Satellite telemetry application mode and architecture of three-level protection mechanism
Technical Field
The invention relates to a satellite telemetry application mode and architecture of a three-level protection mechanism, and belongs to the field of satellite overall design.
Background
Current conventional satellite telemetry designs typically use satellite-service generated telemetry as a satellite downlink telemetry package, i.e., normal telemetry is mentioned in this patent. The scheme has high dependence on software and hardware reliability of the satellite system. Once the satellite service system has software and hardware faults, the satellite loses downlink signals, so that the information of the ground to the satellite is lost, the satellite can only be blindly controlled, and the safety of the whole satellite is endangered. The invention breaks through the traditional telemetry design thought, provides telemetry application modes of a normal telemetry, key telemetry and self telemetry three-level protection mechanism, gradually improves telemetry reliability and importance in the application modes, gradually reduces telemetry information coverage, provides a step-by-step analysis and debugging means according to different telemetry in satellite fault states, and improves satellite on-orbit safety and reliability.
Disclosure of Invention
The invention aims at overcoming the defects of the prior art and provides a satellite telemetry application mode and architecture of a three-level protection mechanism.
The aim of the invention is realized by the following technical scheme:
A satellite telemetry method of a three-level protection mechanism comprises normal telemetry, key telemetry and self telemetry. The normal telemetry is a telemetry data packet generated by collecting satellite traffic and subsystem engineering telemetry, the key telemetry is a telemetry data packet generated by collecting key engineering telemetry through a point-to-point dedicated line by the overall circuit subsystem, and the self telemetry is a telemetry data packet generated by a measurement and control transponder, and the three telemetry are protected step by step.
The satellite telemetry application mode of the three-level protection mechanism mainly comprises that the measurement and control subsystem transmits normal telemetry when the measurement and control subsystem monitors normal telemetry with the star service generation, the measurement and control subsystem transmits key telemetry when the measurement and control subsystem monitors normal telemetry without the star service generation and transmits self telemetry when the measurement and control subsystem does not have key telemetry generated by the overall circuit subsystem.
The satellite architecture comprises measurement and control subsystems capable of respectively transmitting self-telemetry, key telemetry and normal telemetry under different states on the satellite, an overall circuit subsystem capable of collecting key engineering telemetry of the key subsystems through a point-to-point dedicated line and then generating key telemetry, a satellite subsystem capable of collecting normal engineering telemetry of all subsystems through a bus form and generating normal telemetry, and other subsystems. The measurement and control subsystem is connected with the overall circuit subsystem through a special line, the satellite subsystem is connected with the overall circuit subsystem through a special line, and the other subsystems are connected with the overall circuit subsystem through special lines of the respective subsystems.
Compared with the prior art, the invention has the beneficial effects that:
Different from the traditional single telemetry design of the satellite, the invention provides the normal telemetry, key telemetry and self telemetry concepts, and based on the three telemetry reliability and importance progressive improvement, telemetry information coverage progressive decline, and the progressive layering analysis concept is utilized to realize a multistage telemetry layering application mode.
Drawings
FIG. 1 is a flow chart of a satellite telemetry application mode of a three-level protection mechanism;
FIG. 2 is a schematic diagram of a satellite architecture for a satellite telemetry application mode based on a three-level protection mechanism.
Detailed description of the preferred embodiments
FIG. 1 is a flow chart of a satellite telemetry application mode of a three-level protection mechanism, and the flow chart mainly comprises that a measurement and control subsystem transmits normal telemetry when the measurement and control subsystem monitors normal telemetry with the star service generation, transmits key telemetry when the measurement and control subsystem monitors normal telemetry without the star service generation and transmits self telemetry when the measurement and control subsystem does not have key telemetry generated by the overall circuit subsystem.
FIG. 2 is a schematic view of a satellite architecture for a satellite telemetry application model based on a three-level protection scheme, mainly comprising:
The system comprises a measurement and control subsystem 1 capable of respectively transmitting self-telemetry, key telemetry and normal telemetry under different states on the satellite, a general circuit subsystem 2 capable of collecting key engineering telemetry of the key subsystem through a point-to-point special line and then generating key telemetry, a satellite subsystem 3 capable of collecting normal engineering telemetry of all subsystems and generating normal telemetry through a bus form, and other subsystems 4. The measurement and control subsystem 1, the overall circuit subsystem 2 and the satellite subsystem 3 are connected with the rest subsystem 4 through a bus 5, the measurement and control subsystem 1 is connected with the overall circuit subsystem 2 through a special line 6, the satellite subsystem 3 is connected with the overall circuit subsystem 2 through a special line 7, and the rest subsystems 4 are connected with the overall circuit subsystem 2 through special lines 8 of the respective subsystems.
The following is a detailed description of a satellite telemetry application mode and architecture application example based on a three-level protection mechanism:
The measurement and control subsystem, the overall circuit subsystem and the satellite subsystem are defined by the traditional subsystem, the measurement and control subsystem is characterized by being capable of generating self-telemetry and respectively transmitting the self-telemetry, the key telemetry and the normal telemetry according to different states on the satellite, the overall circuit subsystem is characterized by being capable of collecting key engineering telemetry of the key subsystem through a point-to-point dedicated line and then generating the key telemetry, the fact that the traditional satellite does not have the key telemetry is required to be specially explained, the satellite system is in a new telemetry form provided herein, and the satellite subsystem is characterized by being capable of collecting normal engineering telemetry of all the subsystems through a bus form and generating the normal telemetry. According to the traditional satellite design, from the aspects of satellite component type selection or system reliability design, the reliability ordering of the three subsystems is that a measurement and control subsystem is that of a total circuit subsystem and a satellite service subsystem, so that the reliability ordering of the three telemetry is that of self telemetry is that of key telemetry and normal telemetry. However, as the interactive information quantity of the three sub-systems and the rest sub-systems under the satellite architecture is sequenced as normal telemetry > key telemetry > self telemetry, a mechanism that the reliability is gradually reduced according to the sequence of self telemetry, key telemetry and normal telemetry is formed, and the information quantity is gradually enriched is utilized to form a multistage telemetry layering application mode, and a step-by-step analysis and debugging means according to telemetry under the condition of satellite in-orbit fault which is not possessed by the traditional satellite is provided.
Based on the above definition and description, the bus of the specific embodiment herein uses a CAN bus as an example, and the point-to-point dedicated line between each subsystem uses SPI as an example. The satellite subsystem collects engineering telemetry of each subsystem through the CAN bus, generates normal telemetry packets according to telemetry packet formats, and then sends the normal telemetry packets to the measurement and control subsystem, the overall circuit subsystem collects key engineering telemetry of each subsystem through each SPI dedicated line to generate key telemetry packets, and simultaneously sends the key telemetry packets to the measurement and control subsystem, and the measurement and control subsystem collects connection states of the satellite subsystem and other subsystems and software and hardware states of the satellite subsystem to generate self telemetry packets. The distribution mechanism of the measurement and control subsystem adopts the following strategies that if normal telemetry of the star service is received, normal telemetry is sent to the ground, if normal telemetry of the star service is not received but key telemetry of the overall circuit is received, key telemetry is sent to the ground, and if both normal telemetry of the star service and key telemetry of the overall circuit are not received, self telemetry is sent to the ground.
The previous description of the disclosed examples is provided to enable any person skilled in the art to make or use the present invention. Various modifications to this example will be readily apparent to those skilled in the art. The method is characterized in that the method comprises the steps of determining the number of the satellite telemetry application modes and the architecture examples based on the three-level protection mechanism, wherein the number of the satellite telemetry application modes and the architecture examples are increased and decreased in the measurement and control subsystem, the total circuit subsystem and the satellite service subsystem, and the changes in names of the satellite telemetry application modes and the architecture examples are all within the protection scope of the corresponding claims of the method, and the changes of three telemetry names, the realization subsystem carriers and the like are also within the protection scope of the corresponding claims of the method. Thus, the present invention is not intended to be limited to the examples shown herein but is to be accorded the widest scope consistent with the principles disclosed herein.