camera caused by accidental movement of the pin assembly 2.

[0067] Based on any of the above embodiments, the worm gear box assembly 41 includes a worm gear box body 411, a first worm 412, a second bevel gear 413, a first bearing 414, and a first pressure cover 415;

[0068] The first bearing 414 is fitted onto the first worm gear 412. The first worm gear 412 is rotatably mounted inside the worm gear housing 411 via the first bearing 414. The first pressure cover 415 is used to press the first bearing 414 into place. One end of the first worm gear 412 extends out of the worm gear housing 411. The second bevel gear 413 is fixed to the end of the first worm gear 412 that extends out of the worm gear housing 411.

[0069] There are two first bearings 414, which are respectively fitted at the two ends of the shaft section of the first worm 412. The first worm 412 is rotatably installed in the preset mounting hole of the worm housing 411 through the first bearings 414 at both ends, so as to realize the flexible rotational cooperation between the first worm 412 and the worm housing 411 and reduce the rotational friction resistance.

[0070] The first pressure cap 415 is a single unit, which is fixed to the outer end face of the worm gear housing 411 corresponding to the first bearing 414 by fasteners, forming a pressing installation on the first bearing 414, which can axially limit the first bearing 414 and prevent it from moving during the rotation of the first worm gear 412.

[0071] One end of the first worm 412 extends axially out of the outside of the worm gear housing 411. The second bevel gear 413 is fixed to the shaft head of the extended end by a snap ring and a pin, so that the second bevel gear 413 and the first worm 412 form an integrated structure that rotates synchronously. The second bevel gear 413 meshes with the first bevel gear 33, so as to realize the precise transmission of power from the drive assembly 3 to the worm gear housing assembly 41, and ensure the coaxiality and stability of the power transmission.

[0072] Based on any of the above embodiments, the adjusting shim 35 is reserved with a trimming allowance, which is used to make the rotation axis 422 line of the first bevel gear 33 and the rotation axis 422 line of the second bevel gear 413 coplanar.

[0073] The adjusting shim 35 is a customized metal shim, with a thickness adjustment allowance reserved during the processing stage to adapt to assembly adjustments. This adjustment allowance can be precisely ground and adjusted according to the actual assembly conditions. During the assembly of the locking shaft assembly, the spatial position of the rotation shaft 422 line of the second bevel gear 413 is measured, and the actual thickness of the adjusting shim 35 is adjusted accordingly. This allows for fine-tuning of the overall installation height and horizontal position of the brushless motor 31, motor base 34, and first bevel gear 33, ultimately ensuring that the rotation shaft 422 line of the first bevel gear 33 and the rotation shaft 422 line of the second bevel gear 413 achieve coplanar fit.

[0074] This design effectively eliminates the problem of misaligned axes of the two bevel gears caused by cumulative machining and assembly errors, avoids uneven loading, jamming, or uneven meshing clearance during gear meshing, significantly improves the meshing accuracy and transmission smoothness of the bevel gear pair, reduces gear meshing wear, and ensures the efficiency of power transmission from the drive assembly 3 to the worm gear box assembly 41.

[0075] Based on any of the above embodiments, the turbine housing assembly 42 includes a turbine housing 421, a rotating shaft 422, a first turbine 423, a second bearing 424, a second pressure cap 425, a rotational encoder 426, and a spur gear 427. The spur gear 427 is installed at the end of the rotating shaft 422, and the first turbine 423 is installed in the middle of the rotating shaft 422.

[0076] The first turbine 423 is installed in the middle of the rotating shaft 422. The rotating shaft 422 is rotatably installed in the turbine housing 421 through the second bearing 424, and one end of the rotating shaft 422 extends out of the turbine housing 421. The spur gear 427 is installed at the end of the rotating shaft 422 that extends out of the turbine housing 421. The second cover 425 is used for pressing the second bearing 424. The angle encoder 426 is installed in the turbine housing 421.

[0077] There are two second bearings 424, which are respectively fitted at both ends of the shaft 422. The shaft 422 is rotatably installed in the pre-set mounting holes of the turbine housing 421 through the second bearings 424 at both ends, so as to realize the flexible rotational cooperation between the shaft 422 and the turbine housing 421, reduce the rotational friction resistance, and adapt to the rotational requirements in the low temperature environment of near space. There is one second pressure cap 425, which is fixed to the outer end face of the turbine housing 421 corresponding to the second bearing 424 by fasteners, forming a pressing installation of the second bearing 424, axially limiting the second bearing 424, and preventing it from axially moving with the rotation of the shaft 422.

[0078] The first turbine 423 is fixedly installed in the middle section of the rotating shaft 422, and the first turbine 423 meshes with the first worm 412 in the worm gear box assembly 41 to realize the power transmission of the turbine worm. One end of the rotating shaft 422 extends axially out of the outside of the turbine box 421, and the spur gear 427 is fixedly installed at the shaft head of the extended end, forming an integrated structure that rotates synchronously with the rotating shaft 422, which is used for subsequent power docking with the translation execution assembly 1. The angle encoder 426 is fixedly installed on the preset mounting position of the turbine box 421 through a special encoder seat, and cooperates with the transmission end of the rotating shaft 422. It can collect the rotation angle and speed data of the rotating shaft 422 in real time, realize the precise position detection and control of the transmission process of the locking shaft assembly, and ensure the displacement accuracy of the extension and retraction of the pin assembly 2.

[0079] Through the above structure, the turbine gearbox assembly 42 realizes the power reception and secondary reduction amplification from the worm gearbox assembly 41, and at the same time works with the angle encoder 426 to complete the precise measurement and control of the transmission process, making the locking and unlocking actions of the pin assembly 2 more precise and controllable.

[0080] Based on any of the above embodiments, the translation execution component 1 also includes a guide rail seat 11, a linear guide rail 12, and a rack 13;

[0081] The linear guide 12 includes two spaced-apart lines. The linear guide 12 is fixed to the housing assembly 5 by the guide seat 11. The pin assembly 2 is slidably mounted on the linear guide 12. The rack 13 is mounted on the pin assembly 2 and meshes with the spur gear 427.

[0082] Two linear guide rails 12 are arranged in parallel and spaced apart, and both are fixedly installed on the guide rail base 11 by fasteners. The guide rail base 11 is stably connected to the base 51 of the housing assembly 5, providing a reliable installation foundation for the linear guide rails 12. The pin assembly 2 is connected to the sliding end of the two linear guide rails 12 to achieve sliding engagement with the linear guide rails 12, so that the pin assembly 2 can only move reciprocally in a linear direction along the axis of the two linear guide rails 12, constraining the movement trajectory of the pin assembly 2 and avoiding its deviation or jamming problems.

[0083] The rack 13 is fixedly installed on the side of the pin assembly 2 by fasteners, and the tooth direction of the rack 13 is consistent with the axial direction of the linear guide rail 12. The rack 13 meshes with the spur gear 427 at the end of the rotating shaft 422 in the turbine housing assembly 42 to form a gear rack 13 transmission structure. This structure can accurately convert the rotational motion of the spur gear 427 into the linear motion of the pin assembly 2 along the linear guide rail 12, thereby achieving efficient power transmission from the turbine housing assembly 42 to the translational actuator 1 and ensuring the smoothness and accuracy of the extension and retraction of the pin assembly 2.

[0084] Based on any of the above embodiments, the pin assembly 2 includes a pin head 21 and a pin sleeve 22, the pin sleeve 22 is installed on the pin head 21, and the pin sleeve 22 is a polytetrafluoroethylene part.

[0085] The pin sleeve 22 is a sleeve structure made of polytetrafluoroethylene (PTFE), which is tightly fitted onto the outer wall of the pin head 21, forming an integral mating structure with the pin head 21. PTFE material has an extremely low coefficient of friction, making it suitable for the complex environment of near-space ultra-low temperature and vacuum. It will not cause material hardening or a sudden increase in the coefficient of friction due to low temperature, effectively reducing the frictional resistance of the pin assembly 2 when it reciprocates on the linear guide rail 12.

[0086] Furthermore, during actual assembly, ultra-low temperature aviation grease can be applied to the outer surface of the pin sleeve 22 to further reduce the coefficient of friction, significantly reduce the driving torque required for the locking shaft assembly to complete the locking or unlocking action, avoid problems such as action jamming and insufficient driving torque caused by excessive frictional resistance, improve the smoothness and flexibility of the pin assembly 2 movement, and further ensure the reliability and stability of the locking shaft assembly in the near space environment for locking and unlocking actions.

[0087] A near-space aerial camera lock includes a camera lock body, and a near-space aerial camera lock shaft assembly is applied to the camera lock body.

[0088] This aircraft camera lock is suitable for near-space working altitudes of 20km and above, and can achieve precise and reliable locking and storage of the aircraft camera servo axis system. The core includes the camera lock body, and the near-space aircraft camera lock axis assembly is integrated into the camera lock body, serving as the core actuator for the camera lock to perform locking and unlocking actions.

[0089] The camera lock body is a matching locking structure for near-space aerial cameras and is compatible with the servo axis system of the aerial cameras. It has a pre-set locking slot that matches the locking pin assembly 2 of the locking axis assembly, and also has a reserved integrated mounting position for the locking axis assembly. The locking axis assembly and the camera lock body can be firmly connected by fasteners to ensure the coaxiality and fitting accuracy of the two assembly. This allows the pin assembly 2 of the locking axis assembly to be accurately aligned with the locking slot of the camera lock body, achieving efficient cooperation with the servo axis system of the aerial cameras.

[0090] The specific usage process of this device is as follows:

[0091] After the locking assembly enters the near-space working environment with the aerial camera, the thermal control layer 6 is the first to enter the working state: the inner heating layer 61 actively generates heat, and achieves efficient heat conduction through the tight adhesion of the adhesive to the shell assembly 5, keeping the internal temperature of the shell stable above -40℃; the middle insulation layer 62 blocks the entry of external ultra-low temperature cold energy of -85℃, reducing the heat loss of the heating layer 61; the outer radiation protection layer 63 resists uneven solar radiation and avoids uneven heating and deformation of the shell and internal components.

[0092] When the aerial camera is not in operation, and the servo axis needs to be rotated to a preset position and locked, the camera control system issues a locking command, and the locking axis assembly initiates the power transmission and execution process:

[0093] The brushless high-speed motor starts in the forward direction. After the power is reduced and amplified by the planetary reducer 32, it is transmitted to the first bevel gear 33, realizing the reduction of the power speed, the increase of the torque, and the reversal of the direction. The first bevel gear 33 and the second bevel gear 413 mesh precisely, and the power is transmitted to the first worm 412 of the worm gear box assembly 41. The first worm 412 meshes with the first worm gear 423 of the worm gear box assembly 42, completing the second stage of reduction and amplification, further increasing the output torque to meet the locking power requirements in the air-tight environment. The rotating shaft 422 of the worm gear box assembly 42 rotates synchronously with the first worm gear 423. The spur gear 427 at the end of the rotating shaft 422 engages with the translation actuator. The rack 13 of component 1 engages, precisely converting the rotational motion into the linear motion of the rack 13; the rack 13 drives the pin assembly 2 to extend along two parallel linear guide rails 12, the pin assembly 2 extends from the preset opening of the housing component 5, precisely inserts into the locking slot of the aircraft camera lock body, and engages with the locking structure of the aircraft camera servo axis system, completing the locking action of the servo axis system; throughout the transmission process, the angle encoder 426 collects the rotation angle of the rotating shaft 422 in real time and feeds the data back to the control system. When the pin assembly 2 reaches the preset locking position, the control system issues a command, the brushless high-speed motor stops working, and the locking action is completed.

[0094] After the brushless high-speed motor stops, the locking shaft assembly relies on the self-locking characteristics of the worm gear transmission structure to maintain the stable locking position of the pin assembly 2: even in the random vibration environment of the near space, the worm cannot drive the worm to rotate in the opposite direction, and the subsequent spur gear 427, rack 13 and pin assembly 2 will not be displaced, and will always maintain the engagement state with the aerial camera servo shaft system, eliminating the risk of loosening.

[0095] During this stage, the thermal control layer 6 continues to work to maintain the normal operating temperature of the internal components. The angle encoder 426 remains in standby detection mode, providing real-time feedback on the position data of the pin assembly 2. If abnormal displacement occurs, it can promptly issue an early warning to the control system.

[0096] When the aerial camera needs to operate and the servo axis needs to be released from its locked state, the camera control system issues an unlocking command, and the locking assembly unlocks by reversing the process:

[0097] The brushless high-speed motor starts in reverse, and the power is transmitted to the first worm gear 412 through the planetary reducer 32, the first bevel gear 33, and the second bevel gear 413. The worm gear drives the turbine to rotate in reverse, realizing the reverse transmission of power. The shaft 422 of the turbine housing assembly 42 rotates in reverse, and the spur gear 427 drives the rack 13 to retract along the linear guide rail 12. The rack 13 pulls the pin assembly 2 to retract synchronously. The pin assembly 2 disengages from the locking slot and servo shaft locking structure of the aircraft camera lock body and gradually retracts into the housing assembly 5. The angle encoder 426 collects the angle of the reverse rotation of the shaft 422 in real time. When the pin assembly 2 is fully retracted to the preset unlock position and the aircraft camera servo shaft can rotate freely, the control system issues a stop command, the brushless high-speed motor stops working, and the unlocking action is completed. After unlocking, the transmission components of the lock shaft assembly are reset, the pin assembly 2 remains inside the housing, the thermal control layer 6 continues to work, the angle encoder 426 returns to zero, and the entire assembly returns to the standby state, waiting for the next locking command.

[0098] It should be noted that in this specification, relational terms such as first and second are used only to distinguish one entity from several other entities, and do not necessarily require or imply any such actual relationship or order between these entities.

[0099] The above provides a detailed description of the near-space aerial camera locking assembly provided in this application. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are merely for the purpose of helping to understand the solution and core ideas of this application. It should be noted that those skilled in the art can make various improvements and modifications to this application without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of this application.

Claims

1. A locking assembly for a near-space aerial camera, characterized in that, include: Translation execution component (1), wherein a pin assembly (2) is mounted on the translation execution component (1), and the pin assembly (2) reciprocates along the translation execution component (1); The drive assembly (3) includes a brushless motor (31) and a transmission assembly (4). The output end of the brushless motor (31) drives the pin assembly (2) to reciprocate through the transmission assembly (4). The transmission assembly (4) has a self-locking function. The housing assembly (5) is equipped with the translation actuator (1) and the drive assembly (3) inside the housing assembly (5), the pin assembly (2) can extend out from the housing assembly (5), and the housing assembly (5) is provided with a thermal control layer (6) on the outside.

2. The near-space aerial camera locking assembly according to claim 1, characterized in that, The housing assembly (5) includes a base (51) and a top cover (52), and the thermal control layer (6) covers the outer surfaces of the housing and the top cover (52).

3. The near-space aerial camera locking assembly according to claim 2, characterized in that, The thermal control layer (6) consists of a heating layer (61), a heat insulation layer (62), and a radiation shielding layer (63) attached to one side of the housing assembly (2) from the inside to the outside.

4. The near-space aerial camera locking assembly according to claim 1, characterized in that, The brushless motor (31) is connected to a reducer (32). One end of the reducer (32) is connected to the output shaft of the brushless motor (31), and the other end is connected to a first bevel gear (33). The brushless motor (31) is fixed to the housing assembly (5) by a motor mount (34), and the motor mount (34) is provided with an adjustment pad (35).

5. The near-space aerial camera locking assembly according to claim 4, characterized in that, The transmission assembly (4) includes a worm gear box assembly (41) and a turbine box assembly (42).

6. The near-space aerial camera locking assembly according to claim 5, characterized in that, The worm gear box assembly (41) includes a worm gear box body (411), a first worm (412), a second bevel gear (413), a first bearing (414), and a first pressure cap (415). The first bearing (414) is fitted onto the first worm (412), and the first worm (412) is rotatably mounted in the worm housing (411) via the first bearing (414). The first pressure cap (415) is used to press the first bearing (414) into place. One end of the first worm (412) extends out of the worm housing (411), and the second bevel gear (413) is fixed to the end of the first worm (412) that extends out of the worm housing (411).

7. The near-space aerial camera locking assembly according to claim 6, characterized in that, The adjusting pad (35) is reserved for adjustment amount, which is used to make the rotation axis (422) line of the first bevel gear (33) and the rotation axis (422) line of the second bevel gear (413) coplanar.

8. The near-space aerial camera locking assembly according to claim 6, characterized in that, The turbine housing assembly (42) includes a turbine housing (421), a rotating shaft (422), a first turbine (423), a second bearing (424), a second pressure cap (425), a rotary encoder (426), and a spur gear (427). The spur gear (427) is installed at the end of the rotating shaft (422), and the first turbine (423) is installed in the middle of the rotating shaft (422). The first turbine (423) is installed in the middle of the rotating shaft (422). The rotating shaft (422) is rotatably installed in the turbine housing (421) via the second bearing (424) and one end of the rotating shaft (422) extends out of the turbine housing (421). The spur gear (427) is installed at the end of the rotating shaft (422) that extends out of the turbine housing (421). The second pressure cover (425) is used for pressing the second bearing (424). The angle encoder (426) is installed on the turbine housing (421) and the rotating shaft (422).

9. The near-space aerial camera locking assembly according to claim 8, characterized in that, The translation execution component (1) also includes a guide rail seat (11), a linear guide rail (12), and a rack (13); The linear guide (12) includes two spaced-apart rails. The linear guide (12) is fixed to the housing assembly (5) by the guide rail seat (11). The pin assembly (2) is slidably mounted on the linear guide (12). The rack (13) is mounted on the pin assembly (2) and meshes with the spur gear (427).

10. The near-space aerial camera locking assembly according to claim 9, characterized in that, The pin assembly (2) includes a pin head (21) and a pin sleeve (22), the pin sleeve (22) being mounted on the pin head (21), and the pin sleeve (22) being a polytetrafluoroethylene part.

11. A lock for a near-space aerial camera, characterized in that, The near-space aerial camera locking axis assembly according to any one of claims 1-10 is applied to the camera locking body, including the camera locking body.

Images