Mechanical spring ejection separation mechanism for lunar transfer mechanism

Abstract

The present application relates to a mechanical ejection separation mechanism of a lunar surface transfer mechanism, and belongs to the technical field of ejection separation mechanisms, in particular to a mechanical ejection separation mechanism of a lunar surface transfer mechanism, comprising: a support structure arranged on a container; a plurality of first compression nuts, the plurality of first compression nuts penetrating the support structure and being connected with the container; two second compression nuts symmetrically arranged on the support structure and located at the middle part of the support structure, the first compression nuts and the second compression nuts being connected with a lander; and a plurality of ejection separation mechanisms respectively arranged on the two sides of the second compression nuts. The mechanical ejection separation mechanism of the lunar surface transfer mechanism is easy to unlock the container, does not need to increase an unlocking mechanism, and has high unlocking reliability; under the pre-tightening force of the ejection separation mechanism, the mechanism can meet the safe ejection requirement. The mechanical ejection separation mechanism of the lunar surface transfer mechanism can be widely applied in the fields of machinery and aerospace.

Description

Technical Field

[0001] This invention relates to the field of projectile separation mechanism technology, and specifically to a mechanical projectile separation mechanism for a lunar transfer mechanism. Background Technology

[0002] From satellite launch to the safe landing of the lander on the moon, the lunar rover and containers were installed on the symmetrical side walls of the lander.

[0003] During the flight phase and before lunar landing and transfer, in emergency mode, the lunar rover and containers can be rapidly ejected when the lander is in a certain attitude. The ejection process can effectively ensure that the ejection trajectory of the payload does not collide with the cabin and equipment, that the ejection force does not cause deformation or damage to the cabin structure, and that the ejection on both sides is synchronized.

[0004] After the lander lands on the moon, in normal mode, the astronauts manually transfer the lunar rover or container to a safe distance on the lunar surface. Then, the transfer mechanism is safely ejected from the lander, making the lander ready for a second takeoff. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the safety problems in the prior art of separating the lunar rover and container without causing collisions with the lunar lander and other objects during the separation process, thereby providing a mechanical ejection separation mechanism for a lunar surface transfer mechanism.

[0006] To address the aforementioned technical problems, this invention provides a mechanical ejection and separation mechanism for a lunar transfer mechanism, comprising: a support structure mounted on a container; multiple first clamping nuts, which pass through the support structure and are connected to the container; two second clamping nuts, symmetrically disposed on the support structure and located in the middle of the support structure, both the first and second clamping nuts being connected to a lander; and multiple ejection and separation mechanisms, respectively disposed on both sides of the second clamping nuts.

[0007] Furthermore, the launching mechanism includes a guide structure, a launching component, a push rod, and a locking nut; one end of the guide structure is connected to the support structure, the launching component is sleeved on the outer wall of the guide structure, one end of the push rod is inserted into the guide structure, the other end is connected to the lander, and the locking nut is located on the push rod.

[0008] Furthermore, the guide structure includes a guide sleeve and a guide rod, the guide sleeve being connected to the support frame mechanism, and the guide rod being inserted into the guide sleeve.

[0009] Furthermore, the guide sleeve includes a cylindrical body and fixed plates disposed at both ends of the cylindrical body, the fixed plates being connected to the support structure, and the ejector being sleeved on the cylindrical body.

[0010] Furthermore, the launching component is a launching spring.

[0011] Furthermore, it also includes a first nut seat and a second nut seat, both of which are disposed on the support structure, with the first clamping nut disposed on the first nut seat and the second clamping nut disposed on the second nut seat.

[0012] Furthermore, the first nut seat includes: a mounting surface formed on both sides of the support structure, with a flange on the outer edge of the mounting surface; and a through hole penetrating the support structure, with the first clamping nut penetrating the through hole and disposed on the mounting surface.

[0013] Furthermore, the second nut seat includes: a hollow frame formed in the middle of the support structure; and a reinforcing rib disposed on the outer wall of the hollow frame and connected to the support structure.

[0014] Furthermore, the support structure includes a side frame and two crossbeams, with the first nut seat and the second nut seat both located on the side frame.

[0015] Furthermore, the first and second clamping nuts are fire-resistant nuts.

[0016] The technical solution of this invention has the following advantages:

[0017] 1. The mechanical ejection and separation mechanism of the lunar transfer mechanism provided by the present invention includes: a support structure disposed on a container; a plurality of first clamping nuts, the plurality of first clamping nuts passing through the support structure and connected to the container; two second clamping nuts, symmetrically disposed on the support structure and located in the middle of the support structure, the first and second clamping nuts being connected to the lander; and a plurality of ejection and separation mechanisms, respectively disposed on both sides of the second clamping nuts.

[0018] The support structure is mounted on the container, providing an installation platform for it. Both a first and a second clamping nut are located on the support structure, with multiple first clamping nuts evenly distributed and penetrating the structure, connecting to both the container and the lander. A second clamping nut is located in the middle of the support structure and is also connected to the lander. During container transfer, after the first clamping nuts are released, the two second clamping nuts maintain the connection between the lander and the support structure while simultaneously maintaining the compression of the launching mechanism. Upon completion of the container transfer and the support structure returning to its initial position, the two second clamping nuts are released, and the launching mechanism generates a launching force, causing the support structure, the first and second clamping nuts, and the launching mechanism to detach from the lander with a certain lateral acceleration, completing the launching process.

[0019] The mechanical ejection separation mechanism of this lunar transfer mechanism can be used in automated ejection and separation mechanical structures requiring short-distance ejection. This structure is simple to implement, highly reliable, and uses a pyrotechnic unlocking ejection mechanism. Unlocking the container is easy with this mechanical ejection separation mechanism, requiring no additional unlocking mechanism and offering high unlocking reliability. Under the pre-tension of the ejection mechanism, the mechanism can safely eject the ejection. This makes the mechanical ejection separation mechanism of this lunar transfer mechanism widely applicable in the mechanical and aerospace fields.

[0020] 2. The mechanical projectile separation mechanism of the lunar transfer mechanism provided by the present invention includes a second nut seat comprising: a hollow frame formed in the middle of the supporting structure; and reinforcing ribs disposed on the outer wall of the hollow frame and connected to the supporting structure. The axis of the second clamping nut passes through the supporting structure, and the supporting structure is connected as a whole by the second clamping nut seat. In order to improve the rigidity of the projectile action section, reinforcing ribs are designed on both sides of the second clamping nut seat.

[0021] 3. The mechanical ejection and separation mechanism of the lunar transfer mechanism provided by the present invention includes a support structure comprising a side frame and two crossbeams, wherein the first nut seat and the second nut seat are both disposed on the side frame. The side frame and the two crossbeams are connected by welding, thereby ensuring the overall strength and rigidity of the support structure.

[0022] The summary section is provided to present the chosen concepts in a simplified form, which will be further described in the detailed description below. The summary section is not intended to identify essential or necessary features of this disclosure, nor is it intended to limit the scope of this disclosure. Attached Figure Description

[0023] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0024] Figure 1 A schematic diagram of the mechanical ejection separation mechanism of the lunar transfer mechanism provided by the present invention;

[0025] Figure 2 A schematic diagram of the support structure of the mechanical ejection separation mechanism of the lunar transfer mechanism provided by the present invention;

[0026] Figure 3 A flowchart illustrating the installation process of the ejection and separation mechanism of the mechanical ejection and separation mechanism of the lunar transfer mechanism provided by the present invention;

[0027] Figure 4 A schematic diagram of the structure of the first clamping nut of the mechanical ejection separation mechanism of the lunar transfer mechanism provided by the present invention;

[0028] Figure 5 A schematic diagram of the structure of the second clamping nut of the mechanical ejection separation mechanism of the lunar transfer mechanism provided by the present invention;

[0029] Figure 6 A schematic diagram of the structure of the first nut seat of the mechanical ejection separation mechanism of the lunar transfer mechanism provided by the present invention;

[0030] Figure 7 A schematic diagram of the second nut seat of the mechanical ejection separation mechanism of the lunar transfer mechanism provided by the present invention.

[0031] Explanation of reference numerals in the attached figures:

[0032] 1. Support structure; 11. Side frame; 12. Crossbeam; 2. Container; 3. First clamping nut; 4. Second clamping nut; 5. Dispensing mechanism; 51. Guide structure; 511. Guide sleeve; 512. Guide rod; 52. Dispensing component; 53. Push rod; 54. Locking nut; 55. Preload screw; 6. First nut seat; 61. Mounting surface; 62. Through hole; 63. Flange; 7. Second nut seat; 71. Hollow frame; 12. Reinforcing rib; 8. Nut; 9. Fixing component; 10. Lander. Detailed Implementation

[0033] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of this disclosure. Therefore, the drawings and description are to be considered exemplary in nature and not restrictive.

[0034] In the description of this disclosure, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this disclosure. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this disclosure, "a plurality of" means two or more, unless otherwise explicitly specified.

[0035] In the description of this disclosure, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joint" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections, electrical connections, or connections that allow for communication; they can refer to direct connections or indirect connections through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this disclosure according to the specific circumstances.

[0036] In this disclosure, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0037] The following disclosure provides numerous different embodiments or examples for implementing various structures of this disclosure. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the scope of this disclosure. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, various specific examples of processes and materials are provided in this disclosure, but those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0038] The preferred embodiments of this disclosure are described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0039] Please see Figures 1 to 7 As shown, the present invention provides a mechanical ejection and separation mechanism for a lunar transfer mechanism, comprising: a support structure 1 disposed on a container 2; a plurality of first clamping nuts 3, which pass through the support structure 1 and are connected to the container 2; two second clamping nuts 4, which are symmetrically disposed on the support structure 1 and located in the middle of the support structure 1, and both the first clamping nuts 3 and the second clamping nuts 4 are connected to the lander 10; and a plurality of ejection and separation mechanisms 5, which are respectively disposed on both sides of the second clamping nuts 4.

[0040] By mounting the support structure 1 on the container 2, a platform is provided on the container 2 for the support structure 1. First clamping nuts 3 and second clamping nuts 4 are both mounted on the support structure 1, with multiple first clamping nuts 3 evenly distributed on the support structure 1 and penetrating through it, connecting to the container 2 and the lander 10. Second clamping nuts 4 are located in the middle of the support structure 1 and are also connected to the lander 10. During the transfer of the container 2, when the first clamping nuts 3 are unlocked, the two second clamping nuts 4 maintain the connection between the lander 10 and the support structure 1, while simultaneously maintaining the compression of the launching mechanism 5. Upon completion of the container 2 transfer and when the support structure 1 returns to its initial position, the two second clamping nuts 4 unlock, and the launching mechanism 5 generates a launching force, causing the support structure 1, the first clamping nuts 3, the second clamping nuts 4, and the launching mechanism 5 to detach from the lander 10 with a certain lateral acceleration, completing the launching process.

[0041] The mechanical ejection separation mechanism of this lunar transfer mechanism can be used in automatic ejection and separation mechanical structures requiring short-distance ejection. This structure is simple, easy to implement, and highly reliable. Using a pyrotechnic unlocking ejection mechanism 5, the mechanical ejection separation mechanism of this lunar transfer mechanism easily unlocks the container 2 without requiring an additional unlocking mechanism, ensuring high unlocking reliability. Under the pre-tension of the ejection mechanism 5, the mechanism can complete the safe ejection requirements. This makes the mechanical ejection separation mechanism of this lunar transfer mechanism widely applicable in the mechanical and aerospace fields.

[0042] The first compression nut 3 has four parts, which are respectively set at the four top corners of the support structure 1. The second compression nut 8 is set in the middle of the support structure 1, and the distance between the second compression nuts 8 is equal.

[0043] In some optional embodiments, the launching mechanism 5 includes a guide structure 51, a launching component 52, a push rod 53, and a locking nut 54; one end of the guide structure 51 is connected to the support structure 1, the launching component 52 is sleeved on the outer wall of the guide structure 51, one end of the push rod 53 is inserted into the guide structure 51, and the other end is connected to the lander 10, and the locking nut 54 is disposed on the push rod 53.

[0044] The function of the throwing mechanism 5 is to generate throwing force by compressing the throwing component 52. The throwing component 52 is symmetrically arranged on both sides of the second clamping nut 4, and the second clamping nut 4 maintains the compressed energy storage of the throwing component 52.

[0045] In this embodiment, the launching component 52 is a launching spring.

[0046] In some optional embodiments, the guide structure 51 includes a guide sleeve 511 and a guide rod 512, the guide sleeve 511 being connected to the support frame mechanism, and the guide rod 512 being inserted into the guide sleeve 511.

[0047] The guide sleeve 511 is connected to the support structure 1 by screws. The inside of the guide sleeve 511 is in cooperation with the guide rod 512. The launcher 52 is installed between the end faces of the guide sleeve 511 and the guide rod 512. The guide rod 512 is equipped with an adjustable push rod 53 at the contact end with the lander 10. The installation dimensions of the launcher 52 and the lander 10 can be finely adjusted. After adjustment, it can be locked by locking nut 54.

[0048] In this embodiment, the guide sleeve 511 includes a cylindrical body and fixing plates disposed at both ends of the cylindrical body. The fixing plates are connected to the support structure 1, and the ejector 52 is sleeved on the cylindrical body.

[0049] The installation process of the launching mechanism 5 is as follows: First, fix the guide sleeve 511 and install the guide sleeve 511 on the support structure 1. Then, install the launching component 52, guide rod 512, pre-tightening screw 55, and nut 8. Then, rotate the nut 8 to force the launching component 52 to compress. Install the pre-tightening fixing component 9 and tighten it with screws. Then, remove the pre-tightening screw 55 and install the push rod 53 and locking nut 54 to fine-tune the size. Finally, connect the support structure 1 and the launching mechanism 5 to the lander 10 and remove the fixing component 9.

[0050] In some optional embodiments, the mechanical ejection separation mechanism of the lunar transfer mechanism further includes a first nut seat 6 and a second nut seat 7, both of which are disposed on the support structure 1. The first clamping nut 3 is disposed on the first nut seat 6, and the second clamping nut 4 is disposed on the second nut seat 7.

[0051] In this embodiment, the first nut seat 6 includes a mounting surface 61, a flange, and a through hole 62; wherein, the mounting surface 61 is formed on both sides of the support structure 1, and a flange 63 is provided on the outer edge of the mounting surface 61; the through hole 62 penetrates the support structure 1, and the first clamping nut 3 penetrates the first through hole 62 and is disposed on the mounting surface 61, that is, the first clamping nut 3 is snapped into the flange 63, thereby realizing the connection between the first clamping nut 3 and the support structure 1, the lander 10, and the container 2.

[0052] In some optional embodiments, the second nut seat 7 includes a hollow frame 71 and a reinforcing rib 12; wherein the hollow frame 71 is formed in the middle of the support structure 1; the reinforcing rib 12 is provided on the outer wall of the hollow frame 71 and connected to the support structure 1. The axis of the second clamping nut 4 passes through the support structure 1, and the support structure 1 is connected as a whole by the second clamping nut 4 seat. In order to improve the rigidity of the action section of the projectile, reinforcing ribs 12 are designed on both sides of the second clamping nut 4 seat.

[0053] In some optional embodiments, the support structure 1 includes a side frame 11 and two crossbeams 12, with the first nut seat 6 and the second nut seat 7 both disposed on the side frame 11. The side frame 11 and the two crossbeams 12 together form the support structure 1, wherein the side frame 11 and the two crossbeams 12 are connected by welding, thereby ensuring the overall strength and rigidity of the support structure 1.

[0054] In this embodiment, the first clamping nut 3 and the second clamping nut 4 are fire-resistant nuts.

[0055] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A mechanical ejection and separation mechanism for a lunar transfer mechanism, characterized in that, include: Support structure (1) is mounted on container (2); The first clamping nut (3) has multiple first clamping nuts (3) passing through the support structure (1) and connected to the container (2); The second clamping nut (4) has two, which are symmetrically arranged on the support structure (1) and located in the middle of the support structure (1). The first clamping nut (3) and the second clamping nut (4) are both connected to the lander (10). The dispensing mechanism (5) has multiple components, which are respectively located on both sides of the second clamping nut (4); It also includes a first nut seat (6) and a second nut seat (7), both of which are provided on the support structure (1). The first clamping nut (3) is provided on the first nut seat (6), and the second clamping nut (4) is provided on the second nut seat (7). The first nut seat (6) includes: Mounting surface (61) is formed on both sides of support structure (1), and flange (63) is provided on the outer edge of mounting surface (61). A through hole (62) passes through the support structure (1), and a first clamping nut (3) passes through the through hole (62) and is located on the mounting surface (61); The second nut seat (7) includes: A hollow frame (71) is formed in the middle of the supporting structure (1); A reinforcing rib (72) is provided on the outer wall of the hollow frame (71) and is connected to the supporting structure (1); During the transfer of container (2), after the first clamping nut (3) is unlocked, the two second clamping nuts (4) maintain the connection between the lander (10) and the support structure (1), while maintaining the compression of the throwing mechanism (5); when the transfer of container (2) is completed and the support structure (1) returns to the initial position, the two second clamping nuts (4) are unlocked, the throwing mechanism (5) generates a throwing force, and the support structure (1), the first clamping nut (3), the second clamping nut (4), and the throwing mechanism (5) detach from the lander (10) with a predetermined lateral acceleration, thus completing the throwing.

2. The mechanical ejection and separation mechanism of the lunar transfer mechanism according to claim 1, characterized in that, The launching mechanism (5) includes a guide structure (51), a launching component (52), a push rod (53), and a locking nut (54). One end of the guide structure (51) is connected to the support structure (1), the launching component (52) is sleeved on the outer wall of the guide structure (51), one end of the push rod (53) is inserted into the guide structure (51), and the other end is connected to the lander (10). The locking nut (54) is located on the push rod (53).

3. The mechanical ejection and separation mechanism of the lunar transfer mechanism according to claim 2, characterized in that, The guide structure (51) includes a guide sleeve (511) and a guide rod (512). The guide sleeve (511) is connected to the support frame mechanism, and the guide rod (512) is inserted into the guide sleeve (511).

4. The mechanical ejection and separation mechanism of the lunar transfer mechanism according to claim 3, characterized in that, The guide sleeve (511) includes a cylinder and fixed plates at both ends of the cylinder. The fixed plates are connected to the support structure (1), and the ejector (52) is sleeved on the cylinder.

5. The mechanical ejection and separation mechanism of the lunar transfer mechanism according to any one of claims 1-4, characterized in that, The launching component (52) is a launching spring.

6. The mechanical ejection and separation mechanism of the lunar transfer mechanism according to claim 5, characterized in that, The support structure (1) includes a side frame (11) and two crossbeams (12), with the first nut seat (6) and the second nut seat (7) both located on the side frame (11).

7. The mechanical ejection and separation mechanism of the lunar transfer mechanism according to claim 1, characterized in that, The first clamping nut (3) and the second clamping nut (4) are fire-working nuts.

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