Supporting structure for truss type space camera

Abstract

The invention discloses a truss type space camera supporting structure, and relates to the technical field of space remote sensing, the truss type space camera supporting structure comprises a top seat and a base, and the top seat and the base are connected through a plurality of truss rods; the base is used for installing the primary mirror assembly and the three-mirror assembly, the top seat is used for installing the secondary mirror assembly and the focal plane assembly, each truss rod comprises an inner carbon fiber rod and an outer carbon fiber rod, and the inner carbon fiber rod is arranged in the outer carbon fiber rod. According to the invention, a double-layer nested carbon fiber rod mounting mode is adopted, so that the stability of the space camera is greatly improved under the conditions that the requirement on the size of the space camera is low and the space camera is not suitable for layered rod system layout.

Description

Technical Field

[0001] The invention relates to the technical field of space remote sensing, and in particular to a supporting structure for a truss-type space camera. Background Art

[0002] The support structure is the core bearing unit of the space camera's optical-mechanical system, providing installation interfaces and positioning benchmarks for optical and optoelectronic imaging subsystems including reflectors and focal planes. Its dimensional accuracy, thermal structural stability, and stiffness are crucial to ensuring the camera's imaging quality. In addition, sub-meter ultra-wide-width cameras are gradually developing from single-unit development to batch development to meet the needs of commercial remote sensing satellite constellations for high-resolution and massive data acquisition. Therefore, higher requirements are placed on the camera's support structure, which must not only meet the performance indicators of high lightweight rate and high stability, but also require it to have good processing and assembly processability.

[0003] At present, the support structure of large-aperture space cameras generally adopts a truss-type rod structure and / or a frame-type plate structure. The rod structure generally uses a tubular carbon fiber composite material as the body and a titanium alloy joint made by bonding technology. It has high specific stiffness, good material processability, and good stability in space environment. However, in space cameras with an aspect ratio exceeding 1.4, in order to ensure the dynamic stiffness of the entire machine, the rod support structure will adopt a multi-layer installation method. Considering the different optical designs of different optical systems, the layered installation method has certain limitations due to higher requirements on spatial dimensions.

[0004] Therefore, those skilled in the art provide a support structure for a truss-type space camera to solve the problems raised in the above background technology. Summary of the invention

[0005] The present invention provides a support structure for a truss-type space camera, which solves the problem of insufficient dynamic stiffness of a space camera with a large aspect ratio when the space requirement is high and the layered rod system installation method is not conducive.

[0006] In order to achieve the above object, the present invention provides the following technical solutions:

[0007] A support structure for a truss-type space camera of the present invention comprises a top seat and a base, wherein the top seat and the base are connected by a plurality of truss rods; the base is used to install a primary mirror assembly and a three-mirror assembly, and the top seat is used to install a secondary mirror assembly and a focal plane assembly.

[0008] Each of the truss rods comprises an inner carbon fiber rod and an outer carbon fiber rod, wherein the inner carbon fiber rod is arranged inside the outer carbon fiber rod.

[0009] Furthermore, the two ends of the outer carbon fiber rod are respectively connected to the top seat and the base through a first mounting joint. The first mounting joint facilitates the connection of the outer carbon fiber rod with the base and the top seat.

[0010] Furthermore, the first mounting joint includes a first base, one side of the first base is connected to the top seat or the base, the other side of the first base protrudes outward to form a first protrusion, the upper side of the first protrusion away from the first base is recessed inward to form a first through hole, and the first through hole extends to the side of the first base connected to the top seat or the base.

[0011] Furthermore, a positioning ring is provided in the end of the first through hole away from the first protrusion, and the outer carbon fiber rod abuts against the top surface of the positioning ring.

[0012] Furthermore, a second through hole is provided on the top seat and the base corresponding to the position of the first through hole, the first through hole and the second through hole are coaxially arranged, and the diameter of the second through hole is the same as that of the positioning ring.

[0013] Furthermore, two ends of the inner carbon fiber rod pass through the corresponding first through hole and second through hole respectively, and are connected to the top seat and the base through a second mounting joint.

[0014] Furthermore, the second mounting joint includes a second base, the top surface of the second base protrudes outward to form a second protrusion, and the end of the inner carbon fiber rod is sleeved on the second protrusion.

[0015] Furthermore, the second base is fixed in the top seat and the base through an adapter, and the side surfaces of the adapter can be connected to the corresponding side surfaces of the top seat and the base to fix the second base in the top seat and the base.

[0016] In the above technical solution, the present invention provides a truss-type space camera support structure, which has the following beneficial effects:

[0017] 1. This application adopts this installation method in a limited space to increase the space utilization of the space camera and make the supporting structure more compact.

[0018] 2. Greatly improve the dynamic rigidity of the whole machine to ensure the stability of the space camera.

[0019] 3. The installation method of double-layer nested carbon fiber rods greatly improves the stability of the space camera when the size requirement of the space camera is small and it is not suitable for the layered rod layout. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0021] Figure 1 A front view of a truss-type space camera support structure provided in Example 1 of the present invention;

[0022] Figure 2 for Figure 1 A schematic diagram of the enlarged structure of the middle part A;

[0023] Figure 3 for Figure 1 The enlarged structural diagram of the middle B part;

[0024] Figure 4 for Figure 2 A structural diagram of the connection between the first mounting joint and the outer carbon fiber rod;

[0025] Figure 5 for Figure 3 The connection structure diagram of the second mounting joint and the inner carbon fiber rod;.

[0026] Description of reference numerals:

[0027] 10. Top seat;

[0028] 20. Base;

[0029] 30. Truss rod; 31. Inner carbon fiber rod; 32. Outer carbon fiber rod; 33. First mounting joint; 34

[0030] 331, first base; 332, first protrusion; 333, first through hole; 334, positioning ring;

[0031] 341, second base; 342, second protrusion;

[0032] 40. Adapter. DETAILED DESCRIPTION

[0033] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings.

[0034] See also Figure 1 As shown;

[0035] A support structure for a truss-type space camera according to an embodiment of the present invention comprises a top seat 10 and a base 20, wherein the top seat 10 and the base 20 are connected by a plurality of truss rods 30; the base 20 is used to install a primary mirror assembly and a three-mirror assembly, and the top seat 30 is used to install a secondary mirror assembly and a focal plane assembly.

[0036] Each of the truss rods 30 includes an inner carbon fiber rod 31 and an outer carbon fiber rod 32 , and the inner carbon fiber rod 31 is disposed inside the outer carbon fiber rod 32 .

[0037] When in use, the outer carbon fiber rod 32 and the inner carbon fiber rod 31 form a double-layer structure with inner and outer nesting to increase the rigidity of the overall support structure, increase the space utilization of the space camera in a limited space, and make the support structure more compact. At the same time, the dynamic rigidity of the whole machine is greatly improved to ensure the stability of the space camera.

[0038] See also Figure 1-2 , as shown in 4;

[0039] Further, the two ends of the outer carbon fiber rod 32 are respectively connected to the top seat 10 and the base 20 through the first mounting joint 33. The first mounting joint 33 facilitates the connection of the outer carbon fiber rod 32 with the base 20 and the top seat 10. The outer carbon fiber rod 32 and the first mounting joint 33 are bonded by glue.

[0040] The first mounting joint 33 includes a first base 331, one side of the first base 331 is connected to the top seat 10 or the base 20, the other side of the first base 331 protrudes outward to form a first protrusion 332, the upper side of the first protrusion 332 away from the first base 331 is recessed inward to form a first through hole 333, and the first through hole 333 extends to the side of the first base 331 connected to the top seat 10 or the base 20.

[0041] The outer carbon fiber rod 32 can extend into the first through hole 333 and be fixed, so as to ensure the connection rigidity between the outer carbon fiber rod 32 and the top seat 10 and the base 20 through the first mounting structure 33 .

[0042] A positioning ring 334 is disposed in the end of the first through hole 333 away from the first protrusion 332 , and the outer carbon fiber rod 32 abuts against the top surface of the positioning ring 334 .

[0043] The positioning ring 334 limits the upper and lower ends of the outer carbon fiber rod 32 to prevent the outer carbon fiber rod 32 from deviating, thereby effectively ensuring the overall rigidity. The positioning ring 334 and the first base 331 are an integrally formed structure.

[0044] See also Figure 1-3 , as shown in 5;

[0045] The top seat 10 and the base 20 are both provided with a second through hole 11 at a position corresponding to the first through hole 333 , and the first through hole 333 and the second through hole 11 are coaxially arranged. The second through hole 11 has the same diameter as the positioning ring 334 .

[0046] The two ends of the inner carbon fiber rod 31 pass through the corresponding first through hole 333 and the second through hole 11, and are connected to the top seat 10 and the base 20 through the second mounting joint 34. The inner carbon fiber rod 31 and the second mounting joint 34 are bonded by glue.

[0047] Both ends of the inner carbon fiber rod 31 pass through the corresponding first through hole 333 and the second through hole 11 in sequence, which can enhance the connection stiffness between the inner carbon fiber rod 31 and the top seat 10 and the base 20; the inner carbon fiber rod 31 is connected to the top seat 10 and the base 20 through the second mounting joint 34 to ensure a fixed connection between the inner carbon fiber rod 31 and the top seat 10 and the base 20, thereby improving the overall connection stiffness.

[0048] The second mounting joint 34 includes a second base 341 , the top surface of the second base 341 protrudes outward to form a second protrusion 342 , and the end of the inner carbon fiber rod 31 is sleeved on the second protrusion 342 ; the second base 342 is embedded in the top seat 10 and the base 20 .

[0049] Both ends of the inner carbon fiber rod 31 are respectively sleeved on the corresponding second protrusions 342 and can be abutted on the corresponding second base 341, thereby achieving a fixed connection between the inner carbon fiber rod 31 and the top seat 10 and the base 20, thereby improving the overall connection stiffness.

[0050] The second base 341 is fixed in the top seat 10 and the base 20 through the adapter 40. The side of the adapter 40 can be connected to the corresponding side of the top seat 10 and the base 20, and the second base 341 is fixed in the top seat 10 and the base 20 to ensure the connection rigidity between the second base 341 and the top seat 10 and the base 20.

[0051] The specific installation method of this application is as follows.

[0052] 1. Insert the bottom end of the outer carbon fiber rod 32 into the first through hole 333 on the first base 331 and abut against the positioning ring 334, and use screws to install the first base 331 on the top surface of the base 20;

[0053] 2. Insert the top of the outer carbon fiber rod 32 into the first through hole 333 on the other first base 331 and abut against the positioning ring 334, and use screws to install the other first base 331 on the bottom surface of the top base 10;

[0054] 3. Extend the inner carbon fiber rod 31 into the outer carbon fiber rod 32 to form a double-layer nested structure;

[0055] 4. Sleeve the bottom end of the inner carbon fiber rod 31 onto the second protrusion 342 of the second base 341, connect the second base 341 to the adapter 40, and then connect the adapter 40 to the bottom surface of the base 20;

[0056] 5. Sleeve the top end of the inner carbon fiber rod 31 onto the second protrusion 342 of another second base 341, connect the other second base 341 to the corresponding adapter 40, and then connect the adapter 40 to the bottom surface of the top seat 10; the outer carbon fiber rod 32 and the inner carbon fiber rod 31 form a double-layer carbon fiber nested structure, and connect the remaining outer carbon fiber rods 32 and inner carbon fiber rods 31 to the top seat 10 and the base 20 according to the above steps.

[0057] Those skilled in the art should understand that the present invention is not limited to the above embodiments, and the above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, and these changes and improvements fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A truss-type space camera support structure, characterized in that: The invention comprises a top seat (10) and a base (20), wherein the top seat (10) and the base (20) are connected via a plurality of inner carbon fiber rods (31) and outer carbon fiber rods (32), each inner carbon fiber rod (31) is arranged inside a corresponding outer carbon fiber rod (32) to form a truss rod (30), and the two ends of the outer carbon fiber rod (32) are respectively connected to the top seat (10) and the base (20) via a first mounting joint (33).

2. The support structure for a truss-type space camera according to claim 1, characterized in that: The first mounting joint (33) comprises a first base (331), one side of the first base (331) is connected to the top seat (10) or the base (20), the other side of the first base (331) protrudes outward to form a first protrusion (332), the upper side of the first protrusion (332) away from the first base (331) is recessed inward to form a first through hole (333), and the first through hole (333) extends to the side of the first base (331) connected to the top seat (10) or the base (20).

3. The support structure for a truss-type space camera according to claim 2, characterized in that: A positioning ring (334) is provided in the end of the first through hole (333) away from the first protrusion (332), and the outer carbon fiber rod (32) abuts against the top surface of the positioning ring (334).

4. The support structure for a truss-type space camera according to claim 2, characterized in that: A second through hole (11) is provided on the top seat (10) and the base seat (20) at a position corresponding to the first through hole (333); the first through hole (333) and the second through hole (11) are coaxially arranged; and the second through hole (11) and the positioning ring (334) have the same diameter.

5. The support structure for a truss-type space camera according to claim 2, characterized in that: The two ends of the inner carbon fiber rod (31) respectively pass through the corresponding first through hole (333) and the second through hole (11), and are connected to the top seat (10) and the base seat (20) via a second mounting joint (34).

6. The support structure for a truss-type space camera according to claim 5, characterized in that: The second mounting joint (34) comprises a second base (341), the top surface of the second base (341) protrudes outward to form a second protrusion (342), and the end of the inner carbon fiber rod (31) is sleeved on the second protrusion (342).

7. The support structure for a truss-type space camera according to claim 6, characterized in that: The second base (341) is fixed in the top seat (10) and the base (20) through an adapter (40); the side surfaces of the adapter (40) can be connected to the corresponding side surfaces of the top seat (10) and the base (20), and the second base (341) is fixed in the top seat (10) and the base (20).

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