A modular self-organizing multifunctional satellite system

Abstract

The present invention discloses a modular self-organizing multifunctional satellite system, comprising one or more of a propulsion unit, a control unit, a measurement, control and communication unit, and a payload; the propulsion unit and the control unit are connected by a rigid connecting arm; the control unit is respectively connected to the measurement, control and communication unit and the payload by a flexible connecting arm; the propulsion unit, the control unit, and the payload are all provided with a distributed attitude control system, a distributed power supply system, and a distributed measurement, control and communication system; the measurement, control and communication unit is provided with a distributed attitude control system and a distributed power supply system. The present invention is based on a module that can operate independently and adaptively, and then defines a core function for each module, and then autonomously networks on-orbit through links between modules to form a large-scale space structure with different functions as the main body. In addition, the system can be updated by replacing the faulty core module, maintaining the long-term on-orbit operation of the entire system and improving its quality-efficiency ratio.

Description

Technical Field

[0001] The present invention relates to a modular self-organizing multifunctional satellite system, which is applicable to the field of aerospace information. Background Art

[0002] With the development of space technology, more and more spacecraft are launched into Earth's space orbit to perform specific missions. However, due to the limited carrying capacity of launch vehicles, it is difficult to build large-scale space structures at one time. In addition, due to the limitations of on-orbit maintenance technology, it is difficult to perform on-orbit operations, such as adding fuel, resulting in relatively low quality and efficiency of spacecraft, which hinders the progress of space technology. Summary of the Invention

[0003] In order to overcome the deficiencies of the prior art, the object of the present invention is to provide a modular self-organizing multifunctional satellite system.

[0004] A modular self-organizing multifunctional satellite system, comprising one or more of a propulsion unit, a control unit, a measurement and control and communication unit, and a payload;

[0005] The propulsion unit and the control unit are connected via a rigid connecting arm;

[0006] The control unit is connected to the measurement, control and communication unit and the load respectively through flexible connecting arms;

[0007] The propulsion unit, control unit, and payload are all equipped with a distributed attitude control system, a distributed power supply system, and a distributed measurement, control, and communication system;

[0008] The measurement, control and communication unit is provided with a distributed attitude control system and a distributed power supply system.

[0009] The propulsion unit, control unit, measurement and control and communication unit, and payload are autonomously networked or replaced on orbit.

[0010] The propulsion unit includes a main thruster, a distributed attitude control system, a distributed power supply system and a distributed measurement, control and communication system. The propulsion unit operates in orbit as an independent unit, or forms a whole with other modules to provide power.

[0011] The control unit is responsible for data calculation and operates independently in orbit through its own distributed attitude control system, distributed power supply system and distributed measurement, control and communication system, or serves as a computing center responsible for complex calculations of the entire self-organizing multifunctional satellite system.

[0012] The measurement, control and communication unit is used for communication of the self-organizing multifunctional satellite system and reception of ground information.

[0013] The payload is one or more, and each of the payloads is equipped with a distributed attitude control system, a distributed power supply system, a distributed measurement, control and communication system, and also includes a load capacity module.

[0014] The load-carrying capacity modules include optical cameras, SAR payloads, and communication payloads.

[0015] The length of the rigid connecting arms is modified according to a pre-designed design; the rigid connecting arms are connected via a telescopic locking rod and a locking head.

[0016] The middle of the flexible connecting arm is a data transmission interface, and the length is modified according to the different systems to be formed.

[0017] The flexible connecting arms are connected via a telescopic locking rod and a locking head.

[0018] Beneficial effects of the present invention:

[0019] (1) Through the development of modular self-organizing multifunctional satellite systems, the construction of large-scale space organizations can be quickly realized.

[0020] (2) Through the development of a modular self-organizing multifunctional satellite system, damaged or problematic modules can be replaced without affecting the operation of the entire system.

[0021] (3) Through the development of a modular self-organizing multifunctional satellite system, the system's on-orbit operating time can be extended by replacing modules that have expired. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural block diagram of a modular self-organizing multifunctional satellite system.

[0023] Figure 2 It is a structural diagram of the rigid connecting arm.

[0024] Figure 3 It is a structural schematic diagram of the flexible connecting arm.

[0025] In the figure, there are a rigid connecting arm 3, a retractable locking rod 4, a locking head 5, a flexible connecting arm 6, and a data line 7. Specific implementation plan

[0026] The present invention will be further described below with reference to the accompanying drawings and examples.

[0027] like Figure 1-3 As shown, a modular self-organizing multifunctional satellite system includes one or more of a propulsion unit, a control unit, a measurement and control and communication unit, and a payload.

[0028] The propulsion unit and the control unit are connected via a rigid connecting arm 3;

[0029] The control unit is connected to the measurement and control and communication unit and the load through a flexible connecting arm 6;

[0030] The propulsion unit, control unit, and payload are all equipped with a distributed attitude control system, a distributed power supply system, and a distributed measurement, control, and communication system;

[0031] The measurement, control and communication unit is provided with a distributed attitude control system and a distributed power supply system.

[0032] The propulsion unit, control unit, measurement and control and communication unit, and payload are autonomously networked or replaced on orbit.

[0033] The propulsion unit includes a main thruster, a distributed attitude control system, a distributed power supply system and a distributed measurement, control and communication system. The propulsion unit operates in orbit as an independent unit, or forms a whole with other modules to provide power.

[0034] The control unit is responsible for data calculation and operates independently in orbit through its own distributed attitude control system, distributed power supply system and distributed measurement, control and communication system, or serves as a computing center responsible for complex calculations of the entire self-organizing multifunctional satellite system.

[0035] The measurement, control and communication unit is used for communication of the self-organizing multifunctional satellite system and reception of ground information.

[0036] The payload is one or more, and each of the payloads is equipped with a distributed attitude control system, a distributed power supply system, a distributed measurement, control and communication system, and also includes a load capacity module.

[0037] The load-carrying capacity modules include optical cameras, SAR payloads, and communication payloads.

[0038] like Figure 2 As shown, the length of the rigid connecting arm 3 is modified according to the pre-design; the rigid connecting arms are connected by a retractable locking rod 4 and a locking head 5.

[0039] like Figure 3 As shown, the middle of the flexible connecting arm 6 is a transmission port for the data line 7, and the length is modified according to the different systems to be formed.

[0040] The flexible connecting arms 6 are connected via a telescopic locking rod 4 and a locking head 5 .

[0041] This invention is based on a core system of independently adaptable modules. Each module is then assigned a core function, and then interconnected on-orbit to autonomously network and form a large-scale spatial structure focused on different functions. Furthermore, system upgrades can be performed by replacing faulty core modules, maintaining the long-term on-orbit operation of the entire system and improving its quality-efficiency ratio. Distributed measurement, control, and communication units, a distributed attitude control unit, and a distributed power supply are all essential.

[0042] The control unit is the "brain" of the entire system, responsible for all data calculations. It also uses its own distributed attitude control system and distributed power supply system to assess the independent on-orbit operation of the distributed measurement, control, and communication system, or acts as a computing center responsible for the complex calculations of the entire system. The measurement, control, and communication system is mainly an autonomous module with measurement, control, and communication capabilities. Its core function is to be responsible for the communication of the entire system and the reception of ground information. The payload includes a distributed attitude control system, a distributed power supply system, a distributed measurement, control, and communication system, and a core payload capacity module. The payload can be an optical camera, a SAR payload, a communication payload, etc. The flexible connecting arm is connected to the control unit, the measurement, control, and communication unit, the payload unit, etc., with a data transmission interface in the middle. The length can be modified according to the different systems to be composed.

[0043] The embodiments described above can further achieve a rigid connection by changing the form of the flexible connecting arm.

[0044] The above-described embodiments can further achieve distributed full connectivity of the entire system by connecting different loads without affecting its functionality.

[0045] The above-described embodiments merely illustrate several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that a person skilled in the art would be able to make numerous modifications and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be determined by the appended claims.

Claims

1. A modular self-organizing multifunctional satellite system, characterized by: Includes one or more of a propulsion unit, a control unit, a measurement and control and communication unit, and a payload; The propulsion unit and the control unit are connected via a rigid connecting arm; The control unit is connected to the measurement, control and communication unit and the load respectively through flexible connecting arms; The propulsion unit, control unit, and payload are all equipped with a distributed attitude control system, a distributed power supply system, and a distributed measurement, control, and communication system; The measurement, control and communication unit is equipped with a distributed attitude control system and a distributed power supply system; The propulsion unit, control unit, measurement and control and communication unit, and payload are autonomously networked or replaced on-orbit; The propulsion unit includes a main thruster, a distributed attitude control system, a distributed power supply system, and a distributed measurement, control, and communication system. The propulsion unit operates in orbit as an independent unit, or forms a whole with other modules to provide power. The control unit is responsible for data calculations and operates independently on orbit through its own distributed attitude control system, distributed power supply system, and distributed measurement, control, and communication system, or serves as a computing center responsible for complex calculations of the entire self-organizing multifunctional satellite system; The measurement, control and communication unit is used for communication with the self-organizing multifunctional satellite system and receiving ground information; The payload is one or more, and each of the payloads is equipped with a distributed attitude control system, a distributed power supply system, a distributed measurement, control and communication system, and also includes a load capacity module; The modules of payload capacity include optical camera, SAR payload and communication payload; The length of the rigid connecting arms is modified according to the pre-design; the rigid connecting arms are connected by a retractable locking rod and a locking head; The middle of the flexible connecting arm is a data transmission interface, and the length is modified according to the different systems to be formed; The flexible connecting arms are connected via a telescopic locking rod and a locking head.

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