A honeycomb buffer structure for a low-Earth orbit satellite payload compartment

Abstract

This utility model relates to the field of low-Earth orbit satellite payload compartment buffer technology, specifically a honeycomb buffer structure for a low-Earth orbit satellite payload compartment. It includes a payload compartment body, with a fixing frame inside. Several shock-absorbing buckles are tightly fitted to the bottom of the fixing frame. Each shock-absorbing buckle has an upper cover plate at its bottom. The upper cover plate has three sets of buffer components at its bottom. Each top buffer component has several upper-layer honeycomb holes, each middle buffer component has several middle-layer honeycomb holes, and each bottom buffer component has several lower-layer honeycomb holes. A lower cover plate is located at the bottom of the bottom buffer component, and a support frame is tightly fitted to the bottom of the lower cover plate. This utility model uses the fixing frame to position the top fixing bolts, and the shock-absorbing buckles are bent to make them elastic, thus achieving vibration reduction. The adapter groove is used to position the top fixing bolts, allowing for the adaptation of different sized vibration-damping plates.

Description

Technical Field

[0001] This utility model belongs to the field of low-Earth orbit satellite payload cabin buffer technology, specifically a honeycomb buffer structure for a low-Earth orbit satellite payload cabin. Background Technology

[0002] With the rapid development of aerospace technology, low-Earth orbit (LEO) satellites are playing an increasingly important role in fields such as communication, remote sensing, and scientific exploration. During launch and operation, LEO satellites are subject to various complex mechanical environments, such as the severe vibrations during rocket launch and the impact forces during satellite entry into orbit and orbit changes. These external forces may damage the precision instruments and equipment inside the satellite's payload bay, affecting the satellite's normal operation and service life.

[0003] However, existing satellite buffer structures mainly include traditional rubber buffer pads and spring buffer devices. Although rubber buffer pads have a certain buffering effect, their energy absorption efficiency is low, resulting in poor buffering effect. To address this issue, this invention designs a honeycomb buffer structure for the payload compartment of a low-Earth orbit satellite. Utility Model Content

[0004] In view of the above situation and to overcome the defects of the prior art, this utility model provides a honeycomb buffer structure for a low-orbit satellite payload compartment, which effectively solves the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a honeycomb buffer structure for a low-orbit satellite payload compartment, comprising a payload compartment body, a service compartment body on the top of the payload compartment body, a communication antenna fixed on the top of the service compartment body, solar panels on both the left and right ends of the service compartment body, a fixing frame inside the payload compartment body, several shock-absorbing buckles tightly fitted to the bottom of the fixing frame, vibration damping plates tightly fitted to the bottom of the several shock-absorbing buckles, an upper cover plate tightly fitted to the bottom of the vibration damping plates, three sets of buffer components at the bottom of the upper cover plate, several upper honeycomb holes inside each of the top buffer components, several middle honeycomb holes on each of the middle buffer components, several lower honeycomb holes on each of the bottom buffer components, a lower cover plate at the lower end of the bottom buffer component, a support frame tightly fitted to the bottom of the lower cover plate, and electrical components fixed to the bottom of the support frame.

[0006] Preferably, the payload compartment body has a light-transmitting plate at the bottom, the service compartment body is fixedly connected to the solar panel at one end of the service compartment body via a connecting rod, and the payload compartment body is fastened to the service compartment body at the top of the payload compartment body via a fixing plate.

[0007] Preferably, the fixing frame is fixedly connected to the load chamber body outside it by a support ring. The fixing frame is provided with a plurality of fitting slots. A plurality of top fixing bolts are engaged with the top of the upper cover plate. Each top fixing bolt is slidably connected to the fitting slot outside it. The bottom of each top fixing bolt is engaged with the damping plate. Each top fixing bolt is provided with a damping spring on its exterior.

[0008] Preferably, each buffer member has two sliders fixed at its left and top ends, and each buffer member has a groove at its right and bottom ends. Each groove is slidably connected to the slider at its right end. The bottom of the upper cover plate has three sets of upper cover plate grooves. The topmost slider is slidably connected to the outer upper cover plate groove. The top of the lower cover plate has several sets of lower cover plate sliders fixed, and the bottommost slider is slidably connected to the lower cover plate slider inside it.

[0009] Preferably, each of the buffer components is fastened to the upper end with an upper connecting bolt, and the bottom of each of the buffer components is engaged with a lower connecting bolt. The top of the support frame is fastened to the lower cover plate by a number of fixing bolts. A high-precision camera is also fixed to the bottom of the support frame. The inner diameter ratio of the lower honeycomb hole, the middle honeycomb hole, and the upper honeycomb hole is 1:2:3.

[0010] Compared with the prior art, the beneficial effects of this utility model are:

[0011] (1) This utility model uses a fixed frame to position the top fixed bolt, and the shock-absorbing buckle is bent to make the shock-absorbing buckle elastic, thereby achieving the purpose of vibration reduction. The adapter groove is used to position the top fixed bolt, so that it can be adapted to different sizes of shock-absorbing plates, thereby improving the application range of the entire device. The shock-absorbing spring is elastic, thereby further reducing the vibration of the support frame, thereby further ensuring the buffering effect.

[0012] (2) The present invention can fasten the damping plate, the top cover plate and the damping buckle by the top fixing bolt, thereby ensuring the stability of the top cover plate and the damping buckle can reduce vibration, thereby ensuring the buffering effect, thereby ensuring the safety of electrical components and high-precision camera, thereby improving the service life of electrical components. The damping plate is used for vibration reduction, thereby ensuring the buffering effect.

[0013] (3) This utility model can reduce the vibration of electrical components and high-precision cameras by combining the upper, middle and lower honeycomb holes, thereby ensuring the buffering effect. The honeycomb core layer of the upper, middle and lower honeycomb holes is arranged in a regular hexagonal honeycomb cell array. This structure has high specific strength and specific stiffness, and can effectively bear and disperse loads while being lightweight. The honeycomb core layer adopts a layered structure design. The size and wall thickness of the honeycomb cells in different layers are different. The bottom honeycomb cells near the bottom cover plate are smaller and have relatively thinner walls. They are mainly used to cope with small high-frequency vibration impacts and can respond quickly and absorb energy. The size of the honeycomb cells in the middle layer gradually increases and the wall thickness also increases accordingly. They mainly bear larger impact forces and absorb a large amount of energy through larger deformation. The top honeycomb cells near the top cover plate are the largest and have the thickest walls. They are used to provide stable support in the final stage of impact and prevent excessive deformation of the structure. Through this layered design, the honeycomb core layer can better adapt to impact loads of different intensities and frequencies. Attached Figure Description

[0014] The accompanying drawings are provided to further understand the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention and do not constitute a limitation thereof.

[0015] In the attached diagram:

[0016] Figure 1 This is a schematic diagram of the overall design of this utility model;

[0017] Figure 2 This is a schematic diagram of the overall top of this utility model;

[0018] Figure 3 This is a schematic diagram of the interior of the payload compartment of this utility model;

[0019] Figure 4 This is a schematic diagram of the top of the fixing frame of this utility model;

[0020] Figure 5 This is a schematic diagram of the buffer component of this utility model;

[0021] Figure 6 This is a schematic diagram of the internal structure of the shock-absorbing buckle of this utility model;

[0022] Figure 7 This is a schematic diagram of the top of the support frame of this utility model.

[0023] In the diagram: 1-Payload compartment body; 2-Service compartment body; 3-Fixing frame; 4-Upper cover plate; 5-Electrical components; 6-Buffer component; 101-Light-transmitting plate; 102-Fixing plate; 201-Solar panel; 202-Communication antenna; 203-Connecting rod; 301-Support ring; 302-Shock-absorbing buckle; 303-Adaptor slot; 304-Top fixing bolt; 305-Vibration damping spring; 401-Lower cover plate; 402-Support frame; 403-Vibration damping plate; 404-Fixing bolt; 501-High-precision camera; 601-Upper honeycomb hole; 602-Middle honeycomb hole; 603-Lower honeycomb hole; 604-Slider; 605-Slide groove; 606-Upper connecting bolt; 607-Lower connecting bolt; 608-Upper cover plate slide groove; 609-Lower cover plate slider. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the protection scope of the present utility model.

[0025] Example 1, by Figure 1 , Figure 3 , Figure 5The present invention includes a payload bay body 1, which is made of alloy material and supports the entire low-Earth orbit satellite. A service bay body 2 is located on top of the payload bay body 1 and is used to control the entire low-Earth orbit satellite. A communication antenna 202 is fixed on top of the service bay body 2 for facilitating communication with the ground. Solar panels 201 are located at both ends of the service bay body 2 for charging the entire low-Earth orbit satellite. The payload bay body 1 contains a solid... The fixing frame 3 is made of alloy material and is used to position the top fixing bolt 304. Several shock-absorbing buckles 302, also made of alloy material, are tightly fitted to the bottom of the fixing frame 3. These buckles are bent to give them elasticity, thus achieving vibration damping. Vibration damping plates 403, made of rubber material, are tightly fitted to the bottom of the buckles 302. These plates are used for vibration damping, ensuring a buffering effect. A top cover plate 4 is tightly fitted to the bottom of plate 403. The top cover plate 4 is made of alloy material. Three sets of buffer members 6 are provided at the bottom of the top cover plate 4. The buffer members 6 are made of plastic material and are used for cushioning. Each top buffer member 6 has several upper honeycomb holes 601 inside, each middle buffer member 6 has several middle honeycomb holes 602, and each bottom buffer member 6 has several lower honeycomb holes 603. The upper honeycomb holes 601, the middle honeycomb holes 602, and the lower honeycomb holes 603 work together to reduce the electrical current. The vibration of the electrical component 5 and the high-precision camera 501 is mitigated to ensure a buffering effect. The bottom of the buffer 6 is provided with a lower cover plate 401. The upper honeycomb hole 601 is made of alloy material. The upper cover plate 4 and the buffer 6 at its bottom are tightly bonded with high-strength adhesive. The lower cover plate 401 and the buffer 6 at its top are also tightly bonded with high-strength adhesive. A support frame 402 is tightly attached to the bottom of the lower cover plate 401. The support frame 402 is used to support the electrical component 5. The electrical component 5 is fixed at the bottom of the support frame 402.

[0026] Example 2, based on Example 1, combined with... Figure 2 , Figure 4 , Figures 6-7The payload compartment body 1 has a light-transmitting plate 101 at its bottom, which facilitates monitoring by the high-precision camera 501. The service compartment body 2 is fixedly connected to the solar panel 201 at one end via a connecting rod 203. The payload compartment body 1 and the service compartment body 2 at its top are fastened together by a fixing plate 102. The fixing frame 3 is fixedly connected to the payload compartment body 1 outside the frame via a support ring 301. The support ring 301 is made of alloy material and is used to support the fixing frame 3. The fixing frame 3 has several adapter slots 303 with a straight groove structure. The adapter slots 303 are used to position the top fixing bolts 304, thereby... The vibration damping plate 403 can be adapted to different sizes, thereby improving the overall usability of the structure. The top cover plate 4 is connected to several top fixing bolts 304, which fasten the vibration damping plate 403, the top cover plate 4, and the shock-absorbing buckle 302. This ensures the stability of the top cover plate 4 while providing vibration damping through the shock-absorbing buckle 302, thus ensuring a buffering effect and protecting the electrical components 5 and the high-precision camera 501, thereby extending the service life of the electrical components 5. Each top fixing bolt 304 is slidably connected to its external adapter groove 303, and the bottom of each top fixing bolt 304 is engaged with the vibration damping plate 403. Bolt 304 is externally equipped with a damping spring 305. The damping spring 305 is elastic, thereby further damping the support frame 402 and ensuring a better cushioning effect. Each buffer member 6 has two sliders 604 fixed to its left and top ends. The sliders 604 are made of plastic material. Each buffer member 6 has a groove 605 at its right and bottom ends. The groove 605 is used to position the slider 604, and each groove 605 is slidably connected to the slider 604 at its right end. The bottom of the upper cover plate 4 has three sets of upper cover plate grooves 608, which are used to position the sliders 604 inside. The topmost slider 604 is slidably connected to the outer upper cover plate groove 608. Several sets of lower cover plate sliders 609 are fixed to the top of the cover plate 401. The lower cover plate sliders 609 are made of alloy material and are used to position the bottommost slide groove 605. Each bottommost slider 604 is slidably connected to the lower cover plate slider 609 inside it. Each buffer member 6 has an upper connecting bolt 606 fastened to its upper end. The upper connecting bolt 606 is used to connect the upper and lower buffer members 6. Each bottommost buffer member 6 has a lower connecting bolt 607 engaged at its bottom. The lower connecting bolt 607 is used to connect the bottommost buffer member 6 to the support frame 402. The top of the support frame 402 is fastened to the lower cover plate 401 by several fixing bolts 404.A high-precision camera 501 is also fixed to the bottom of the support frame 402. The inner diameter ratio of the lower honeycomb holes 603, the middle honeycomb holes 602, and the upper honeycomb holes 601 is 1:2:3. The upper honeycomb holes 601, the middle honeycomb holes 602, and the lower honeycomb holes 603 adopt a honeycomb structure. The honeycomb core layer adopts a layered structure design, with different cell sizes and wall thicknesses in different layers. The bottom honeycomb cells near the lower cover plate are smaller and have relatively thinner walls, mainly used to cope with smaller high-frequency vibration impacts, enabling rapid response and energy absorption. The cell sizes of the middle layer gradually increase, and the wall thickness also increases accordingly, mainly bearing larger impact forces and absorbing a large amount of energy through larger deformation. The top honeycomb cells near the upper cover plate are the largest and have the thickest walls, used to provide stable support in the final stage of impact and prevent excessive structural deformation. Through this layered design, the honeycomb core layer can better adapt to impact loads of different intensities and frequencies.

[0027] Before using this structure, the operator fixes the fixing frame 3 inside the load chamber body 1 using the support ring 301. At this time, the operator uses the top fixing bolt 304 to pass through the adapter groove 303 and the shock-absorbing buckle 302 to securely connect with the damping plate 403 and the upper cover plate 4. Then, the operator inserts the upper slider 604 of the top buffer 6 into the upper cover plate slide groove 608 and firmly bonds it with high-strength adhesive. Finally, the operator inserts the slider 604 at the bottom... 04 and the slide 605 are used to install two sets of buffer members 6. At this time, the upper buffer member 6 has upper honeycomb holes 601 inside, the middle buffer member 6 has middle honeycomb holes 602 inside, and the lower buffer member 6 has lower honeycomb holes 603 inside. The upper and lower buffer members 6 are further secured by several upper connecting bolts 606, and the lower cover plate 401 is further secured at its bottom by lower connecting bolts 607. The support frame 402 is further secured to the lower cover plate 401 by fixing bolts 404. The cover plate 401 is fastened. When the low-orbit satellite is subjected to impact loads during launch or operation, the impact force first acts on the damping plate 403. At this time, the damping buckle 302 and the damping spring 305 perform initial damping. The remaining impact is then transmitted to the upper cover plate 4. The upper cover plate 4 then evenly transmits the impact force to the honeycomb core layer. Due to the unique structural design of the honeycomb core layer, the honeycomb cells begin to deform. During the deformation process, the thickened area at the edge of the upper honeycomb hole 601 undergoes plastic deformation first, absorbing some energy. As the deformation continues, the edge of the middle honeycomb hole 602 also gradually participates in the deformation, further absorbing energy. The remaining energy is then transmitted to the edge of the lower honeycomb hole 603. At the same time, the layered honeycomb core layer can have different layers of honeycomb cells play their roles sequentially according to the magnitude and frequency of the impact force, achieving efficient energy absorption and buffering. After multiple buffering operations, the electrical components 5 and the high-precision camera 501 inside the satellite's payload compartment 1 are effectively protected from impact damage.

[0028] The working process of this utility model is as follows: Before using this structure, the operator fixes the fixing frame 3 inside the load chamber body 1 through the support ring 301. At this time, the operator uses the top fixing bolt 304 to pass through the adapter groove 303 and the shock-absorbing buckle 302 to fasten it to the damping plate 403 and the upper cover plate 4. Then, the operator inserts the upper slider 604 of the top buffer 6 into the upper cover plate slide groove 608 in sequence, and firmly bonds it with high-strength adhesive. Two sets of buffer components 6 are installed at the bottom through the cooperation of the slider 604 and the groove 605. At this time, the upper buffer component 6 has the upper honeycomb holes 601 inside, the middle buffer component 6 has the middle honeycomb holes 602 inside, and the lower buffer component 6 has the lower honeycomb holes 603 inside. The upper and lower buffer components 6 are further secured by several upper connecting bolts 606, and the lower cover plate 401 is further secured at its bottom by lower connecting bolts 607. The support frame 4 is further secured by the fixing bolts 404. 02 is fastened to the lower cover plate 401. When the low-orbit satellite is subjected to impact loads during launch or operation, the impact force first acts on the damping plate 403. At this time, the damping buckle 302 and the damping spring 305 perform initial damping, and further transmit the remaining impact to the upper cover plate 4. The upper cover plate 4 then evenly transmits the impact force to the honeycomb core layer. Due to the unique structural design of the honeycomb core layer, the honeycomb cells begin to deform. During the deformation process, the thickened area at the edge of the upper honeycomb hole 601 undergoes plastic deformation first, absorbing some energy. As the deformation continues, the edge of the middle honeycomb hole 602 also gradually participates in the deformation, further absorbing energy. The remaining energy is further transmitted to the edge of the lower honeycomb hole 603. At the same time, the layered honeycomb core layer can have different layers of honeycomb cells play their roles in sequence according to the magnitude and frequency of the impact force, achieving efficient energy absorption and buffering. After multiple buffering, the electrical components 5 and the high-precision camera 501 inside the satellite's payload compartment 1 are effectively protected from impact damage.

[0029] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0030] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A honeycomb buffer structure for a low-Earth orbit satellite payload compartment, characterized in that: The system includes a payload compartment body (1), a service compartment body (2) on top of the payload compartment body (1), a communication antenna (202) fixed on top of the service compartment body (2), solar panels (201) on both the left and right ends of the service compartment body (2), a mounting frame (3) inside the payload compartment body (1), several shock-absorbing buckles (302) tightly attached to the bottom of the mounting frame (3), vibration damping plates (403) tightly attached to the bottom of the several shock-absorbing buckles (302), and a top cover plate tightly attached to the bottom of the vibration damping plates (403). (4) The bottom of the upper cover plate (4) is provided with three sets of buffers (6). Each buffer (6) at the top is provided with several upper honeycomb holes (601), each buffer (6) in the middle is provided with several middle honeycomb holes (602), and each buffer (6) at the bottom is provided with several lower honeycomb holes (603). The bottom of the buffer (6) at the bottom is provided with a lower cover plate (401). The bottom of the lower cover plate (401) is tightly fitted with a support frame (402), and the bottom of the support frame (402) is fixed with electrical components (5).

2. The honeycomb buffer structure for a low-Earth orbit satellite payload compartment according to claim 1, characterized in that: The payload compartment body (1) has a light-transmitting plate (101) at the bottom. The service compartment body (2) is fixedly connected to the solar panel (201) at one end of the service compartment body (2) via a connecting rod (203). The payload compartment body (1) is fastened to the service compartment body (2) at the top via a fixing plate (102).

3. The honeycomb buffer structure for a low-Earth orbit satellite payload compartment according to claim 2, characterized in that: The fixed frame (3) is fixedly connected to the load chamber body (1) outside it through a support ring (301). The fixed frame (3) is provided with a number of adapter slots (303). The top of the upper cover plate (4) is engaged with a number of top fixing bolts (304). Each top fixing bolt (304) is slidably connected to the adapter slot (303) outside it. The bottom of each top fixing bolt (304) is engaged with the damping plate (403). Each top fixing bolt (304) is provided with a damping spring (305) outside it.

4. The honeycomb buffer structure for a low-Earth orbit satellite payload compartment according to claim 3, characterized in that: Each buffer (6) has two sliders (604) fixed at its left and top ends, and each buffer (6) has a groove (605) at its right and bottom ends. Each groove (605) is slidably connected to the slider (604) at its right end. The bottom of the upper cover plate (4) has three sets of upper cover plate grooves (608). Each slider (604) at the top is slidably connected to the upper cover plate groove (608) on the outside. The top of the lower cover plate (401) has several sets of lower cover plate sliders (609) fixed, and each slider (604) at the bottom is slidably connected to the lower cover plate slider (609) inside it.

5. The honeycomb buffer structure for a low-Earth orbit satellite payload compartment according to claim 4, characterized in that: Each of the buffer components (6) is fastened to the upper end with an upper connecting bolt (606), and the bottom of each of the buffer components (6) is engaged with a lower connecting bolt (607). The top of the support frame (402) is fastened to the lower cover plate (401) by several fixing bolts (404). A high-precision camera (501) is also fixed to the bottom of the support frame (402). The inner diameter ratio of the lower honeycomb hole (603), the middle honeycomb hole (602), and the upper honeycomb hole (601) is 1:2:3.

Images