Method, system, medium and device for controlling a common travel switch

Abstract

The application provides a control method, system, medium and equipment of shared travel switch, including: each travel switch used has two pairs of contacts, which are respectively used for power controller power-on control signal and integrated electronic computer software program control start signal; multiple travel switches are used to realize satellite autonomous power-on and software self-start control, wherein the power-on control signal of the power controller is connected in a mode that multiple travel switches are connected in parallel with each other, so that the satellite is autonomously powered on when any travel switch is released; the integrated electronic computer software program control start signal is connected in a mode that multiple travel switches are connected in series, so that the active satellite will not be caused to be program-controlled to start due to the false release of a single travel switch; and for the case that a single travel switch is invalid after the satellite and the rocket are separated, the satellite completes software program control start by receiving a ground program control start instruction.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular, to a control method, system, medium and equipment of shared travel switch. BACKGROUND

[0002] In the launch process of a satellite, the separation link between the satellite and the launch vehicle is crucial. Due to the weight and space limitations of small satellites, they usually adopt a passive mechanism to achieve power-up after being launched and separated from the launch vehicle. In traditional satellite design, the autonomous power-up and software self-start after satellite-rocket separation are usually controlled separately, which may lead to increased control complexity and reduced reliability. Especially in the case of not being powered during the active stage, a more accurate and reliable control method is needed to ensure the normal operation of the satellite at critical moments. SUMMARY

[0003] In view of the defects in the prior art, the purpose of the present application is to provide a control method, system, medium and equipment of shared travel switch.

[0004] The control method of shared travel switch provided by the present application comprises:

[0005] The travel switch is arranged between the power controller power-up control signal and the integrated electronic computer software program-controlled start signal;

[0006] The output end of the travel switch is connected to the input end of the power controller, and the power controller is pre-set to respond to the signal of the travel switch and control the power supply of the computer;

[0007] The control software is written or used to receive the state information from the travel switch and perform corresponding operations according to the preset logic; in the control software, it is set that when the integrated electronic computer receives the travel switch signal, the start program or script is automatically run.

[0008] The travel switch contains two pairs of contacts, which are connected between the power controller power-up control signal and the integrated electronic computer software program-controlled start signal.

[0009] Preferably, the integrated electronic computer software program-controlled start signal is realized by a series connection mode of multiple travel switches.

[0010] Preferably, the power controller power-up control signal is realized by a parallel connection mode of multiple travel switches.

[0011] Preferably, the travel switch is arranged at the satellite and launch vehicle separation interface, and is evenly arranged on the outer edge of the satellite-rocket separation surface, and every two travel switches are separated by at least 50mm.

[0012] The control system of the shared travel switch comprises:

[0013] The travel switch is arranged between the power controller on power control signal and the integrated electronic computer software program control start signal;

[0014] The output end of the travel switch is connected to the input end of the power controller, and the power controller is pre-set to respond to the signal of the travel switch and control the power supply of the computer;

[0015] The control software is written or used to receive the state information from the travel switch and perform corresponding operations according to the preset logic; in the control software, when the integrated electronic computer receives the travel switch signal, the start program or script is automatically run.

[0016] The travel switch comprises two pairs of contacts, which are connected between the power controller on power control signal and the integrated electronic computer software program control start signal.

[0017] Preferably, the integrated electronic computer software program control start signal is realized by the series connection of multiple travel switches.

[0018] Preferably, the power controller on power control signal is realized by the parallel connection of multiple travel switches.

[0019] Preferably, the travel switch is arranged at the satellite and launch vehicle separation interface, is uniformly arranged at the outer edge of the satellite and launch vehicle separation surface, and every two travel switches are separated by at least 50 mm.

[0020] The computer readable storage medium storing the computer program provided by the application, when the computer program is executed by the processor, realizes the steps of the shared travel switch control method.

[0021] The electronic device provided by the application comprises a memory, a processor and a computer program stored on the memory and executable on the processor, and when the computer program is executed by the processor, realizes the steps of the shared travel switch control method.

[0022] Compared with the prior art, the application has the following beneficial effects:

[0023] (1) The application provides a shared travel switch control method, which effectively improves the autonomy and reliability of the satellite in the key stage through the satellite and launch vehicle separation travel switch shared circuit design;

[0024] (2) The software program control start signal is realized by the series connection of multiple travel switches, which can prevent the software program control start from being triggered due to the false release of a single travel switch, and ensure the energy safety of the satellite;

[0025] (3) Self-power-on control signal is achieved by parallel connection of the travel switches, which can ensure that the release of any one of the travel switches can result in autonomous power-on of the satellite; when a single travel switch fails after the satellite and the launch vehicle are separated, the satellite can be normally powered on and complete software program-controlled start-up by receiving program-controlled start-up instructions from the ground. BRIEF DESCRIPTION OF DRAWINGS

[0026] Other features, objects, and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, when read in conjunction with the accompanying drawings:

[0027] Figure 1 Figure 1 is a schematic diagram of a travel switch circuit shared by autonomous power-on and software self-start-up of an embodiment of the application. DETAILED DESCRIPTION

[0028] The application will be described in greater detail with reference to specific embodiments. The following embodiments are helpful for those skilled in the art to further understand the application, but do not limit the application in any form. It should be noted that, for those skilled in the art, without departing from the concept of the application, a number of changes and improvements can be made. These all belong to the protection scope of the application.

[0029] Embodiment 1

[0030] As Figure 1 , the connection relationship diagram of the travel switch shared by autonomous power-on and software self-start-up in the embodiment of the application, the application provides a travel switch control method shared by autonomous power-on and software self-start-up, which effectively improves the autonomy and reliability of the satellite in the key stage through the travel switch shared circuit design of the satellite and the launch vehicle separation.

[0031] Specifically includes the following steps:

[0032] Step S1: using the travel switch to perform self-power-on of the satellite, which is arranged at both ends of the power controller power-on control signal and both ends of the software program-controlled start-up signal of the integrated electronic computer;

[0033] Step S2: the contacts connected between both ends of the power controller power-on control signal are in parallel, and the contacts connected between both ends of the software program-controlled start-up signal of the integrated electronic computer are in series;

[0034] The travel switch includes two pairs of contacts, as Figure 1 shown, Ka1 and Kb1 are two pairs of contacts of the same travel switch, which are used to connect both ends of the power controller power-on control signal and both ends of the software program-controlled start-up signal of the integrated electronic computer, respectively. Ka2 and Kb2 to Kan and Kbn are the same.

[0035] In step S1, the software program control start signal of the integrated electronic computer is realized by connecting the multiple trip switches of Kb2 to Kbn in series to prevent the software program control start from being triggered by the false release of a single trip switch.

[0036] In step S2, the self power-on control signal of the power controller is realized by connecting the multiple trip switches of Ka1 and Kb1 in parallel to ensure that the release of any one of the trip switches can result in the autonomous power-on of the satellite.

[0037] When a single trip switch fails after the satellite-rocket separation, the parallel connection of Ka1 and Kb1 enables the satellite to be normally powered on and complete the software program control start by receiving the program control start instruction from the ground.

[0038] When a single trip switch is released by mistake during the active stage of the satellite, the series connection of Kb2 to Kbn can ensure that the satellite software program control does not start, thereby ensuring the safety of the satellite energy.

[0039] The trip switch is of the 2KX-1 type and is arranged at the satellite-rocket separation interface to activate the trip switch when the satellite and the rocket are separated.

[0040] The trip switch control method is used to realize the autonomous power-on and software self-start after the satellite-rocket separation.

[0041] The trip switch is designed to be stable in extreme environments, including high temperature, low temperature, high pressure, low pressure, strong vibration and vacuum environment.

[0042] The application also provides a computer readable storage medium storing a computer program, which, when executed by a processor, implements the steps of the control method of the shared trip switch.

[0043] The application also provides an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, which, when executed by the processor, implements the steps of the control method of the shared trip switch.

[0044] Embodiment 2

[0045] The application also provides a control system of the shared trip switch, which can be realized by executing the flow steps of the control method of the shared trip switch, i.e., the control method of the shared trip switch can be understood by those skilled in the art as the preferred embodiment of the control system of the shared trip switch.

[0046] The control system of the shared travel switch comprises: the travel switch is arranged between the power-on control signal of the power supply controller and the software program control start signal of the integrated electronic computer; the output end of the travel switch is connected to the input end of the power supply controller, the power supply controller is pre-set to respond to the signal of the travel switch and control the power supply of the computer; the control software is written or used to receive the state information from the travel switch and perform corresponding operation according to the preset logic; the start program or script is automatically run in the control software when the integrated electronic computer receives the travel switch signal. The travel switch comprises two pairs of contacts, which are connected between the power-on control signal of the power supply controller and the software program control start signal of the integrated electronic computer.

[0047] The software program control start signal of the integrated electronic computer is realized by the series connection of multiple travel switches.

[0048] The power-on control signal of the power supply controller is realized by the parallel connection of multiple travel switches.

[0049] The travel switch is arranged at the separation interface between the satellite and the carrier rocket, is uniformly arranged at the outer edge of the satellite-rocket separation surface, and is separated by at least 50 mm.

[0050] Those skilled in the art know that, in addition to realizing the system, device and each module thereof provided by the present application in the form of pure computer readable program code, the same program can also be realized in the form of logic gate, switch, application specific integrated circuit, programmable logic controller and embedded microcontroller by logically programming the method steps. Therefore, the system, device and each module thereof provided by the present application can be considered as a hardware component, and the modules included therein for realizing various programs can also be considered as structures in the hardware component; the modules for realizing various functions can also be considered as both software programs for realizing methods and structures in the hardware component.

[0051] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be combined with each other in any way without conflict.

Claims

1. A control method of a common travel switch, characterized by, The application relates to a control method of a common travel switch. The travel switch is arranged between the power-on control signal of the power controller and the software programmable start signal of the general electronic computer. The output end of the travel switch is connected to the input end of the power controller, the power controller is previously set to respond to the signal of the travel switch and control the power supply of the computer, and control software is written or used to receive the state information from the travel switch and execute corresponding operations according to preset logic. The travel switch contains two pairs of contacts which are connected between the power-on control signal of the power controller and the software programmable start signal of the general electronic computer. The software programmable start signal of the general electronic computer is realized through the series connection of multiple travel switches. The power-on control signal of the power controller is realized through the parallel connection of multiple travel switches. The travel switches are arranged at the separation interface between a satellite and a carrier rocket, are uniformly arranged at the outer edge of the satellite-rocket separation surface, and are separated by at least 50 mm. The application relates to a control method of a common travel switch.

2. A control system for a common travel switch, characterized by The travel switch is arranged between the power-on control signal of the power controller and the software programmable start signal of the general electronic computer. The output end of the travel switch is connected to the input end of the power controller, the power controller is previously set to respond to the signal of the travel switch and control the power supply of the computer, and control software is written or used to receive the state information from the travel switch and execute corresponding operations according to preset logic. The travel switch contains two pairs of contacts which are connected between the power-on control signal of the power controller and the software programmable start signal of the general electronic computer. The software programmable start signal of the general electronic computer is realized through the series connection of multiple travel switches. The power-on control signal of the power controller is realized through the parallel connection of multiple travel switches. The travel switches are arranged at the separation interface between a satellite and a carrier rocket, are uniformly arranged at the outer edge of the satellite-rocket separation surface, and are separated by at least 50 mm. The computer program is executed by a processor to realize the steps of the control method of the common travel switch. The computer program is executed by a processor to realize the steps of the control method of the common travel switch.

3. A computer readable storage medium storing a computer program, characterized in that, ​ 4. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, ​

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