Supporting structure for truss type space camera

Abstract

The utility model discloses a supporting structure for a truss type space camera, which relates to the technical field of space remote sensing and comprises a top seat and a bottom seat which 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 utility model, the installation mode of the double-layer nested carbon fiber rod 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 layered rod system layout is not suitable.

Description

TECHNICAL FIELD

[0001] The utility model relates to space remote sensing technical field especially relates to a kind of for truss type space camera support structure. BACKGROUND

[0002] Support structure is the core bearing unit of space camera optical machine system, provides installation interface and positioning reference for including mirror, focal plane and other optical and photoelectric imaging subsystem, its size precision, thermal structure stability and rigidity and other performances have vital role to guarantee the imaging quality of camera.In addition, sub-meter super large width camera gradually develops from single development to batch development, to meet the demand of commercial remote sensing satellite constellation for high-resolution mass data acquisition, so higher requirements are put forward to camera support structure, not only to meet the performance index of high lightweight ratio, high stability, but also require it to have good processing and assembly process.

[0003] Current large-aperture space camera support frame generally adopts truss type rod system structure and or frame type plate system structure, rod system structure generally adopts carbon fiber composite material as body and titanium alloy joint to be made by adhesive bonding process, with high specific stiffness, good material process and good space environment stability, but in the space camera with length-width ratio exceeding 1.4, to ensure the dynamic stiffness of whole machine, rod system support structure will adopt multi-layer installation mode, considering that different optical systems have different optical designs, multi-layer installation mode has certain limitation in higher space size requirement.

[0004] Therefore, the person skilled in the art provides a truss type space camera support structure to solve the problems raised in the background art. UTILITY MODEL CONTENTS

[0005] The utility model provides a truss type space camera support structure to solve the problem of insufficient dynamic stiffness of large length-width ratio space camera under the condition that space requirements are high and layered rod system installation mode is not conducive.

[0006] To achieve the above object, the utility model provides the following technical scheme:

[0007] The utility model discloses a truss type space camera support structure, which comprises a top seat and a bottom seat, the top seat and the bottom seat are connected by a plurality of truss rods, the bottom seat is used for installing a main mirror assembly and a three-mirror assembly, the top seat is used for installing a secondary mirror assembly and a focal plane assembly,

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

[0009] Further, the outer carbon fiber rod is connected with the top base and the bottom base through the first mounting joint at two ends respectively.

[0010] Further, the first mounting joint comprises a first base, one side of the first base is connected with the top base or the bottom 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, the first through hole extends to the side of the first base connected with the top base or the bottom base.

[0011] Further, a positioning ring is arranged 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] Further, the top base and the bottom base are provided with a second through hole corresponding to the position of the first through hole, the first through hole and the second through hole are coaxially arranged, and the second through hole has the same diameter as the positioning ring.

[0013] Further, the two ends of the inner carbon fiber rod pass through the corresponding first through hole and the second through hole, and are connected with the top base and the bottom base through the second mounting joint.

[0014] Further, the second mounting joint comprises 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] Further, the second base is fixed in the top base and the bottom base through an adapter, the side surface of the adapter can be connected with the corresponding side surface of the top base and the bottom base, and the second base is fixed in the top base and the bottom base.

[0016] In the above technical solution, the utility model provides a kind of for truss type space camera support structure, with following beneficial effects:

[0017] 1, the space utilization of space camera is increased in limited space by using this installation mode, and the support structure is more compact.

[0018] 2, the dynamic stiffness of the whole machine is greatly improved, and the stability of space camera is guaranteed.

[0019] 3, the installation mode of double-layer nested carbon fiber rod is adopted, in the case that the size requirement of space camera is smaller and is not suitable for layered rod system layout, the stability of space camera is greatly improved. DETAILED DESCRIPTION

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings.

[0021] Figure 1 A front view of a support structure for a truss type space camera according to Embodiment 1 of the present application;

[0022] Figure 2 A front view of a support structure for a truss type space camera according to Embodiment 1 of the present application; Figure 1 An enlarged structural schematic view of part A in the middle;

[0023] Figure 3 An enlarged structural schematic view of part B in the middle; Figure 1 An enlarged structural schematic view of part B in the middle;

[0024] Figure 4 An enlarged structural schematic view of part B in the middle; Figure 2 A connection structure diagram of the first mounting joint and the outer carbon fiber rod;

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

[0026] Explanation of reference signs:

[0027] 10, top base;

[0028] 20, bottom 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 make those skilled in the art better understand the technical solutions of the present application, the present application will be further described in detail below with reference to the drawings.

[0034] Referring to Figure 1 ;

[0035] The utility model discloses a kind of for truss type space camera support structure, including top seat 10 and base 20, the top seat 10 and base 20 are connected by multiple truss rods 30;The base 20 is used to install main mirror assembly and three mirror components, top seat 30 is used to install secondary mirror assembly and focal plane component,

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

[0037] Specific use, by the double-layer structure of inside and outside nesting formed by outer carbon fiber rod 32 and inner carbon fiber rod 31, to increase the rigidity of overall support structure, increase the space utilization of space camera in limited space, support structure is more compact.Meanwhile, the dynamic stiffness of whole machine is greatly improved, and the stability of space camera is ensured.

[0038] Referring to Figures 1-2 , 4 shows;

[0039] Further, the outer carbon fiber rod 32 is connected with the top seat 10 and the base 20 through the first mounting joint 33 at both ends respectively. The first mounting joint 33 is used to connect 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 connected by adhesive.

[0040] The first mounting joint 33 includes a first base 331, one side of the first base 331 is connected with 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 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 with the top seat 10 or the base 20.

[0041] The outer carbon fiber rod 32 can be inserted into the first through hole 333 and fixed to ensure the connection stiffness of the outer carbon fiber rod 32 with the top seat 10 and the base 20 through the first mounting structure 33.

[0042] A positioning ring 334 is arranged 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 avoid the deviation of the outer carbon fiber rod 32, and effectively ensures the overall stiffness. The positioning ring 334 and the first base 331 are integrally formed.

[0044] Referring to Figures 1-3 , 5 shows;

[0045] The second through hole 11 is coaxially arranged with the first through hole 333.

[0046] The two ends of the inner carbon fiber rod 31 pass through the corresponding first through hole 333 and second through hole 11 respectively, and are connected between the top seat 10 and the bottom seat 20 through the second mounting joint 34. The inner carbon fiber rod 31 is adhesively connected with the second mounting joint 34.

[0047] The two ends of the inner carbon fiber rod 31 pass through the corresponding first through hole 333 and second through hole 11 respectively, and are connected between the top seat 10 and the bottom seat 20 through the second mounting joint 34. The inner carbon fiber rod 31 is adhesively connected with the second mounting joint 34.

[0048] The second mounting joint 34 comprises a second base 341, the top surface of the second base 341 outwardly protrudes 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 bottom seat 20.

[0049] The two ends of the inner carbon fiber rod 31 are sleeved on the corresponding second protrusions 342 and can abut against the corresponding second bases 341, thereby realizing the fixed connection between the inner carbon fiber rod 31 and the top seat 10 and the bottom seat 20, and improving the overall connection stiffness.

[0050] The second base 341 is fixed in the top seat 10 and the bottom seat 20 through the adapter 40, the side surface of the adapter 40 can be connected with the corresponding side surface of the top seat 10 and the bottom seat 20, and the second base 341 is fixed in the top seat 10 and the bottom seat 20, so as to ensure the connection stiffness of the second base 341 and the top seat 10 and the bottom seat 20.

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

[0052] 1, the bottom end of the outer carbon fiber rod 32 is inserted into the first through hole 333 on the first base 331 and abuts against the positioning ring 334, and the first base 331 is installed on the top surface of the bottom seat 20 by using a screw;

[0053] 2, the top of the outer carbon fiber rod 32 is inserted into the first through hole 333 on the other first base 331 and abuts against the positioning ring 334, and the other first base 331 is installed on the bottom surface of the top seat 10 by using a screw;

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

[0055] 4. The bottom end of the inner carbon fiber rod 31 is sleeved on the second protrusion 342 of the second base 341, the second base 341 is connected with the adapter 40, and then the adapter 40 is connected with the bottom surface of the base 20;

[0056] 5. The top end of the inner carbon fiber rod 31 is sleeved on the second protrusion 342 of another second base 341, the other second base 341 is connected with the corresponding adapter 40, and then the adapter 40 is connected with the bottom surface of the top base 10; the outer carbon fiber rod 32 and the inner carbon fiber rod 31 form a double-layer carbon fiber nested structure, and the remaining outer carbon fiber rod 32, the inner carbon fiber rod 31 and the top base 10 and the base 20 are connected according to the above steps.

[0057] Those skilled in the art should understand that the present application is not limited to the above embodiments, and the above embodiments and descriptions in the specification are only to illustrate the principles of the present application, and various changes and improvements can be made without departing from the spirit and scope of the present application, and these changes and improvements all fall within the scope of the claimed present application. The scope of protection of the present application is defined by the appended claims and their equivalents.

Claims

1. A support structure for a truss-type space camera, characterized in that, It includes a top seat (10) and a base (20), which are connected by multiple truss rods (30); Each of the truss rods (30) includes an inner carbon fiber rod (31) and an outer carbon fiber rod (32), wherein the inner carbon fiber rod (31) is disposed inside the outer carbon fiber rod (32).

2. The support structure for a truss-type space camera according to claim 1, characterized in that: The two ends of the outer carbon fiber rod (32) are connected to the top seat (10) and the base (20) respectively through the first mounting joint (33).

3. A support structure for a truss-type space camera according to claim 2, characterized in that: The first mounting connector (33) includes a first base (331), one side of which is connected to a top seat (10) or a base (20), and the other side of the first base (331) protrudes outward to form a first protrusion (332). The 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).

4. A support structure for a truss-type space camera according to claim 3, characterized in that: A positioning ring (334) is provided at 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).

5. A support structure for a truss-type space camera according to claim 3, characterized in that: The top seat (10) and the base (20) are each provided with a second through hole (11) corresponding to the position of the first through hole (333). The first through hole (333) and the second through hole (11) are coaxially arranged, and the diameter of the second through hole (11) is the same as that of the positioning ring (334).

6. A support structure for a truss-type space camera according to claim 3, characterized in that: The two ends of the inner carbon fiber rod (31) pass through the corresponding first through hole (333) and second through hole (11) respectively, and are connected to the top seat (10) and the base (20) through the second mounting joint (34).

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

8. A support structure for a truss-type space camera according to claim 7, characterized in that: The second base (341) is fixed inside the top seat (10) and the base (20) by means of an 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 inside the top seat (10) and the base (20).

Images