CN112682418A - Space suit fixing mechanism - Google Patents

Abstract

The invention relates to a space suit fixing mechanism which comprises a base, a clamping component and a locking component, wherein a cavity is formed in the base, the top and one side of the base are open, a connecting hole communicated with the cavity is formed in one side perpendicular to the open side, the clamping component and the locking component are respectively located on the top of the base and the side where the connecting hole is located, the locking component comprises a locking pin, the locking component further comprises a first handle and a pin sleeve, the first handle is rotatably connected with the locking pin, one end of the pin sleeve is located in the connecting hole, the other end of the pin sleeve is fixed on the base, and a spring is sleeved on the locking pin and is located in the pin sleeve. The locking pin in the locking assembly in the fixing mechanism is more convenient in the locking and unlocking process.

Description

Space suit fixing mechanism

Technical Field

The invention relates to a fixing mechanism for a space suit.

Background

At present, the chest position of the space suit is mostly provided with a pivot for fixing. And the common fixing mechanism of the space suit is realized by fixing the pivot. The pivot is provided with an annular groove, so that the torsion spring can be fixed by matching with the olecranon hook. This fixing is very convenient, but is only suitable for the frequent use of space suits. When the space suit is not used for a long time, the pins are required to be held by the astronauts and inserted into the base and the olecranon hook to lock the pins. This approach requires the astronaut to align the pins with the pin holes in space, and is extremely inconvenient in complex space environments.

Disclosure of Invention

The invention aims to provide a fixing mechanism of a space suit, which can ensure that the space suit is more convenient to lock.

In order to achieve the purpose, the invention provides a space suit fixing mechanism which comprises a base, a clamping component and a locking component, wherein a cavity is formed in the base, the top and one side of the base are open, a connecting hole communicated with the cavity is formed in one side perpendicular to the open side, the clamping component and the locking component are respectively located on the top of the base and the side where the connecting hole is located, the locking component comprises a locking pin, the locking component further comprises a first handle and a pin sleeve, the first handle is rotatably connected with the locking pin, one end of the pin sleeve is located in the connecting hole, the other end of the pin sleeve is fixed on the base, and a spring is sleeved on the locking pin and located in the pin sleeve together.

According to one aspect of the invention, the pin bushing has a sleeve portion and a mounting portion;

the sleeve portion is located in the connecting hole, and a blocking protrusion is arranged inside the sleeve portion.

The installation part is fixedly connected to the base.

According to one aspect of the invention, the locking pin has a locking end and a connecting end;

the diameter of the locking end is larger than that of the connecting end, and the spring is sleeved on the connecting end;

the locking pin and the spring are located in the sleeve portion, the spring being located between the locking end and the blocking projection.

According to one aspect of the invention, the first handle has a grip portion and a connecting portion that are perpendicular to each other;

the holding part is a rectangular flat plate and is provided with an anti-skid hole penetrating along the thickness of the holding part;

the connecting part is a rectangular flat plate and is provided with openings which penetrate through three sides of the connecting part along the direction vertical to the thickness direction of the connecting part;

the connecting part is connected with the connecting end of the locking pin through a pin, and a baffle capable of preventing the pin from coming off is fixedly connected to one surface of the connecting part.

According to one aspect of the invention, the connecting part of the first handle is rounded at the lower end of the side edge close to the base, and the upper end of the side edge extends towards the base;

the holding part is connected to the side edge of the connecting part far away from the base, and the lower end of the side edge extends downwards.

According to one aspect of the invention, the base inner wall is stepped at the bottom and is higher away from the open side thereof.

According to one aspect of the invention, the clamping assembly comprises a second handle, a clamping piece and a supporting shaft;

one end of the second handle is fixedly connected with the top of the clamping piece, and the other end of the second handle is tilted upwards and has a width larger than the middle part of the second handle;

one end of the bottom of the clamping piece is provided with a hook which is bent downwards and backwards, and the side surface of the end is provided with a locking hole which can be matched with the locking pin;

the other end of the bottom of the clamping piece is provided with two supporting plates oppositely.

According to one aspect of the invention, the supporting plate is provided with a through shaft hole, and the supporting shaft is sleeved with a torsion spring.

According to one aspect of the invention, the supporting shaft passes through the cavity of the base and the through shaft hole of the supporting plate, and two torsion bars of the torsion spring respectively abut against the bottom of the inner wall of the base and the clamping piece.

According to one aspect of the invention, the base has a side surface with a central portion that is sloped inwardly.

According to one aspect of the invention, a locking assembly is provided on the base and the clamping assembly. The locking pin in the locking assembly is used for maintaining the locking state of the clamping assembly, and the pin sleeve provides a movable space for the locking pin. The first handle is rotatably connected with the locking pin, so that when the first handle is pulled upwards or downwards, the locking pin can be driven to enter or exit the locking hole of the clamping piece, and locking and unlocking are achieved. The locking pin is sleeved with a spring, and a blocking bulge which provides support for the spring to abut against is arranged in the pin sleeve. The locking pin and the spring are co-located in the pin sleeve such that during movement of the locking pin, the spring is allowed to expand or compress to perform the task of maintaining the locked and unlocked states of the locking assembly, respectively. The mode enables the astronaut to lock the pin without aligning the pin with the pin hole and only by pulling the handle.

According to one scheme of the invention, due to the existence of the pin bush, the structural design of the connecting hole on the base is simpler and only needs to be a through hole. Thereby reducing the difficulty of processing and design and improving the assembly precision. The first handle is divided into a holding part and a connecting part, two extension sections on the connecting part can be respectively used for blocking in the locking state and the unlocking state, and the rotation angle of the first handle is prevented from being too large, so that human errors are reduced. The lower end of one side of the connecting part in contact with the base is rounded, so that the rotation of the connecting part is smoother.

According to one scheme of the invention, one end of the second handle in the clamping component tilts upwards, so that the mode of unlocking the clamping component by a astronaut can be a pressing mode, and the operability of the mechanism is improved. The crotch on the joint spare is down and is buckled backward for its one side in the face of the outside is the inclined plane, thereby inserts the joint spare can be by jack-up voluntarily behind the base at the space suit pivot, makes the use of this mechanism more convenient.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

FIG. 1 schematically illustrates an isometric view of an aerospace garment securement mechanism in a locked condition, in accordance with an embodiment of the invention;

FIG. 2 schematically illustrates an exploded view of a space suit securing mechanism in accordance with an embodiment of the present invention;

FIG. 3 schematically illustrates a cross-sectional view of an aerospace garment securing mechanism in a locked condition, in axial view, in accordance with an embodiment of the invention;

FIG. 4 schematically illustrates a cross-sectional side view of a space suit securing mechanism in a locked condition in accordance with an embodiment of the present invention;

FIG. 5 schematically illustrates a perspective view from an axial perspective of an aerospace garment attachment mechanism in a locked condition, in accordance with an embodiment of the invention.

Detailed Description

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.

In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.

The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.

Referring to fig. 1, the space suit fixing mechanism of the invention comprises a base 1, a clamping assembly 2 and a locking assembly 3. Wherein, the whole cuboid that is of base 1's shape, joint subassembly 2 are located base 1's top, and locking Assembly 3 then is located base 1's right side.

Referring to fig. 2, the base 1 has a flat plate at the rear end thereof for fixing the base 1 in the spacecraft cabin. The base 1 has a cavity inside and is open at the top and front side. The open front side serves to allow the pivot of the space suit to be inserted into the base 1. Therefore, the bottom of the inner wall of the base 1 is cylindrical and is suitable for the appearance of the aerospace suit pivot; the upper open region is adapted to the contour of the base 1. In addition, the right side surface of the base 1 is provided with a connection hole 12 which communicates with the cavity (upper side).

As shown in fig. 2, the clip assembly 2 includes a second handle 21, a clip 22, and a support shaft 23. Wherein, the clamping piece 22 is composed of three parts. Specifically, the upper end of the clip member 22 is a rectangular block for connecting the second handle 21. The lower end of the fastening member 22 has a two-part structure, the front side of which is provided with a hook 221 bent downward and backward, and the two sides of the rear side of which are provided with two opposite supporting plates 222. The support plate 222 functions to support the clip 22 on the support shaft 23, and therefore is further provided with a through-shaft hole 222a for passing the support shaft 23 therethrough. The front end of the clamping piece 22 arranged as above is narrow, the rear end is wide, the clamping component 2 is integrally positioned at the top of the base 1, and the supporting plate 222 extends into the cylindrical space at the lower side of the cavity from the rear side of the top of the base 1 after being assembled. The upper shape of the cavity of the base 1 should therefore also be adapted to the design of the snap-in element 22. Of course, this would make the upper portion of the bed 1 uneven in thickness, affecting the counterweight and wasting material. Therefore, the side surface of the base 1 at the approximate middle position is an inward inclined surface. Specifically, as shown in the embodiment of fig. 3, the middle of the base 1 is a diamond-shaped section. Of course, according to this concept, the cross-sectional shape of this segment may also be rectangular diagonally to the overall cross-section of the base 1.

With reference to fig. 2, the second handle 21 is shaped as a strip plate, the front end of the second handle is fixedly connected to the upper end of the clamping member 22, the rear end of the second handle is tilted upwards, and the width of the second handle is slightly larger than the width of the middle part of the second handle, so that the second handle is convenient for the astronaut to press. The supporting shaft 23 is a stepped shaft as a whole, the diameter of the right end is larger than that of the middle part, and the left end is provided with a threaded hole. During installation, the supporting shaft 23 is required to pass radially through the lower cylindrical part of the cavity of the base 1 and to be screwed at the end. Corresponding holes are thus also provided in the side walls of the base 1 for the bearing shafts 23 to pass through and be supported on. In the invention, the supporting shaft 23 is also provided with the torsion spring 24, and the torsion spring 24 is only sleeved on the supporting shaft 23 without being connected with the supporting shaft 23. In the assembled state shown in fig. 2, the torsion spring 24 and the two support plates 222 are both fitted over the support shaft 23. After assembly, two torsion bars a (see fig. 4 and 5) of the torsion spring 24 are respectively attached to the bottom of the inner wall of the base 1 and the left side of the clip 22.

The fixing mechanism with the two components can basically complete the splicing work of the aerospace suit pivot, namely the temporary fixing of the aerospace suit. However, in the face of a complicated space environment, the locking work performed only by the elastic force of the torsion spring 24 is not firm. Therefore, the locking component 3 is arranged in the fixing mechanism of the invention, so as to realize firmer fixation when the space suit is not used for a long time. The locking assembly 3 comprises the most basic locking member, the locking pin 31. Of course, in order to avoid the prior art situation where the locking pin 31 is required to be aligned with the pin hole by the astronaut, the locking assembly 3 of the present invention further includes a first handle 32 and a pin sleeve 33. The assembly formed by the three components can be assembled with the base 1 and the clamping assembly 2 into a whole to form a highly integrated space suit fixing mechanism.

Specifically, referring to fig. 2 and 3, the locking pin 31 is a cylindrical rod member having a locking end 31a and a connecting end 31 b. The locking end 31a has a diameter greater than that of the connecting end 31b but a smaller length, wherein the connecting end 31b is sleeved with a spring 35. Of course, the connection mode of the spring 35 and the connection end 31b may be a fixed connection, and the fixed point may be the left end in the figure, or may also be directly sleeved thereon. The pin sleeve 33 functions to provide a moving space for the locking pin 31 and guide the movement thereof. The pin bush 33 has a bush portion 33a and a mounting portion 33 b. The sleeve portion 33a is integrally a cylinder for accommodating the lock pin 31; the mounting portion 33b is located at the right end of the sleeve portion 33a, and its specific shape is not particularly limited, but it is provided with a mounting hole so that it can be mounted to the base 1 by means of a screw or the like. After mounting, the sleeve portion 33a is entirely located in the connection hole 12, i.e., the outer diameter of the sleeve portion 33a corresponds to the bore diameter of the connection hole 12. The locking pin 31 and the pin sleeve 33 are mounted in such a manner that the locking pin 31 is inserted into the sleeve portion 33a together with the spring 35. Therefore, it is preferable to design so that the inner dimension of the sleeve portion 33a is the same as the locking end 31 a. In the present invention, the interior of the sleeve portion 33a is provided with a stop projection 34, the stop projection 34 acting to provide an abutting support for the spring 35, whereby the spring 35 is located between the connecting end 31b and the stop projection 34 after installation. In practice, the blocking projection 34 can also be understood as a section of the bore with a smaller diameter at the end of the sleeve portion 33 a. As described above, the coupling hole 12 of the base 1 corresponds to the pin sleeve 33. However, since the structure of the locking pin 31 is special, if the connecting hole 12 is directly used as a hole for moving the locking pin 31, the entire structure of the base 1 is complicated, the processing difficulty is large, and the precision is not easy to be ensured. Thereby, the lock pin 31 can move back and forth inside the sleeve portion 33 a. Since the locking pin 31 of the present invention is used to lock the latch 22 in the latch assembly 2, one end of the hook 221 is not tilted. Therefore, as shown in fig. 3, the side surface of the one end of the clip 22 where the hook 221 is provided with a lock hole 223 engageable with the lock pin 31, and specifically, the lock hole 223 may be set to be coaxial with the sleeve portion 33a in the clip state (i.e., the state shown in fig. 3).

Referring to fig. 2, the first handle 32 is formed of a two-part structure, a grip portion 32a and a connecting portion 32 b. The grip portion 32a is a rectangular flat plate, and a non-slip hole 32c is formed in the middle thereof. The anti-slip hole 32c is also rectangular and penetrates along the thickness of the grip portion 32 a. In fact, the anti-slip hole 32c has both an anti-slip function and a weight reduction function, and thus its specific size and shape may be set according to the overall size of the grip portion 32 a. The connecting portion 32b is formed by a single rectangular plate with a rectangular cutout 32d formed in the middle. The slit 32d penetrates the upper, lower, and left sides of the connecting portion 32b in a direction perpendicular to the thickness direction of the connecting portion 32 b. By this design, it is also understood that the connecting portion 32b is formed by connecting two rectangular flat plates spaced apart from each other via the right side edge. It will be appreciated that the gripping portion 32a and the connecting portion 32b are both generally rectangular in shape, and the first handle 32 of the present invention is designed to be positioned perpendicular to each other to facilitate pulling by the astronaut. In the present invention, the first handle 32 is rotatably connected to the locking pin 31, the connection point on the first handle 32 is located at the lower left end of the connecting portion 32b, and the connection point on the locking pin 31 is located at the right end of the connecting portion 31 b. The specific connection between the two is realized by a pin B, so that a pin hole is arranged at the corresponding position of the locking pin 31 and the first handle 32, and the pin B is inserted from one side shown in fig. 2 to realize the connection. In order to avoid the falling of the pin B, the invention is also provided with a baffle plate 36. As shown in fig. 2, the baffle 36 in this embodiment is a long strip plate with two circular ends, the right end of the baffle is fixed on the side surface of the connecting portion 32B, and the left end of the baffle can block the outside of the pin B, so as to prevent the pin B from falling out. When the astronaut pulls down the first handle 32, the connecting portion 32b of the first handle 32 rotates around the lower left end of the base 1, clinging to the sidewall of the base 1. At this time, since the connecting portion 32b is connected to the locking pin 31, the rotation of the first handle 32 drives the locking pin 31 to move backward and gradually exit from the locking hole 223 on the clamping member 22, when the holding portion 32a of the first handle 32 is completely horizontal, the bottom edge of the connecting portion 32b is attached to the base 1, and at this time, the locking end 31a of the locking pin 31 completely exits from the locking hole 223, so as to complete unlocking. Due to the provision of the slit 32d, the first handle 32 does not interfere with the locking pin 31 when rotated. When the astronaut presses the second handle 21 downwards, the clamping piece 22 rotates around the supporting shaft 23, so that the hook 221 tilts upwards to be separated from the annular groove on the astronaut suit pivot, and the unlocking is completed. In the process, the rotation of the clamping member 22 simultaneously enables the torsion spring 24 to be twisted and compressed, so that the torsion spring has elastic potential energy, and when the astronaut looses his hands, the torsion spring can automatically return. Also, since the hook 221 is bent backward, its side facing the spacesuit is inclined. Thus, when the space suit is fixed again, the pivot shaft is directly inserted into the cavity, the clamping piece 22 can be jacked up and tilted backwards, and after the pivot shaft is inserted in place, the torsion spring 24 can drive the clamping piece 22 to automatically return, so that the hook 221 is automatically clamped in the annular groove of the pivot shaft of the space suit, and the fixing is completed. Of course, when the latch 2 is automatically returned to its original position and represents the pivot being mounted in place, the second handle 21 should be pressed to withdraw the pivot and reinstall it. If the torsion spring 24 is designed to have a small size, the bottom of the inner wall of the base 1 is stepped in a left-right direction as shown in fig. 4 and 5 so that the torsion bar a of the torsion spring 24 can contact the bottom of the inner wall of the base 1.

When locked, the astronaut pulls up on the first handle 32 to return the grip portion 32a to the upright position. Before this, the spring 35 is in a compressed state, so that the accumulated elastic potential energy thereof during locking automatically drives the locking pin 31 to move towards the locking hole 223, so that the locking process is very labor-saving. After the locking is completed, the right side edge of the connecting portion 32b of the first handle 32 abuts the base 1. Since the process is manually operated, in order to avoid over-rotation, the present invention extends the left upper end of the connecting portion 32b to the right and the right lower end thereof to the lower side, and the two extending sections respectively serve as blocking functions of the locked state and the unlocked state. Of course, these two extensions should also be adapted to the provision of the slit 32d so as to avoid interference with the locking pin 31. Also, since the coupling portion 32b is rotated about the left lower end thereof throughout the process, it is preferable to round the end so that the rotation is smoother.

In summary, the overall working process of the space suit fixing mechanism of the invention is as follows: first, the first handle 32 is pulled to make the grip portion 32a horizontal. The chest pivot of the space suit is aligned with the lower end of the cavity on the base 1. The pivot is then inserted into the cavity and the hooks 221 of the snap-in members 22 are automatically lifted during the pushing-in process. After the garment is installed in place, the hook 221 falls down and automatically returns to the locked state. If the hook 221 is not dropped (i.e., is always raised), it means that the garment is not in place and needs to be reinstalled. After being pivoted into position, the first handle 32 is pulled upwardly to erect the grip 32a to complete the locking. When unlocked, the first handle 32 is pulled down to fully withdraw the locking pin 31 from the locking hole 223. The second handle 21 is pressed downward to tilt one end of the hook 221 of the engaging member 22 away from the pivot annular groove. And finally, pulling out the pivot. Of course, after the garment is removed, the first handle 32 should be pulled upward to return the entire fastening mechanism to the locked state, so as to prevent the components in the fastening assembly 2 from moving freely.

The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and it is apparent to those skilled in the art that various modifications and variations can be made in the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. A space suit fixing mechanism comprises a base (1), a clamping component (2) and a locking component (3), wherein the base (1) is internally provided with a cavity, the top and one side of the base are open, a connecting hole (12) communicated with the cavity is arranged on one side vertical to the open side, the clamping assembly (2) and the locking assembly (3) are respectively positioned on the top of the base (1) and one side where the connecting hole (12) is positioned, the locking assembly (3) comprises a locking pin (31), characterized in that the locking assembly (3) further comprises a first handle (32) and a pin bushing (33), the first handle (32) is rotatably connected with the locking pin (31), one end of the pin sleeve (33) is positioned in the connecting hole (12), the other end is fixed on the base (1), the locking pin (31) is sleeved with a spring (35) and is positioned in the pin sleeve (33) together.

2. The space suit securing mechanism of claim 1, wherein the pin sleeve (33) has a sleeve portion (33a) and a mounting portion (33 b);

the sleeve portion (33a) is located in the connection hole (12) and is internally provided with a blocking projection (34).

The mounting part (33b) is fixedly connected to the base (1).

3. The space suit fixing mechanism of claim 2, characterized in that the locking pin (31) has a locking end (31a) and a connecting end (31 b);

the diameter of the locking end (31a) is larger than that of the connecting end (31b), and the spring (35) is sleeved on the connecting end (31 b);

the locking pin (31) and the spring (35) are located in the sleeve portion (33a), the spring (35) being located between the locking end (31a) and the blocking projection (34).

4. The space suit fixing mechanism of claim 3, wherein the first handle (32) has a grip portion (32a) and a connecting portion (32b) perpendicular to each other;

the holding part (32a) is a rectangular flat plate and is provided with an anti-skid hole (32c) penetrating along the thickness of the holding part;

the connecting part (32b) is a rectangular flat plate and is provided with notches (32d) which penetrate through three sides of the connecting part along the direction vertical to the thickness direction of the connecting part;

the connecting part (32b) is connected with the connecting end (31b) of the locking pin (31) through a pin, and a baffle plate (36) capable of preventing the pin from falling off is fixedly connected to one surface of the connecting part (32 b).

5. Mechanism according to claim 4, wherein the connecting portion (32b) of the first handle (32) is rounded close to the lower end of the side of the base (1) whose upper end extends in the direction of the base (1);

the holding part (32a) is connected to the side of the connecting part (32b) far away from the base (1), and the lower end of the side extends downwards.

6. Mechanism according to claim 5, wherein the base (1) is stepped at the bottom of its inner wall and is higher away from its open side.

7. Mechanism according to claim 6, characterized in that the clamping assembly (2) comprises a second handle (21), a clamping member (22) and a supporting shaft (23);

one end of the second handle (21) is fixedly connected with the top of the clamping piece (22), and the other end of the second handle is tilted upwards and has a width larger than the middle part of the second handle (21);

one end of the bottom of the clamping piece (22) is provided with a hook (221) which is bent downwards and backwards, and the side surface of the end is provided with a locking hole (223) which can be matched with the locking pin (31);

the other end of the bottom of the clamping piece (22) is provided with two supporting plates (222) oppositely.

8. The space suit fixing mechanism according to claim 7, characterized in that the support plate (222) is provided with a through-hole (222a), and the support shaft (23) is sleeved with a torsion spring (24).

9. Mechanism according to claim 7, characterized in that said supporting shaft (23) passes through the cavity of said base (1) and through-shaft hole (222a) of said supporting plate (222), the two torsion bars of said torsion spring (24) resting on the bottom of the inner wall of said base (1) and on said snap-in element (22), respectively.

10. Mechanism according to claim 1, wherein the base (1) is beveled in the middle of its sides, which slopes inwards.

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