Control circuit for setting initial orbit injection state of spacecraft without power on active section and spacecraft

Abstract

The invention provides a control circuit for setting an initial orbit injection state of a spacecraft without power-on at an active section. The control circuit comprises a travel switch group, a self-power-on circuit, a storage battery pack and a satellite bus, the self-power-on circuit is respectively connected with a storage battery pack and a satellite bus, 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 an initiating explosive device locking signal generating circuit of a satellite, and the travel switch is electrically connected with a program control starting signal generating circuit of the satellite. Various combination modes are constructed by utilizing different contacts of the travel switches, the reliability of satellite-rocket separation signals can be improved, the safety margin of an initiating explosive device is improved, multiple functions are realized through a circuit formed by the simple travel switches, the initial state setting of orbit injection of a spacecraft without being powered up in an active section is completed, and the reliability of the spacecraft is improved. And the requirement of multi-task parallel triggering is met.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft technology, and in particular, to a method and system for setting the initial state of an active-stage unpowered spacecraft entering orbit, and in particular, to a circuit involving the generation of satellite-rocket separation signals and locking signals, self-power-on control and program-controlled starting, so as to complete the initial state setting of an active-stage unpowered spacecraft entering orbit. Background Art

[0002] The satellite-rocket separation signal is an important reference standard for the integrated management unit to control the whole device to work according to the normal time sequence. After the satellite-rocket separation and the spacecraft enters space, the integrated management unit uses the time point of satellite-rocket separation as the starting point of the spacecraft's operating time, and sends program control instructions in time sequence to ensure the normal operation of the whole device in orbit.

[0003] Before launch, the solar array and satellite-to-ground communication antennas and other equipment are all folded and pressed against the cabin through a locking device. After entering space, they will be deployed and work will be carried out through the detonation of pyrotechnics. Before launch, in order to prevent the pyrotechnic busbar from being connected, the pyrotechnics from detonating, and then causing unplanned deployment of the solar array and other equipment, causing damage to them, a circuit for locking the pyrotechnic positive line connection command line is designed; at the same time, after the separation of the satellite and the rocket, the satellite-rocket separation signal is not given, resulting in the failure of the pyrotechnics to detonate and the mechanism to deploy, leading to the failure of the mission, so a circuit for forcibly unlocking the pyrotechnic positive line connection is designed. Therefore, it is an important task to design a circuit for locking the pyrotechnic positive line connection command line and a circuit for forcibly unlocking the pyrotechnic positive line connection circuit.

[0004] For spacecraft that launches without power to the active segment, whether the bus can be successfully established by self-powering is of utmost importance for the success of the entire device. When the spacecraft is powered on for the last time before launch, the self-power-on enable is set to the allowed state, and then the discharge control circuit is disconnected, the travel switch is pressed, and the entire device enters the power-off state until the active segment and the rocket are separated. When the rocket and the satellite are separated, the travel switch is released, the self-power-on circuit is connected, and the energy of the battery is transferred to the bus, the entire device is powered on, and the battery supplies power to the entire device. The integrated information subsystem sends a discharge control circuit connection command to enter the normal on-orbit working mode. Therefore, for spacecraft that launch without power to the active segment, it is of great significance to use a travel switch to design a self-power-on circuit.

[0005] In the Chinese patent document with the announcement number CN113665851B, a pyrotechnic separation signal locking circuit for deep space exploration is disclosed. The main content of the document is that 5 relays and the instrument-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 instrument-rocket separation plug and the first relay K1 are connected in series in sequence. The circuit of the invention is simple and has high reliability. When the instrument-rocket separation signal fails, the pyrotechnic can still be unlocked normally by connecting the fifth relay. It is suitable for the pyrotechnic separation locking design of spacecraft such as deep space exploration.

[0006] In a Chinese patent document with the announcement number CN113636111B, a system, method and medium for the mixed use of electromechanical separation signals for spacecraft are disclosed. The main content of the document is that the separation electrical connector provides an electrical separation signal to remove the protection of the pyrotechnics on the spacecraft and provide for comprehensive electronic single-machine collection; the travel switch provides a mechanical separation signal to confirm the mechanical separation of the satellite and the rocket, and sends a separation signal for the single-machine signal on the spacecraft. The electrical separation signal and the mechanical separation signal are comprehensively collected for confirmation, so that the separation signal on the spacecraft changes from a single instruction to a double confirmation. The invention can improve the reliability of the separation signal, increase the safety margin of the spacecraft pyrotechnics, and reduce the overall risk.

[0007] In the Chinese patent document with the announcement number CN111969999B, a reliable launch vehicle separation signal isolation detection and self-locking circuit is disclosed. The main content of the document is: the filter shaping protection circuit receives the separation contact signal input from the outside and filters its jitter noise; the optocoupler isolation circuit receives the separation contact signal after noise filtering, and performs isolation detection and signal conditioning on it; the self-locking output circuit receives the conditioned separation contact signal and realizes self-locking and buffering output. The invention realizes the isolation detection and self-locking of the separation signal through a pure electronic component circuit. The circuit is simple, small in size and low in cost, and more reliable than the mechanical self-locking system.

[0008] In the Chinese patent document with the announcement number CN108945530B, a satellite-rocket separation signal simulation method is disclosed. The main content of the document is to use resistors to divide the two isolated 28V satellite bus voltages into 10V signals respectively, and then pass through the plugs and sockets of the two satellite-rocket separation electrical connectors, and then perform AND logic operations 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 by the ground relay to realize the simulated satellite-rocket separation. The present invention generates satellite-rocket separation and simulated satellite-rocket separation signals, and the implementation method is simple and reliable, and the safety of the satellite-rocket separation signal circuit is improved.

[0009] In the Chinese patent document with the announcement number CN113746472B, a matrix-type pyrotechnics driving circuit and control method for deep space detectors are disclosed. The main contents of the scheme are the first relay, etc. The drain of the first PMOS tube is connected to the first resistor, the second resistor, the third resistor, and the fourth resistor (also forming a total of 4 circuits), and the second relay is connected to the source of the first NMOS tube, the second NMOS tube, the third NMOS tube, and the fourth NMOS tube. The invention adopts a matrix-type control pyrotechnics driving with PMOS positive line switches and NMOS negative line switches, with few devices and high integration, which is suitable for satellites to drive pyrotechnics with large quantities, low costs, and high integration. Summary of the invention

[0010] In view of the defects in the prior art, the purpose of the present invention is to provide a control circuit and a spacecraft for setting the initial state of a spacecraft entering orbit without power supply in the active segment.

[0011] According to the present invention, a control circuit for setting the initial state of a spacecraft entering orbit without power supply in an active segment comprises: a travel switch group, a self-powering circuit, a battery group and a satellite bus;

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

[0013] The travel switch is electrically connected to the satellite's pyrotechnic locking signal generating circuit, and the travel switch is electrically connected to the satellite's program-controlled start signal generating circuit.

[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 to the battery pack, the source of the first MOS tube and the source of the second MOS tube are electrically connected to the satellite bus; the gate of the first MOS tube and the gate of the second MOS tube are connected in parallel and are electrically connected to the positive electrode of the battery pack through the travel switch group.

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

[0016] 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;

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

[0018] Preferably, it also includes a self-power-on enabling circuit, wherein two ends of the self-power-on enabling circuit are electrically connected to 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 includes a switch S3 and a switch S4, and the switch S3 and the switch S4 are arranged in parallel.

[0020] Preferably, the first MOS transistor and the second MOS transistor are both PMOS transistors.

[0021] Preferably, it also includes a discharge control circuit, wherein the discharge control circuit is connected to the battery pack and the satellite bus respectively;

[0022] The discharge control circuit includes a switch S1 and a switch S2 which are connected in parallel.

[0023] Preferably, 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;

[0024] The switch K1_4, the switch K21_4, and the switch K3_4 are arranged in series, and are all normally closed switches; the two ends of the switch K1_4, the switch K21_4, and the switch K3_4 after being connected in series are electrically connected to the positive and negative ends of the locking signal generating circuit respectively;

[0025] When the positive and negative ends of the locking signal generating circuit are disconnected, an initiating device locking signal is generated, and when the positive and negative ends of the locking signal generating circuit are connected, an initiating device forced unlocking signal is generated.

[0026] Preferably, 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;

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

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

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

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

[0031] A spacecraft provided according to the present invention comprises the control circuit for setting the initial state of the spacecraft entering orbit without power supply in the active section.

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

[0033] 1. The present invention aims at the locking signal generating circuit, which is implemented by three normally closed contacts in parallel, which come from three travel switches respectively, so as to avoid the failure of one of the travel switches, resulting in the erroneous generation of the satellite-rocket separation signal or the failure to generate the satellite-rocket separation signal, resulting in the failure of the subsequent task.

[0034] 2. The present invention adopts cold backup to force unlocking of the pyrotechnic main line connection command line to prevent multiple faults from causing the satellite-rocket separation and not giving a satellite-rocket separation signal. At this time, by sending a forced unlocking of the pyrotechnic main line connection command, subsequent tasks such as pyrotechnic busbar connection are completed.

[0035] 3. Switch K1_1, switch K2_1 and switch K3_1 are from three different travel switches respectively to avoid failure of one of the travel switches, resulting in erroneous generation of satellite-rocket separation signal or failure to generate satellite-rocket separation signal, leading to failure of subsequent missions.

[0036] 4. Switch K1_1, switch K2_1 and switch K3_1 are three normally open contact travel switches connected in series to ensure power on. After the satellite-rocket separation, any switch is disconnected, triggering the satellite-rocket separation signal and starting the self-power on circuit.

[0037] 5. The self-power-on circuit uses two MOS tubes in parallel to enhance reliability. During ground testing, the self-power-on circuit is disabled to prevent accidental startup of the self-power-on circuit.

[0038] 6. The program-controlled start signal generating circuit of the present invention uses six pairs of normally open contacts, which come from three different travel switches respectively, to prevent one of the travel switches from failing, resulting in the erroneous generation of a satellite-rocket separation signal or the inability to generate a satellite-rocket separation signal, leading to the failure of subsequent tasks. The six pairs of normally open contact travel switches are implemented in two series and three parallel to ensure that power is not incorrectly turned on. Before the satellite-rocket separation, if any switch is disconnected, the satellite-rocket separation signal will not be triggered by mistake; after the satellite-rocket separation, if any switch is not disconnected, it will not affect the generation of the satellite-rocket separation signal; if any clamping point is released by mistake, the satellite-rocket separation signal will not be triggered. The satellite-rocket separation signal interfaces provided to other subsystems are isolated from each other to enhance reliability.

[0039] 7. In the present invention, the three travel switches are distributed at different positions of the satellite-rocket interface, which effectively reflects the separation and connection status of different parts between the carrier and the spacecraft, and avoids false triggering of the satellite-rocket separation signal. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0041] Figure 1 This is a diagram of the satellite-rocket separation signal plan.

[0042] Figure 2 It is a self-powered design schematic.

[0043] Figure 3 It is a circuit diagram of the satellite-rocket separation signal for the integrated management unit (before the satellite-rocket separation)

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

[0045] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0046] The present invention utilizes an initial state setting control circuit for a spacecraft entering orbit without power on an active segment, comprising a travel switch that locks a pyrotechnic positive line connection command line before satellite-rocket separation, and unlocks the pyrotechnic positive line connection command line after satellite-rocket separation, completing pyrotechnic connection according to a program-controlled procedure; the travel switch provides a mechanical satellite-rocket separation signal, confirms the mechanical separation of the satellite-rocket, generates multiple satellite-rocket separation signals and transmits them to a single unit on the spacecraft; the launch active segment is not powered on, and after receiving the satellite-rocket separation, the power controller on the spacecraft completes self-powering by connecting the discharge path of the platform bus MOS tube, and the battery supplies power to the entire device to ensure normal operation of the entire device; after receiving the satellite-rocket separation signal, the power controller unlocks the pyrotechnic positive line connection command; the integrated management unit collects the received satellite-rocket separation signal, and controls each single unit of the entire device to carry out work according to the program-controlled procedure.

[0047] Specifically, the circuit structure is:

[0048] A control circuit for setting the initial state of an active segment unpowered spacecraft entering orbit comprises: a travel switch group, a self-powering circuit, a battery group and a satellite bus. The self-powering circuit is respectively connected to the battery group and the satellite bus, the travel switch is connected to the self-powering circuit, and the travel switch generates a state control signal to the self-powering circuit; the travel switch is electrically connected to a satellite pyrotechnic locking signal generating circuit, and the travel switch is electrically connected to a satellite program-controlled start signal generating circuit.

[0049] Specifically, 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 to the battery pack, the source of the first MOS tube and the source of the second MOS tube are electrically connected to the satellite bus; the gate of the first MOS tube and the gate of the second MOS tube are connected in parallel and are electrically connected to the positive electrode 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 switches K1_1, K2_1 and K3_1 are connected in series and are electrically connected to the battery pack and the gate of the first MOS tube and the gate of the second MOS tube respectively.

[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 K21_4, and the switch K3_4 are arranged in series, and are all normally closed switches; the two ends of the switch K1_4, the switch K21_4, and the switch K3_4 after being connected in series are electrically connected to the positive and negative ends of the locking signal generating circuit respectively;

[0053] When the positive and negative ends of the locking signal generating circuit are disconnected, an initiating device locking signal is generated, and when the positive and negative ends of the locking signal generating circuit are connected, an initiating device forced unlocking signal is generated.

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

[0055] The switch K1_2 and the switch K2_2 are arranged in series, and the switch K1_3 and the switch K3_3 are arranged in series. The switch K2_3 and the switch K3_2 are arranged in series; the three sets of switches arranged in series are arranged in parallel, and after being connected in parallel, they are respectively connected to the two ends of the program-controlled start signal generating circuit;

[0056] When both ends of the program-controlled start signal generating circuit are closed, no satellite-rocket separation signal is generated;

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

[0058] It also includes a self-power-on enabling circuit, the two ends of which are electrically connected to the travel switch group and the gate of the first MOS tube and the gate of the second MOS tube respectively; the self-power-on enabling circuit includes a switch S3 and a switch S4, and the switch S3 and the switch S4 are arranged in parallel.

[0059] It also includes a discharge control circuit, which is connected to the battery pack and the satellite bus respectively;

[0060] The discharge control circuit includes a switch S1 and a switch S2 which are arranged in parallel.

[0061] The specific working process of the circuit, such as Figure 1 As shown:

[0062] Before the separation of the rocket and the satellite, the pyrotechnic positive line connection command line circuit is locked and the pyrotechnic positive line connection circuit is forcibly unlocked. Before the launch, the travel switch is in the compressed state, and the travel switches K1-4, K2-4 and K3-4 are all in the normally open state, locking the pyrotechnic positive line connection command line; after the separation of the rocket and the satellite, the travel switches are all released and in the normally closed state, unlocking the pyrotechnic positive line connection line. Under normal conditions, the relay (two in parallel) is disconnected. If there is a fault in the rocket and satellite separation signal, the relay (two in parallel) is connected by sending a command to forcibly unlock the pyrotechnic positive line connection line.

[0063] Before the separation of the rocket and the satellite, the self-powered circuit, such as Figure 1 and Figure 2 , the discharge switches S1 and S2 are disconnected, the self-power-on is enabled, S3 and S4 are connected, and the travel switches K1-1, K2-1 and K3-1 are in a compressed state, that is, the connected state; after the satellite and rocket are separated, the travel switches are all released, that is, 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 pack is connected to the whole device bus to realize the whole device power-on.

[0064] Programmable start circuit before rocket-satellite separation, such as Figure 3 and Figure 4 As shown, the travel switches K1-2, K2-2, K1-3, K3-3, K2-3 and 3-2 are in a compressed state, i.e., in the on state, and the satellite-rocket separation indication telemetry shows a high level before the satellite-rocket separation; after the satellite-rocket separation, the travel switches are all released, i.e., in the off state, and the satellite-rocket separation indication telemetry shows a low level after the satellite-rocket separation, the program control program starts, and the whole device starts working.

[0065] The present invention also provides a spacecraft, which adopts the above-mentioned active segment non-powered spacecraft orbit entry initial state setting control circuit.

[0066] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0067] The above describes the specific embodiments of the present invention. It should be understood that the present invention 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 essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A control circuit for initial setting of a spacecraft entering orbit without power supply in the active segment, characterized in that: include: Travel switch group, self-powering circuit, battery group and satellite bus; The self-powering circuit is connected to the battery pack and the satellite bus respectively, the travel switch is connected to the self-powering circuit, and the travel switch generates a state control signal to the self-powering circuit; The travel switch is electrically connected to the satellite's pyrotechnic locking signal generating circuit, and the travel switch is electrically connected to the satellite's program-controlled start signal generating circuit.

2. The control circuit for setting the initial state of a spacecraft entering orbit without power supply in the active segment according to claim 1, characterized in that: 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 to the battery pack, the source of the first MOS tube and the source of the second MOS tube are electrically connected to the satellite bus; the gate of the first MOS tube and the gate of the second MOS tube are connected in parallel and are electrically connected to the positive electrode of the battery pack through the travel switch group.

3. The control circuit for setting the initial state of a spacecraft entering orbit without power supply in the active segment according to claim 2, characterized in that: 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 electrically connected to the battery pack and the gate of the first MOS tube and the gate of the second MOS tube respectively.

4. The control circuit for setting the initial state of a spacecraft entering orbit without power supply in the active segment according to claim 2 or 3, characterized in that: It also includes a self-power-on enabling circuit, wherein two ends of the self-power-on enabling circuit are electrically connected to the travel switch group and the gate of the first MOS tube and the gate of the second MOS tube respectively; The self-power-on enabling circuit includes a switch S3 and a switch S4, and the switch S3 and the switch S4 are arranged in parallel.

5. The control circuit for setting the initial state of a spacecraft entering orbit without power supply in the active segment according to claim 2, characterized in that: The first MOS tube and the second MOS tube are both PMOS tubes.

6. The control circuit for setting the initial state of a spacecraft entering orbit without power supply in the active segment according to claim 1, characterized in that: It also includes a discharge control circuit, which is connected to the battery pack and the satellite bus respectively; The discharge control circuit includes a switch S1 and a switch S2 which are connected in parallel.

7. The control circuit for setting the initial state of a spacecraft entering orbit without power supply in the active segment according to claim 1, characterized in that: 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; The switch K1_4, the switch K21_4, and the switch K3_4 are arranged in series, and are all normally closed switches; the two ends of the switch K1_4, the switch K21_4, and the switch K3_4 after being connected in series are electrically connected to the positive and negative ends of the locking signal generating circuit respectively; When the positive and negative ends of the locking signal generating circuit are disconnected, an initiating device locking signal is generated, and when the positive and negative ends of the locking signal generating circuit are connected, an initiating device forced unlocking signal is generated.

8. The control circuit for setting the initial state of a spacecraft entering orbit without power supply in the active segment according to claim 1, characterized in that: 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 and switch K2_2 are arranged in series, and the switch K1_3 and switch K3_3 are arranged in series. The switch K2_3 and switch K3_2 are arranged in series; the three sets of switches arranged in series are arranged in parallel, and after being connected in parallel, they are respectively connected to the two ends of the program-controlled start signal generating circuit; When both ends of the program-controlled start signal generating circuit are closed, no satellite-rocket separation signal is generated; When both ends of the program-controlled start signal generating circuit are disconnected, a satellite-rocket separation signal is generated.

9. The control circuit for setting the initial state of a spacecraft entering orbit without power supply in the active segment according to claim 8, characterized in that: The switches K1_2, K1_3, K2_2, K2_3, K3_2 and K3_2 are all normally closed switches.

10. A spacecraft, characterized in that: It includes the control circuit for setting the initial state of the active segment unpowered spacecraft into orbit as described in any one of claims 1-9.

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