Grid rudder transportation locking device

Abstract

The present invention provides a grid fin transportation locking device, which relates to the field of aerospace technology. The grid fin transportation locking device provided by the present invention includes: a support member and a fixing member. The support member is arranged between the grid fin and the rocket body, and one end of the support member abuts against the rocket body; one end of the fixing member is connected to the grid fin, and the other end is connected to the end of the support member away from the rocket body, so that the position of the grid fin relative to the rocket body can be locked. The grid fin transportation locking device of the present invention can firmly fix the grid fin on the rocket body, improve the stability of grid fin transportation, and thus improve the reusability of the grid fin.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a grid rudder transportation locking device. Background Art

[0002] The grid rudder is a space multi-lift surface system composed of an outer frame and numerous internal grid walls arranged in a frame or honeycomb form. The grid rudder is used to control the flight attitude of the rocket during flight. For example, during the process of rocket recovery and precise landing, the grid rudder can control the attitude of the rocket during recovery to ensure that the rocket debris can land in the set area.

[0003] During the transportation of the launch vehicle's grid rudder, the mechanical environmental conditions make it vulnerable to external forces such as bumps. It is difficult to fix the grid rudder itself only by relying on the self-locking force of the folding and unfolding servo at the connection between the grid rudder and the rocket body, making it easy for the grid rudder to shake relative to the rocket body, causing damage to the grid rudder or the rocket body. Summary of the invention

[0004] Therefore, the technical problem to be solved by the present invention is the defect in the prior art that the grid rudder is easy to shake relative to the arrow body, causing damage to the grid rudder or the arrow body, so as to provide a grid rudder transportation locking device that can firmly fix the grid rudder on the arrow body, improve the stability of the grid rudder transportation, and thus improve the reusability of the grid rudder.

[0005] In order to solve the above problems, the present invention provides a grid rudder transportation locking device, comprising:

[0006] A support member is disposed between the grid rudder and the arrow body, and one end of the support member abuts against the arrow body;

[0007] A fixing member, one end of which is connected to the grid rudder, and the other end of which is connected to an end of the supporting member away from the arrow body, so that the grid rudder can be locked in position relative to the arrow body.

[0008] As a preferred technical solution of the grid rudder transportation locking device, the fixing member includes:

[0009] A clamping part, wherein the clamping part has a hollow cavity, one end of the hollow cavity is an open end, the grid rudder is suitable for being inserted into the open end, and the other end is a closed end;

[0010] The fixing part is formed on the outer wall of the opening end, and the fixing part is detachably connected to the supporting member.

[0011] As a preferred technical solution of the grid rudder transportation locking device, the grid rudder includes a frame, and a plurality of intersecting and spaced grid walls are arranged inside the frame. The outer side wall of the hollow cavity has a long groove arranged along the length direction of the clamping part. The grid walls are adapted to be inserted into the open end and the long groove and abut against the closed end.

[0012] As a preferred technical solution of the grid rudder transportation locking device, the cross-sectional shape of the hollow cavity perpendicular to its length direction is cross-shaped.

[0013] As a preferred technical solution of the grid rudder transportation locking device, the cross-sectional shape of the clamping part perpendicular to its length direction is cross-shaped, and the long groove is formed at four protruding ends of the clamping part.

[0014] As a preferred technical solution of the grid rudder transportation locking device, the support member includes:

[0015] A support part, which is detachably connected to the fixed part;

[0016] An installation part, which is detachably connected to the rocket body.

[0017] As a preferred technical solution of the grid rudder transportation locking device, the support member further includes a connecting part, and two ends of the connecting part are respectively connected to the support part and the installation part.

[0018] As a preferred technical solution of the grid rudder transportation locking device, it further includes a strengthening part, which is symmetrically arranged on both sides of the connecting part and is perpendicular to the connecting part. One end of the strengthening part facing the installation part is connected to the installation part.

[0019] As a preferred technical solution of the grid rudder transportation locking device, a plurality of arc-shaped holes are evenly formed in the support part, and the plurality of arc-shaped holes are arranged at intervals around the axis of the support part. The arc-shaped holes cooperate with the assembly holes on the fixed part.

[0020] As a preferred technical solution of the grid rudder transportation locking device, the transportation locking device is arranged away from the hinge point between the grid rudder and the rocket body.

[0021] The technical solution of the present invention has the following advantages:

[0022] 1. The grid fin transportation locking device provided by the present invention includes: a support member and a fixing member. The support member is disposed between the grid fin and the rocket body, and one end of the support member abuts against the rocket body; one end of the fixing member is connected to the grid fin, and the other end is connected to the end of the support member away from the rocket body, so that the position of the grid fin relative to the rocket body can be locked. Preferably, the fixing member passes through the grid fin and is connected to the support member, so that the position of the grid fin relative to the rocket body can be locked. By providing the support member and the fixing member, the grid fin can be firmly fixed on the rocket body, effectively avoiding the shaking of the grid fin during transportation, improving the stability of the grid fin transportation, reducing the load borne by the grid fin, and improving the reusability of the grid fin.

[0023] 2. The grid fin transportation locking device provided by the present invention, wherein the fixing member includes: a clamping portion and a fixing portion. The clamping portion is formed with a hollow cavity. One end of the hollow cavity is an open end, and the other end is a closed end. The grid fin can be inserted into the open end. The outer side wall of the hollow cavity has a long groove provided along the length direction of the clamping portion; the fixing portion is formed on the outer wall of the open end, and the fixing portion is detachably connected to the support member. By providing a clamping portion with a hollow cavity closed at one end, the grid fin can be inserted into the fixing member through the open end and the long groove and abut against the closed end. Then, by providing the fixing portion, the fixing member is fixed to the support member, and the fixing member uses machining forming technology, with a simple structure and convenient installation.

[0024] 3. The grid fin transportation locking device provided by the present invention, the cross-sectional shape of the hollow cavity of the clamping portion perpendicular to its length direction is the same as the cross-sectional shape of the clamping portion perpendicular to its length direction. Therefore, a suitable fixing member can be selected according to grid fins of different sizes and shapes, and the applicability is strong.

[0025] 4. The grid fin transportation locking device provided by the present invention, the support member includes a support portion and a mounting portion. The support portion is detachably connected to the fixing portion; the mounting portion is detachably connected to the rocket body. By providing the support portion and the mounting portion, the support member is detachably connected to the fixing member and the rocket body, and the support member uses machining forming technology, with a simple structure and convenient installation.

[0026] 5. The grid fin transportation locking device provided by the present invention, the support member further includes a connecting portion and a strengthening portion. Both ends of the connecting portion are respectively connected to the support portion and the mounting portion. The strengthening portions are symmetrically arranged on both sides of the connecting portion and are perpendicular to the connecting portion. One end of the strengthening portion facing the mounting portion is connected to the mounting portion. By providing the strengthening portion at the connection between the connecting portion and the mounting portion, the strength of the connection between the two can be enhanced, and the stability and reliability of the support of the support member can be improved.

[0027] 6. The grid fin transportation locking device provided by the present invention has a plurality of arc-shaped holes uniformly formed in the support portion. The plurality of arc-shaped holes are arranged at intervals around the axis of the support portion and cooperate with the assembly holes on the fixing portion. By providing the plurality of arc-shaped holes, compared with the traditional circular bolt holes, the arc-shaped bolt holes facilitate the installation of bolts and improve the assembly efficiency of the support portion and the fixing portion.

[0028] 7. The grid fin transportation locking device provided by the present invention is arranged away from the hinge point between the grid fin and the rocket body. The grid fin and the rocket body are hinged through a connecting assembly, enabling the grid fin to be folded / unfolded relative to the rocket body around the folding / unfolding axis of the connecting assembly. The connecting assembly includes: a rudder shaft and a rudder shaft support. The rudder shaft is connected to the grid fin through a rotating shaft; one end of the rudder shaft support is connected to the rocket body, and the other end is connected to the rudder shaft. By providing the rudder shaft and the rudder shaft support, the grid fin and the rocket body are connected, enabling the entire grid fin to be connected to the rocket body by two support points, namely the rotating shaft hinge point at the upper part and the locking device arranged away from the hinge point, which can effectively avoid the problems caused by the shaking of the grid fin during transportation and further improve the stability of the grid fin during transportation. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0030] Figure 1 It is a schematic structural diagram of the grid fin locking device provided by the present invention;

[0031] Figure 2 It is a schematic structural diagram of the fixing member of the grid fin locking device provided by the present invention;

[0032] Figure 3 It is a schematic structural diagram of the support member of the grid fin locking device provided by the present invention;

[0033] Figure 4 It is an assembly diagram of the grid fin locking device and the grid fin provided by the present invention from the first perspective;

[0034] Figure 5 For Figure 4 The partial enlarged view at A in

[0035] Figure 6 It is an assembly diagram of the grid fin locking device and the grid fin provided by the present invention from the second perspective;

[0036] Figure 7 It is an assembly diagram of the grid fin locking device, the grid fin and the rocket body provided by the present invention.

[0037] Description of the reference numerals:

[0038] 1. Arrow body; 2. Grid fin; 21. Frame; 22. Grid wall; 3. Support member; 31. Support part; 311. Arc-shaped hole; 32. Mounting part; 321. Mounting hole; 33. Connecting part; 34. Reinforcing part; 4. Fixing member; 41. Clamping part; 411. Open end; 412. Closed end; 42. Fixing part; 421. Assembly hole; 43. Long slot; 44. Extended end; 51. Rudder shaft; 52. Rotating shaft. Detailed implementation manners

[0039] Next, the technical solutions of the present invention will be described clearly and completely in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0040] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0041] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "mounted", "connected", "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0042] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0043] Such as Figure 1 、 2As shown in Figures 2 and 3, it is a preferred embodiment of the grid fin transportation locking device of the present invention. This grid fin transportation locking device can firmly fix the grid fin 2 on the rocket body 1, improve the stability of grid fin transportation, effectively prevent the grid fin 2 from shaking relative to the rocket body 1 during transportation, make the grid fin 2 not easily damaged due to shaking and bumping, have a long service life, and thus improve the reusability of the grid fin 2.

[0044] The grid fin transportation locking device of this embodiment includes a support member 3 and a fixing member 4. The support member 3 is arranged between the grid fin 2 and the rocket body 1, and one end of the support member 3 abuts against the rocket body 1; one end of the fixing member 4 is connected to the grid fin 2, and the other end is connected to the end of the support member 3 away from the rocket body, so that the position of the grid fin 2 relative to the rocket body 1 can be locked.

[0045] By arranging the support member 3 and the fixing member 4, the above-mentioned grid fin transportation locking device can firmly fix the grid fin 2 on the rocket body 1. Under the mechanical environment during transportation, the grid fin 2 is not easily shaken relative to the rocket body 1, effectively avoiding the bumping between the grid fin 2 and the rocket body 1 during transportation, improving the stability of grid fin transportation, making the grid fin 2 have a longer service life, enabling the grid fin 2 to be reused, and having a higher utilization rate.

[0046] In a preferred embodiment, the fixing member 4 includes a clamping portion 41 and a fixing portion 42. The clamping portion 41 has a hollow cavity. One end of the hollow cavity is an open end 411, and the grid fin 2 is adapted to be inserted into the open end 411. The other end of the hollow cavity is a closed end 412. The fixing portion 42 is formed on the outer wall of the open end 411, and the fixing portion 42 is detachably connected to the support member 3.

[0047] Specifically, as Figure 2 shown, the outer side wall of the hollow cavity has a long groove 43 arranged along the length direction of the vertical extending end 44. The long groove 43 is formed on multiple extending ends 44 of the clamping portion 41. The clamping portion 41 can be inserted into the grid fin 2 from the intersection position of the grid wall 22 through the open end 411 and the long groove 43 until the grid wall 22 abuts against the closed end 412. The long groove 43 plays a role of guiding and limiting the installation of the fixing member 4, guiding the fixing member 4 to be quickly and accurately aligned and inserted with the grid wall 22. And the cross-sectional shape of the long groove 43 perpendicular to its length direction is arc-shaped. The arc-shaped structure is convenient for taking, and is convenient for observation when inserting the grid fin 2, further improving the assembly efficiency and reliability of the fixing member 4 and the grid fin 2. The fixing portion 42 is arranged at the end of the clamping portion 41 away from the closed end 412. The fixing portion 42 extends along the direction perpendicular to the length of the clamping portion 41. An assembly hole 421 is arranged on any fixing portion 42. The fixing member 4 is detachably connected to the support member 3 through the assembly hole 421. The fixing member 4 is integrally formed by mechanical processing technology, with a simple structure and convenient installation.

[0048] In a preferred embodiment, the cross-sectional shape of the hollow cavity perpendicular to its length direction is a cross shape, that is, it has four protruding ends 44. Specifically, as Figure 2 , 4 and shown in 5, the grid rudder 2 includes a frame 21, and a plurality of intersecting and spaced grid walls 22 are arranged in the frame 21. The grid walls 22 include transverse grid plates and longitudinal grid plates. The cross-sectional shape at the intersection of the transverse grid plate and the longitudinal grid plate is a cross shape. The cross-sectional shape of the hollow cavity perpendicular to its length direction is the same as that of the grid wall 22, both being a cross shape. The applicable fixing member 4 can be selected according to the grid rudders 2 of different sizes and shapes, and the applicability is strong.

[0049] In other alternative embodiments, the cross-sectional shape at the intersection of the transverse grid plate and the longitudinal grid plate can be an X shape. Correspondingly, the cross-sectional shape of the hollow cavity perpendicular to its length direction and the cross-sectional shape of the clamping portion 41 perpendicular to its length direction are also X shapes, and can also be a T shape, etc., as long as the firm connection between the fixing member 4 and the grid rudder 2 can be achieved.

[0050] In a preferred embodiment, the support member 3 includes a support portion 31 and a mounting portion 32. The support portion 31 is detachably connected to the fixing portion 42; the mounting portion 32 is detachably connected to the arrow body 1. Specifically, as Figure 3 shown, a plurality of through holes are arranged on the support portion 31 at intervals around the axis of the support portion 31. The through holes cooperate with the assembly holes 421 on the fixing member 4, and the fixing portion 42 and the support portion 31 are connected and fixed by fastening screws, so that the support member 3 and the fixing member 4 are detachably connected. A plurality of mounting holes 321 are arranged on the mounting portion 32 at intervals around the axis of the support portion 31. The mounting holes 321 cooperate with the screw holes on the arrow body 1, and the mounting portion 32 and the arrow body 1 are connected by fastening screws. The support member 3 is integrally formed by machining technology, with a simple structure and convenient installation.

[0051] In a preferred embodiment, the through hole is an arc-shaped hole 311, and a plurality of arc-shaped holes 311 are arranged at intervals around the axis of the support portion 31. The arc-shaped holes 311 cooperate with the assembly holes 421 on the fixing portion 42. By arranging a plurality of arc-shaped holes 311, compared with traditional circular bolt holes, the arc-shaped bolt holes are convenient for bolt installation, can achieve rapid positioning and installation, and improve the assembly efficiency of the support portion 31 and the fixing portion 42. In this embodiment, both the mounting holes 321 and the arc-shaped holes 311 are provided with four.

[0052] In other alternative embodiments, the numbers of the mounting holes 321 and the arc-shaped holes 311 can be set as required, such as three, five, etc.

[0053] In a preferred embodiment, the support member 3 further includes a connecting portion 33 and a reinforcing portion 34. Two ends of the connecting portion 33 are respectively connected to the supporting portion 31 and the mounting portion 32. The reinforcing portions 34 are symmetrically arranged on both sides of the connecting portion 33 and are perpendicular to the connecting portion 33. One end of the reinforcing portion 34 facing the mounting portion 32 is connected to the mounting portion 32. Specifically, as Figure 3 shown, the central axes of the supporting portion 31, the connecting portion 33, and the mounting portion 32 coincide, ensuring the structural strength of the support member 3. The thickness of the connecting portion 33 gradually decreases from the end connected to the supporting portion 31 to the end connected to the mounting portion 32, and the width gradually increases, enabling the connecting portion 33 to reduce production costs while ensuring its connection strength. The number of the reinforcing portions 34 is two. The cross-sectional shape of the reinforcing portion 34 along its length direction (and perpendicular to the connecting portion 33) is triangular. Two right-angled sides of the triangle are respectively connected to the connecting portion 33 and the mounting portion 32, further improving the structural strength and rigidity at the connection between the connecting portion 33 and the mounting portion 32, and enhancing the stability and reliability of the support of the support member 3.

[0054] In other alternative embodiments, the number of the reinforcing portions 34 can be four or more, and they can be arranged symmetrically or asymmetrically on both sides of the connecting portion 33.

[0055] In a preferred embodiment, the transportation locking device is arranged away from the hinge point between the grid fin 2 and the rocket body 1. Specifically, as Figure 7 shown, in this embodiment, a transportation locking device is adopted between the grid fin 2 and the rocket body 1, and the transportation locking device is arranged below the hinge point of the grid fin 2 and the rocket body 1 ( Figure 7 the angle shown), and the position where the transportation locking device is arranged is the supporting position of the grid fin 2.

[0056] The grid fin 2 and the rocket body 1 are hinged through a connecting assembly. The connecting assembly includes a rudder shaft 51 and a rudder shaft support. The rudder shaft 51 is connected to the grid fin 2 through a rotating shaft 52. The rudder shaft support is connected to the rocket body 1. The rudder shaft 51 is installed on the rudder shaft support. By setting the connecting assembly to connect the grid fin 2 and the rocket body 1, the grid fin 2 can be folded / unfolded relative to the rocket body 1 around the rotating shaft 52. The hinged position of the grid fin 2 and the rocket body 1 is the position of the rotating shaft 52. The grid fin 2 is connected to the rocket body 1 through the hinged position and the supporting position (two supporting points). The farther the distance between the two supporting points is, the higher the overall stability of the grid fin 2. During transportation, the grid fin 2 is in a folded state and is fixed by fitting against the outer surface of the rocket body 1. There is no relative movement between the grid fin 2 and the rocket body 1, reducing the load borne by the rudder shaft 51, effectively avoiding problems caused by the shaking of the grid fin 2 during transportation, protecting the structures of the grid fin 2 and the rocket body 1 from being damaged, improving the stability of the grid fin 2 during transportation, and protecting the grid fin 2 and the rocket body 1 from being easily knocked and damaged.

[0057] In other alternative embodiments, the number of transportation locking devices can be increased according to actual situations. For example, when the area of the grid rudder 2 is relatively large, two, three or more transportation locking devices can be provided, and multiple transportation locking devices can be arranged at intervals.

[0058] Obviously, the above embodiments are merely examples given for clear illustration and are not limitations on the implementation manners. For those of ordinary skill in the art, other different forms of changes or alterations can be made based on the above description. It is not necessary and impossible to list all the implementation manners here. And the obvious changes or alterations derived therefrom are still within the protection scope of the present invention.

Claims

1. A transportation locking device for grid rudders, characterized in that, Comprising: A support member (3) is disposed between the grid fin (2) and the rocket body (1), and one end of the support member (3) abuts against the rocket body (1); A fixing member (4), one end of which is connected to the grid fin (2), and the other end is connected to the end of the support member (3) away from the rocket body (1), so that the position of the grid fin (2) relative to the rocket body (1) can be locked; The fixing member (4) includes: A clamping portion (41) having a hollow cavity therein. One end of the hollow cavity is an open end (411), and the grid fin (2) is adapted to be inserted into the open end (411), and the other end is a closed end (412); A fixing portion (42) formed on the outer wall of the open end (411), and the fixing portion (42) is detachably connected to the support member (3); The grid fin (2) includes a frame (21), and a plurality of intersecting and spaced grid walls (22) are provided in the frame (21). The outer side wall of the hollow cavity has a long groove (43) arranged along the length direction of the clamping portion (41), and the grid wall (22) is adapted to be inserted into the open end and the long groove (43) and abut against the closed end (412).

2. The transportation locking device according to claim 1, characterized in that, The cross-sectional shape of the hollow cavity perpendicular to its length direction is cross-shaped.

3. The transportation locking device according to claim 2, characterized in that, The cross-sectional shape of the clamping portion (41) perpendicular to its length direction is cross-shaped, and the long groove (43) is formed at four protruding ends of the clamping portion (41).

4. The transportation locking device according to claim 1, characterized in that, The support member (3) includes: A support portion (31) detachably connected to the fixing portion (42); A mounting portion (32) detachably connected to the rocket body (1).

5. The transportation locking device according to claim 4, characterized in that, The support member (3) further includes a connecting portion (33), and both ends of the connecting portion (33) are respectively connected to the support portion (31) and the mounting portion (32).

6. The transportation locking device according to claim 5, characterized in that, It further includes a reinforcing portion (34) symmetrically disposed on both sides of the connecting portion (33) and perpendicular to the connecting portion (33), and one end of the reinforcing portion (34) facing the mounting portion (32) is connected to the mounting portion (32).

7. The transportation locking device according to claim 5, characterized in that, The support portion (31) is uniformly provided with a plurality of arc-shaped holes (311), and the plurality of arc-shaped holes (311) are spaced apart around the axis of the support portion (31), and the arc-shaped holes (311) cooperate with the assembly holes (421) on the fixing portion (42).

8. The transportation locking device according to any one of claims 1 - 7, characterized in that, The transportation locking device is disposed away from the hinge point between the grid fin (2) and the rocket body (1).

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