Control circuit for initial state setting of unpowered active stage spacecraft and spacecraft

Abstract

The application provides a control circuit for setting the initial state of a non-powered spacecraft in an orbit, comprising a travel switch group, a self-powering circuit, a battery group and a satellite bus; the self-powering circuit is connected with the battery group and the satellite bus respectively, the travel switch is connected with the self-powering circuit, the travel switch generates a state control signal to the self-powering circuit; the travel switch is electrically connected with a pyrotechnic lock signal generating circuit of the satellite and an electrically controlled starting signal generating circuit of the satellite. The application uses different contact points of the travel switch to build multiple combination modes, which can improve the reliability of the satellite-rocket separation signal and the safety margin of the pyrotechnics, and the circuit composed of the simple travel switch realizes multiple functions, completes the initial state setting of the non-powered spacecraft in the active stage and meets the requirements of multiple task parallel triggering.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of spacecraft technology, in particular, to a method and system for setting the initial state of a spacecraft without power supply during the active stage, and more particularly, to a signal generation, self-power-on control and program-controlled starting circuit for star-rocket separation signal and locking signal to complete the initial state setting of a spacecraft without power supply during the active stage. BACKGROUND

[0002] The star-rocket separation signal is an important reference standard for the integrated management unit to perform program-controlled procedure control of the whole device according to the normal time sequence. After the star-rocket separation, the integrated management unit takes the star-rocket separation time point as the starting point of the star time running on the spacecraft, and the program-controlled instructions are sent according to the time sequence to ensure the normal operation of the whole device in orbit.

[0003] The solar cell array and the satellite-communication antenna and other devices are collected and compressed in the cabin body by the locking device before launch, and will be unfolded by the explosive initiation to carry out work in space. Before launch, the explosive initiator is prevented from being connected to the bus, and the solar cell array and other devices are prevented from being unfolded unplanned, which may cause damage. Therefore, a locking explosive initiator positive line connection instruction line circuit is designed. At the same time, after the star-rocket separation, the star-rocket separation signal is not given, which prevents the explosive initiator from being initiated and the mechanism from being unfolded, resulting in the failure of the mission. Therefore, a forced unlocking explosive initiator positive line connection circuit is designed. Therefore, it is an important work to design the locking explosive initiator positive line connection instruction line circuit and the forced unlocking explosive initiator positive line connection circuit.

[0004] For a spacecraft without power supply during the launch active stage, whether the self-power-on can successfully establish the bus is the most important for the success of the whole device. Before launch, the last power-on of the spacecraft sets the self-power-on enable to the allowed state, and then the discharge control circuit is disconnected, the travel switch is compressed, and the whole device enters the power-off state until the star-rocket separation during the active stage. After the star-rocket separation, the travel switch is released, the self-power-on circuit is connected, the energy of the storage battery is transmitted to the bus, the whole device is powered on, and the storage battery supplies power to the whole device. The integrated information system sends the discharge control circuit connection instruction to enter the normal working mode in orbit. Therefore, for a spacecraft without power supply during the launch active stage, it is of great significance to use the travel switch to design the self-power-on circuit.

[0005] In the Chinese patent document with publication number CN113665851B, a pyrotechnic separation signal locking circuit for deep space exploration is disclosed. The main content of the document is that five relays and a rocket separation plug are connected in series and parallel to lock the pyrotechnic separation signal. The first relay K1, the second relay K2, and the fifth relay K5 are connected in parallel. The third relay K3 and the fourth relay K4 are connected in parallel. The third relay K3, the rocket separation plug, and the first relay K1 are connected in series. The invention has simple circuit, high reliability, and when the rocket separation signal fails, the fifth relay can still be turned on to ensure the normal unlocking of the pyrotechnic device, which is suitable for the design of pyrotechnic separation locking of spacecraft such as deep space exploration.

[0006] In the Chinese patent document with publication number CN113636111B, a spacecraft electromechanical separation signal hybrid use system, method and medium are disclosed. The main content of the document is that the separation electrical connector provides an electrical separation signal for the pyrotechnic protection and comprehensive electronic single machine signal acquisition on the spacecraft. The travel switch provides a mechanical separation signal to confirm the mechanical separation of the satellite and rocket, and provides a single machine signal separation signal on the spacecraft. The comprehensive acquisition of the electrical separation signal and the mechanical separation signal confirms that the separation signal on the spacecraft changes from a single command to a double confirmation. The invention can improve the reliability of the separation signal, improve the safety margin of the spacecraft pyrotechnics, and reduce the overall risk.

[0007] In the Chinese patent document with publication number CN111969999B, a reliable launch vehicle separation signal isolation detection and self-locking circuit is disclosed. The main content of the document is that the filter shaping protection circuit receives the external input separation contact signal and filters out the jitter noise; the optocoupler isolation circuit receives the noise filtered separation contact signal and performs isolation detection and signal conditioning; the self-locking output circuit receives the conditioned separation contact signal and realizes self-locking and buffer output. The invention realizes isolation detection and self-locking of the separation signal through a pure electronic element circuit, which is simple, small in size and low in cost, and more reliable than mechanical self-locking systems.

[0008] In the Chinese patent document with publication number CN108945530B, a satellite-rocket separation signal simulation method is disclosed. The main content of the document is that two isolated 28V satellite bus voltages are divided by resistors to 10V signals, respectively, through the plugs and sockets of two satellite-rocket separation electrical connectors, and then logical operations are performed to obtain the satellite-rocket separation indication signal. The satellite-rocket separation signal and its ground wire are led to the ground from the satellite-rocket separation electrical connector, and the two are short-circuited through the ground relay to simulate satellite-rocket separation. The invention generates satellite-rocket separation and simulated satellite-rocket separation signals, and the method is simple, reliable, and improves the safety of the satellite-rocket separation signal circuit.

[0009] In the Chinese patent literature with publication number CN113746472B, a kind of for deep space probe matrix pyrotechnics driving circuit and its control method, the main content of this scheme is first relay etc., first PMOS tube drain and first resistance, second resistance, third resistance, fourth resistance are connected (also make up a total of 4-way), second relay and the source of first NMOS tube, second NMOS tube, third NMOS tube and fourth NMOS tube are connected.The application adopts the matrix control pyrotechnics driving of PMOS positive line switch, NMOS negative line switch, and the device is less, the integration degree is high, it is suitable for satellite to the driving requirements of a large number of low-cost, high integration of pyrotechnics. SUMMARY

[0010] In view of the defects in the prior art, the purpose of the present application is to provide a main section not powered spacecraft orbit insertion initial state setting control circuit and spacecraft.

[0011] According to the present application, a kind of main section not powered spacecraft orbit insertion initial state setting control circuit, comprising: travel switch group, self power-on circuit, battery pack and satellite bus;

[0012] The self power-on circuit is connected with the battery pack and the satellite bus respectively, the travel switch is connected with the self power-on circuit, and the travel switch generates a state control signal to the self power-on circuit;

[0013] The travel switch is electrically connected with the pyrotechnics locking signal generating circuit of the satellite, and the travel switch is electrically connected with the program-controlled starting signal generating circuit of the satellite.

[0014] Preferably, the self power-on circuit includes a first MOS tube and a second MOS tube, the first MOS tube and the second MOS tube are arranged in parallel, the drain of the first MOS tube and the drain of the second MOS tube are electrically connected with the battery pack, the source of the first MOS tube and the source of the second MOS tube are electrically connected with the satellite bus;The gate of the first MOS tube and the gate of the second MOS tube are connected in parallel and then connected with the positive electrode of the battery pack through the travel switch group.

[0015] Preferably, the travel switch group includes travel switch K1, travel switch K2 and travel switch K3;

[0016] The travel switch K1 includes switch K1_1, the travel switch K2 includes switch K2_1, and the travel switch K3 includes switch K3_1;

[0017] The switch K1_1, the switch K2_1 and the switch K3_1 are connected in series and are respectively connected with the battery pack and the gate of the first MOS tube and the gate of the second MOS tube.

[0018] Preferably, a self-power-on enabling circuit is further included, two ends of the self-power-on enabling circuit are electrically connected with the travel switch group and the gate of the first MOS tube and the gate of the second MOS tube respectively.

[0019] The self-power-on enabling circuit comprises switches S3 and S4 which are arranged in parallel.

[0020] Preferably, the first MOS tube and the second MOS tube are both PMOS tubes.

[0021] Preferably, a discharge control circuit is further included, the discharge control circuit is connected with the battery pack and the satellite bus respectively.

[0022] The discharge control circuit comprises switches S1 and S2 which are arranged in parallel.

[0023] Preferably, the travel switch K1 comprises a switch K1_4, the travel switch K2 comprises a switch K2_4, and the travel switch K3 comprises a switch K3_4.

[0024] The switches K1_4, K2_4 and K3_4 are arranged in series and are all normally closed switches; two ends of the series-connected switches K1_4, K2_4 and K3_4 are electrically connected with the positive and negative terminals of the lock signal generating circuit respectively.

[0025] When the positive and negative terminals of the lock signal generating circuit are disconnected, a pyrotechnic lock signal is generated; when the positive and negative terminals of the lock signal generating circuit are connected, a pyrotechnic forced unlocking signal is generated.

[0026] Preferably, the travel switch K1 comprises switches K1_2 and K1_3, the travel switch K2 comprises switches K2_2 and K2_3, and the travel switch K3 comprises switches K3_2 and K3_2.

[0027] The switches K1_2 and K2_2 are arranged in series, the switches K1_3 and K3_3 are arranged in series, and the switches K2_3 and K3_2 are arranged in series; the three groups of series-connected switches are arranged in parallel, and two ends of the parallel-connected switches are connected with the two ends of the program-controlled start signal generating circuit respectively.

[0028] When the two ends of the program-controlled start signal generating circuit are closed, no satellite-rocket separation signal is generated.

[0029] When the two ends of the program-controlled start signal generating circuit are disconnected, a satellite-rocket separation signal is generated.

[0030] Preferably, the switches K1_2, K1_3, K2_2, K2_3, K3_2 and K3_2 are all normally closed switches.

[0031] The application provides a spacecraft, which comprises the active stage non-powered spacecraft orbiting initial state setting control circuit.

[0032] Compared with the prior art, the application has the following beneficial effects:

[0033] 1、The application is aimed at a locking signal generating circuit, which is realized by three sets of normally closed contacts and is respectively from three travel switches, so that the failure of one of the travel switches can be avoided, and the false generation of the satellite-rocket separation signal or the failure of generating the satellite-rocket separation signal can be avoided, and the subsequent task failure can be avoided.

[0034] 2、The application adopts a cold backup forced unlocking pyrotechnic positive line connection instruction line, so that after the satellite-rocket separation caused by multiple faults, the satellite-rocket separation signal is not given, and at this time, the forced unlocking pyrotechnic positive line connection instruction is sent to complete the subsequent task of the pyrotechnic bus connection.

[0035] 3、The switch K1_1, the switch K2_1 and the switch K3_1 are respectively from three different travel switches, so that the failure of one of the travel switches can be avoided, and the false generation of the satellite-rocket separation signal or the failure of generating the satellite-rocket separation signal can be avoided, and the subsequent task failure can be avoided.

[0036] 4、The switch K1_1, the switch K2_1 and the switch K3_1 are three sets of normally open contact travel switches in series, and power-on is ensured. After the satellite-rocket separation, any one of the switches is disconnected, the satellite-rocket separation signal is triggered, and the self-power-on circuit is started.

[0037] 5、The self-power-on circuit uses two MOS tubes in parallel form, and the reliability is enhanced. During the ground test, the self-power-on circuit is in the prohibited state, and the accidental start of the self-power-on circuit is prevented.

[0038] 6、The application uses six sets of normally open contacts in the travel control start signal generating circuit, which are respectively from three different travel switches, so that the failure of one of the travel switches can be avoided, and the false generation of the satellite-rocket separation signal or the failure of generating the satellite-rocket separation signal can be avoided, and the subsequent task failure can be avoided. The six sets of normally open contact travel switches are realized in two strings and three parallel forms, and power-on is ensured. Before the satellite-rocket separation, any one of the switches is disconnected, and the satellite-rocket separation signal is not triggered by mistake. After the satellite-rocket separation, any one of the switches is not disconnected, and the satellite-rocket separation signal is not affected. Any one of the pressing points is not released, and the satellite-rocket separation signal is not triggered. The satellite-rocket separation signal interfaces of other subsystems are isolated from each other, and the reliability is enhanced.

[0039] 7、The three travel switches in the application are distributed at different positions of the satellite-rocket docking surface, the separation and connection states of different parts between the carrier and the spacecraft are effectively reflected, and the false triggering of the satellite-rocket separation signal is avoided. BRIEF DESCRIPTION OF DRAWINGS

[0040] Other features, objects, and advantages of the application will become more apparent from the following detailed description when read in conjunction with the accompanying drawings, in which:

[0041] Figure 1 is a scheme diagram of the star-rocket separation signal.

[0042] Figure 2 is a schematic diagram of an autonomous power-on design.

[0043] Figure 3 is a circuit diagram of a star-rocket separation signal circuit (before star-rocket separation) of a comprehensive management unit.

[0044] Figure 4 is a program-controlled starting circuit diagram. DETAILED DESCRIPTION

[0045] The application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be pointed out that those skilled in the art can make several changes and improvements without departing from the concept of the application. These are within the scope of the application.

[0046] The application utilizes an active stage non-powered spacecraft orbit insertion initial state setting control circuit, which includes a travel switch that locks a pyrotechnic positive line connection instruction line before star-rocket separation, and after star-rocket separation, the pyrotechnic positive line connection instruction line is unlocked, and the pyrotechnic connection is completed according to the program-controlled procedure; the travel switch provides a mechanical star-rocket separation signal to confirm the mechanical separation of the star-rocket, and generates a multi-path star-rocket separation signal to be transmitted to a single machine on the spacecraft; the launch active stage is not powered, and the power supply controller on the spacecraft receives the star-rocket separation signal to complete self-power-on through the platform bus MOS tube discharge path connection, the battery supplies power to the whole device to ensure normal operation of the whole device; the power supply controller receives the star-rocket separation signal to unlock the pyrotechnic positive line connection instruction; the comprehensive management unit collects the star-rocket separation signal and controls each single machine of the whole device to work according to the program-controlled procedure.

[0047] Specifically, the circuit structure is:

[0048] An active stage non-powered spacecraft orbit insertion initial state setting control circuit includes a travel switch group, a self-power-on circuit, a battery group, and a satellite bus. The self-power-on circuit is connected to the battery group and the satellite bus respectively, the travel switch is connected to the self-power-on circuit, and the travel switch generates a state control signal to the self-power-on circuit; the travel switch is electrically connected to a pyrotechnic lock signal generation circuit of the satellite and a program-controlled starting signal generation circuit of the satellite.

[0049] Specifically, the power-on circuit includes a first MOS tube and a second MOS tube, the first MOS tube and the second MOS tube are arranged in parallel, the drain of the first MOS tube and the drain of the second MOS tube are electrically connected with the battery pack, the source of the first MOS tube and the source of the second MOS tube are electrically connected with the satellite bus; the gate of the first MOS tube and the gate of the second MOS tube are electrically connected with the positive pole of the battery pack through the travel switch group. The first MOS tube and the second MOS tube are both PMOS tubes.

[0050] The travel switch group includes a travel switch K1, a travel switch K2 and a travel switch K3; the travel switch K1 includes a switch K1_1, the travel switch K2 includes a switch K2_1, and the travel switch K3 includes a switch K3_1; the switch K1_1, the switch K2_1 and the switch K3_1 are connected in series and are respectively electrically connected with the battery pack and the gate of the first MOS tube and the gate of the second MOS tube.

[0051] The travel switch K1 includes a switch K1_4, the travel switch K2 includes a switch K2_4, and the travel switch K3 includes a switch K3_4.

[0052] The switch K1_4, the switch K2_4 and the switch K3_4 are connected in series and are all normally closed switches; the two ends of the switch K1_4, the switch K2_4 and the switch K3_4 connected in series are respectively electrically connected with the positive pole and the negative pole of the lock signal generating circuit.

[0053] When the positive pole and the negative pole of the lock signal generating circuit are disconnected, the pyrotechnic lock signal is generated; when the positive pole and the negative pole of the lock signal generating circuit are connected, the pyrotechnic forced unlocking signal is generated.

[0054] The travel switch K1 includes a switch K1_2 and a switch K1_3, the travel switch K2 includes a switch K2_2 and a switch K2_3, and the travel switch K3 includes a switch K3_2 and a switch K3_2; the switch K1_2, the switch K1_3, the switch K2_2, the switch K2_3, the switch K3_2 and the switch K3_2 are all normally closed switches.

[0055] The switch K1_2 and the switch K2_2 are connected in series, the switch K1_3 and the switch K3_3 are connected in series, and the switch K2_3 and the switch K3_2 are connected in series; the three groups of switches connected in series are connected in parallel, and the two ends of the switches connected in parallel are respectively connected with the two ends of the program-controlled starting signal generating circuit.

[0056] When the two ends of the program-controlled starting signal generating circuit are closed, the satellite-rocket separation signal is not generated.

[0057] When the two ends of the program-controlled starting signal generating circuit are disconnected, the satellite-rocket separation signal is generated.

[0058] The self-power-on circuit is connected with the travel switch group and the first MOS tube gate and the second MOS tube gate respectively.

[0059] The discharge control circuit is connected with the battery group and the satellite bus respectively.

[0060] The discharge control circuit comprises the switch S1 and the switch S2 which are connected in parallel.

[0061] The specific working process of the circuit is shown in the following: Figure 1

[0062] Before the separation of the satellite and the rocket, the positive line connection instruction line circuit of the lock pyrotechnics and the positive line connection circuit of the forced unlocking pyrotechnics are connected, and before the launch, the travel switches are in the pressed state, and the travel switches K1-4, K2-4 and K3-4 are all in the normally open state, and the positive line connection instruction line of the lock pyrotechnics is connected; after the separation of the satellite and the rocket, the travel switches are all released and in the normally closed state, and the positive line connection line of the unlocking pyrotechnics is unlocked; in the normal state, the relay (two parallel) is in the open state, and if the satellite and the rocket separation signal fault occurs, the relay (two parallel) is connected through the sending instruction, and the positive line connection line of the unlocking pyrotechnics is forced to be connected.

[0063] Before the separation of the satellite and the rocket, the self-power-on circuit is connected, as shown in the following: Figure 1 and Figure 2 The discharge switches S1 and S2 are disconnected, the self-power-on enabling S3 and S4 are connected, and the travel switches K1-1, K2-1 and K3-1 are in the pressed state, i.e. in the connected state; after the separation of the satellite and the rocket, the travel switches are all released, i.e. in the disconnected state, the self-power-on circuit is connected, the P tube GS voltage is established, and the P tube is connected. The battery group is connected to the bus of the integrator, and the power-on of the integrator is realized.

[0064] Before the separation of the satellite and the rocket, the program-controlled starting circuit is connected, as shown in the following: Figure 3 and Figure 4 The travel switches K1-2, K2-2, K1-3, K3-3, K2-3 and 3-2 are in the pressed state, i.e. in the connected state, the satellite and the rocket separation indication telemetry is in the high level before the separation of the satellite and the rocket; after the separation of the satellite and the rocket, the travel switches are all released, i.e. in the disconnected state, the satellite and the rocket separation indication telemetry is in the low level after the separation of the satellite and the rocket, the program-controlled program is started, and the integrator works.

[0065] The application further provides a spacecraft, which adopts the above-mentioned active stage non-power-on spacecraft orbit insertion initial state setting control circuit.

[0066] ​In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like refer to the orientation or positional relationship shown in the drawings, and are only intended to facilitate the description of the present application and simplify the description, and are not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0067] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which do not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict, provided that they do not conflict.

Claims

1. A control circuit for setting an initial state of an unpowered orbiter during a powered phase, characterized in that, The application relates to a satellite power supply system, which comprises a travel switch group, a self-power-on circuit, a battery group and a satellite bus. The self-power-on circuit is connected with the battery group and the satellite bus respectively, the travel switch is connected with the self-power-on circuit, and the travel switch generates a state control signal to the self-power-on circuit. The travel switch is electrically connected with a pyrotechnic lock signal generating circuit of the satellite and a program-controlled starting signal generating circuit of the satellite. The self-power-on circuit comprises a first MOS tube and a second MOS tube, the first MOS tube and the second MOS tube are arranged in parallel, the drain of the first MOS tube and the drain of the second MOS tube are electrically connected with the battery group, the source of the first MOS tube and the source of the second MOS tube are electrically connected with the satellite bus, the gate of the first MOS tube and the gate of the second MOS tube are electrically connected with the positive pole of the battery group through the travel switch group. The travel switch group comprises travel switches K1, K2 and K3. The travel switch K1 comprises a switch K1_1, the travel switch K2 comprises a switch K2_1, and the travel switch K3 comprises a switch K3_1. The switch K1_1, the switch K2_1 and the switch K3_1 are connected in series and are respectively electrically connected with the battery group and the gate of the first MOS tube and the gate of the second MOS tube. The travel switch K1 comprises a switch K1_4, the travel switch K2 comprises a switch K2_4, and the travel switch K3 comprises a switch K3_4. The switch K1_4, the switch K2_4 and the switch K3_4 are arranged in series and are all normally closed switches, and the two ends of the series-connected switch K1_4, the switch K2_4 and the switch K3_4 are respectively electrically connected with the positive pole and the negative pole of the lock signal generating circuit. When the positive pole and the negative pole of the lock signal generating circuit are disconnected, a pyrotechnic lock signal is generated, and when the positive pole and the negative pole of the lock signal generating circuit are connected, a pyrotechnic forced unlocking signal is generated. The application further comprises a self-power-on enabling circuit, and the two ends of the self-power-on enabling circuit are respectively electrically connected with the travel switch group and the gate of the first MOS tube and the gate of the second MOS tube.

2. The control circuit according to claim 1, wherein The self-power-on enabling circuit comprises switches S3 and S4, and the switches S3 and S4 are arranged in parallel. The first MOS tube and the second MOS tube are both PMOS tubes.

3. The control circuit according to claim 1, wherein The application further comprises a discharge control circuit, and the discharge control circuit is connected with the battery group and the satellite bus respectively.

4. The control circuit according to claim 1, wherein The discharge control circuit comprises switches S1 and S2 arranged in parallel. The travel switch K1 comprises switches K1_2 and K1_3, the travel switch K2 comprises switches K2_2 and K2_3, and the travel switch K3 comprises switches K3_2 and K3_2.

5. The control circuit according to claim 1, wherein The switch K1_2 and the switch K2_2 are arranged in series, the switch K1_3 and the switch K3_3 are arranged in series, and the switch K2_3 and the switch K3_2 are arranged in series; the three groups of series-connected switches are arranged in parallel, and the two ends of the parallel-connected switches are respectively connected with the two ends of the program-controlled starting signal generating circuit. When the two ends of the program-controlled starting signal generating circuit are closed, no satellite-rocket separation signal is generated. When the two ends of the program-controlled starting signal generating circuit are disconnected, a satellite-rocket separation signal is generated. ​ 6. The control circuit according to claim 5, wherein The switch K1_2, the switch K1_3, the switch K2_2, the switch K2_3, the switch K3_2 and the switch K3_2 are all normally closed switches.

7. A spacecraft, characterized by, The control circuit is used for setting the initial state of the non-electric powered spacecraft in orbit.

Images