A satellite power cabin structure capable of carrying large-capacity propellant

Abstract

The invention discloses a satellite power cabin structure capable of carrying large-capacity propellants, comprising a satellite lower skirt, a columnar bearing cylinder, a conical bearing cylinder, a tank mounting plate and a supporting partition; the satellite lower skirt is fixed to the lower end of the columnar bearing cylinder for connecting a launch vehicle; the tank mounting plate is fixed to the middle of the inner side of the columnar bearing cylinder, a plurality of tank mounting holes are evenly distributed on the tank mounting plate, each tank mounting hole corresponds to a fixed installation connection with the lower flange of a tank, the upper flanges of a plurality of tanks are connected to the upper end of the columnar bearing cylinder through a tank pull rod and a tank connecting plate, thereby limiting the lateral position of the tank; the supporting partition is installed under the tank mounting plate, the upper side of the supporting partition is connected to the tank mounting plate, and the outer side of the supporting partition is connected to the columnar bearing cylinder. It is used to accommodate and carry large-capacity propellants, and is used for large-scale on-orbit maneuvers during the life of the satellite, and can follow the satellite body throughout the entire life cycle, and can provide a better mechanical environment for the tank.

Description

Technical Field

[0001] The present invention relates to a satellite power cabin structure in the field of aerospace applications, and in particular to a satellite power cabin structure capable of carrying a large-capacity propellant. Background Art

[0002] As the requirements for satellite maneuverability in orbit increase, a large amount of propellant is needed to promote satellite maneuvers in orbit. Generally, the space of the satellite itself is limited, and the size of the tank is limited, which cannot accommodate enough propellant. Therefore, for satellites with large requirements for in-orbit maneuverability, a power cabin with a separate size and structure needs to be designed to carry a large amount of propellant to achieve the satellite's in-orbit maneuverability.

[0003] There are currently two types of power module structures. One is a larger satellite with a larger space to accommodate the tank. The other is a shorter-lived power module similar to an upper stage, which brings the satellite into a predetermined orbit and then separates from the satellite.

[0004] Purpose of the Invention

[0005] The present invention aims to design a new satellite power cabin structure with strong adaptability, which is used to accommodate and carry large-capacity propellants and to perform large-scale maneuvers in orbit during the life of the satellite. It can follow the satellite body throughout the entire life cycle and provide a better mechanical environment for the tank.

[0006] The technical solution of the present invention is: a satellite power cabin structure capable of carrying a large volume of propellant, comprising a satellite lower skirt, a columnar bearing cylinder, a conical bearing cylinder, a tank mounting plate and a supporting partition; the columnar bearing cylinder, the conical bearing cylinder and the tank mounting plate are coaxially mounted;

[0007] The satellite lower skirt is fixed to the lower end of the cylindrical bearing cylinder and is used to connect to the launch vehicle;

[0008] The conical bearing cylinder comprises a conical cylinder body, the bottom open end of the conical cylinder body is fixed to the upper end of the cylindrical bearing cylinder, and the top open end of the conical cylinder body is used to connect to the satellite body;

[0009] The tank mounting plate is fixed to the middle of the inner side of the columnar bearing cylinder, and a plurality of tank mounting holes are evenly distributed on the tank mounting plate. Each tank mounting hole is fixedly mounted and connected to a corresponding lower flange of a tank, and the upper flanges of the plurality of tanks are connected to the upper end of the columnar bearing cylinder through a tank tie rod and a tank connecting plate, thereby limiting the lateral position of the tanks.

[0010] The supporting partition is installed under the tank mounting plate, the upper side of the supporting partition is connected to the tank mounting plate, and the outer side of the supporting partition is connected to the columnar bearing cylinder, so as to improve the longitudinal rigidity of the supporting tank and realize response control.

[0011] Furthermore, the main bodies of the columnar load-bearing cylinder, the conical load-bearing cylinder, the tank mounting plate and the supporting partition are all made of carbon fiber honeycomb sandwich structure skin materials formed by the surface skin of the carbon fiber honeycomb sandwich structure.

[0012] Furthermore, a load-bearing frame is pre-embedded in the tank mounting plate.

[0013] Furthermore, the cylindrical bearing cylinder is pre-embedded with a cylindrical bearing cylinder upper end frame, a cylindrical bearing cylinder middle end frame and a cylindrical bearing cylinder lower end frame; the upper flange of the tank is connected to the cylindrical bearing cylinder upper end frame of the cylindrical bearing cylinder through a tank pull rod and a tank connecting plate; the satellite lower skirt is connected to the cylindrical bearing cylinder lower end frame; the bottom open end of the conical cylinder body is connected to the cylindrical bearing cylinder upper end frame.

[0014] Furthermore, a conical bearing tube upper end frame and a conical bearing tube lower end frame are pre-embedded in the conical bearing tube, and the conical bearing tube upper end frame and the conical bearing tube lower end frame are connected by a conical bearing tube reinforcement strip; the conical bearing tube upper end frame is reserved with a connection interface with the satellite body for connection with the satellite body, and the conical bearing tube lower end frame is reserved with a connection interface with the upper end of the columnar bearing tube for connection with the upper end of the columnar bearing tube.

[0015] Furthermore, four storage tanks are evenly mounted on the storage tank mounting plate.

[0016] Furthermore, the upper flange of each tank is fixedly connected to the upper flanges of two adjacent tanks through a tank connecting plate, and the upper flange of each tank is fixedly connected to the nearest part of the upper end of the columnar bearing cylinder through a tank tie rod at the symmetrical position between the two tank connecting plates; 4 tanks, 4 tank connecting plates and 8 tank tie rods form a tic-tac-toe structure, so that the tanks can be firmly installed horizontally.

[0017] Furthermore, the tank pull rod is a telescopic rod with adjustable length, which is used to release the longitudinal freedom of the tank and eliminate manufacturing errors and longitudinal dimensional changes caused by tank pressurization.

[0018] Furthermore, the volume of each tank is not less than 200L, and the conical cylinder can carry a satellite body with a mass of not less than 650Kg.

[0019] Furthermore, the supporting partition includes four rectangular partitions, and the four rectangular partitions are spliced ​​into a cross-shaped structure.

[0020] The beneficial effects of the present invention are as follows: a satellite power cabin is designed to carry large-capacity propellants, can carry four 200L tanks, and realize response control of the tanks, providing a good mechanical environment for the tanks;

[0021] The power cabin of the present invention supports the satellite body with a mass of 650 kg through the conical bearing cylinder, and can achieve the requirement that the satellite has a maneuverability greater than 1000 m / s for five years in orbit;

[0022] The power cabin structure of the present invention has sufficient rigidity and strength to meet the frequency characteristic index requirements of the whole satellite structure.

[0023] The power cabin structure of the present invention can be promoted for use in low-orbit small and medium-sized satellites with high maneuverability, and has certain adaptability;

[0024] The power cabin described in the present invention can adapt to satellite bodies with different interface sizes through adaptive changes of the conical load-bearing cylinder. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic diagram of the power cabin appearance;

[0026] Figure 2 This is a schematic diagram of the internal installation of the power compartment;

[0027] Figure 3 It is a schematic diagram of the connection of the supporting partition;

[0028] Figure 4 It is a schematic diagram of the composition of the tapered bearing cylinder;

[0029] Figure 5 It is a schematic diagram of the composition of the columnar bearing cylinder;

[0030] Figure 6 This is a schematic diagram of the tank mounting plate;

[0031] Figure 7 This is a cross-sectional view of the tank mounting plate.

[0032] In the figure: 1 is the satellite lower skirt, 2 is the columnar bearing cylinder, 3 is the conical bearing cylinder, 4 is the tank mounting plate, 5 is the supporting partition, 6 is the tank pull rod, 7 is the tank connecting plate, 8 is the tank, 11 is the bearing frame, 12 is the skin, 13 is the carbon fiber honeycomb sandwich structure, 21 is the columnar bearing cylinder upper end frame, 22 is the columnar bearing cylinder middle end frame, 23 is the columnar bearing cylinder lower end frame, 31 is the conical bearing cylinder upper end frame, 32 is the conical bearing cylinder reinforcement strip, 33 is the conical bearing cylinder lower end frame, 34 is the conical cylinder body, and 41 is the tank mounting hole. DETAILED DESCRIPTION

[0033] The present invention will be further described below in conjunction with the accompanying drawings.

[0034] The power cabin structure designed by the present invention is as follows Figure 1 , 2As shown, the satellite power cabin structure of the present invention mainly consists of satellite lower skirt 1, columnar bearing cylinder 2, conical bearing cylinder 3, tank mounting plate 4, supporting partition 5, tank tie rod 6, tank connecting plate 7 and connecting angle piece and other structural parts. The conical bearing cylinder 3, columnar bearing cylinder 2 and tank mounting plate 4 are coaxially installed.

[0035] The tank 8 is mounted on the tank mounting plate 4. The tank mounting plate 4 (embedded load-bearing frame 11), the supporting partition plate 5, the columnar load-bearing cylinder 2 and the satellite lower skirt 1 constitute the main force transmission path of the propellant tank.

[0036] The satellite body is mounted on the conical bearing cylinder 3, and the conical bearing cylinder 3, the columnar bearing cylinder 2 and the satellite lower skirt 1 form a force transmission path.

[0037] The columnar bearing cylinder is one of the main bearing structures of the power cabin. It also bears the mass of the propulsion subsystem (including propellants, tanks and pipeline accessories, etc.) and the satellite body. It is a key product that affects the stiffness of the entire satellite. In order to ensure the bearing capacity of the columnar bearing cylinder and reduce the weight of the columnar bearing cylinder body, the columnar bearing cylinder body is made of a carbon fiber honeycomb sandwich structure 13 surface skin 12 formed by a carbon fiber honeycomb sandwich structure skin material. Figure 5 As shown, the cylindrical bearing cylinder 2 is pre-buried with a cylindrical bearing cylinder upper end frame 21, a cylindrical bearing cylinder middle end frame 22 and a cylindrical bearing cylinder lower end frame 23, and the upper flange of the tank is connected to the cylindrical bearing cylinder upper end frame 21 of the cylindrical bearing cylinder 2 through the tank tie rod 6 and the tank connecting plate 7. The satellite lower skirt 1 is connected to the cylindrical bearing cylinder lower end frame 23. The bottom open end of the conical cylinder 34 is connected to the cylindrical bearing cylinder upper end frame 21. They are used to improve the connection strength and overall rigidity with the conical bearing cylinder, the tank mounting plate and the satellite lower skirt.

[0038] The conical bearing cylinder is the second main bearing structure of the power cabin, bearing the mass of the satellite body, and is a key product that affects the stiffness of the entire satellite. In order to ensure the bearing capacity of the conical bearing cylinder and reduce the weight of the conical bearing cylinder body, the conical bearing cylinder body is made of a carbon fiber honeycomb sandwich structure 13 surface skin 12 formed by a carbon fiber honeycomb sandwich structure skin material. Figure 4As shown, the conical bearing cylinder 3 includes a conical cylinder body 34, the bottom open end of the conical cylinder body 34 is pre-embedded with a conical bearing cylinder lower end frame 33, and the top open end of the conical cylinder body 34 is pre-embedded with a conical bearing cylinder upper end frame 31. The conical bearing cylinder upper end frame 31 and the conical bearing cylinder lower end frame 33 are connected by a conical bearing cylinder reinforcement strip 32. The conical bearing cylinder upper end frame 31 reserves a connection interface with the satellite body for connection with the satellite body, and the conical bearing cylinder lower end frame 33 reserves a connection interface with the upper end of the columnar bearing cylinder 2 for connection with the upper end of the columnar bearing cylinder 2, so as to improve the connection strength and overall stiffness with the satellite body and the columnar bearing cylinder. The reinforcement strip is used to improve the lateral and longitudinal stiffness of the conical bearing cylinder.

[0039] The tank mounting plate is the third main load-bearing structural member of the power compartment and is a key product for carrying the tank. In order to ensure the bearing capacity of the tank mounting plate while reducing the weight of the tank mounting plate body, Figure 7 As shown, the material used for the tank mounting plate is a carbon fiber honeycomb sandwich structure skin material formed by a carbon fiber honeycomb sandwich structure 13 surface skin 12, and a load-bearing frame 11 is pre-embedded in the plate, as shown in FIG. Figure 7 The outer side of the tank mounting plate 4 is connected to the middle of the inner side of the columnar bearing tube 2, and the lower side is connected to the upper side of the supporting partition plate, so as to improve the supporting rigidity and strength of the tank mounting plate.

[0040] like Figure 2 , 6 As shown, four tank mounting holes 41 are evenly distributed on the tank mounting plate 4, and the lower flange of the tank 8 is fixedly mounted on the tank mounting plate by fasteners. The upper flange of the tank is connected to the upper end frame 21 of the columnar bearing tube through a tank tie rod and a tank connecting plate. Specifically, the upper flange of each tank 8 is fixedly connected to the upper flanges of two adjacent tanks 8 through a tank connecting plate 7, and the upper flange of each tank 8 is fixedly connected to the upper end of the columnar bearing tube 2 at the symmetrical positions of the two tank connecting plates 7 through a tank tie rod 6. The four tanks, the four tank connecting plates 7 and the eight tank tie rods 6 form a "well"-shaped structure to achieve a firm horizontal installation of the tanks, see Figure 2 The tank pull rod 6 is of a length-adjustable structure, which is used to release the longitudinal freedom of the tank and eliminate manufacturing errors and longitudinal dimensional changes caused by tank pressurization.

[0041] The supporting partition 5 is one of the main load-bearing structural members of the power cabin. According to the configuration design of the power cabin, the power cabin has a total of 4 rectangular partitions, which are spliced ​​into Figure 3 The cross-shaped structure shown in the figure. The outer side of each partition is directly connected to the columnar bearing cylinder through fasteners, and the partitions are connected together through angle pieces. The connection form is shown in Figure 3 The partitions are designed using a carbon fiber honeycomb sandwich structure skin material formed by a carbon fiber honeycomb sandwich structure 13 and a surface skin 12 to reduce its weight.

[0042] The present invention realizes the on-orbit maneuvering requirements of the satellite during its life by adding an independent power cabin under the satellite body. The power cabin of the present invention can be promoted for use in low-orbit small satellites with high maneuverability and has certain adaptability.

[0043] The technology of this embodiment is used to design a satellite power module for carrying large-capacity propellants. It can carry four 200L tanks and realize the response control of the tanks, providing a good mechanical environment for the tanks. The power module carries the satellite body with a mass of 650Kg through a conical bearing cylinder, which can achieve the requirement of a satellite maneuverability greater than 1000m / s for five years in orbit.

[0044] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A satellite power module structure capable of carrying a large volume of propellant, characterized in that: It comprises a satellite lower skirt (1), a columnar bearing cylinder (2), a conical bearing cylinder (3), a tank mounting plate (4) and a supporting partition (5); the columnar bearing cylinder (2), the conical bearing cylinder (3) and the tank mounting plate (4) are coaxially mounted; The satellite lower skirt (1) is fixed to the lower end of the columnar bearing cylinder (2) and is used for connecting to the carrier rocket; The conical bearing cylinder (3) comprises a conical cylinder body (34), the bottom open end of the conical cylinder body (34) is fixed to the upper end of the cylindrical bearing cylinder (2), and the top open end of the conical cylinder body (34) is used to connect to the satellite body; The tank mounting plate (4) is fixed to the middle part of the inner side of the columnar bearing cylinder (2), and a plurality of tank mounting holes (41) are evenly distributed on the tank mounting plate (4). Each tank mounting hole (41) is fixedly mounted and connected to a lower flange of a corresponding tank (8). The upper flanges of the plurality of tanks are connected to the upper end of the columnar bearing cylinder (2) through a tank tie rod (6) and a tank connecting plate (7), thereby limiting the lateral position of the tanks. The support baffle (5) is installed below the tank mounting plate (4), the upper side of the support baffle (5) is connected to the tank mounting plate (4), and the outer side of the support baffle (5) is connected to the columnar bearing cylinder (2); The columnar bearing cylinder (2) is pre-buried with a columnar bearing cylinder upper end frame (21), a columnar bearing cylinder middle end frame (22) and a columnar bearing cylinder lower end frame (23); the upper flange of the tank is connected to the columnar bearing cylinder upper end frame (21) of the columnar bearing cylinder (2) through a tank tie rod (6) and a tank connecting plate (7); the satellite lower skirt (1) is connected to the columnar bearing cylinder lower end frame (23); the bottom open end of the conical cylinder (34) is connected to the columnar bearing cylinder upper end frame (21); The conical bearing cylinder (3) is pre-buried with a conical bearing cylinder upper end frame (31) and a conical bearing cylinder lower end frame (33); the conical bearing cylinder upper end frame (31) and the conical bearing cylinder lower end frame (33) are connected via a conical bearing cylinder reinforcement strip (32); the conical bearing cylinder upper end frame (31) is reserved with a connection interface with a satellite body for connection with the satellite body, and the conical bearing cylinder lower end frame (33) is reserved with a connection interface with an upper end of a columnar bearing cylinder (2) for connection with the upper end of the columnar bearing cylinder (2).

2. A satellite power module structure capable of carrying a large volume of propellant according to claim 1, characterized in that: The main bodies of the columnar bearing cylinder (2), the conical bearing cylinder (3), the tank mounting plate (4) and the supporting partition plate (5) are all made of a carbon fiber honeycomb sandwich structure skin material formed by a surface skin (12) of a carbon fiber honeycomb sandwich structure (13).

3. A satellite power module structure capable of carrying a large volume of propellant according to claim 2, characterized in that: A load-bearing frame (11) is also pre-buried in the storage tank mounting plate (4).

4. A satellite power module structure capable of carrying a large volume of propellant according to claim 1, characterized in that: Four storage tanks (8) are evenly mounted on the storage tank mounting plate (4).

5. A satellite power module structure capable of carrying a large volume of propellant according to claim 4, characterized in that: The upper flange of each tank (8) is fixedly connected to the upper flanges of two adjacent tanks (8) via a tank connecting plate (7); the upper flange of each tank (8) is fixedly connected to the nearest part of the upper end of the columnar load-bearing cylinder (2) via a tank tie rod (6) at a position symmetrical to the two tank connecting plates (7); the four tanks, the four tank connecting plates (7) and the eight tank tie rods (6) form a tic-tac-toe structure.

6. A satellite power module structure capable of carrying a large volume of propellant according to claim 1 or 5, characterized in that: The tank pull rod (6) is a telescopic rod with adjustable length.

7. A satellite power module structure capable of carrying a large volume of propellant according to claim 4, characterized in that: The volume of each tank (8) is not less than 200L, and the conical cylinder (34) can carry a satellite body with a mass of not less than 650Kg.

8. The satellite power module structure capable of carrying a large volume of propellant according to claim 1, characterized in that: The supporting partition (5) comprises four rectangular partitions, and the four rectangular partitions are spliced ​​into a cross-shaped structure.

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