A space camera carbon fiber bipod support device and a space camera device

Abstract

The present application relates to a kind of space camera carbon fiber bipod support device and space camera device, space camera carbon fiber bipod support device includes upper base, lower base, carbon fiber rod, lower base is two, each lower base is hinged on one carbon fiber rod, carbon fiber rod upper end is hinged on upper base;Carbon fiber rod is cylindrical, the side wall of carbon fiber rod includes multiple groups of composite lay-up, each group of composite lay-up includes the damping layer and carbon fiber layer of composite layer lamination bonding layer.By adjusting the lay-up material, lay-up thickness, lamination mode etc. of carbon fiber rod, the stiffness and damping adjustment of carbon fiber rod can be realized, so as to adapt to the requirements of different camera loads;Carbon fiber bipod support device can reduce the overall vibration frequency of camera load, in the form of overall vibration of camera load, most of the vibration energy is absorbed, so as to reduce the vibration energy acting on the weak part of camera itself, improve the vibration environment adaptability of camera load.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace remote sensing technology, and particularly relates to a space camera carbon fiber bipod supporting device and a space camera device. BACKGROUND

[0002] With the development of aerospace remote sensing technology, remote sensing cameras are increasingly used, and with the improvement of camera resolution, the requirements for camera installation conditions are also increasing. Currently, there are two main problems, first, due to design, processing, assembly and other limitations, the flatness of the camera mounting surface of the satellite platform cannot meet the requirements of high-resolution cameras; second, as cameras become more complex, the tolerance of cameras to vibration environment is gradually reduced.

[0003] To solve the above problems, the space camera currently starts to use a 3-point bipod vibration reduction device for support, which commonly includes a metal flexible leg and a metal damping truss. The metal flexible leg can realize stress unloading and deformation decoupling of the camera, but the flexible leg is prone to structural instability during the launch active stage, which poses a safety hazard, so a locking design during launch and an unlocking design after entering orbit are often used to support, but the additional unlocking device is high in cost and heavy in weight, increasing an additional launch cost, which is very costly. The metal damping truss can effectively isolate vibration during camera launch and realize decoupling installation requirements of the camera, but the assembly process of the existing damping truss is complex, often requiring multiple glue injection, which is complex in production process and long in production cycle, and is not suitable for wide promotion. SUMMARY

[0004] The present application provides a space camera carbon fiber bipod supporting device and a space camera device to solve one or several technical problems existing in the prior art.

[0005] The technical solution of the present application to solve the above technical problems is as follows: a space camera carbon fiber bipod supporting device, comprising an upper base, a lower base and a carbon fiber rod, the lower base is two, each lower base is hinged with a carbon fiber rod, the upper end of the carbon fiber rod is hinged on the upper base; the carbon fiber rod is in a cylindrical shape, the side wall of the carbon fiber rod comprises a plurality of composite layers, each composite layer comprises a damping layer and a carbon fiber layer which are laminated and bonded.

[0006] The beneficial effects of the present application are: in the structural design with higher dimensional stability requirements, in order to avoid the influence of external deformation on the dimensional stability of the high stability structure, the high stability structure and the external spacecraft structure must be decoupled, and the high stability structure is generally required to be static, and the static installation mode is referred to as kinematic installation. The space camera carbon fiber bipod support device provides a static installation mode for the camera load, and the kinematic support principle is the classic Hexapod support, mainly solving the installation decoupling and vibration resistance of the space camera. The space camera carbon fiber bipod support device adopts carbon fiber rods, and the stiffness and damping of the carbon fiber rods can be adjusted by adjusting the layering material, layering thickness and layering mode of the carbon fiber rods, so as to adapt to the requirements of different camera loads; the carbon fiber bipod support device can reduce the overall vibration frequency of the camera load, and most of the vibration energy can be absorbed in the form of overall vibration of the camera load, so as to reduce the vibration energy acting on the weak parts of the camera itself and improve the vibration resistance of the camera load.

[0007] Based on the above technical solutions, the present application can be further improved as follows.

[0008] Further, the side wall of the carbon fiber rod is from the outer surface of the side wall to the inner surface of the side wall, and the laying sequence of the damping layer and the carbon fiber layer in each group of composite layers is: +45° carbon fiber layer, damping layer, -45° carbon fiber layer, 0° carbon fiber layer, damping layer, -90° carbon fiber layer.

[0009] The beneficial effects of the above further scheme are: the carbon fiber layer and the damping layer structure with different laying directions can quickly attenuate vibration, and can effectively reduce the dynamic response of the camera load in the active launch section.

[0010] Further, the side wall of the carbon fiber rod includes four groups of composite layers.

[0011] The beneficial effects of the above further scheme are: the four groups of composite layers can further reduce the overall vibration frequency of the camera load.

[0012] Further, in each group of composite layers, the thickness of the carbon fiber layer is 0.125mm, and the thickness of the damping layer is 0.125mm.

[0013] Further, the carbon fiber layer is composed of carbon fiber material and cyanate no-woven cloth.

[0014] Further, the damping layer is made of butyl, acrylate, polysulfide, butyronitrile and silicone rubber, polyurethane, polyvinyl chloride or epoxy resin.

[0015] Further, the two ends of the carbon fiber rod are respectively inserted and fixed with rod joints, the rod joint is in a U-shaped structure, the upper base and the lower base are respectively provided with a hinged plate, the hinged plate is provided with a hinged hole, the rod joints at the two ends of the carbon fiber rod are respectively sleeved on the hinged plates of the upper base and the lower base, and the hinged rods pass through the rod joints and the hinged holes of the U-shaped structure to realize the hinging of the rod joints and the hinged plates.

[0016] The beneficial effect of the above further scheme is that the cooperation of the rod joint in a U-shaped structure and the hinged plate can realize the stable hinging cooperation between the upper and lower bases and the hinged plates.

[0017] Further, the two ends of the carbon fiber rod are respectively inserted and fixed with rod joints, the rod joint is in a U-shaped structure, the upper base and the lower base are respectively provided with a hinged plate, the hinged plate is provided with a hinged hole, the rod joints at the two ends of the carbon fiber rod are respectively sleeved on the hinged plates of the upper base and the lower base, and the hinged rods pass through the rod joints and the hinged holes of the U-shaped structure to realize the hinging of the rod joints and the hinged plates.

[0018] The beneficial effect of the above further scheme is that the cooperation of the rod joint in a U-shaped structure and the hinged plate can realize the stable hinging cooperation between the upper and lower bases and the hinged plates.

[0019] Further, the two ends of the carbon fiber rod are respectively inserted and fixed with rod joints, the rod joint is in a U-shaped structure, the upper base and the lower base are respectively provided with a hinged plate, the hinged plate is provided with a hinged hole, the rod joints at the two ends of the carbon fiber rod are respectively sleeved on the hinged plates of the upper base and the lower base, and the hinged rods pass through the rod joints and the hinged holes of the U-shaped structure to realize the hinging of the rod joints and the hinged plates.

[0020] The beneficial effect of the above further scheme is that the cooperation of the rod joint in a U-shaped structure and the hinged plate can realize the stable hinging cooperation between the upper and lower bases and the hinged plates.

[0021] A space camera device comprises the space camera carbon fiber bipod support device, and further comprises a space camera and a support plate, wherein the support plate is circular and is provided with three space camera carbon fiber bipod support devices at the bottom, the three space camera carbon fiber bipod support devices are uniformly arranged along the circumference of the support plate, the upper base of the space camera carbon fiber bipod support device is fixed to the lower surface of the support plate, and the space camera is fixed to the upper surface of the support plate.

[0022] The space camera device can solve the technical problems of installation decoupling and emission vibration resistance of a space camera, is composed of three uniformly distributed bipod assemblies in a circle, forms a typical Hexapod support, and the support system comprises six rods and twelve connecting points, wherein the twelve connecting points adopt a ball hinge mode, and the influence of insufficient flatness and thermal deformation on a remote sensing camera is eliminated through rotation of the ball hinges at the two ends of the support rods. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 FIG. 1 is a perspective view of a space camera carbon fiber bipod support device according to the present application;

[0024] Figure 2 This is a schematic diagram of the main structure of the carbon fiber bipod support device for the space camera of the present invention;

[0025] Figure 3 for Figure 2 Schematic diagram of the cross-sectional structure of DD;

[0026] Figure 4 This is a cross-sectional view of the carbon fiber rod of the present invention.

[0027] Figure 5 This is a schematic diagram of the space camera device of the present invention viewed from below;

[0028] Figure 6 This is a schematic diagram of the structure used in the experimental examples of the present invention;

[0029] Figure 7 The response curve of the sinusoidal vibration in the X direction of this invention;

[0030] Figure 8 This is the response curve of the sinusoidal vibration in the Y direction of the present invention;

[0031] Figure 9 This is the response curve of the Z-axis sinusoidal vibration of the present invention.

[0032] The attached diagram lists the components represented by each number as follows:

[0033] 1. Upper base; 2. Lower base;

[0034] 3. Carbon fiber rod; 31. +45° carbon fiber layup; 32. Damping layup; 33. -45° carbon fiber layup; 34. 0° carbon fiber layup; 35. -90° carbon fiber layup;

[0035] 4. Rod joint; 5. Hinge plate; 6. Ball joint; 7. Hinge rod; 8. Support plate; 9. Metal plate; 91. Mounting bracket; 92. Measuring point; 93. Metal cylinder. Detailed Implementation

[0036] The principles and features of the present invention are described below with reference to the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0037] like Figures 1-4As shown in the drawings, the carbon fiber bipod support device of the space camera of the embodiment comprises an upper base 1, a lower base 2, and a carbon fiber rod 3. The lower base 2 is two, and each lower base 2 is hinged with a carbon fiber rod 3. The upper end of the carbon fiber rod 3 is hinged on the upper base 1. The carbon fiber rod 3 is in a cylindrical shape, and the side wall of the carbon fiber rod 3 comprises a plurality of composite layers. Each composite layer comprises a damping layer 32 and a carbon fiber layer which are laminated and bonded.

[0038] As shown in the drawings, Figure 4 As shown in the drawings, the side wall of the carbon fiber rod 3 of the embodiment comprises a plurality of composite layers from the outer surface of the side wall to the inner surface of the side wall. The laying sequence of the damping layer 32 and the carbon fiber layer in each composite layer is: +45° carbon fiber layer 31, damping layer 32, -45° carbon fiber layer 33, 0° carbon fiber layer 34, damping layer 32, -90° carbon fiber layer 35. Each carbon fiber layer and damping layer is fixed by bonding. The carbon fiber layer and damping layer structure with different laying directions can quickly attenuate the vibration and effectively reduce the dynamic response of the camera load in the active launch segment.

[0039] A preferred scheme of the embodiment is that the side wall of the carbon fiber rod 3 comprises four composite layers, i.e. one cycle of six layers, and four cycles in total. The use of four composite layers can further reduce the overall vibration frequency of the camera load. Of course, three, five or other multiple composite layers can also be set according to the needs, and the stiffness and damping of the carbon fiber rod can be adjusted by adjusting the thickness of the composite layer.

[0040] Specifically, in each composite layer, the thickness of the carbon fiber layer is 0.125mm, and the thickness of the damping layer 32 is 0.125mm.

[0041] A further scheme of the embodiment is that the carbon fiber layer is composed of carbon fiber material and cyanate without weft cloth. The carbon fiber material here can also be M55J fiber, M40, T700, T800 and other carbon fiber materials.

[0042] The damping layer 32 is made of butyl, acrylate, polysulfide, butyronitrile and silicone rubber, polyurethane, polyvinyl chloride or epoxy resin.

[0043] Specifically, as shown in the drawings, Figures 1-3As shown, the two ends of the carbon fiber rod 3 of the embodiment are respectively inserted and fixed with rod joints 4, the rod joints 4 are in U-shaped structure, the upper base 1 and the lower base 2 are respectively provided with hinged plates 5, the hinged plates 5 are provided with hinged holes, the rod joints 4 at the two ends of the carbon fiber rod 3 are respectively sleeved on the hinged plates 5 of the upper base 1 and the lower base 2, and the hinged plates 5 and the rod joints 4 are hinged through the hinged rod 7 passing through the rod joints 4 in U-shaped structure and the hinged holes. The rod joints in U-shaped structure and the hinged plates are matched to realize the stable hinged matching between the upper base and the lower base and the hinged plates.

[0044] As shown in the drawings, Figures 1-3 The two ends of the upper base 1 of the embodiment are respectively provided with one hinged plate 5, each of the lower bases 2 is provided with one hinged plate 5, the hinged plates 5 on the upper base 1 and the lower base 2 are located in the same vertical plane, and the hinged rod 7 and the hinged holes on the hinged plates 5 are hinged through bearings or ball hinges 6. The bearings or ball hinges are arranged to make the hinge more stable and flexible.

[0045] As shown in the drawings, Figure 1 and Figure 2 The upper base 1 and the lower base 2 of the embodiment are arranged in parallel, and a plurality of connecting channels are arranged on the upper base 1 and the lower base 2. The connecting channels arranged on the upper base and the lower base can be used to realize the connection and fixation with a camera or other support structures.

[0046] In the structural design with high dimensional stability requirement, in order to avoid the influence of external deformation on the dimensional stability of the high stability structure, the high stability structure and the external spacecraft structure must be decoupled in deformation, and the high stability structure is generally required to be static, and this static installation method is called kinematic installation. The space camera carbon fiber bipod support device of the embodiment provides a static installation method for the camera load, and the kinematic support principle is the classic Hexapod support, which mainly solves two problems of installation decoupling and vibration resistance of the space camera. The space camera carbon fiber bipod support device of the embodiment adopts carbon fiber rods, and the stiffness and damping of the carbon fiber rods can be adjusted by adjusting the layering material, layering thickness and layering mode of the carbon fiber rods, so as to adapt to the requirements of different camera loads; the carbon fiber bipod support device can reduce the overall vibration frequency of the camera load, absorb most of the vibration energy in the form of overall vibration of the camera load, thereby reducing the vibration energy acting on the weak parts of the camera, and improving the vibration resistance of the camera load.

[0047] As shown in the drawings, Figure 5As shown, the embodiment also provides a space camera device, comprising the above-mentioned space camera carbon fiber bipod support device, further comprising a space camera and a support plate 8, the support plate 8 is circular and is provided with three space camera carbon fiber bipod support devices at the bottom, the three space camera carbon fiber bipod support devices are uniformly arranged along the circumference of the support plate 8; the upper base 1 of the space camera carbon fiber bipod support device is fixed to the lower surface of the support plate 8, and the space camera is fixed to the upper surface of the support plate 8.

[0048] The space camera device of the embodiment can solve the technical problems of mounting decoupling and resistance to launch vibration environment of the space camera, and is composed of three bipod assemblies uniformly distributed in the circumference to form a typical Hexapod support, the support system has six rods and twelve connection points, the twelve connection points are in the form of spherical hinges, and the influence of insufficient flatness and thermal deformation on the remote sensing camera is eliminated by rotating the spherical hinges at both ends of the support rod. The bipod assembly is composed of two carbon fiber rods, two lower bases and one upper base. Four spherical hinge nodes are designed for each bipod assembly, four identical joint bearings are selected for implementation, the two carbon fiber rods are completely identical, and the bases are also completely identical, so that the universality and replaceability of the design are strong.

[0049] Test example

[0050] In order to verify the dynamic characteristics of the space camera carbon fiber bipod support device of the embodiment, a test verification is performed. A triangular metal plate is used to simulate the camera body of the space camera, and a metal cylinder 93 is used to simulate the secondary lens barrel of the camera, as shown in Figure 6 As shown, the triangular metal plate 9 is installed on the three space camera carbon fiber bipod support devices through the inverted V-shaped mounting bracket 91, and the measuring points 92 are placed at the top of the three supports respectively to measure the response curves of the bottom and top of the supports. The vibration table used in this test is a space hill 15-ton vibration table, model: MPA3324 / H1248A, VR control instrument, model: VR9500. The test direction is as shown in Figure 6 As shown, it is X / Y / Z three directions respectively.

[0051] The X-direction sinusoidal vibration is as shown in Figure 7 As shown, CH4, CH7 and CH10 are the X-direction sinusoidal response curves of the top of the three supports, and the amplification at the top of the supports is less than 2 times. There is no obvious resonance peak, the vibration peak is very flat, and the damping is large.

[0052] The Y-direction sinusoidal vibration is as shown in Figure 8 As shown, CH5, CH8 and CH11 are the Y-direction sinusoidal response curves of the top of the three supports, and the amplification at the top of the supports is less than 2.5 times. There is no obvious resonance peak, the vibration peak is very flat, and the damping is large.

[0053] Z-directional sinusoidal vibration is as shown in Figure 9 As shown in the figure, CH6, CH9, CH12 are three Z-directional sinusoidal response curves of supporting top, and it can be seen that there is no obvious resonance peak and the vibration peak is very gentle with large damping when the supporting top is enlarged less than 1.5 times.

[0054] It can be seen from the vibration test result that the spatial camera carbon fiber bipod supporting device of the embodiment can provide necessary deformation stress unloading and good vibration reduction for the camera equipment, the system damping is large, and the vibration response at the camera mounting point position is not obviously enlarged.

[0055] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0056] In addition, the terms "first", "second" are only for descriptive purpose, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise specifically limited.

[0057] In the present application, unless otherwise specifically defined and limited, the terms "mounting", "connection", "connection", "fixing" and the like should be understood in a broad sense, for example, it can be fixed connection, or detachable connection, or integral; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium, it can be the internal communication of two elements or the interaction relationship of two elements, unless otherwise specifically limited. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0058] In the present application, unless otherwise explicitly specified and limited, a first feature is "on" or "under" a second feature can mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature is "over", "above" and "on top of" the second feature can mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is horizontally higher than the second feature. The first feature is "under", "below" and "underneath" the second feature can mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is horizontally lower than the second feature.

[0059] In the description of the present application, the description of the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in one or more embodiments or examples. In addition, the person skilled in the art can combine and combine the different embodiments or examples described in the present application and the features of the different embodiments or examples without contradiction.

[0060] Although the embodiments of the present application have been shown and described above, it is understood that the above-described embodiments are exemplary and are not to be construed as limiting the present application, and the person skilled in the art can make changes, modifications, replacements and variations to the above-described embodiments within the scope of the present application.

Claims

1. A space camera device, characterized in that, The device includes a carbon fiber bipod support for a space camera, a space camera, and a support plate. The carbon fiber bipod support for the space camera includes an upper base, a lower base, and a carbon fiber rod. There are two lower bases, and a carbon fiber rod is hinged to each lower base. The upper end of the carbon fiber rod is hinged to the upper base. The carbon fiber rod is cylindrical, and the sidewall of the carbon fiber rod includes multiple sets of composite plies. Each set of composite plies includes a composite laminated and bonded damping ply and a carbon fiber ply. The sidewall of the carbon fiber rod extends from the outer surface of the sidewall to the inner surface of the sidewall. The laying sequence of the damping layup and the carbon fiber layup in each composite layup is as follows: +45° carbon fiber layup, damping layup, -45° carbon fiber layup, 0° carbon fiber layup, damping layup, -90° carbon fiber layup. The support plate is circular and has three carbon fiber bipod support devices for space cameras at its bottom. The three carbon fiber bipod support devices for space cameras are evenly arranged along the circumference of the support plate. The upper base of the carbon fiber bipod support device for space cameras is fixed to the lower surface of the support plate, and the space camera is fixed to the upper surface of the support plate. The sidewall of the carbon fiber rod includes four sets of composite lay-ups, with each six lay-ups forming one cycle, for a total of four cycles; In each composite layup, the thickness of the carbon fiber layup is 0.125 mm, and the thickness of the damping layup is 0.125 mm. The carbon fiber layup is composed of carbon fiber material and cyanate ester nonwoven fabric; The damping layer is made of butyl, acrylate, polysulfide, nitrile and silicone rubber, polyurethane, polyvinyl chloride or epoxy resin.

2. The space camera device according to claim 1, characterized in that, The carbon fiber rod has rod connectors fixed at both ends. The rod connectors are U-shaped. The upper base and the lower base are respectively provided with hinge plates. The hinge plates are provided with hinge holes. The rod connectors at both ends of the carbon fiber rod are respectively sleeved on the hinge plates of the upper base and the lower base. The hinge is achieved by the hinge rod passing through the U-shaped rod connector and the hinge hole.

3. The space camera device according to claim 2, characterized in that, Each of the upper bases has a hinge plate at both ends, and each of the lower bases has a hinge plate. The hinge plates on the upper bases and the hinge plates on the lower bases are located in the same vertical plane. The hinge rod is hinged to the hinge hole on the hinge plate by a bearing or a ball joint.

4. The space camera device according to claim 1, characterized in that, The upper base and the lower base are arranged in parallel, and each of the upper base and the lower base is provided with multiple connecting channels.

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