A rocket satellite support structure

Abstract

The application provides a rocket satellite support structure, comprising: a multi-satellite distributor connecting plate, a stringer frame structure and a bottom connecting part; the multi-satellite distributor connecting plate is a circular ring plate structure; the multi-satellite distributor connecting plate is used for fixed connection with a multi-satellite distributor base to realize the connection of the satellite support and the multi-satellite distributor; the stringer frame structure is fixedly connected with the multi-satellite distributor connecting plate; the bottom connecting part is arranged at one end of the stringer frame structure away from the multi-satellite distributor connecting plate; the bottom connecting part is used for connection with a rocket upper stage mounting plate; the bottom connecting part of the stringer frame structure forms a plurality of bottom connecting parts connected with the rocket upper stage mounting plate, thereby realizing the stable and reliable connection of the stringer frame structure and the rocket upper stage mounting plate. The satellite support structure is more light and convenient, the overall mass of the satellite support structure is reduced, and the overall effective carrying capacity of the rocket is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rockets, in particular to a rocket satellite support structure. BACKGROUND

[0002] The rocket satellite support is a transition connecting piece between the rocket satellite and the rocket body, which bears the weight of all the effective load and ensures the safety and stability of the satellite during the flight of the rocket.

[0003] The traditional satellite support used in cooperation with the upper stage generally adopts a conical barrel section structure, the lower end is connected to the upper end surface of the upper stage, and the upper end is connected to a multi-satellite distributor. The conical barrel structure has a large mass, and in order to avoid the equipment on the upper stage, the taper of the satellite support is small, and the height is high.

[0004] Therefore, the technical problem to be solved at present is how to provide a rocket satellite support structure which is more light and convenient, reduces the overall mass of the satellite support structure, and improves the overall effective carrying capacity of the rocket. SUMMARY

[0005] The purpose of the present application is to provide a rocket satellite support structure which is more light and convenient, reduces the overall mass of the satellite support structure, and improves the overall effective carrying capacity of the rocket.

[0006] In order to achieve the above purpose, the present application provides a rocket satellite support structure, comprising: a multi-satellite distributor connecting plate, a stringer frame structure and a bottom surface connecting part; the multi-satellite distributor connecting plate is used for fixed connection with the multi-satellite distributor base; the stringer frame structure is fixedly connected with the multi-satellite distributor connecting plate; the bottom surface connecting part is arranged at one end of the stringer frame structure away from the multi-satellite distributor connecting plate; and the bottom surface connecting part is used for connection with the rocket upper stage mounting plate.

[0007] The rocket satellite support structure as described above, wherein the stringer frame structure is conical; the two ends of the stringer frame structure are small-diameter end and large-diameter end respectively; the diameter of the circle where the small-diameter end is located is smaller than the diameter of the circle where the large-diameter end is located; the small-diameter end is fixedly connected with the multi-satellite distributor connecting plate; and the large-diameter end is provided with the bottom surface connecting part.

[0008] The rocket satellite support structure as described above, wherein the stringer frame structure comprises a plurality of inclined columns; the plurality of inclined columns are arranged at intervals along the edge of the multi-satellite distributor connecting plate, and each inclined column is arranged obliquely to the outside of the multi-satellite distributor connecting plate.

[0009] The rocket satellite support structure as described above, wherein the stringer frame structure further comprises a connecting cross bar; the connecting cross bar is connected between two adjacent inclined columns; and the connecting cross bar is parallel to the multi-satellite distributor connecting plate.

[0010] The rocket satellite support structure as described above, wherein the connecting cross bars include a first connecting cross bar and a second connecting cross bar; the first connecting cross bar and the second connecting cross bar are different in distance from the multi-satellite distributor connecting plate; any one of the inclined columns is fixedly connected with the inclined columns on both sides thereof through the first connecting cross bar and the second connecting cross bar, respectively.

[0011] The rocket satellite support structure as described above, wherein the truss frame structure further includes a cross beam structure; the cross beam structure is fixedly connected with the connecting cross bars; and the cross beam structure is fixedly connected with the rocket upper stage mounting plate.

[0012] The rocket satellite support structure as described above, wherein the cross beam structure includes a cross beam and a cross beam column; the plane where the cross beam is located is parallel to the plane where the multi-satellite distributor connecting plate is located; the cross beam is fixedly connected with the connecting cross bars; the cross beam column is perpendicular to the cross beam; one end of the cross beam column is fixedly connected with the cross beam, and the other end is fixedly connected with the rocket upper stage mounting plate.

[0013] The rocket satellite support structure as described above, wherein the cross beam includes a cross bar and a longitudinal bar; the cross bar is fixedly connected with the longitudinal bar perpendicularly; both ends of the cross bar are fixedly connected with the connecting cross bars; and both ends of the longitudinal bar are fixedly connected with the connecting cross bars.

[0014] The rocket satellite support structure as described above, wherein two cross beam columns are fixedly connected with the side of the cross bar away from the multi-satellite distributor connecting plate; and two cross beam columns are fixedly connected with the side of the longitudinal bar away from the multi-satellite distributor connecting plate.

[0015] The rocket satellite support structure as described above, wherein the multi-satellite distributor connecting plate is a circular ring-shaped plate structure.

[0016] The beneficial effects achieved by the present application are as follows:

[0017] (1) The rocket satellite support structure of the present application adopts a truss frame structure, which is open for installation and facilitates the installation and operation of parts on the rocket upper stage mounting plate.

[0018] (2) The truss frame structure of the present application is more lightweight than the cone barrel segment structure in the prior art, thereby reducing the overall mass of the rocket satellite support structure itself and improving the overall effective carrying capacity of the rocket.

[0019] (3) The truss frame structure of the present application increases the rigidity of the rocket upper stage structure by adding a bottom frame, thereby reducing the overall mass of the rocket upper stage structure and the rocket satellite support structure.

[0020] (4) The truss frame structure of the present application avoids the height of the storage tank and other equipment, is more compact, the height of the multi-satellite distributor connecting plate from the upper stage mounting plate of the rocket is smaller, the height of the multi-satellite distributor mounting plate is reduced, and the height of the multi-satellite distributor mounting surface is further reduced, which is beneficial to reducing the length of the fairing and reducing the overall mass of the rocket.

[0021] (5) The cross beam column of the present application is fixedly connected with the upper stage mounting plate of the rocket, and simultaneously enhances the rigidity and strength of the upper stage mounting plate of the rocket and the satellite support structure of the rocket. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments described in the present application, and other drawings can also be obtained by those skilled in the art according to these drawings.

[0023] Figure 1 It is a perspective view of a rocket satellite support structure according to an embodiment of the present application.

[0024] Figure 2 It is a top view of a rocket satellite support structure according to an embodiment of the present application.

[0025] Figure 3 It is a side view of a rocket satellite support structure according to an embodiment of the present application.

[0026] Figure 4 It is a perspective view of a rocket satellite support structure connected with an upper stage mounting plate of a rocket according to an embodiment of the present application.

[0027] Figure 5 It is a top view of a rocket satellite support structure connected with an upper stage mounting plate of a rocket according to an embodiment of the present application.

[0028] Figure 6 It is a side view of a rocket satellite support structure connected with an upper stage mounting plate of a rocket according to an embodiment of the present application.

[0029] Figure 7 It is a perspective view of a rocket satellite support structure connected with an upper stage structure of a rocket according to an embodiment of the present application.

[0030] Figure 8 It is a top view of a rocket satellite support structure connected with an upper stage structure of a rocket according to an embodiment of the present application.

[0031] Figure 9 It is a side view of a rocket satellite support structure connected with an upper stage structure of a rocket according to an embodiment of the present application.

[0032] 1 - Multi-star distributor connecting plate; 2 - Cable-stayed column; 3 - Cross beam structure; 4 - Bottom connecting part; 5 - Upper stage mounting plate of rocket; 21 - First connecting cross bar; 22 - Second connecting cross bar; 31 - Cross beam; 32 - Cross beam column; 51 - Tank; 52 - First electrical equipment; 53 - Second electrical equipment; 54 - Engine. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the present application will be described clearly and completely below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0034] As shown in the drawings, Figures 1-9 The present application provides a rocket satellite support structure, comprising: a multi-star distributor connecting plate 1, a stringer frame structure and a bottom connecting part 4; the multi-star distributor connecting plate 1 is a circular plate structure; the multi-star distributor connecting plate 1 is used for fixed connection with the multi-star distributor base to realize the connection of the satellite support and the multi-star distributor; the stringer frame structure is fixedly connected with the multi-star distributor connecting plate 1; the bottom connecting part 4 is arranged at one end of the stringer frame structure away from the multi-star distributor connecting plate 1; the bottom connecting part 4 is used for connection with the upper stage mounting plate 5 of the rocket, and the bottom connecting parts 4 connected with the upper stage mounting plate 5 of the rocket are formed at the bottom connecting part of the stringer frame structure, so as to realize the stable and reliable connection of the stringer frame structure and the upper stage mounting plate 5 of the rocket.

[0035] As a specific embodiment of the present application, the stringer frame structure is conical; the two ends of the stringer frame structure are small-diameter end and large-diameter end respectively; the diameter of the circle where the small-diameter end is located is smaller than the diameter of the circle where the large-diameter end is located; the small-diameter end is fixedly connected with the multi-star distributor connecting plate 1; and the large-diameter end is provided with the bottom connecting part 4.

[0036] As shown in the drawings, Figures 1-9 The stringer frame structure comprises a plurality of cable-stayed columns 2; the plurality of cable-stayed columns 2 are arranged at intervals along the edge of the multi-star distributor connecting plate 1, and each cable-stayed column 2 is arranged obliquely to the outside of the multi-star distributor connecting plate 1.

[0037] As a specific embodiment of the present application, the satellite support and the rocket upper stage structure are connected in a distributed multi-point manner. Specifically, the end of each of the plurality of inclined columns 2 is provided with a bottom connecting portion 4, and the bottom connecting portion 4 is located at the end of the inclined column 2 away from the multi-satellite distributor connecting plate 1; the end of each of the plurality of inclined columns 2 is fixedly connected to the rocket upper stage mounting plate 5 through the bottom connecting portion 4, thereby realizing the distributed multi-point connection of the satellite support and the rocket upper stage structure and improving the stability and reliability of the connection between the satellite support and the rocket upper stage structure.

[0038] As a preferred embodiment of the present application, the plurality of inclined columns 2 comprises eight inclined columns 2, and the eight inclined columns 2 are arranged at intervals and are arranged to form a conical surface, thereby improving the stability and reliability of the satellite support structure. The number of inclined columns 2 is not limited herein, and a person skilled in the art can select and design according to the actual situation.

[0039] As a specific embodiment of the present application, the bottom connecting portion 4 and the rocket upper stage mounting plate 5 can be threadedly connected, clamped, or connected by a latch, and the like. The fixed connection manner of the bottom connecting portion 4 and the rocket upper stage mounting plate 5 is not limited herein, and a person skilled in the art can select and design according to the actual situation as long as the fixed connection of the bottom connecting portion 4 and the rocket upper stage mounting plate 5 is realized.

[0040] As a specific embodiment of the present application, the truss frame structure further comprises a connecting cross bar; the connecting cross bar is connected between adjacent two inclined columns 2; and the connecting cross bar is parallel to the multi-satellite distributor connecting plate 1. The connecting cross bar is used to improve the stability and reliability of the connection between the inclined columns 2 and to improve the overall strength and rigidity of the truss frame structure.

[0041] As shown in Figures 1-3 , the connecting cross bar comprises a first connecting cross bar 21 and a second connecting cross bar 22; the first connecting cross bar 21 and the second connecting cross bar 22 are connected on both sides of the inclined column 2 and are arranged staggered, and the first connecting cross bar 21 and the second connecting cross bar 22 are different in distance from the multi-satellite distributor connecting plate 1; and any one inclined column 2 and the inclined columns 2 on both sides thereof are fixedly connected through the first connecting cross bar 21 and the second connecting cross bar 22, respectively. The staggered arrangement of the first connecting cross bar 21 and the second connecting cross bar 22 further improves the stability and reliability of the connection between the inclined columns 2 and improves the overall strength and rigidity of the truss frame structure.

[0042] As shown in Figures 4-6 , the truss frame structure further comprises a cross beam structure 3; the cross beam structure 3 is fixedly connected to the connecting cross bar; and the cross beam structure 3 is fixedly connected to the rocket upper stage mounting plate 5. The cross beam structure 3 improves the stability and reliability of the connection between the connecting cross bars, further improves the stability and reliability of the connection between the inclined columns 2, and improves the overall strength, stability, and reliability of the truss frame structure.

[0043] As shown in Figures 4-6 The cross beam structure 3 includes a cross beam 31 and a cross beam column 32; the plane where the cross beam 31 is located is parallel to the plane where the multi-satellite distributor connecting plate 1 is located; the cross beam 31 is fixedly connected with the connecting cross beam; the cross beam column 32 is perpendicular to the cross beam 31; one end of the cross beam column 32 is fixedly connected with the cross beam 31, and the other end is fixedly connected with the rocket upper stage mounting plate 5. After the cross beam column 32 is fixedly connected with the rocket upper stage mounting plate 5, the rigidity and strength of the rocket upper stage mounting plate 5 and the rocket satellite support structure are simultaneously enhanced. The cross beam column 32 at the bottom of the satellite support frame is designed in an isolated manner with the multi-satellite distributor connecting plate 1 at the upper part of the frame. Specifically, the cross beam column 32 is not connected with the multi-satellite distributor connecting plate 1, and the deformation and vibration of the middle part of the rocket upper stage mounting plate 5 are transferred to the bottom corner of the satellite support, that is, to the stringer frame structure, so as to avoid the deformation and vibration of the middle part of the rocket upper stage mounting plate 5 from being conducted to the upper end surface of the satellite support, that is, to the multi-satellite distributor connecting plate 1, thereby avoiding the influence on the multi-satellite distributor connected with the multi-satellite distributor connecting plate 1.

[0044] As a specific embodiment of the present application, the cross beam 31 includes a cross beam and a longitudinal beam; the cross beam is fixedly connected with the longitudinal beam in a perpendicular manner; both ends of the cross beam are fixedly connected with the connecting cross beam; both ends of the longitudinal beam are fixedly connected with the connecting cross beam. The cross beam and the longitudinal beam improve the stability and reliability of the connection between the connecting cross beams, further improve the stability and reliability of the connection between the inclined columns 2, and improve the strength, stability and reliability of the overall stringer frame structure.

[0045] As a preferred embodiment of the present application, both ends of the cross beam and the longitudinal beam are fixedly connected with the first connecting cross beam 21; thereby improving the stability and reliability of the connection between the first connecting cross beams 21, improving the strength, stability and reliability of the overall stringer frame structure.

[0046] As shown in Figure 4 Two cross beam columns 32 are fixedly connected on the side of the cross beam away from the multi-satellite distributor connecting plate 1; two cross beam columns 32 are fixedly connected on the side of the longitudinal beam away from the multi-satellite distributor connecting plate 1. The cross beam columns 32 are fixedly connected on the rocket upper stage mounting plate 5 in a perpendicular manner, thereby improving the stability of the cross beam 31, improving the strength, stability and reliability of the overall stringer frame structure.

[0047] As shown in Figures 7-9As shown, the rocket upper stage mounting plate 5 is fixedly connected with a storage tank 51, a first electrical equipment 52, a second electrical equipment 53 and an engine 54, the storage tank 51 is fixedly connected in the storage tank mounting hole of the rocket upper stage mounting plate 5, and the two sides of the storage tank 51 protrude from the rocket upper stage mounting plate 5; the first electrical equipment 52 and the second electrical equipment 53 are arranged on the upper end surface of the rocket upper stage mounting plate 5; the engine 54 is fixedly connected to the lower end surface of the rocket upper stage mounting plate 5, and the stringer frame structure is fixedly connected to the upper end surface of the rocket upper stage mounting plate 5, avoiding the storage tank 51, the first electrical equipment 52 and the second electrical equipment 53.

[0048] As a specific embodiment of the present application, the inclined pull pillar 2 avoids the outer shape surface of the storage tank 51, effectively reduces the height of the multi-satellite distributor connecting plate 1, and avoids the installation space for the first electrical equipment 52 and the second electrical equipment 53. Compared with the cone barrel section structure in the prior art, the stringer frame structure is more compact, more portable, and has smaller mass, and the height of the multi-satellite distributor connecting plate 1 from the rocket upper stage mounting plate 5 is smaller, thereby improving the overall effective carrying capacity of the rocket.

[0049] The beneficial effects achieved by the present application are as follows:

[0050] (1) The rocket satellite support structure of the present application adopts a truss type frame structure, which is open for installation and facilitates the installation and operation of parts on the rocket upper stage mounting plate.

[0051] (2) Compared with the cone barrel section structure in the prior art, the stringer frame structure of the present application is more portable, reduces the overall mass of the rocket satellite support structure itself, and improves the overall effective carrying capacity of the rocket.

[0052] (3) The bottom frame of the stringer frame structure of the present application increases the rigidity of the rocket upper stage structure, thereby reducing the overall mass of the rocket upper stage structure and the rocket satellite support structure.

[0053] (4) The stringer frame structure of the present application avoids the height of the storage tank and other equipment, and is more compact, so that the height of the multi-satellite distributor connecting plate from the rocket upper stage mounting plate is smaller, the height of the multi-satellite distributor mounting plate is reduced, and the height of the multi-satellite distributor mounting surface is reduced, which is beneficial to reducing the length of the fairing and reducing the overall mass of the rocket.

[0054] (5) After the cross beam column of the present application is fixedly connected with the rocket upper stage mounting plate, the rigidity and strength of the rocket upper stage mounting plate and the rocket satellite support structure are simultaneously enhanced.

[0055] In the description of the present application, the terms "first", "second", etc. are used only to describe the purpose and are not to be construed as indicating or implying relative importance or a specific number of the technical features indicated. Thus, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise explicitly and specifically limited.

[0056] In the description of the present application, the word "for example" is used to mean "serving as an example, instance, or illustration." Any embodiment described as "for example" in this application is not necessarily to be construed as preferred or advantageous over other embodiments. The following description is presented to enable any person skilled in the art to make and use the application. In the following description, for purposes of explanation, specific details are set forth. It will be apparent to those skilled in the art that the present application can be practiced without the specific details. In other instances, well-known structures and processes are not elaborated in order not to obscure the description of the present application with unnecessary details. Thus, the present application is not intended to be limited by the embodiments shown, but is to be accorded with the widest scope consistent with the principles and features disclosed.

[0057] The above description is merely illustrative of the embodiments of the present application, and is not intended to limit the present application. The present application can be variously changed and modified by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.

Claims

1. A rocket satellite support structure, characterized by, include: Multi-star distributor connecting plate, truss frame structure and bottom connection part; The multi-star distributor connecting plate is used for fixed connection with the multi-star distributor base; The stringer frame structure is fixedly connected to the multi-star distributor connecting plate; The bottom connecting part is located at one end of the stringer frame structure away from the multi-satellite distributor connecting plate; the bottom connecting part is used to connect with the rocket upper stage mounting plate; The truss frame structure includes multiple diagonally tied columns; Multiple inclined tie columns are spaced apart along the edge of the multi-star distributor connecting plate, and each inclined tie column is inclined outward towards the multi-star distributor connecting plate; The truss frame structure also includes connecting crossbars; The connecting crossbar connects two adjacent inclined tie columns; The connecting crossbar is parallel to the multi-star distributor connecting plate; The stringer frame structure also includes a cross beam structure; The crossbeam structure is fixedly connected to the connecting crossbar; The crossbeam structure is fixedly connected to the upper stage mounting plate of the rocket. The cross beam structure includes a cross beam and cross beam columns; The plane containing the cross beam is parallel to the plane containing the multi-star distributor connecting plate; The cross beam is fixedly connected to the connecting crossbar; The crossbeam column is perpendicular to the crossbeam; One end of the crossbeam column is fixedly connected to the crossbeam, and the other end is fixedly connected to the rocket upper stage mounting plate.

2. The rocket satellite support structure according to claim 1, characterized in that, The stringer frame structure is conical; The two ends of the truss frame structure are a small diameter end and a large diameter end, respectively; the diameter of the circle containing the small diameter end is smaller than the diameter of the circle containing the large diameter end. The smaller diameter end is fixedly connected to the multi-star distributor connecting plate; the larger diameter end is provided with the bottom surface connecting part.

3. The rocket satellite support structure according to claim 1, characterized in that, The connecting crossbar includes a first connecting crossbar and a second connecting crossbar; The first connecting crossbar and the second connecting crossbar are at different distances from the multi-star distributor connecting plate; Each of the inclined tie columns is fixedly connected to the inclined tie columns on both sides by the first connecting crossbar and the second connecting crossbar, respectively.

4. The rocket satellite support structure according to claim 1, characterized in that, The cross beam includes horizontal bars and vertical bars; The crossbar is fixedly connected to the longitudinal bar perpendicularly. The two ends of the crossbar are fixedly connected to the connecting crossbar; The two ends of the longitudinal bar are fixedly connected to the connecting crossbar.

5. The rocket satellite support structure according to claim 4, characterized in that, Two crossbeam columns are fixedly connected to the side of the crossbar away from the multi-star distributor connecting plate; two crossbeam columns are fixedly connected to the side of the longitudinal bar away from the multi-star distributor connecting plate.

6. The rocket satellite support structure according to claim 1, characterized in that, The multi-star distributor connecting plate has a circular flat plate structure.

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