Lightweight spacecraft pyrotechnics initiation circuit and protection method

Abstract

The present invention provides a lightweight spacecraft pyrotechnic initiation circuit and protection method, comprising: a ground launch control console, a first travel switch, a second travel switch, a first satellite table connector, a second satellite table connector, a pyrotechnic flight plug, a pyrotechnic emergency release switch, a pyrotechnic initiation main line switch, a satellite-rocket separation filter data acquisition circuit, and a pyrotechnic initiation circuit. The present invention includes a pyrotechnic plug status indicator circuit. During ground installation, the circuit collects status information from the ground launch control console via the second satellite table connector on the ground. This circuit provides the pyrotechnic plug's reliable connection status, thus preventing pyrotechnic initiation failures caused by improperly connected or unconnected pyrotechnic devices.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft circuits, and in particular to a lightweight spacecraft pyrotechnics initiation circuit and a protection method thereof. Background Art

[0002] With the increasing miniaturization of spacecraft, the demand for lightweight is getting higher and higher. Correspondingly, the separation method of spacecraft has also changed from traditional tape separation to point separation, and the generation of separation signals has also changed from traditional plug-and-play separation to lightweight mechanical travel switches to generate satellite-rocket separation signals. For specific pyrotechnic detonation circuits, the negative line main switch has been eliminated, and two-level protection has been adopted, and lightweight MOS tube devices have been used.

[0003] The locking of the pyrotechnic detonation circuit has been changed from the traditional star-table transfer protection design for all pyrotechnic power supply and distribution line circuits to indirect locking protection of only the public command signal line or the command power line through a relay controlled by a separate signal. The command locking flight weight is lighter, but locking through a separate signal brings additional locking circuit overhead.

[0004] As a mechanical disconnect mechanism, limit switches are subject to the following primary failure mechanisms: false disconnection, momentary contact disconnection, or disconnection. A momentary contact disconnection occurs when a switch is subjected to a large shock or vibration load exceeding the specified level, causing the contacts, which should be connected, to momentarily disconnect. The disconnection time is in the microsecond or millisecond range. Excessive shock levels can damage or break the switch's internal components. Alternatively, the switch's pressing mechanism may become loose, fail to press properly, or create a gap and displacement, leading to contact disconnection. Non-disconnection can occur when the microswitch button malfunctions or the limit switch button becomes stuck or stuck, preventing the state from switching.

[0005] Currently, the most common prevention measures for pyrotechnic control circuits are to install multiple control switches in the positive and negative power supply circuits and the detonation circuits of the pyrotechnics. For example, the patent "A pyrotechnic control circuit and a controller using the same" (application number CN201410208785.1) discloses a method that reduces the risk of pyrotechnic misdetonation by installing multiple switches. However, most spacecraft are currently designed with programmable instructions for pyrotechnic detonation to automatically unlock. The installation of multiple switches does not completely avoid the risk of pyrotechnic misdetonation, and especially the risk of pyrotechnic failure to detonate.

[0006] The public patent "A safe detonation circuit and detonation method for aircraft pyrotechnics" (application number CN201410454194) discloses a safe detonation circuit and detonation method for aircraft pyrotechnics. Through unlocking and detonating circuits and a five-stage detonation process, the pyrotechnics detonation is efficient, safe and reliable. Multiple control switches are set to logically ensure safe detonation, and the timing action of the two-stage unlocking needs to rely on the reasonable setting and control of external feedback signals (aircraft takeoff and rocket separation) to ensure it. No safe detonation measures for pyrotechnics when ground simulation and separation signals are abnormal are given.

[0007] The public patent "A Reusable Carrier Pyrotechnic Protection Circuit" (application number CN201610844703) discloses a reusable carrier pyrotechnic protection circuit, which realizes on-demand protection, on-demand release and detection of pyrotechnics, but does not have the ability of automatic unlocking and abnormal unlocking. At the same time, all adopt the form of relay initiation, and each release and protection detection circuit is collected, and the overall weight is heavy.

[0008] The published patent "A pyrotechnic detonation enabling circuit based on satellite-rocket separation plug design" (application number CN201921824609) uses pyrotechnic enabling protection to prevent accidental detonation of the pyrotechnic device by adding separation contacts in the satellite-rocket separation plug, avoiding the risk of accidental detonation caused by accidental operation and failure before satellite-rocket separation. It is not suitable for use in lightweight spacecraft.

[0009] The public patent "A spacecraft electromechanical separation signal mixing system for deep space exploration" (application number CN202110975708.9) discloses a high-reliability separation signal mixing system. In order to improve the reliability of pyrotechnic detonation, an integrated satellite-rocket shedding plug and a travel switch are used to simultaneously deprotect the pyrotechnics. However, the system is heavy and the high reliability protection of the entire process is insufficient.

[0010] The public patent "Pyrotechnic Separation Signal Locking Circuit for Deep Space Exploration" (application number CN202111016271.2) discloses a pyrotechnic separation signal locking circuit for deep space exploration. It uses four relays K1, K2, K3, and K4 and a satellite-rocket separation plug to achieve separation locking. During ground test locking, a 29V command pull-up power supply pull-up protection must be used for a long time. It is not suitable for spacecraft that are not powered in the active segment. At the same time, the switches for protection and testing are all relays. Multiple relays are locked by external separation signals to indirectly lock the pyrotechnic command line, which increases the complexity, reliability, and weight of the pyrotechnic circuit itself. Summary of the Invention

[0011] In view of the defects in the prior art, the purpose of the present invention is to provide a lightweight spacecraft pyrotechnics initiation circuit and protection method.

[0012] According to the present invention, a lightweight spacecraft pyrotechnics initiation circuit is provided, comprising: a ground launch control console, a first travel switch, a second travel switch, a first satellite table connector, a second satellite table connector, a pyrotechnics flight plug, a pyrotechnics emergency unlocking switch, a pyrotechnics initiation main line switch, a satellite-rocket separation filter collection circuit, and a pyrotechnics initiation circuit;

[0013] The ground control console is connected to the second star table connector, the second star table connector is connected to the first star table connector, the pyrotechnic flight plug is connected to the first star table connector, and the first star table connector is respectively connected to the pyrotechnic bus detonating main line main switch, the pyrotechnic detonating circuit, the first travel switch, the second travel switch and the satellite-rocket separation filter acquisition circuit. The other end of the pyrotechnic detonating main line main switch is used to connect to the bus power supply, and a pyrotechnic emergency unlocking switch is connected in series between the pyrotechnic detonating main line switch and the pyrotechnic detonating circuit.

[0014] Preferably, the first travel switch and the second travel switch are both multi-contact switches.

[0015] A method for detonating a lightweight spacecraft explosive device according to the present invention includes the following steps:

[0016] Step S1: When the pyrotechnic device is installed on the ground, the flight plug of the pyrotechnic device is connected to the ground control console through the second satellite table connector to collect status and provide the reliability connection status of the flight plug of the pyrotechnic device;

[0017] Step S2: During the simulated separation on the ground, the launch control console module separation switch generates a simulated satellite-rocket separation signal, and the pyrotechnic detonation circuit locks the command line of the pyrotechnic detonation main line switch by using a two-stage locking method in series with a first travel switch, a second travel switch, and a first satellite connector without a flight plug;

[0018] Step S3: Before the separation of the active stage rocket and satellite, the pyrotechnic device detonation circuit is connected to the first satellite table connector using a flight plug, and the first and second travel switches are connected in series to the command line of the pyrotechnic device detonation main line switch;

[0019] Step S4: After the satellite-rocket separation, the pyrotechnic device detonation circuit generates a satellite-rocket separation signal by connecting the first and second travel switches in series and then in parallel, thereby starting the pyrotechnic device program control instruction chain.

[0020] Step S5: When an abnormality occurs in the satellite-rocket separation travel switch, the pyrotechnic emergency unlocking switch is used to emergency unlock the pyrotechnic detonation main line switch positive line instruction, and trigger the one-button pyrotechnic program control instruction chain.

[0021] Preferably, the pyrotechnic detonating circuit locks the positive line switch instruction of the pyrotechnic detonating positive line main switch and / or locks the negative line switch instruction of the pyrotechnic detonating negative line main switch by serially connecting a travel switch.

[0022] Preferably, the emergency unlocking switch of the pyrotechnic device adopts an anti-malfunction design in which two pairs of contacts of a relay are connected in series.

[0023] Preferably, the first and second travel switches are designed with four pairs of contacts, wherein the satellite-rocket separation signal adopts two independent travel switches with two pairs of contacts first connected in series and then in parallel, and the pyrotechnic locking adopts two independent travel switches with one pair of contacts connected in series to prevent false operation, and the telemetry of the two travel switches adopts the remaining pair of contacts of each.

[0024] Preferably, the pyrotechnic flight plug has a ground status indication function, providing a connection prompt of the pyrotechnic to the ground.

[0025] Preferably, the ground control console includes a modular switch and a pyrotechnic plug status indication circuit, the modular switch includes a pair of ground simulated flight control switches K3 and ground simulated flight control switches K4 arranged in parallel, and the ground simulated flight control switch K3 and the ground simulated flight control switch K4 both adopt a two-stage switch series design.

[0026] Preferably, the ground launch control console and the satellite-rocket separation filtering and acquisition circuit are connected in parallel to the satellite-table connector, and the separation signal is generated by any one of the ground launch control console, the pyrotechnic flight plug and the travel switch.

[0027] Preferably, the two limit switches are arranged at two diagonals and pressed against the point-type separation mechanism, and both ends of each limit switch are mounted on the mounting surface of the carrier rocket and the spacecraft.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] 1. The present invention is provided with an pyrotechnic device plug status indication circuit. When the pyrotechnic device is installed on the ground, the status is collected from the ground control console through the second ground star table connector, and the reliability connection status of the pyrotechnic device plug is given, thereby avoiding the failure to detonate caused by the pyrotechnic device not being properly connected.

[0030] 2. The pyrotechnic device initiation circuit is directly connected to the main switch command line of the pyrotechnic device initiation positive line through a limit switch, eliminating the need for an external disconnect plug or a lock relay generated by a disconnect signal generated by a limit switch to lock the command negative line. This solves the problems of pyrotechnic devices using an external short-circuit plug, such as the heavy weight and complex operation and testing. It can also be directly applied to pyrotechnic device protection circuits and devices without a main switch for the pyrotechnic device negative line, saving weight and cost.

[0031] 3. The setting of the emergency unlocking switch for pyrotechnics effectively avoids potential faults such as the stuck travel switch and the inability to effectively release the command line of the main switch of the detonating main line. On the basis of preventing accidental detonation, it enhances the ability of emergency detonation. At the same time, the emergency switch for pyrotechnics adopts an anti-false action design with two pairs of contacts in series of a magnetic latching relay, which reduces the fault of false failure of the first-level pyrotechnic protection strategy in the active section.

[0032] 4. The satellite-rocket separation signal adopts a design in which two pairs of contacts of two independent travel switches are first connected in series and then in parallel to enhance the ability to prevent accidental detonation. Through the pyrotechnic locking, two independent travel switches, each with one pair of contacts, are used in series to prevent accidental operation, effectively avoiding the risk of program-controlled accidental detonation of pyrotechnics caused by the failure of one travel switch; the telemetry of the travel switch adopts a design in which two independent travel switches, each with one pair of contacts, are used. On the one hand, it provides a quantifiable satellite-rocket separation signal for the entire satellite, which serves as a telemetry criterion indicator of satellite-rocket separation, and on the other hand, it also serves as an effective criterion for the health status of the travel switch itself.

[0033] 5. The present invention adopts a two-stage satellite array series design to realize the generation of satellite-rocket separation signals and the locking protection control of pyrotechnics, while taking into account the remote transfer and conditioning requirements of the simulated satellite-rocket separation signals.

[0034] 6. The present invention provides a ground status indication function for the satellite catalog, which can effectively provide a high-reliability connection prompt for the final flight plug, and provides telemetry by a pair of contacts of each of the two limit switches, which can provide a telemetry criterion indication for satellite-rocket separation, thereby improving reliability.

[0035] 7. The ground-based flight simulation circuit adopts a two-stage magnetic latching series protection design to prevent power failure and malfunction. At the same time, the ground-based flight simulation circuit is remotely driven by ground commands from the control console, and the ground short-circuit isolation fault is used to improve reliability.

[0036] 8. The satellite-rocket separation filtering and acquisition circuit achieves high-reliability filtering and acquisition and anti-open circuit design by adopting an acquisition and filtering network with resistors and diodes in parallel, filtering out millisecond-level signals caused by possible momentary disconnection of the travel switch, while enhancing the ability to prevent open circuit.

[0037] 9. The ground-based flight simulation circuit utilizes a satellite table parallel design. Separation signals can be generated through three methods: a ground-based analog switch, a satellite table plug, and the release of a travel switch. Ground-based testing utilizes a ground-based analog switch for remote control. The travel switch is released, eliminating the reliability degradation associated with repeated compression of the travel switch by ground tooling during each simulated satellite-rocket separation. The tower is protected by a flight plug, minimizing the possibility of false separation signals due to inadvertent disconnection of the ground-based simulated separation switch. During active-stage satellite-rocket separation, the two contacts of the travel switch are connected in series and then in parallel to enhance reliability, ultimately achieving highly reliable initiation of the pyrotechnic circuit.

[0038] 10. The carrier and the spacecraft provide installation surfaces and pressing surfaces for each other's travel switches. Both sides can generate satellite-rocket separation signals at the same time, making the overall flight weight lighter and the structure simpler. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0040] Figure 1 This is a schematic diagram of a lightweight detonation circuit for pyrotechnics in the present invention;

[0041] Figure 2 This is a schematic diagram of a lightweight and highly reliable detonation circuit for pyrotechnic devices in the present invention;

[0042] Figure 3 It is a schematic diagram of the installation form of the travel switch in the present invention. DETAILED DESCRIPTION

[0043] The present invention will be described in detail below with reference to specific embodiments. The following examples 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 skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0044] Reference Figures 1 to 3 The present invention discloses a lightweight spacecraft pyrotechnic initiation circuit, comprising: a ground launch control console, a first travel switch, a second travel switch, a first satellite table connector, a second satellite table connector, a pyrotechnic flight plug, a pyrotechnic emergency unlocking switch, a pyrotechnic initiation main line switch, a satellite-rocket separation filter acquisition circuit, and a pyrotechnic initiation circuit.

[0045] The ground control console is connected to the second star table connector, the second star table connector is connected to the first star table connector, the pyrotechnic flight plug is connected to the first star table connector, and the first star table connector is respectively connected to the pyrotechnic bus detonating main line main switch, the pyrotechnic detonating circuit, the first travel switch KX-1, the second travel switch KX-2 and the satellite-rocket separation filter acquisition circuit. The other end of the pyrotechnic detonating main line main switch is used to connect to the bus power supply, and a pyrotechnic emergency unlocking switch is connected in series between the pyrotechnic detonating main line main switch and the pyrotechnic detonating circuit.

[0046] This circuit adopts the design of two satellite-table connectors in series. The first satellite-table connector is used to realize the satellite-rocket separation signal and the pyrotechnic locking protection control. The second satellite-table connector is used to realize the remote transfer and conditioning control of the pyrotechnic flight plug and the simulated satellite-rocket separation signal.

[0047] The first and second travel switches are both multi-contact switches. In a preferred embodiment, the first and second travel switches utilize a four-pair contact design. The satellite-rocket separation signal utilizes two independent travel switches, with the two pairs of contacts first connected in series and then in parallel. The pyrotechnic device lock utilizes two independent travel switches, each with one contact connected in series, to prevent false operation. Telemetry for the two travel switches utilizes the remaining pair of contacts on each.

[0048] The pyrotechnic detonating circuit locks the positive line switch instruction of the pyrotechnic detonating positive line main switch and / or locks the negative line switch instruction of the pyrotechnic detonating negative line main switch by serially connecting a travel switch.

[0049] The pyrotechnic emergency unlocking switch K2 adopts a design to prevent false operation by connecting two pairs of contacts of a relay in series, as shown by K2_1 and K2_2 in the figure.

[0050] The pyrotechnic flight plug has a ground status indication function, which can effectively provide high-reliability connection prompts for ground pyrotechnics; the two limit switches each provide a pair of contact redundant telemetry, which can provide telemetry judgment indications for satellite-rocket separation during the flight phase.

[0051] The ground control console includes a modular switch and a pyrotechnic plug status indication circuit. The modular switch includes a pair of ground simulated flight control switches K3 and K4 arranged in parallel. The ground simulated flight control switches K3 and K4 both adopt a two-stage switch series design.

[0052] The satellite-rocket separation filter acquisition circuit uses a collection and filtering network with resistors and diodes in parallel to achieve high reliability filter acquisition and anti-open circuit design.

[0053] The ground launch control console and the satellite-rocket separation filtering and acquisition circuit are connected in parallel to the satellite table connector, and the separation signal is generated by any one of the ground launch control console, the pyrotechnic flight plug and the travel switch.

[0054] The two limit switches are arranged at two diagonals and pressed together with a point-type separation mechanism, and the carrier and the spacecraft provide mounting surfaces for each other's limit switches.

[0055] The present invention discloses a method for detonating a lightweight spacecraft explosive device, comprising the following steps:

[0056] Step S1: When the pyrotechnic device is installed on the ground, the flight plug of the pyrotechnic device is connected to the ground control console through the second satellite table connector to collect status and provide the reliability connection status of the flight plug of the pyrotechnic device;

[0057] Step S2: During the simulated separation on the ground, the launch control console module separation switch generates a simulated satellite-rocket separation signal, and the pyrotechnic detonation circuit uses a two-stage locking method, which uses a travel switch and a first satellite connector connected to a non-flight plug in series, to lock the command line and separation signal of the pyrotechnic detonation main line switch (KM1 and KM2) to prevent the ground pyrotechnic from being accidentally detonated by program control;

[0058] Step S3: Before the separation of the active stage rocket and satellite, the pyrotechnic device detonation circuit is connected to the first satellite table connector using a flight plug, and the first and second travel switches are connected in series to the command lines of the pyrotechnic device detonation main line switches (KM1 and KM2) to prevent the active stage pyrotechnic device from accidentally detonating;

[0059] Step S4: After the satellite-rocket separation, the pyrotechnic device detonation circuit generates a satellite-rocket separation signal by connecting the first and second travel switches in series and then in parallel, thereby starting the pyrotechnic device program control instruction chain.

[0060] Step S5: When an abnormality occurs in the satellite-rocket separation travel switch, the pyrotechnic emergency unlocking switch is used to emergency unlock the pyrotechnic detonation main line switch positive line instruction, and trigger the one-button pyrotechnic program control instruction chain.

[0061] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A lightweight spacecraft explosive device initiation circuit, characterized in that: include: Ground launch control console, first travel switch, second travel switch, first satellite table connector, second satellite table connector, pyrotechnic flight plug, pyrotechnic emergency unlocking switch, pyrotechnic detonation main line switch, satellite-rocket separation filter acquisition circuit, and pyrotechnic detonation circuit; The ground control console is connected to the second star table connector, the second star table connector is connected to the first star table connector, the pyrotechnic flight plug is connected to the first star table connector, and the first star table connector is respectively connected to the pyrotechnic detonation main line switch, the pyrotechnic detonation circuit, the first travel switch, the second travel switch and the satellite-rocket separation filter acquisition circuit. The other end of the pyrotechnic detonation main line switch is used to connect to the bus power supply, and a pyrotechnic emergency unlocking switch is connected in series between the pyrotechnic detonation main line switch and the pyrotechnic detonation circuit.

2. The lightweight spacecraft explosive device initiation circuit according to claim 1, characterized in that: The first travel switch and the second travel switch are both multi-contact switches.

3. A method for detonating a lightweight spacecraft pyrotechnic device, based on the lightweight spacecraft pyrotechnic device detonating circuit according to claim 1 or 2, characterized in that: The following steps are involved: Step S1: When the pyrotechnic device is installed on the ground, the flight plug is connected to the ground control console via the second satellite table connector to collect the status of the flight plug of the pyrotechnic device and provide the reliability connection status of the flight plug of the pyrotechnic device; Step S2: During the simulated separation on the ground, the ground launch control console module separation switch generates a simulated satellite-rocket separation signal, and the pyrotechnic detonation circuit uses a two-stage locking method in which the first and second travel switches are connected in series with the first satellite connector without a flight plug to lock the command line of the pyrotechnic detonation main line switch; Step S3: Before the separation of the active stage rocket and satellite, the pyrotechnic device detonation circuit is connected to the first satellite table connector using a flight plug, and the first and second travel switches are connected in series to the command line of the pyrotechnic device detonation main line switch; Step S4: After the satellite-rocket separation, the pyrotechnic device detonation circuit generates a satellite-rocket separation signal by connecting the first and second travel switches in series and then in parallel, thereby starting the pyrotechnic device program control instruction chain. Step S5: When an abnormality occurs in the satellite-rocket separation travel switch, the pyrotechnic emergency unlocking switch is used to emergency unlock the pyrotechnic detonation main line switch positive line instruction, and trigger the one-button pyrotechnic program control instruction chain.

4. The method for detonating lightweight spacecraft explosives according to claim 3, characterized in that: The pyrotechnic detonating circuit locks the positive line switch instruction of the pyrotechnic detonating positive line main switch and / or locks the negative line switch instruction of the pyrotechnic detonating negative line main switch by serially connecting a travel switch.

5. The method for detonating lightweight spacecraft explosives according to claim 3, characterized in that: The emergency unlocking switch for explosive devices adopts an anti-malfunction design in which two pairs of contacts of a relay are connected in series.

6. The method for detonating lightweight spacecraft explosives according to claim 3, characterized in that: The first and second travel switches are designed with four pairs of contacts, wherein the satellite-rocket separation signal adopts two independent travel switches with two pairs of contacts connected in series first and then in parallel; the pyrotechnic locking adopts two independent travel switches with one pair of contacts connected in series to prevent false operation; the telemetry of the two travel switches adopts the remaining pair of contacts of each.

7. The method for detonating lightweight spacecraft explosives according to claim 3, characterized in that: The pyrotechnic flight plug has a ground status indication function, which provides the ground with a connection prompt of the pyrotechnic.

8. The method for detonating lightweight spacecraft explosives according to claim 3, characterized in that: The ground control console includes a modular switch and a pyrotechnic plug status indication circuit. The modular switch includes a pair of ground simulated flight control switches K3 and K4 arranged in parallel. The ground simulated flight control switches K3 and K4 both adopt a two-stage switch series design.

9. The method for detonating lightweight spacecraft explosives according to claim 3, characterized in that: The ground launch control console and the satellite-rocket separation filtering and acquisition circuit are connected in parallel to the first satellite table connector and the second satellite table connector, and the separation signal is generated by any one of the ground launch control console, the pyrotechnic flight plug and the travel switch.

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