A semi-high bearing tube all-electric propulsion satellite configuration

Abstract

The present invention discloses a half-height bearing cylinder all-electric propulsion satellite configuration, including a bearing cylinder, a back floor, an east bulkhead of a propulsion cabin, a west bulkhead of a propulsion cabin, a top plate of a bearing cylinder, an east bulkhead of an electronic cabin, a west bulkhead of an electronic cabin, a floor, north-south bulkheads, an east plate, a west plate, a south plate, and a north plate. The present invention cuts the height of the traditional bearing cylinder so that the propellant filling amount requirement of the all-electric propulsion satellite matches the volume of the bearing cylinder, thereby solving the problem of space waste when the all-electric propulsion satellite uses the traditional bearing cylinder configuration. The satellite height can be flexibly adjusted according to the load bearing demand without being restricted by the height of the bearing cylinder. The satellite based on the configuration of the present invention has a high load bearing capacity, a wide load adaptability, a strong expansion capability, and a broad application prospect.

Description

Technical Field

[0001] The invention relates to a half-high bearing tube all-electric propulsion satellite configuration, belonging to the technical field of spacecraft design. Background Art

[0002] The central load-bearing tube is a cylindrical structure located in the center of the satellite. The load-bearing tube runs through the entire height of the satellite, connected to the carrier at the bottom and the satellite floor at the top. Traditional satellite structures mostly use the central load-bearing tube main structure configuration, such as the LS-1300 satellite platform of the United States' Laura Company, the SpaceBus4000 platform of Europe's TAS Company, the Eurostar3000 platform of Europe's ADS Company, and China's DFH-4 satellite platform.

[0003] Compared with other structural forms, the central load-bearing cylinder has the following advantages: when transmitting load, the load can be evenly distributed along the entire cylinder, and there is no large concentrated load, which makes the structural design more reasonable; the propellant can be loaded into a spherical tank and installed inside the load-bearing cylinder. Because the central space inside the satellite is far from the heat dissipation surface and is not suitable for installing equipment, this part of the space is given to the tank, and the internal space of the satellite is efficiently utilized.

[0004] Traditional geostationary orbit satellites use chemical propellants for orbit change and position maintenance. Taking the Dongfanghong-4 platform satellite as an example, the satellite body is about 3.6 meters high and the inner diameter of the support tube is about 1.3 meters. Due to the low specific impulse of chemical propellants, a larger amount of propellant is required. Considering the orbit change from the geosynchronous transfer orbit with an inclination of 28.5 degrees, for a satellite with a launch weight of 5000kg, based on a 15-year satellite lifespan, the propellant loading will reach about 3000kg, and the corresponding tank volume is about 3000L. The internal volume of the support tube with a height of 3.6 meters and a diameter of 1.3 meters is about 5000L. The internal volume of the support tube is basically matched with the required volume, and the internal space of the support tube is not wasted.

[0005] In recent years, satellite propulsion systems have gradually shifted from chemical propulsion systems to electric propulsion systems. Compared with traditional chemical propulsion, the biggest advantage of electric propulsion is its high specific impulse and the resulting low propellant consumption. The satellite payload weight can be greatly increased while keeping the takeoff weight and service life unchanged.

[0006] The specific impulse of electric propulsion is about 5 to 10 times that of chemical propulsion, and the corresponding propellant loading is reduced to 1 / 10 to 1 / 5 of that of chemical propulsion. There are some outstanding problems when all-electric propulsion satellites use traditional bearing cylinder configurations:

[0007] Because the propellant loading and tank volume are greatly reduced, the space inside the support cylinder will be vacant. At the same time, due to the reduction in propellant loading, the satellite can carry more payload equipment, but the space occupied by the support cylinder cannot be used to install payload equipment, resulting in space waste, which greatly restricts the improvement of the satellite's carrying capacity.

[0008] The height of the load compartment is restricted by the height of the load-bearing cylinder, the height cannot be flexibly adjusted, and the load adaptability is poor.

[0009] In order to improve the payload carrying capacity of the satellite platform, it is necessary to solve the problem of space waste in the load-bearing cylinder and convert the space into space for payload equipment layout. At the same time, the height of the payload cabin should be decoupled from the load-bearing cylinder so that the height of the payload cabin can be flexibly adjusted, thereby improving the carrying capacity and adaptability of the satellite payload. Summary of the invention

[0010] The technical problem solved by the present invention is: in view of the problem that the carrying capacity and load adaptability are restricted when the electric propulsion satellite uses the central bearing cylinder configuration, a half-height bearing cylinder all-electric propulsion satellite configuration is proposed. This configuration solves the problem of waste of bearing cylinder space when the satellite uses a traditional bearing cylinder configuration when a small amount of propellant is loaded, and converts the space into load layout space; the height of the electronic cabin can be flexibly adjusted according to the load-bearing requirements, and is decoupled from the bearing cylinder height, which greatly improves the flexibility of satellite application and the carrying capacity of the effective payload.

[0011] The technical solution of the present invention is:

[0012] A half-height bearing cylinder all-electric propulsion satellite structure, comprising a propulsion cabin and an electronic cabin, wherein the propulsion cabin is composed of a bearing cylinder, a back floor, an east bulkhead of the propulsion cabin, and a west bulkhead of the propulsion cabin, and the electronic cabin is composed of a top plate of the bearing cylinder, an east bulkhead of the electronic cabin, a west bulkhead of the electronic cabin, a floor, north-south bulkheads, a south plate, and a north plate;

[0013] The bearing cylinder is arranged vertically, and its lower end is a carrier docking surface. A propellant tank is arranged inside the bearing cylinder; the back floor is connected to the carrier docking surface of the bearing cylinder; the east bulkhead and the west bulkhead of the propulsion cabin are arranged vertically, and are respectively connected to the bearing cylinder and the back floor;

[0014] The floor panels are arranged in parallel, and are connected to the top edges of the vertically arranged north-south partitions, the east partition of the electronic compartment, the west partition of the electronic compartment, the south plate and the north plate; the south plate and the north plate are connected to the north-south partitions; the bottom edges of the east partition of the electronic compartment and the west partition of the electronic compartment are respectively connected to the north-south partitions and the top plate of the load-bearing cylinder arranged in parallel; the top plate of the load-bearing cylinder is connected to the north-south partitions, and is embedded in the middle of the north-south partitions; a rectangular notch is provided in the middle of the lower part of the north-south partitions to avoid the load-bearing cylinder;

[0015] When the propulsion cabin is docked with the electronic cabin, the electronic cabin falls vertically from directly above the propulsion cabin, and the top plate of the load-bearing cylinder is connected to the east partition of the propulsion cabin, the top edge of the west partition of the propulsion cabin, and the top surface of the load-bearing cylinder; the north and south partitions are connected to the cylindrical surface of the load-bearing cylinder and the upper surface of the back floor; the south plate and the north plate are respectively connected to the back floor.

[0016] Furthermore, it also includes a vertically arranged east plate and a west plate, and the east plate and the west plate are respectively connected to the south plate, the north plate, the opposite floor plate, the back floor, the east partition plate of the propulsion cabin, the west partition plate of the propulsion cabin, and the top plate of the load-bearing cylinder to form a closed satellite structure.

[0017] Furthermore, the height between the floor and the top plate of the load-bearing cylinder is adjustable, which is determined by the space requirement for installing the payload equipment.

[0018] Furthermore, when the height changes, the lengths of the north-south partitions, the east partition of the electronic compartment, the west partition of the electronic compartment, the south plate, the north plate, the east plate, and the west plate change, and the remaining structures and connection relationships remain unchanged.

[0019] Furthermore, it also includes an antenna fixed to the outer side of the east plate, the west plate and the floor panel when the satellite is launched.

[0020] Furthermore, it also includes solar wings that are folded and fixed to the outer sides of the south plate and the north plate when the satellite is launched.

[0021] The beneficial effects of the present invention compared with the prior art are:

[0022] (1) The propulsion module of the present invention reduces the height of the traditional bearing cylinder so that the required amount of propellant for the all-electric propulsion satellite matches the internal volume of the bearing cylinder, thereby solving the problem of wasted space when using a traditional full-height bearing cylinder when a small amount of electric propellant is loaded, converting the wasted space into load layout space, thereby improving the satellite carrying capacity;

[0023] (2) The height of the satellite electronic cabin of the present invention can be flexibly adjusted according to the load bearing requirements, the cabin plate connection method remains unchanged, and the structure of the satellite propulsion cabin is not affected, which is convenient for satellite technical status control and mass production;

[0024] (3) The propulsion module and the electronic module of the present invention are designed with an open structure, which is convenient for assembly, integration and testing. Assembly and integration can be carried out in parallel, and docking can be carried out after completing their respective work, thus shortening the satellite development cycle;

[0025] (4) The satellite structure of the present invention has a regular shape, a small number of structural plates, and a simple connection method, which reduces the structural cost and weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 An exploded diagram of a satellite structure provided by an embodiment of the present invention;

[0027] Figure 2 A satellite compartment division diagram provided by an embodiment of the present invention;

[0028] Figure 3 A schematic diagram of a satellite structure after assembly is completed provided by an embodiment of the present invention;

[0029] Figure 4 A schematic diagram of satellite altitude expansion provided by an embodiment of the present invention;

[0030] Figure 5 A schematic diagram of a satellite launch state provided by an embodiment of the present invention;

[0031] In the figure, there are load-bearing cylinder 1, back floor 2, east partition 3 of propulsion cabin, west partition 4 of propulsion cabin, top plate 5 of load-bearing cylinder, east partition 6 of electronic cabin, west partition 7 of electronic cabin, opposite floor 8, north-south partition 9, south plate 10, north plate 11, east plate 12, west plate 13, propellant tank 14, electronic cabin 15 and propulsion cabin 16. DETAILED DESCRIPTION

[0032] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments:

[0033] like Figure 1 As shown, the all-electric propulsion satellite has a semi-high load-bearing cylinder configuration, and the satellite structure consists of a load-bearing cylinder 1, a back floor 2, a propulsion cabin east partition 3, a propulsion cabin west partition 4, a load-bearing cylinder top plate 5, an electronic cabin east partition 6, an electronic cabin west partition 7, a floor 8, north-south partitions 9, an east plate 12, a west plate 13, a south plate 10, and a north plate 11.

[0034] like Figure 2 As shown, the satellite can be divided into two compartments: an electronics compartment 15 and a propulsion compartment 16;

[0035] The structure of the propulsion cabin 16 is composed of a load-bearing cylinder 1, a back floor 2, an east bulkhead 3 and a west bulkhead 4 of the propulsion cabin; the lower end of the load-bearing cylinder 1 is a carrier docking frame, and a propellant tank 14 is installed inside the load-bearing cylinder 1; the back floor 2 is connected above the carrier docking surface of the load-bearing cylinder 1, and reaction wheels, sensors, propulsion pipelines, thrusters, etc. are installed on the back floor 2; the east bulkhead 3 and the west bulkhead 4 of the propulsion cabin are respectively connected to the load-bearing cylinder 1 and the back floor 2, and the space on both sides of the east bulkhead 3 and the west bulkhead 4 of the propulsion cabin is used to install various pipes, valves and pipelines of the propulsion system.

[0036] The structure of the electronic cabin 15 is composed of a counter floor 8, north-south partitions 9, a south plate 10, a north plate 11, a load-bearing cylinder top plate 5, an east partition 6 of the electronic cabin, and a west partition 7 of the electronic cabin; the counter floor 8 is connected to the corresponding sides of the north-south partitions 9, the east partition 6 of the electronic cabin, the west partition 7 of the electronic cabin, the south plate 10, and the north plate 11; the counter floor 8 is used to install feed sources, small antennas and some electronic equipment; the south plate 10 and the north plate 11 are respectively connected to the corresponding sides of the counter floor 8 and the north-south partitions 9; the north and south plates 11 are installed with electronic equipment and serve as the thermal radiation surface of the satellite; the east partition 3 and the west partition 7 of the propulsion cabin are respectively connected to the counter floor 8, the south partition 6 and the west partition 7 of the electronic cabin The north partition plate 9 and the corresponding side surfaces of the load-bearing cylinder top plate 5 are connected; the load-bearing cylinder top plate 5 is respectively connected to the corresponding side surfaces of the electronic cabin east partition plate 6, the electronic cabin west partition plate 7 and the north-south partition plates 9, and is embedded in the middle of the north-south partition plates 9; the north-south partition plates 9 are connected to the corresponding side surfaces of the south plate 10, the north plate 11, the electronic cabin east partition plate 6, the electronic cabin west partition plate 7, the counter plate 8 and the load-bearing cylinder top plate 5, and a rectangular notch is provided in the middle of the lower part of the north-south partition plates 9 for avoiding the space of the load-bearing cylinder 1 when docking with the propulsion device. The north-south partition plates 9 are used to install electronic equipment with low heat generation, and serve as cables and waveguide channels for connecting the electronic equipment of the north and south plates.

[0037] The propulsion cabin 16 and the electronic cabin 15 have good spatial openness, and equipment installation and testing and other work can be carried out in parallel. After completing their respective work, they are docked. When the propulsion cabin 16 and the electronic cabin 15 are docked, the electronic cabin 15 falls vertically from directly above the propulsion cabin 16, and the load-bearing cylinder top plate 5 of the electronic cabin 15 is connected with the corresponding side surfaces of the propulsion cabin east partition 3 and the propulsion cabin west partition 4 of the propulsion cabin 16, and the top surface of the load-bearing cylinder 1; the north and south partitions 9 of the electronic cabin 15 are connected with the cylindrical surface of the load-bearing cylinder 1 and the upper surface of the back floor 2 of the propulsion cabin 16; the south plate 10 and the north plate 11 of the electronic cabin 15 are respectively connected with the corresponding side surfaces of the back floor 2 of the propulsion cabin 16;

[0038] like Figure 3 As shown, the east plate 12 and the west plate 13 are respectively connected to the corresponding sides of the south plate 10, the north plate 11, the opposite floor plate 8, the back floor 2, the propulsion cabin east partition 3, the propulsion cabin west partition 4, and the load-bearing cylinder top plate 5, so that the satellite structure is closed.

[0039] like Figure 4As shown, the height between the floor 8 and the load-bearing cylinder top plate 5 is adjustable, which is determined by the space requirement for the installation of the payload equipment; when the height changes, the heights of the north-south partition plates 9, the east partition plate 6 of the electronic cabin, the west partition plate 7 of the electronic cabin, the south plate 10, the north plate 11, the east plate 12, and the west plate 13 change, while the remaining structures and connection relationships remain unchanged, which is convenient for satellite technical status control and mass production.

[0040] like Figure 5 As shown, the antenna of this configuration is folded and fixed to the outer side of the east plate 12, the west plate 13 and the ground plane 8 when the satellite is launched; the solar wing is folded and fixed to the outer side of the south plate 10 and the north plate 11 when the satellite is launched.

[0041] The electric thruster is folded and fixed on the outer side of the back floor 2 .

[0042] The contents not described in detail in the present invention are well known to those skilled in the art.

Claims

1. A half-height bearing tube all-electric propulsion satellite structure, characterized in that: It includes a propulsion cabin and an electronic cabin, wherein the propulsion cabin is composed of a bearing cylinder, a back floor, an east bulkhead of the propulsion cabin, and a west bulkhead of the propulsion cabin, and the electronic cabin is composed of a top plate of the bearing cylinder, an east bulkhead of the electronic cabin, a west bulkhead of the electronic cabin, a floor, north-south bulkheads, a south plate, and a north plate; It also includes a vertically arranged east plate and a west plate, wherein the east plate and the west plate are respectively connected to the south plate, the north plate, the opposite floor plate, the back floor plate, the east bulkhead of the propulsion cabin, the west bulkhead of the propulsion cabin, and the top plate of the bearing cylinder to form a closed satellite structure; The bearing cylinder is arranged vertically, and its lower end is a carrier docking surface. A propellant tank is arranged inside the bearing cylinder; the back floor is connected to the carrier docking surface of the bearing cylinder; the east bulkhead and the west bulkhead of the propulsion cabin are arranged vertically, and are respectively connected to the bearing cylinder and the back floor; The floor panels are arranged in parallel, and are connected to the top edges of the vertically arranged north-south partitions, the east partition of the electronic compartment, the west partition of the electronic compartment, the south plate and the north plate; the south plate and the north plate are connected to the north-south partitions; the bottom edges of the east partition of the electronic compartment and the west partition of the electronic compartment are respectively connected to the north-south partitions and the top plate of the load-bearing cylinder arranged in parallel; the top plate of the load-bearing cylinder is connected to the north-south partitions, and is embedded in the middle of the north-south partitions; a rectangular notch is provided in the middle of the lower part of the north-south partitions to avoid the load-bearing cylinder; The height between the floor and the top plate of the bearing cylinder is adjustable, and is determined by the space requirement for the installation of the payload equipment; When the height changes, the lengths of the north-south partitions, the east partition of the electronic compartment, the west partition of the electronic compartment, the south plate, the north plate, the east plate, and the west plate change, and the remaining structures and connection relationships remain unchanged; When the propulsion cabin is docked with the electronic cabin, the electronic cabin falls vertically from directly above the propulsion cabin, and the top plate of the load-bearing cylinder is connected to the east partition of the propulsion cabin, the top edge of the west partition of the propulsion cabin, and the top surface of the load-bearing cylinder; the north and south partitions are connected to the cylindrical surface of the load-bearing cylinder and the upper surface of the back floor; the south plate and the north plate are respectively connected to the back floor.

2. The semi-high bearing cylinder all-electric propulsion satellite structure according to claim 1 is characterized in that: It also includes an antenna which is folded and fixed to the outer sides of the east plate, the west plate and the floor when the satellite is launched.

3. The semi-high bearing cylinder all-electric propulsion satellite structure according to claim 1 is characterized in that: It also includes solar wings that are folded and fixed to the outer sides of the south plate and the north plate when the satellite is launched.

Images