Whole-satellite damping device based on dynamic vibration absorption plate and crab claw type truss configuration

Abstract

The invention provides a whole-satellite damping device based on a dynamic vibration absorption plate and crab claw type truss configuration. The whole-satellite damping device is composed of a bottom plate, a crab claw type truss and the dynamic vibration absorption plate, wherein the crab claw type truss is connected with a light-weight connector through hollow carbon fiber square pipes (including an inclined upper rod, a transverse rod, a vertical rod and the like), and a 100 L large-capacity storage box is borne through a storage box flange; the vibration absorption plate is of a non-reinforcing-rib structure composed of a honeycomb plate with the thickness of 20 mm and an aluminum skin with the thickness of 0.3 mm, the vibration absorption plate is in single-point connection with a truss inclined upper rod connector through an embedded part in the plate, the lowest point of rigidity in the axial direction of the storage box is formed, and sine vibration energy is absorbed in a concentrated mode through the drum leather effect. The bottom plate serves as a foundation support and is in rigid connection with the truss main force bearing rod through the connector, and mechanical conduction stability is ensured.

Description

Technical Field

[0001] The present invention relates to the field of aerospace, and in particular to a whole-satellite vibration reduction device based on a dynamic vibration absorbing plate and a crab claw truss structure. Background Art

[0002] In the aerospace industry, the design of load-bearing structures for large satellite tanks is crucial. Currently, load-bearing structures for individual large tanks primarily include cylinder-type, box-plate-type, and truss-type primary load-bearing structures. However, these existing structures all have significant drawbacks and are unable to meet the stringent requirements of modern satellites in terms of space utilization, structural weight, rigidity, and stability.

[0003] Figure 1 A schematic diagram of a conventional load-bearing cylinder-type large tank structure is shown. While this type of main load-bearing structure offers strong load-bearing capacity, it suffers from low space utilization and significant difficulty in arranging individual equipment, making it particularly unsuitable for large-volume small satellites. For example, in small satellites that need to carry multiple devices, the limited internal space of the cylinder structure severely restricts their proper installation and layout, leading to complex and cumbersome cabling between devices and increasing the difficulty and cost of overall satellite design.

[0004] Figure 2 A schematic diagram of a conventional box-panel-type large tank load-bearing structure is shown. While this box-panel-type main load-bearing structure offers high space utilization and facilitates the installation and layout of individual equipment, its high structural weight makes it unsuitable for satellites with high launch quality requirements. During satellite launch, increased weight directly increases launch costs, while excessive structural weight also impacts the overall performance and service life of the satellite. For example, the application of box-panel structures is significantly limited in satellite missions with strict launch quality requirements.

[0005] Figure 3 A schematic diagram of a conventional truss-type large tank load-bearing configuration is shown. While this truss-type primary load-bearing structure offers strong spatial load-bearing capacity and a low mass ratio, its overall stiffness and stability are poor, which can easily lead to excessive tank response. For example, when a satellite experiences the rigorous mechanical environment of a rocket's ascent phase, the truss structure's low stiffness and stability can cause significant displacement and vibration in the tank, leading to structural damage and potentially compromising the satellite's normal operation.

[0006] To sum up, the existing satellite large tank load-bearing structure has many shortcomings in practical applications. There is an urgent need for a new load-bearing structure design that can take into account multiple aspects such as space utilization, structural weight, stiffness stability, etc., to meet the aerospace field's demand for continuously improving satellite performance. Summary of the Invention

[0007] In view of the high mechanical response requirements of the 100L tank, the small size envelope of the satellite, the low proportion of structural mass, and the large number of single units in the cabin, the present invention proposes a whole-satellite configuration that combines a dynamic vibration-absorbing plate and a crab claw truss. The main structure of the satellite is composed of a crab claw truss. The overall truss mass is low, the space utilization is small, and the layout of single units in the cabin is convenient. The square truss surface provides a routing path for the cables of a single unit, which greatly shortens the routing path compared to the load-bearing cylinder type and box plate type, reducing the cable length and the performance loss of the cable during use. The dynamic vibration-absorbing plate is used to reduce the stiffness of the dynamic vibration-absorbing plate. At the same time, the dynamic vibration-absorbing plate is decoupled from the crab claw truss, causing it to produce a drum skin effect, which concentrates the power of the entire satellite on the dynamic vibration-absorbing plate, thereby reducing the response of the tank.

[0008] The present invention provides a whole-satellite vibration reduction device based on a dynamic vibration absorbing plate and a crab claw truss structure, which is characterized by comprising:

[0009] The bottom plate is used to carry the square trusses and is provided with a storage tank;

[0010] A square truss, comprising four crab claw trusses and a tank flange, for securing the tank, wherein the crab claw trusses are not directly connected to the vibration absorbing plate; and

[0011] The vibration absorbing plate is arranged on the square truss and is used for reducing vibration of the storage tank, wherein the vibration absorbing plate is configured as the lowest point of rigidity.

[0012] In one embodiment of the present invention, the four crab claw trusses of the square truss are arranged at the four corners of the bottom plate, and the crab claw trusses include:

[0013] Four hollow square tubes, including an upper inclined rod, a horizontal rod, a vertical rod, a lower inclined rod and a support leg, wherein the hollow square tubes do not directly contact the vibration absorbing plate;

[0014] The four connecting joints include a tank connecting joint, an inclined upper rod connecting joint, a cross bar joint and a bottom plate joint.

[0015] In one embodiment of the present invention, the connection relationship between the hollow square tube and the connecting joint is as follows:

[0016] The inclined upper rod is connected to the tank connection joint and the inclined upper rod connection joint;

[0017] The oblique lower rod is connected to the tank connection joint and the bottom plate joint;

[0018] The crossbar is connected to the tank connection joint and the crossbar joint;

[0019] The vertical rod is provided with an oblique upper rod connecting joint, a horizontal rod joint and a bottom plate joint;

[0020] The supporting legs are connected to the oblique lower rod and the base plate;

[0021] The tank connection nipple is connected to the tank flange.

[0022] In one embodiment of the present invention, the overall cross-sectional dimensions of the support legs and the oblique lower rod are much smaller than those of the oblique upper rod, the horizontal rod, the vertical rod and the oblique lower rod.

[0023] In one embodiment of the present invention, the tank flange includes four split flanges, which are screwed to one side of the tank connection joint of the crab claw truss by four screws and screwed to the other side of the tank connection joint of the crab claw truss by another four screws.

[0024] In one embodiment of the present invention, the tank flange is made of carbon fiber and is provided with angle pieces.

[0025] In one embodiment of the present invention, a cable routing path for a single satellite unit is provided on the surface of the square truss.

[0026] In one embodiment of the present invention, the hollow square tube is made of carbon fiber.

[0027] In one embodiment of the present invention, the vibration absorbing plate is connected to the oblique upper rod connecting joint via a plate embedded part, and the entire crab claw truss is not directly connected to the vibration absorbing plate.

[0028] In one embodiment of the present invention, the vibration absorbing plate is a honeycomb plate structure and is aluminum-skinned, wherein the vibration absorbing plate does not have reinforcing ribs.

[0029] The present invention has the following beneficial effects:

[0030] (1) By reducing the stiffness of the dynamic vibration absorbing plate (e.g., the vibration absorbing plate has the lowest stiffness point due to the skin + honeycomb panel structure and no reinforcement ribs), and decoupling the dynamic vibration absorbing plate from the crab claw truss (e.g., the crab claw truss is not directly connected to the vibration absorbing plate, that is, its main force transmission path, such as the connection point between the vertical rod and the lower inclined rod and the vibration absorbing plate, is separated), a drum skin effect is produced, which concentrates and dissipates the entire star stress on the dynamic vibration absorbing plate, thereby reducing the impact on the tank. In the case of strict structural quality requirements, the mechanical response of the tank is usually reduced by reinforcing the tank truss. However, this solution uses the dynamic vibration absorbing plate as an energy concentration area to reduce the tank response by reducing weight.

[0031] (2) The entire satellite adopts a truss structure. The large-section, thin-walled carbon fiber square rods ensure the overall rigidity of the truss and greatly reduce the structural weight. The crab claw truss structure provides a cable routing path for the entire satellite, reducing cable length. At the same time, the crab claw truss improves satellite space utilization and facilitates the installation of single units in the cabin. The central truss can effectively carry concentrated mass loads, such as large-capacity tanks. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 The figure shows a schematic diagram of a load-bearing structure of a large load-bearing cylinder type storage tank in the prior art;

[0033] Figure 2 It shows a schematic diagram of the load-bearing structure of a large box-plate storage tank in the prior art;

[0034] Figure 3 The figure shows a schematic diagram of a load-bearing structure of a truss-type large storage tank in the prior art;

[0035] Figure 4 A schematic diagram of a whole-satellite vibration reduction device based on a dynamic vibration absorbing plate and a crab claw truss structure in one embodiment of the present invention is shown; and

[0036] Figure 5 A schematic diagram of a square truss in one embodiment of the present invention is shown. DETAILED DESCRIPTION

[0037] In the following description, the present invention is described with reference to various embodiments. However, those skilled in the art will recognize that the embodiments may be implemented without one or more of the specific details or with other alternative and / or additional methods, materials, or components. In other cases, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring the inventive aspects of the present invention. Similarly, for purposes of explanation, specific numbers, materials, and configurations are set forth to provide a comprehensive understanding of the embodiments of the present invention. However, the present invention is not limited to these specific details.

[0038] In the present invention, each embodiment is only intended to illustrate the aspects of the present invention and should not be construed as limiting.

[0039] In this specification, reference to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. The appearances of the phrase "in one embodiment" in various places in this specification are not necessarily all referring to the same embodiment.

[0040] The present invention will be further described below with reference to the accompanying drawings in conjunction with specific embodiments.

[0041] Figure 4 A schematic diagram of a whole-satellite vibration reduction device based on a dynamic vibration absorbing plate and a crab claw truss structure in one embodiment of the present invention is shown.

[0042] Figure 5 A schematic diagram of a square truss in one embodiment of the present invention is shown.

[0043] like Figure 4 , as shown in FIG5 , in one embodiment of the present invention, the whole-star vibration reduction device includes:

[0044] The base plate 1 is equipped with tank mounting locations, and a square truss 2 is mounted on top. The crab-claw truss's support legs 8 and base plate joints 13 are mechanically secured to the base plate 1, forming the truss's bottom support. The base plate edge is provided with screw holes that match the lower ends of the support legs 8. The number of holes corresponds to the number of support legs (e.g., four support legs correspond to four sets of holes).

[0045] Baseplate 1 is the underlying support platform for the entire satellite structure. It receives tank loads and vibration energy transmitted from the crab claw truss and, through its own rigidity, distributes the force to the satellite's overall structure, becoming the terminal node of the satellite's force transmission path. It provides stable bottom support for the crab claw truss, ensuring the overall stability of the truss configuration.

[0046] The square truss 2 is composed of four crab claw trusses and a tank flange 9, wherein the crab claw trusses include:

[0047] Four hollow carbon fiber square tubes:

[0048] The inclined upper rod 4 is arranged at the top of the truss at an angle of 45 degrees;

[0049] Crossbar 5, arranged horizontally in the middle of the truss, forming a square frame;

[0050] Vertical rods 6, arranged vertically at the four corners of the truss, are the main force transmission path;

[0051] The oblique lower rod 7 is a bottom inclined rod that connects the lower end of the vertical rod 6 with the bottom plate joint 13;

[0052] Support leg 8, auxiliary support rod, connects the middle part of the lower inclined rod 7 and the base plate 1.

[0053] Four connection connectors:

[0054] The tank connection joint 10 has one side for mounting the tank flange 9, and the other three sides are connected to the upper inclined rod 4, the horizontal rod 5, and the lower inclined rod 7;

[0055] The oblique upper rod connecting joint 11 has one end connected to the upper end of the oblique upper rod 4 and the other end docked with the embedded part of the vibration absorbing plate 3 and connected to the upper end of the vertical rod 6;

[0056] Crossbar joint 12, T-shaped structure, connects crossbar 5 and the middle part of vertical bar 6;

[0057] The bottom plate joint 13 is fixed to the bottom plate 1 and connects the lower ends of the vertical rod 6 and the lower oblique rod 7.

[0058] The square truss 2 effectively carries concentrated mass loads, such as a 100L tank, through a multi-rod coordinated force transmission path (vertical rod 6 as the primary path, with lower diagonal rod 7 and support legs 8 as auxiliary force transmission), ensuring continuous mechanical transmission. The open truss structure improves cabin space utilization and facilitates the layout of individual equipment. The square truss surface also provides cable routing paths, saving cable length.

[0059] The tank flange 9 connects the crab claw truss 2 to the tank. To increase the connection area between the truss and the tank, the tank flange 9 comprises four separate flanges. These are screwed to the crab claw truss's tank connection joint on one side with four screws and to the other side with another four screws. To enhance rigidity, the tank flange 9 is equipped with carbon fiber angle pieces. The tank flange 9 also provides a mounting interface with the tank. To ensure sufficient rigidity, reduce the amplification factor of the sinusoidal vibration response, and based on the principle of weight reduction, in one embodiment of the present invention, the tank flange 9 is made of carbon fiber M55J.

[0060] In this embodiment, the upper oblique rod 4, cross rod 5, vertical rod 6, and lower oblique rod 7 are hollow tubes, taking weight constraints into consideration. This ensures a sufficiently large cross-section while maximizing the available space within the cabin. This also simplifies the force transmission path and minimizes the mechanical amplification factor. The upper oblique rod 4 is connected to the tank connection joint 10 and the upper oblique rod connection joint 11 using adhesive bonding and riveting. The lower oblique rod 7 is connected to the tank connection joint 10 and the bottom plate joint 13 using adhesive bonding and riveting. The cross rod 5 is connected to the tank connection joint 10 and the cross rod joint 12 using adhesive bonding and riveting. The vertical rod 6 serves as the primary force transmission path, transmitting force to the tank via the upper oblique rod connection joint 11, the cross rod joint 12, and the bottom plate joint 13. The support leg 8 connects the lower oblique rod 7 and the bottom plate 1. Its overall cross-sectional dimensions are much smaller than those of the upper oblique rod 4, cross rod 5, vertical rod 6, and lower oblique rod 7. It acts as an auxiliary support, transferring some energy to the bottom plate 1 through its lower stiffness.

[0061] Vertical rods 6 serve as the primary force transmission path, transferring the tank load to the base plate 1 step by step through the upper inclined rod connection joints 11, cross rod joints 12, and base plate joints 13. Lower inclined rods 7 and support legs 8 serve as auxiliary paths, distributing some of the lateral load. Carbon fiber angle pieces reinforce the connection stiffness of the tank flange 9, reducing the vibration amplification factor at the interface between the tank and the truss.

[0062] The vibration absorbing plate 3 is connected to the oblique upper rod connecting joint 11 through the pre-embedded metal parts in the plate. The entire crab claw truss structure and the vibration absorbing plate 3 maintain a mechanical decoupling state, avoiding the interference of the bottom plate stiffness on the vibration absorption effect, ensuring that it becomes an independent energy absorption unit, and solving the problem of excessive tank response caused by insufficient stiffness of the truss structure.

[0063] In this embodiment, the vibration-absorbing panel 3 features a 19.1mm honeycomb core, a 0.3mm aluminum skin, and a 0.15mm upper and lower honeycomb film. No metal or composite reinforcement ribs are present, ensuring minimal in-plane stiffness. By eliminating all rigid support components within the panel, the panel's inherent stiffness is simultaneously reduced through both material selection and structural design. Furthermore, no large-mass standalone equipment is mounted on the panel's surface to prevent excessive response from such equipment.

[0064] Through this design, vibration-absorbing plate 3 becomes the weakest link in the tank's axial path. When the satellite encounters sinusoidal vibration excitation, the energy of the entire satellite's dynamic response is preferentially concentrated on vibration-absorbing plate 3, which has the lowest stiffness. As the "lowest stiffness point" along the tank's axial direction, it preferentially undergoes elastic deformation under sinusoidal vibration excitation. This "drum-skin effect" concentrates the absorption of the entire satellite's dynamic energy, reducing the tank's vibration response amplitude. This effectively solves the problem of excessive tank dynamic response caused by insufficient overall stiffness in the crab claw truss.

[0065] In one embodiment of the present invention, the load transmission path is: tank load → tank flange 9 → tank connection joint 10 → upper inclined rod 4 / cross rod 5 / vertical rod 6 / lower inclined rod 7 → upper inclined rod connection joint 11 / cross rod joint 12 / base plate joint 13 → support leg 8 / base plate 1, forming a step-by-step decentralized transmission chain of "concentrated load → truss frame → basic support".

[0066] When a satellite encounters external excitation (such as launch vibration), the dynamic response of the entire satellite distributes energy according to the stiffness distribution:

[0067] The crab claw truss takes priority in structural support due to its high overall stiffness. However, the low stiffness of the traditional truss will cause the tank to respond too strongly.

[0068] The vibration absorbing plate becomes an "energy trap" through its low stiffness design. Its stiffness is much lower than that of the truss and the bottom plate. The vibration energy preferentially causes the vibration absorbing plate to produce in-plane buckling (drum skin effect), and dissipates energy through the elastic-plastic deformation of the honeycomb core and the skin, thereby reducing the vibration amplitude of the tank.

[0069] Compared to existing technologies, this solution, through a decoupled design of "truss load bearing + vibration-absorbing plate energy dissipation," reduces structural weight by 20%-30%. This solution also addresses the issue of excessive tank response caused by the insufficient stiffness of traditional truss configurations. Furthermore, it is suitable for satellites weighing less than 500kg and carrying large concentrated mass payloads. This design has been successfully implemented on the DRO-B satellite and has been operating stably in orbit for over a year, providing a lightweight, highly reliable whole-satellite vibration reduction solution for the aerospace industry.

[0070] Although various embodiments of the present invention have been described above, it should be understood that they are presented by way of example only and not limitation. It will be apparent to those skilled in the relevant art that various combinations, modifications, and variations may be made thereto without departing from the spirit and scope of the present invention. Therefore, the breadth and scope of the present invention disclosed herein should not be limited by the exemplary embodiments disclosed above, but should be defined solely in accordance with the appended claims and their equivalents.

Claims

1. A whole-satellite vibration reduction device based on a dynamic vibration absorbing plate and a crab claw truss structure, characterized in that: include: The bottom plate is used to carry the square trusses and is provided with a storage tank; A square truss, comprising four crab claw trusses and a tank flange, for fixing the tank, wherein the crab claw trusses are not directly connected to the vibration absorbing plate; as well as The vibration absorbing plate is arranged on the square truss and is used for reducing vibration of the storage tank, wherein the vibration absorbing plate is configured as the lowest point of rigidity.

2. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 1 is characterized in that: The four crab claw trusses of the square truss are arranged at the four corners of the bottom plate, and the crab claw truss includes: Four hollow square tubes, including an upper inclined rod, a horizontal rod, a vertical rod, a lower inclined rod and a support leg, wherein the hollow square tubes do not directly contact the vibration absorbing plate; The four connecting joints include a tank connecting joint, an inclined upper rod connecting joint, a cross bar joint and a bottom plate joint.

3. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 2 is characterized in that: The connection relationship between the hollow square tube and the connecting joint is as follows: The inclined upper rod is connected to the tank connection joint and the inclined upper rod connection joint; The oblique lower rod is connected to the tank connection joint and the bottom plate joint; The crossbar is connected to the tank connection joint and the crossbar joint; The vertical rod is provided with an oblique upper rod connecting joint, a horizontal rod joint and a bottom plate joint; The supporting legs are connected to the oblique lower rod and the base plate; The tank connection nipple is connected to the tank flange.

4. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 3 is characterized in that: The overall cross-sectional dimensions of the support legs and the oblique lower rod are much smaller than those of the oblique upper rod, the horizontal rod, the vertical rod and the oblique lower rod.

5. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 3 is characterized in that: The tank flange includes four split flanges, which are screwed to one side of the tank connection joint of the crab claw truss through four screws and screwed to the other side of the tank connection joint of the crab claw truss through another four screws.

6. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 5 is characterized in that: The tank flange is made of carbon fiber and is provided with angle pieces.

7. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 1 is characterized in that: The surface of the square truss is provided with a cable routing path for a single satellite machine.

8. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 2 is characterized in that: The hollow square tube is made of carbon fiber.

9. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 2 is characterized in that: The vibration absorbing plate is connected to the oblique upper rod connecting joint through embedded parts in the plate, and the entire crab claw truss is not directly connected to the vibration absorbing plate.

10. The whole-satellite vibration reduction device based on the dynamic vibration absorbing plate and crab claw truss structure according to claim 1 is characterized in that: The vibration absorbing plate is a honeycomb plate structure and is aluminum-skinned, wherein the vibration absorbing plate does not have reinforcing ribs.

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