Guiding and positioning method and guiding and locking mechanism for mounting outboard large-mass equipment of on-orbit aircraft

Abstract

The invention discloses a guiding and positioning method and a guiding and locking mechanism for mounting outboard large-mass equipment of an on-orbit aircraft. The guiding and locking mechanism comprises a circular flange, a locking mechanism and a locking mechanism, wherein the circular flange is fixed on the outboard large-mass equipment; the guide columns are arranged on the outer side of the circular flange, a guide groove is formed between every two adjacent guide columns, and the guide columns form a plurality of guide grooves; the mounting plate is fixed on the target aircraft; the mounting plate is arranged on the base, the guide blocks are arranged on the mounting plate, and open holes are formed in the guide blocks and used for mounting a locking pin assembly; and the position distribution of the plurality of guide blocks is matched with the position distribution of the plurality of guide grooves. According to the invention, accurate installation and positioning of the outboard large-mass equipment and the target aircraft are realized through cooperation of the guide groove and the guide block; and furthermore, the round flange is locked through the locking pin assembly, so that the locking of the outboard large-mass equipment and the target aircraft after positioning is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of guiding and positioning for on-orbit installation of extravehicular equipment of a spacecraft, and in particular to a guiding and positioning method and a guiding and locking mechanism for installing large-mass equipment outside the spacecraft cabin on-orbit. Background Art

[0002] With the development of aerospace technology, many space exploration missions have put forward the requirements of on-orbit replacement or on-orbit expansion of spacecraft. Both on-orbit replacement and on-orbit expansion involve the problem of on-orbit assembly of equipment. For some large-mass equipment with a circular shell, the installation needs to meet the installation accuracy requirements in the radial and circumferential directions of the equipment. Due to the constraints of astronauts' operating ability, spacecraft equipment layout, equipment configuration and other conditions, astronauts often cannot meet the equipment installation accuracy requirements when assembling equipment on-orbit. Therefore, it is necessary to design a method and device for on-orbit installation guidance and positioning to facilitate astronauts to accurately position the equipment.

[0003] In the existing guiding and positioning methods, there is no mechanism or device that is simple in structure, light in weight, and can radially and circumferentially position equipment with a circular mounting flange outside the equipment. Relevant research and development is urgently needed in this field. Summary of the invention

[0004] The purpose of the present invention is to provide a guiding and positioning method and a guiding and locking mechanism for the installation of large-mass equipment outside the cabin of an on-orbit vehicle, so as to solve the problem in the prior art that astronauts cannot meet the installation accuracy requirements in the radial and circumferential directions of the equipment when installing some large-mass equipment with a circular outer shell.

[0005] In order to achieve the above object, the present invention first provides a guide locking mechanism for installing a large mass device outside the cabin of an on-orbit aircraft, the guide locking mechanism comprising:

[0006] A circular flange, wherein the circular flange is fixed to a large mass device outside the cabin;

[0007] A plurality of guide posts, wherein the guide posts are arranged on the outer side of the circular flange, a guide groove is formed between every two adjacent guide posts, and the plurality of guide posts form a plurality of guide grooves;

[0008] A mounting plate, the mounting plate being fixed to the target aircraft; and

[0009] A plurality of guide blocks are arranged on the mounting plate, wherein the guide blocks are provided with openings for installing a locking pin assembly;

[0010] Wherein, the position distribution of the plurality of guide blocks matches the position distribution of the plurality of guide grooves;

[0011] When in use, the precise installation and positioning of the large-mass equipment outside the cabin and the target aircraft are achieved through the cooperation between the guide groove and the guide block on the mounting plate; further, the circular flange is locked through the locking pin assembly to achieve the initial fixation of the large-mass equipment outside the cabin and the target aircraft after positioning.

[0012] Preferably, the guide block is a convex structure, and its upper surface includes a radial guide surface and two circumferential guide surfaces, the two end surfaces are limit straight surfaces, and the inner side surface is a limit arc surface;

[0013] When in use, the arc surface of the guide groove is tightly matched with the limit arc surface, and the straight surface of the guide groove is tightly matched with the limit straight surface.

[0014] Preferably, the locking pin assembly comprises a spring and a locking pin; and a locking pin groove is provided on the circular flange at a position corresponding to the guide groove.

[0015] Preferably, the opening passes through the limiting arc surface, and the locking pin is fixedly installed in the opening through the spring;

[0016] When there is no external force, the spring is in an extended state, the locking pin extends out of the limiting arc surface of the guide block, and is embedded in the locking pin groove; conversely, the spring is in a contracted state, and the locking pin is completely located in the opening of the guide block.

[0017] Preferably, the locking pin has a first end, and the upper surface of the first end of the locking pin is an inclined surface or a curved surface.

[0018] Preferably, the plurality of guide grooves are evenly distributed along the outer circumference of the circular flange.

[0019] Preferably, the number of the plurality of guide blocks is consistent with the number of the plurality of guide grooves.

[0020] Preferably, the number of the guide blocks and the number of the guide grooves are both 3.

[0021] On the other hand, the present invention also provides a method for installing a large-mass device outside the cabin of an on-orbit aircraft using the aforementioned guide locking mechanism, wherein the guide block is a convex structure, and its upper surface includes a radial guide surface and two circumferential guide surfaces, and the two end surfaces are limit straight surfaces, and the inner side surface is a limit arc surface, comprising the following steps:

[0022] S1, gradually bringing the circular flange closer to the mounting plate, and when the circular flange contacts the guide block on the mounting plate, using the radial guide surface on the guide block and the arc surface of the guide groove for matching and guiding, gradually and automatically adjusting the deviation of the circular flange in the radial direction until the arc surface of the guide groove of the circular flange fits with the limit arc surface;

[0023] S2, continue to gradually bring the circular flange closer to the mounting plate, use the two circumferential guide surfaces on the guide block and the two straight surfaces of the guide groove to cooperate and guide, and gradually and automatically adjust the deviation of the circular flange in the circumferential direction until the two straight surfaces of the guide groove of the circular flange fit into the limit straight surface;

[0024] S3, continue to gradually move the circular flange closer to the mounting plate. When the circular flange is in contact with the mounting plate, the locking pin is embedded in the locking pin groove, thereby achieving precise guiding, positioning and locking of the large-mass equipment outside the cabin.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] 1. The guiding and positioning method and guiding and locking mechanism for installing a large-mass device outside the cabin of an on-orbit vehicle provided by the present invention limit the freedom of the circular mounting flange of the device in the radial and circumferential directions through the cooperation of the guide block and the guide groove; at the same time, the radial guide surface and the circumferential guide surface can guide the moving direction of the circular mounting flange of the device on the guide block, so that the circular mounting flange of the device fits with the mounting plate; the circular flange is further locked by the locking pin to achieve precise guiding, positioning and locking of the installation of the large-mass device outside the cabin.

[0027] 2. The guiding and positioning method provided by the present invention is simple and easy to operate. The radial and circumferential positioning adjustments required for equipment installation are all performed outside the equipment. At the same time, the guiding and locking mechanism provided by the present invention is simple, light in weight, and has good application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 The figure is a schematic diagram of the composition and working principle of the guide locking mechanism according to an embodiment of the present invention.

[0029] Figure 2 It is a schematic diagram of a mounting plate in a guide locking mechanism according to an embodiment of the present invention.

[0030] Figure 3 It is a schematic diagram of a guide block and a locking pin assembly in a guide locking mechanism according to an embodiment of the present invention.

[0031] Figure 4 It is a schematic diagram of an extravehicular high-mass device including a circular flange in a guide locking mechanism according to an embodiment of the present invention.

[0032] Figure ID:

[0033] Circular flange 1; locking pin groove 11; through hole 12; guide column 2; guide groove 3; arc surface 31 of guide groove; straight surface 32 of guide groove; mounting plate 4; threaded hole 42; guide block 5; opening 51; radial guide surface 52; circumferential guide surface 53; limiting arc surface 54; limiting straight surface 55; locking pin 6; upper surface 61 of the first end of the locking pin; engraved mark 7; large mass equipment outside the cabin 100. DETAILED DESCRIPTION

[0034] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] In the description of the present invention, it should be noted that the term "several" means at least two, three, etc., unless otherwise clearly and specifically defined.

[0036] The following will be combined Figures 1 to 4 Preferred embodiments of the present invention are described in detail.

[0037] like Figures 1 to 4 As shown, in order to achieve the above-mentioned purpose, the present invention first provides a guide locking mechanism for installing a large-mass device outside the cabin of an on-orbit aircraft, and the guide locking mechanism includes:

[0038] A circular flange 1, wherein the circular flange 1 is fixed to a large-mass device 100 outside the cabin;

[0039] A plurality of guide posts 2, wherein the guide posts 2 are arranged on the outer side of the circular flange 1, a guide groove 3 is formed between every two adjacent guide posts 2, and the plurality of guide posts 2 form a plurality of guide grooves 3;

[0040] Mounting plate 4, which is fixed to the target aircraft and is a mounting bracket used by the aircraft to install extravehicular equipment; and,

[0041] A plurality of guide blocks 5 are arranged on the mounting plate 4, and each guide block 5 is provided with an opening 51 for installing a locking pin assembly;

[0042] Wherein, the position distribution of the plurality of guide blocks 5 matches the position distribution of the plurality of guide slots 3;

[0043] When in use, the cooperation between the guide groove 3 and the guide block 5 on the mounting plate 4 realizes the precise installation and positioning of the large-mass extravehicular device 100 and the target aircraft; further, the circular flange 1 is locked by the locking pin assembly to realize the initial fixation of the large-mass extravehicular device 100 and the target aircraft after positioning, so as to prevent the device 100 from detaching from the mounting plate 4 before the device 100 and the mounting plate 4 are connected by screws.

[0044] like Figure 3 As shown, in some embodiments, the guide block 5 is a convex structure, and its upper surface includes a radial guide surface 52 and two circumferential guide surfaces 53, the two end surfaces (i.e., the left and right end surfaces in the figure) are limit straight surfaces 55, and the inner side surface is a limit arc surface 54. Among them, the height of the radial guide surface 52 gradually decreases from the outer side surface of the guide block 5 (i.e., the opposite side of the limit arc surface 54) to the inner side surface (i.e., the limit arc surface 54), and the angle between the radial guide surface 52 and the horizontal plane is not less than 45°. This design is used to gradually and automatically adjust the deviation of the circular flange 1 in the radial direction when in use; the height of the circumferential guide surface 53 gradually decreases from the middle of the guide block to the left end surface (or right end surface), and this design is used to gradually and automatically adjust the deviation of the circular flange 1 in the circumferential direction when in use. In the use state, the arc surface 31 of the guide groove is tightly matched with the limit arc surface 54, and the straight surfaces 32 of the two guide grooves are tightly matched with the corresponding limit straight surfaces 55.

[0045] In some embodiments, the locking pin assembly includes a spring and a locking pin 6. Figure 3 As shown in Figure AB, the opening 51 passes through the limiting arc surface 54, and the second end of the locking pin 6 is fixedly connected to a spring and fixedly installed in the opening 51 through the spring (the spring is located in the opening 51, not clearly shown in the figure). The upper surface 61 of the first end of the locking pin (i.e., the direction facing away from the mounting plate 4) is an inclined surface or an arc surface (the inner arc of the arc surface faces the mounting plate direction), and gradually decreases from the outer surface of the guide block 5 to the inner surface. The angle between the upper surface 61 of the first end of the locking pin and the horizontal plane is not less than 45°, so that in subsequent use, when the circular flange 1 contacts the upper surface 61 of the first end of the locking pin, the locking pin 6 can be smoothly squeezed into the opening 51 of the guide block. At this time, the spring is in a contracted state; when there is no external force, the spring is in an extended state, and the first end of the locking pin 6 extends out of the limiting arc surface 54 of the guide block.

[0046] Furthermore, a locking pin groove 11 is provided on the circular flange at a position corresponding to the guide groove 3 (see Figure 4), the first end of the locking pin 6 is matched with the locking pin groove 11. When the first end of the locking pin 6 extends out of the limiting arc surface 54 of the guide block, the first end of the locking pin 6 is embedded in the locking pin groove 11, and the lower surface of the first end of the locking pin 6 is attached to and locked with the upper surface of the locking pin groove 11, thereby achieving the effect of preliminary connection and fixing.

[0047] The application principle of the locking pin assembly is as follows: when the large-mass equipment 100 outside the cabin gradually approaches the mounting plate 4, before the circular flange 1 contacts the locking pin 6, the spring is in an extended state, and the first end of the locking pin 6 extends out of the opening 51 of the guide block (such as Figure 3 A); when the circular flange 1 contacts the upper surface 61 of the first end of the locking pin, the locking pin 6 is squeezed into the opening 51 of the guide block, and the spring is in a contracted state at this time; further, when the circular flange 1 is in contact with the mounting plate 4, the external force applied to the locking pin 6 disappears, and the locking pin 6 extends out of the opening 51 of the guide block under the action of the spring compression rebound force, and is embedded in the locking pin groove 11, thereby achieving the purpose of locking the large mass equipment 100 outside the cabin.

[0048] In summary, the application principle of the guide locking mechanism provided by the present invention is as follows: when guiding and installing the extravehicular large-mass equipment 100, the circular flange 1 on the equipment 100 gradually approaches the guide block 5 on the mounting plate 4. When the circular flange 1 contacts the guide block 5, the radial guide surface 52 on the guide block 5 cooperates with the arc surface 31 of the guide groove on the circular flange 1 for guidance, and gradually and automatically adjusts the deviation of the circular flange 1 in the radial direction. When the circular flange 1 fits with the limiting arc surface 54, the circular flange 1 is aligned relative to the mounting plate 4 in the radial direction.

[0049] After the circular flange 1 is aligned relative to the mounting plate 4 in the radial direction, the large-mass equipment 100 outside the cabin is continued to be moved closer to the mounting plate 4. At this time, the two circumferential guide surfaces 53 on the guide block 5 will cooperate and guide with the two straight surfaces 32 of the guide groove on the circular flange 1, and gradually and automatically adjust the deviation of the circular flange 1 in the circumferential direction. When the two straight surfaces of the guide groove fit with the limiting straight surface 55, the circular flange 1 is aligned relative to the mounting plate 4 in the circumferential direction.

[0050] After the circular flange 1 is aligned in the circumferential direction relative to the mounting plate 4, the large-mass device 100 outside the cabin continues to be moved closer to the mounting plate 4. When the circular flange 1 is in contact with the mounting plate 4, the first end of the locking pin 6 is embedded in the locking pin groove 11, thereby achieving precise guiding, positioning and locking of the large-mass device 100 outside the cabin.

[0051] In some embodiments, the plurality of guide grooves 3 formed by the plurality of guide posts 2 are evenly distributed along the outer circumference of the circular flange 1 .

[0052] In some embodiments, the number of the plurality of guide blocks 5 is consistent with the number of the plurality of guide slots 3. Figure 1 To Attachment Figure 4 As shown, the number of the guide blocks 5 and the number of the guide grooves 3 are both three.

[0053] like Figure 2 and Figure 4 As shown, the circular flange described in the present invention is also evenly provided with a plurality of through holes, and the mounting plate is provided with a plurality of threaded holes, the number and position distribution of the threaded holes match the number and position distribution of the through holes, and screws are passed through the through holes 12 and the threaded holes 42 to fix the large mass equipment 100 outside the cabin on the mounting plate 4.

[0054] In some embodiments, corresponding engraved markings 7 are provided on the mounting plate and the circular flange 1 for performing preliminary installation and positioning of the extravehicular large-mass equipment 100 .

[0055] The present invention further provides a method for installing a large-mass device outside the cabin of an on-orbit aircraft using the guide locking mechanism of Example 1, which specifically includes the following steps:

[0056] When installing the extravehicular large-mass device 100, the astronauts first move the extravehicular large-mass device 100 to the top of the mounting plate 4, and preliminarily align the relative positions of the large-mass device 100 and the mounting plate 4 according to the engraved marks 7 on the mounting plate 4 and the extravehicular large-mass device 100, and then move the device 100 so that the circular flange 1 on the large-mass device 100 gradually approaches the mounting plate 4. When the circular flange 1 contacts the guide block 5 on the mounting plate 4, the radial guide surface 52 on the guide block 5 cooperates with the arc surface 31 of the guide groove on the circular flange 1 for radial guidance, and the circumferential guide surface 53 on the guide block 5 cooperates with the two straight surfaces 32 of the guide groove on the circular flange 1 for circumferential guidance, and gradually and automatically adjusts the deviation of the large-mass device 100 in the radial and circumferential directions. Finally, when the circular flange 1 is in contact with the mounting plate 4, the deviation is completely eliminated, and the locking pin 6 is embedded in the locking pin groove 11, thereby locking the large-mass device 100. At this time, the through hole 12 on the circular flange 1 is aligned with the threaded hole 42 on the mounting plate, and the astronaut further uses screws to penetrate the through hole 12 and the threaded hole 42, and finally securely installs the extravehicular large-mass equipment 100 on the target aircraft.

[0057] In summary, the guiding and positioning method provided by the present invention is simple and easy to operate, and the radial and circumferential positioning adjustments required for equipment installation are all performed outside the equipment. At the same time, the guiding and locking mechanism provided by the present invention is simple, light in weight, and has good application prospects.

[0058] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be appreciated that the above description should not be considered as a limitation of the present invention. After reading the above content, it will be apparent to those skilled in the art that various modifications and substitutions of the present invention will occur. Therefore, the protection scope of the present invention should be limited by the appended claims.

Claims

1. A guide locking mechanism for installing a large mass device outside the cabin of an on-orbit vehicle, characterized in that: The guide locking mechanism comprises: A circular flange, wherein the circular flange is fixed to a large mass device outside the cabin; A plurality of guide posts, wherein the guide posts are arranged on the outer side of the circular flange, a guide groove is formed between every two adjacent guide posts, and the plurality of guide posts form a plurality of guide grooves; A mounting plate, the mounting plate being fixed to the target aircraft; and A plurality of guide blocks are arranged on the mounting plate, wherein the guide blocks are provided with openings for installing a locking pin assembly; Among them, the position distribution of the several guide blocks matches the position distribution of the multiple guide grooves; when in use, the precise installation and positioning of the large-mass equipment outside the cabin and the target aircraft are achieved through the cooperation between the guide grooves and the guide blocks on the mounting plate; further, the circular flange is locked through the locking pin assembly to achieve the initial fixation of the large-mass equipment outside the cabin and the target aircraft after positioning.

2. The guide locking mechanism for installing a large mass device outside the cabin of an on-orbit vehicle according to claim 1, characterized in that: The guide block is a convex structure, and its upper surface includes a radial guide surface and two circumferential guide surfaces, the two end surfaces are limit straight surfaces, and the inner side surface is a limit arc surface; When in use, the arc surface of the guide groove is tightly matched with the limit arc surface, and the straight surface of the guide groove is tightly matched with the limit straight surface.

3. The guide locking mechanism for installing a large mass device outside the cabin of an on-orbit vehicle as claimed in claim 2, characterized in that: The locking pin assembly comprises a spring and a locking pin; a locking pin groove is provided at a position on the circular flange corresponding to the guide groove.

4. The guide locking mechanism for installing a large mass device outside the cabin of an on-orbit vehicle as claimed in claim 3, characterized in that: The opening passes through the limiting arc surface, and the locking pin is fixedly installed in the opening through the spring; When there is no external force, the spring is in an extended state, the locking pin extends out of the limiting arc surface of the guide block, and is embedded in the locking pin groove; conversely, the spring is in a contracted state, and the locking pin is completely located in the opening of the guide block.

5. The guide locking mechanism for installing a large mass device outside the cabin of an on-orbit vehicle as claimed in claim 3, characterized in that: The locking pin has a first end, and the upper surface of the first end of the locking pin is an inclined surface or an arc surface.

6. The guide locking mechanism for installing a large mass device outside the cabin of an on-orbit vehicle as claimed in claim 1, characterized in that: The plurality of guide grooves are evenly distributed along the outer circumference of the circular flange.

7. The guide locking mechanism for installing a large mass device outside the cabin of an on-orbit vehicle as claimed in claim 1, characterized in that: The number of the plurality of guide blocks is consistent with the number of the plurality of guide grooves.

8. The guide locking mechanism for installing a large mass device outside the cabin of an on-orbit vehicle as claimed in claim 7, characterized in that: The number of the guide blocks and the number of the guide grooves are both three.

9. A method for installing a large-mass device outside the cabin of an on-orbit vehicle using the guide locking mechanism according to any one of claims 1 to 8, characterized in that: The guide block is a convex structure, the upper surface of which includes a radial guide surface and two circumferential guide surfaces, the two end surfaces are limit straight surfaces, and the inner side surface is a limit arc surface, comprising the following steps: S1, gradually bringing the circular flange closer to the mounting plate, and when the circular flange contacts the guide block on the mounting plate, using the radial guide surface on the guide block and the arc surface of the guide groove for matching and guiding, gradually and automatically adjusting the deviation of the circular flange in the radial direction until the arc surface of the guide groove of the circular flange fits with the limit arc surface; S2, continue to gradually bring the circular flange closer to the mounting plate, use the two circumferential guide surfaces on the guide block and the two straight surfaces of the guide groove to cooperate and guide, and gradually and automatically adjust the deviation of the circular flange in the circumferential direction until the two straight surfaces of the guide groove of the circular flange fit into the limit straight surface; S3, continue to gradually move the circular flange closer to the mounting plate. When the circular flange is in contact with the mounting plate, the locking pin is embedded in the locking pin groove, thereby achieving precise guiding, positioning and locking of the large-mass equipment outside the cabin.

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