Integral tooth-meshing type spacecraft sealing cabin door

Abstract

The invention discloses an integral tooth-meshing type spacecraft sealing cabin door device which comprises a base flange module, a sealing cabin door module and a cabin door rotating handle. Wherein the cabin door rotating handle is connected with the sealed cabin door module through a rotating shaft. The base flange module comprises a base flange, a first radial sealing ring, a second radial sealing ring, a first axial sealing ring and a second axial sealing ring, the first radial sealing ring is placed in a sealing groove close to the interior of a cabin, and the second radial sealing ring is placed in a sealing groove close to a cabin door; the first axial sealing ring is placed in the axial sealing groove of the inner ring, and the second axial sealing ring is placed in the axial sealing groove of the outer ring. The cabin door can be used as a cabin door of a sealed spacecraft, axial and radial two-way sealing can be carried out, and the cabin door and the cabin door have double-way redundancy design. For an internal pressure bearing structure, the whole tooth-meshed type sealing structure can form sealing more reliably, and complicated in-cabin operation is avoided.

Description

Technical Field

[0001] The present invention relates to a spacecraft sealed cabin door, in particular to an integral gear-engaging type spacecraft sealed cabin door. Background Art

[0002] Sealed spacecraft operating in space typically require a hatch as a vital passage for the exchange of payloads and personnel inside and outside the cabin. This hatch also ensures the crucial sealing performance of the cabin. Conventional hatches utilize complex peripheral or radially distributed clamping mechanisms to achieve this seal. This complex design, required to ensure a reliable seal, results in complex hatch structures and cumbersome operation, increasing emergency response costs. A hatch structure that is relatively easy to operate, has a relatively simple structure, and provides a reliable seal is needed.

[0003] A Chinese patent (publication number: CN117306971A) discloses a multi-configuration, outward-opening manned spacecraft hatch system. This invention addresses the issue of inward-opening doors often occupying cabin space. However, the system utilizes a spatial linkage mechanism, with the entire door locking unit utilizing numerous hinges and linkages to seal and lock the door, resulting in a complex mechanism. For specific emergency situations, the cost of responding to the hatch is high, and this cost needs to be reduced by simplifying the door locking and sealing design.

[0004] A Chinese patent (Announcement No.: CN102381525A) discloses a toothed quick-opening device, which is suitable for sealing high-temperature containers on the ground. This patent is only applicable to container sealing under ground working conditions and has no adaptability to the high vacuum environment in space. Furthermore, compared with the end face axial seal in this patent, this patent adopts an axial radial double seal form, which greatly improves the sealing reliability. Furthermore, the structure in this patent needs to be driven by large external equipment such as cylinders. The use process is complicated and the structure is bulky. It cannot be operated by personnel and cannot meet the requirements of rapid response in emergency situations. Summary of the Invention

[0005] In response to the cumbersome operating procedures required for existing peripheral and radial layout complex hatches, the present invention proposes a hatch that achieves sealing through an integral toothed structure. Its sealing and locking mechanism simplifies a large number of complex connecting rod mechanisms, simplifies the process of opening and closing the hatch, and can achieve reliable sealing under load-bearing internal pressure environments, while reducing the response cost of emergency situations.

[0006] The present invention is achieved through the following technical solution: an integral toothed spacecraft sealed hatch, comprising: a base flange module, a sealed hatch module, and a hatch handle, wherein the hatch handle is connected to the sealed hatch module via a rotating shaft.

[0007] The base flange module and the sealed hatch of the sealed hatch module are engaged with each other through a structure. When the two are in place, the axial first sealing ring and the axial second sealing ring are compressed and put into working state. The radial first sealing ring and the radial second sealing ring enter the working state under the dual action of engagement and compression of the ejector pin, and the hatch achieves multi-pass reliable sealing.

[0008] The integral gear-engaging spacecraft sealed hatch is installed on the sealed hatch. When sealing, the hatch handle is rotated to rotate the entire sealed hatch. The locking torque mechanism and the limit locking mechanism are located inside the sealed hatch.

[0009] The described integrally toothed spacecraft sealed cabin door has a fixed part of a locking torque mechanism connected to the sealed cabin door by a fastening connection, and the locking torque mechanism is provided with a sensor and a reset mechanism. When the sealed cabin door and the base flange reach a specified engagement position by operating the cabin door handle, the limit locking mechanism enters the limit groove of the base flange under the action of a reset spring, thereby locking the relative position of the cabin door and the flange.

[0010] The base flange of the integral gear-engaging spacecraft sealed hatch has a mechanical engagement structure, and the mechanical engagement structure is provided with a hole for the pressing push rod to pass through.

[0011] The mechanical engagement structure of the integrally geared spacecraft sealed hatch described above utilizes a parametric curved surface design, which creates a local interference fit when meshing with the sealed hatch. This provides force to compress the radial and axial sealing rings, achieving a good seal.

[0012] The described integral toothed spacecraft sealed hatch has an engaging structure. When engaged with the base flange, the teeth of the sealed hatch are mechanically matched with the teeth of the base flange, and the card groove engages with the base flange for sealing and locking the hatch.

[0013] In the integral toothed spacecraft sealed hatch, the meshing structure of the base flange applies axial force to the whole through the guide groove to achieve sealing.

[0014] In the aforementioned integral gear-engaging spacecraft sealed hatch, the locking torque mechanism and the limit locking mechanism are located in the card slot;

[0015] In the integral toothed spacecraft sealed hatch, both the guide groove and the clamping groove of the sealed hatch are subjected to wear-resistant surface treatment to increase the service life of the hatch.

[0016] In the described integral toothed spacecraft sealed hatch, the base flange and the sealed hatch are made of dissimilar materials, and a solid lubricating coating and surface treatment are applied on the contact surfaces between the two to avoid the occurrence of vacuum cold welding.

[0017] The described integral toothed spacecraft sealed cabin door has a clamping push rod that passes through the mounting hole of the base flange and cooperates with the locking torque mechanism. By rotating the handle of the clamping push rod, the locking torque mechanism generates a radial clamping force on the base flange and the sealed cabin door. By adjusting the pull rod state of the clamping push rod, the cooperation relationship between the locking limit push rod and the limit locking device is adjusted to achieve manual unlocking of the cabin door.

[0018] The integrally toothed spacecraft sealed hatch also includes an auxiliary limiting mechanism, which is installed to fix the base flange and the sealed hatch to prevent the hatch from opening abnormally due to astronaut misoperation.

[0019] The beneficial effects of the present invention are:

[0020] 1) The present invention greatly reduces the complexity of the hatch door structure through the tooth meshing structure and sealing, ensuring the reliable response of the hatch door in emergency situations.

[0021] 2) The present invention adopts a redundant design of multiple axial and radial sealing rings to ensure that the hatch door can work reliably under a single fault and can still ensure safe sealing inside the cabin under a double fault.

[0022] 3) The present invention adopts solid lubrication and surface treatment to ensure the reliable use of the cabin door in a space environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a schematic diagram of the three-dimensional structure of an integral gear-engaging spacecraft sealed hatch of the present invention;

[0024] Figure 2 This is an exploded view of the three-dimensional structure of an integral gear-engaging spacecraft sealed hatch of the present invention;

[0025] Figure 3 This is a partial cross-sectional view of an integral gear-engaging spacecraft sealed hatch of the present invention;

[0026] Figure 4 This is a cross-sectional view of the base flange of an integral toothed spacecraft sealed hatch;

[0027] Figure 5 This is a schematic diagram of the sealing hatch parts of an integral gear-engaging spacecraft sealing hatch;

[0028] Figure 6 This is a schematic diagram of the parts under the locking and pressing assembly of an integral gear-engaging spacecraft sealed hatch;

[0029] Figure 7 This is a parts diagram of a compression push rod of an integrally geared spacecraft sealed hatch;

[0030] Figure 8This is a schematic diagram of the internal structure of a sealed hatch door with gear engagement of an integrally geared spacecraft sealed hatch;

[0031] Figure 9 The figure is a schematic diagram of the emergency operation of an integrally geared spacecraft sealed hatch of the present invention. DETAILED DESCRIPTION

[0032] The markings in the accompanying drawings of the present invention are: 1 base flange, 2 sealing hatch, 3 radial first sealing ring, 4 radial second sealing ring, 5 axial first sealing ring, 6 axial second sealing ring, 7 locking torque mechanism, 8 limit locking mechanism, 9 auxiliary limit mechanism, 10 return spring, 11 clamping push rod, 12 hatch handle.

[0033] like Figure 1 As shown, this embodiment includes: a base flange module, a sealed hatch module, and a hatch handle. The base flange 1 of the base flange module engages with the sealed hatch 2 of the sealed hatch module through a structural engagement. When the two are properly engaged, the first axial sealing ring 5 and the second axial sealing ring 6 are compressed and put into operation. The first radial sealing ring 3 and the second radial sealing ring 4 are also compressed and put into operation under the engagement between the base flange and the sealed hatch, achieving a multi-pass reliable seal for the hatch. Under internal pressure, the axial compression force is further enhanced, thereby ensuring sealing reliability.

[0034] like Figure 4 As shown, the base flange has a mechanical engagement structure 1a with a hole 1b through which the pressing rod 11 passes.

[0035] like Figure 3 、 Figure 5 、 Figure 8 As shown, the mechanical structure of the sealed hatch 2 includes a dedicated groove for mounting a locking torque mechanism 7, which is securely connected to the sealing groove 2c on the inner side of the hatch's teeth. A limit lock mechanism 8 is connected to the limit lock mechanism via a return spring 10. When the hatch reaches the designated position, the limit lock mechanism automatically enters the limit groove of the base flange 1, locking the hatch in place.

[0036] like Figure 5 As shown, the sealed hatch 2 includes a meshing structure. When engaged with the base flange 1, the teeth of the sealed hatch 2 mechanically mate with those of the base flange. The meshing structure of the base flange applies an axial force to the entire structure through the guide groove 2b, sealing it. When the hatch reaches a specified position, a limit locking mechanism automatically engages the guide groove to lock the relative position of the two. Further radial force is applied to the entire structure by the action of the compression rod 11, or the position of the locking mechanism 8 is readjusted, thereby unlocking the hatch.

[0037] like Figure 3As shown, the fixed portion of the locking torque mechanism 7 is fastened to the sealed hatch 2. The locking torque mechanism includes a sensor and a reset mechanism. When the sealed hatch 2 and base flange 1 reach a specified engagement position by operating the hatch handle 12, the limit locking mechanism 8, under the action of the reset spring 10, enters the limit groove of the base flange 1, locking the relative position of the hatch and flange. Furthermore, the locking torque mechanism can be further tightened or the position of the hatch limit mechanism 8 adjusted by a compression rod 11.

[0038] like Figures 2-3 As shown in Figures 5 and 6, when the base flange 1 and the sealed hatch 2 are engaged, the meshing portion of the base flange 1 and the meshing teeth of the guide groove of the sealed hatch 2 are designed with a partially formed interference fit. As the sealed hatch 2 gradually reaches the designated position, the meshing teeth of the base flange 1 apply axial compressive force to the sealed hatch 2, ensuring a tight fit between the end faces of the sealed hatch 2 and the base flange 1. This design further ensures sealing reliability under internal pressure.

[0039] like Figures 3-5 As shown, the engaging structure 1a of the base flange and the engaging structure 2a of the sealed hatch are designed with dissimilar materials. In particular, the interior of the sealing guide groove 2b and the card groove 2c are solid lubricated and surface treated to avoid vacuum cold welding in a vacuum and increase the service life of the hatch.

[0040] like Figure 3 、 Figure 7 As shown, the compression rod 11 passes through the mounting hole 1b of the base flange and cooperates with the locking torque mechanism 7. By rotating the compression rod's handle 11b, the locking torque mechanism 7 generates a radial compressive force on the base flange 1 and the sealed hatch 2, thereby further ensuring the relative position of the sealed hatch 2 and the base flange 1, forming a margin design. Simultaneously, the position of the locking limit mechanism can be adjusted using the compression rod's pull rod 11c, achieving manual unlocking of the hatch.

[0041] like Figure 1 、 Figure 6 As shown, when the hatch is not used in orbit for a long time, the base flange 1 and the sealed hatch 2 can be fixed by the auxiliary limiting mechanism 9 to prevent the hatch from opening abnormally due to astronaut misoperation.

[0042] like Figure 9 As shown, when the hatch door needs to be opened and closed frequently in a short period of time or in emergency conditions, the clamping push rod 11 and the auxiliary locking device 9 can be omitted, and the hatch handle 12 can be used directly to open and close the sealed hatch door 2. The basic hatch function is achieved through the mechanical cooperation between the base flange and the sealed hatch door, thereby further simplifying the door opening and closing process in emergency conditions.

[0043] Compared with existing hatch mechanisms, this device has a novel structure and a reasonable design, which greatly simplifies the number and complexity of hatch mechanisms, further improves reliability and simplifies the operating process. The integrated toothed sealing hatch and the base flange are designed to cooperate to achieve the basic function of hatch sealing. The connection between the clamping rod and the locking torque mechanism can further improve the sealing performance of the hatch. The working status of the hatch can be understood in real time through the sensor of the locking torque mechanism. The process of closing the overall hatch is greatly simplified compared to peripheral or distributed hatches, avoiding the need for redundant and complex mechanical components to achieve a single clamping action. The reliability of the hatch is further improved and the probability of failure is reduced. The overall process and operation time of opening and closing the hatch are greatly reduced, further reducing the response cost in emergency situations.

[0044] The above-mentioned specific implementation can be partially adjusted in different ways by those skilled in the art without departing from the principles and purpose of the present invention. The scope of protection of the present invention shall be based on the claims and shall not be limited by the above-mentioned specific implementation. All implementation schemes within its scope shall be subject to the constraints of the present invention.

Claims

1. An integral toothed spacecraft sealed hatch, characterized in that: include: Base flange module, sealed hatch module, hatch handle; The base flange (1) of the base flange module and the sealing hatch (2) of the sealing hatch module are engaged through a structure. When the two are in place, the axial first sealing ring (5) and the axial second sealing ring (6) are pressed into a working state, and the radial first sealing ring (3) and the radial second sealing ring (4) enter a working state under the dual effects of engagement and pressing the ejector pin, and the hatch achieves multi-pass reliable sealing; The hatch handle (12) is mounted on the sealed hatch (2), and the entire sealed hatch (2) is rotated by rotating the hatch handle during sealing; the locking torque mechanism (7) and the limit locking mechanism (8) are located inside the sealed hatch (2); The fixed part of the locking torque mechanism (7) is connected to the sealed cabin door (2) by a fastening connection. The locking torque mechanism is provided with a sensor and a reset mechanism. When the sealed cabin door (2) and the base flange (1) reach a specified engagement position by operating the cabin door handle (12), the limit locking mechanism (8) enters the limit groove of the base flange (1) under the action of the reset spring (10), thereby locking the relative position of the cabin door and the flange.

2. The integral toothed spacecraft sealed hatch according to claim 1, characterized in that: The base flange (1) has a mechanical engagement structure (1a) with a hole (1b) through which a pressing rod passes.

3. The integral toothed spacecraft sealed hatch according to claim 2, characterized in that: The mechanical engagement structure (1a) adopts a parametric curved surface design, so that when it engages with the sealed hatch (2), it presents a local interference fit state, thereby providing a force to compress the radial first sealing ring (3), the radial second sealing ring (4) and the axial first sealing ring (5), and the axial second sealing ring (6), thereby achieving a good seal.

4. The integral toothed spacecraft sealed hatch according to claim 2, characterized in that: The sealed hatch (2) has an engaging structure (2a). When engaged with the base flange (1), the teeth of the sealed hatch are mechanically matched with the teeth of the base flange, and the slot (2c) is engaged with the base flange (1) for sealing and locking the hatch.

5. The integral toothed spacecraft sealed hatch according to claim 4, characterized in that: The engaging structure (1a) of the base flange applies axial force to the whole through the guide groove (2b) to seal.

6. The integral toothed spacecraft sealed hatch according to claim 5, characterized in that: The locking torque mechanism (7) and the position limiting locking mechanism (8) are located in the clamping groove (2c).

7. The integral toothed spacecraft sealed hatch according to claim 6, characterized in that: The sealing hatch guide groove (2b) and the clamping groove (2c) are both subjected to wear-resistant surface treatment to increase the service life of the hatch.

8. The integral toothed spacecraft sealed hatch according to claim 6, characterized in that: The invention also includes a pressing push rod (11), which passes through the mounting hole (1b) of the base flange and cooperates with the locking torque mechanism (7). By rotating the rotary handle (11b) of the pressing push rod, the locking torque mechanism (7) generates a radial pressing force on the base flange (1) and the sealed cabin door (2). By adjusting the state of the pull rod (11c) of the pressing push rod, the cooperation relationship between the locking limit push rod (11a) and the limit locking device (8) is adjusted to realize manual unlocking of the cabin door.

9. The integral toothed spacecraft sealed hatch according to claim 6, characterized in that: The invention also includes an auxiliary limiting mechanism (9), which is installed to fix the base flange (1) and the sealed cabin door (2) to prevent the cabin door from opening abnormally due to astronauts' misoperation.

10. The integral toothed spacecraft sealed hatch according to claim 1, characterized in that: The base flange (1) and the sealing hatch (2) are made of different materials, and a solid lubricating coating and surface treatment are applied on the contact surfaces of the two to avoid the occurrence of vacuum cold welding.

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