Power distribution systems for deep space exploration missions

Abstract

The present invention provides a power distribution system for deep space exploration missions, including an pyrotechnic control master module, an pyrotechnic control slave module, a hybrid power supply module and a control power supply module; the pyrotechnic control master module is connected to the pyrotechnic control slave module, and the pyrotechnic control master module supplies power to the pyrotechnic control slave module; the hybrid power supply module is connected to the control power supply module, and the hybrid power supply module supplies power to the control power supply module. The present invention adopts modular and universal design, can realize flexible expansion of control resources, solves the problem of diverse interfaces and poor universality of power distribution unit products, and reduces the development cycle and R&D cost of single-machine products through standardized design, and is suitable for power distribution control and pyrotechnic control of spacecraft such as deep space probes.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft power supply and distribution, and in particular to a power distribution system for deep space exploration missions. Background Art

[0002] The power distribution unit is an important single-machine product of the spacecraft power supply and distribution subsystem, which mainly completes the functions of spacecraft power supply control and pyrotechnic drive control. After the separation of the rocket and the satellite, the deep space probe needs to use the propulsion system to achieve the long-distance drift and multiple orbit changes of the deep space probe, and carry out scientific tasks such as orbiting and landing after capturing the target star. The mission characteristics of the deep space probe require a high degree of integration of the entire electronic system and a reduction in the mass of the probe, thereby reducing fuel consumption and ensuring the success of the flight mission.

[0003] Patent document with publication number CN100405701C discloses a small power distribution measurement and control system that can be used for satellites, including: system scheduling and control circuit, 1553B bus interface circuit, analog telemetry circuit, digital telemetry circuit, switch command output circuit. Patent document 2 with publication number CN104267636A discloses a power distribution measurement and control unit for spacecraft, including an integrated power supply and distribution module, a remote control module, a telemetry module and a heater control module, wherein the remote control module is respectively controlled and connected with the power supply and distribution module and the heater control module, and the power supply and distribution module is also connected with the telemetry module. However, the above patent document has the defect that it cannot realize the power distribution of the whole satellite and the driving of pyrotechnics.

[0004] The patent document with publication number CN104682548B discloses a high-reliability delay circuit distribution device, including: a power supply module, a power supply control module, a high-reliability delay circuit distribution module, a signal acquisition module, and an input-output interface; the aircraft battery or the ground power supply outputs the DC power supply to the distribution device power module through the input-output interface, and when the power distribution instruction sent by the power supply control module is received, the high-reliability delay circuit distribution module is driven, and the high-reliability delay circuit distribution module realizes power distribution of each path through the power distribution control circuit and the power supply circuit according to the power distribution signal instruction, and the signal acquisition module collects the voltage of each distribution path in real time, and outputs the collected voltage through the input-output interface. The patent document with publication number CN203301231U discloses a power distributor that meets the functions of high-power switching and control signal delay, including a ground power supply input and signal acquisition interface Y177A, an arrow battery input interface Y177B, an arrow power distribution and control function output interface Y177C, electromagnetic relays K11, K12, K13, K21, K22, K31, K32, diodes V1, V2, V3, and resistors R1, R2, R3. Patent document with publication number CN106428589A discloses a spacecraft power supply and distribution device based on solid-state power control technology, the power supply and distribution device includes a control module, multiple power supply and distribution modules, and a fault monitoring module. Each power distribution module corresponds to a power supply with different volt values, wherein the power supply and distribution module includes multiple path switch circuits based on solid-state power control technology, the control module receives external input power distribution control commands and emergency power distribution control signals, controls the connection and disconnection of all path switches in the power distribution module, and supplies power to the corresponding powered equipment; the fault monitoring module receives the detection instructions of the measurement integrated controller, collects the status information, voltage information, and current information of each channel switch circuit of the power supply and distribution module, and reports the detection results to the external measurement integrated controller. However, the above patent document still exists

[0005] The patent document with publication number CN109066977A discloses a distributed intelligent power supply and distribution system for aerospace vehicles, which is composed of pulse batteries, functional batteries, multiple intelligent power distribution centers in different regions, main control equipment, and ground power supply. Pulse batteries are used to power loads on aerospace vehicles that do not require high power supply quality, including pyrotechnics, solenoid valves, equipment heating, and motor power supply; functional batteries are used to power loads on aerospace vehicles that require high power supply quality, including control and measurement stand-alone machines. Intelligent power distribution centers are distributed on aerospace vehicles by region and are interconnected through a standard bus. The intelligent power distribution center receives bus instructions from the main control equipment, completes the on-off control of the power supply of each load on the aerospace vehicle, and realizes intelligent cut-off protection of short circuit and overcurrent of each load. However, this patent document still has the defects of heavy weight, low integration, and low reliability. Summary of the invention

[0006] In view of the defects in the prior art, an object of the present invention is to provide a power distribution system for deep space exploration missions.

[0007] A power distribution system for deep space exploration missions provided according to the present invention includes an pyrotechnic control master module, an pyrotechnic control slave module, a hybrid power supply module and a control power supply module;

[0008] The pyrotechnic control master module is connected to the pyrotechnic control slave module, and the pyrotechnic control master module supplies power to the pyrotechnic control slave module;

[0009] The hybrid power supply module is connected to the control power supply module, and the hybrid power supply module supplies power to the control power supply module.

[0010] Preferably, the pyrotechnic control main module includes a battery negative bus master switch, a first group of battery positive bus master switches, a first pyrotechnic drive circuit, an arrow electrical separation locking circuit, an arrow electrical simulation separation circuit, an arrow mechanical simulation separation circuit and a pyrotechnic detonation current detection circuit;

[0011] The battery negative bus master switch is respectively connected to the first pyrotechnic device driving circuit, the pyrotechnic device detonation current detection circuit and the device-arrow electrical separation locking circuit;

[0012] The first battery group positive busbar master switch is connected to the first pyrotechnic device drive circuit;

[0013] The device-arrow electrical separation locking circuit is connected to the device-arrow electrical simulation separation circuit;

[0014] The device-arrow electrical simulation separation circuit and the device-arrow mechanical simulation separation circuit are both used to connect a separation plug;

[0015] The battery negative bus master switch is connected to the pyrotechnic control slave module.

[0016] Preferably, the battery negative bus master switch and the first group of battery positive bus master switch both use magnetic latching relays.

[0017] Preferably, the first pyrotechnic device driving circuit uses a MOS tube.

[0018] Preferably, the pyrotechnic device detonation current detection circuit adopts a Hall current sensor.

[0019] Preferably, the instrument-arrow electrical simulation separation circuit, the instrument-arrow mechanical simulation separation circuit and the instrument-arrow electrical separation locking circuit all use electromagnetic relays.

[0020] Preferably, the pyrotechnic control slave module comprises a second group of battery positive busbar master switches and a second pyrotechnic drive circuit;

[0021] The second battery group positive busbar master switch is connected to the second pyrotechnic device drive circuit;

[0022] The second battery group positive bus main switch and the second pyrotechnic device drive circuit are both connected to the pyrotechnic device control main module.

[0023] Preferably, the main switch of the positive busbar of the second group of batteries adopts a magnetic latching relay.

[0024] Preferably, the hybrid power supply module comprises a first relay-controlled power supply circuit and a confluence module direct power supply circuit;

[0025] The first relay control power supply circuit is connected to the direct power supply circuit of the convergence module, and both the first relay control power supply circuit and the direct power supply circuit of the convergence module are connected to the control power supply module.

[0026] Preferably, the control power supply module includes a second relay control power supply circuit, and the second relay control power supply circuit is connected to the hybrid power supply module.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. The present invention is based on modular and universal design ideas, which solves the problem of diverse interfaces and poor universality of traditional power distribution unit products. At the same time, it reduces the development cycle and R&D cost of single-machine products through standardized design, and is suitable for power distribution control and pyrotechnic control of spacecraft such as deep space probes;

[0029] 2. The present invention adopts modular and universal design, which can realize flexible expansion of control resources and solve the problem of diverse interfaces and poor universality of distribution unit products;

[0030] 3. The present invention reduces the development cycle and R&D cost of single-machine products through standardized design, and is suitable for power distribution control and pyrotechnic control of spacecraft such as deep space probes. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] 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:

[0032] Figure 1 It is a schematic diagram of the principle diagram of the power distribution system for deep space exploration missions of the present invention;

[0033] Figure 2 This is a schematic diagram of the main module for controlling explosive devices of the present invention;

[0034] Figure 3 This is a schematic diagram of the pyrotechnic control slave module of the present invention;

[0035] Figure 4 It is a schematic diagram of a hybrid power supply module of the present invention;

[0036] Figure 5 It is a schematic diagram of the control power supply module of the present invention. DETAILED DESCRIPTION

[0037] 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.

[0038] Embodiment 1:

[0039] like Figures 1 to 5 As shown, this embodiment provides a power distribution system for deep space exploration missions, including a pyrotechnic control main module, a pyrotechnic control slave module, a hybrid power supply module and a control power supply module. The pyrotechnic control main module is connected to the pyrotechnic control slave module, the pyrotechnic control main module supplies power to the pyrotechnic control slave module, the hybrid power supply module is connected to the control power supply module, and the hybrid power supply module supplies power to the control power supply module.

[0040] The pyrotechnic control main module includes the battery negative bus master switch, the first battery positive bus master switch, the first pyrotechnic drive circuit, the device-arrow electrical separation locking circuit, the device-arrow electrical simulation separation circuit, the device-arrow mechanical simulation separation circuit and the pyrotechnic detonation current detection circuit. The battery negative bus master switch is respectively connected to the first pyrotechnic drive circuit, the pyrotechnic detonation current detection circuit and the device-arrow electrical separation locking circuit. The first battery positive bus master switch is connected to the first pyrotechnic drive circuit, the device-arrow electrical separation locking circuit is connected to the device-arrow electrical simulation separation circuit, and the device-arrow electrical simulation separation circuit and the device-arrow mechanical simulation separation circuit are both used to connect the separation plug. The battery negative bus master switch is connected to the pyrotechnic control slave module. The battery negative bus master switch and the first battery positive bus master switch both use magnetic latching relays, the first pyrotechnic drive circuit uses MOS tubes, the pyrotechnic detonation current detection circuit uses Hall current sensors, and the device-arrow electrical simulation separation circuit, the device-arrow mechanical simulation separation circuit and the device-arrow electrical separation locking circuit all use electromagnetic relays.

[0041] The hybrid power supply module includes a first relay control power supply circuit and a convergence module direct power supply circuit, the first relay control power supply circuit and the convergence module direct power supply circuit are connected, and the first relay control power supply circuit and the convergence module direct power supply circuit are both connected to the control power supply module. The control power supply module includes a second relay control power supply circuit, and the second relay control power supply circuit is connected to the hybrid power supply module.

[0042] The pyrotechnic control slave module includes a second battery positive bus master switch and a second pyrotechnic drive circuit, the second battery positive bus master switch is connected to the second pyrotechnic drive circuit, and the second battery positive bus master switch and the second pyrotechnic drive circuit are both connected to the pyrotechnic control master module. The second battery positive bus master switch uses a magnetic latching relay. In a preferred embodiment, the relay control power supply circuit uses a magnetic latching relay.

[0043] Embodiment 2:

[0044] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1.

[0045] like Figure 1 As shown, the present embodiment provides a power distribution unit for deep space exploration missions, including a pyrotechnic control master module, a pyrotechnic control slave module, a hybrid power supply module and a control power supply module. The pyrotechnic control master module is connected to the pyrotechnic control slave module, and the pyrotechnic control master module supplies power to the pyrotechnic control slave module; the hybrid power supply module is connected to the control power supply module, and the hybrid power supply module supplies power to the control power supply module. The power distribution unit of the present invention is divided into Figure 2 to Figure 5 The four parts shown.

[0046] The main module for pyrotechnic control includes a battery negative bus main switch, an analog separation circuit, an arrow electrical separation locking circuit, a first group of battery positive bus main switches, a pyrotechnic ignition current detection circuit and a pyrotechnic drive circuit, wherein the first group of battery positive bus main switches are connected to the pyrotechnic drive circuit; the battery negative bus main switch is connected to the pyrotechnic drive circuit.

[0047] The pyrotechnic control slave module comprises a second battery positive bus master switch and a pyrotechnic drive circuit, and the second battery positive bus master switch is connected to the pyrotechnic drive circuit.

[0048] The negative bus main switch of the battery, the positive bus main switch of the first group of batteries, and the positive bus main switch of the second group of batteries use magnetic holding relays; the pyrotechnic drive circuit and the pyrotechnic drive circuit use MOS tubes; the pyrotechnic ignition current detection circuit uses Hall current sensors; the analog separation circuit and the device electrical separation locking circuit use electromagnetic relays.

[0049] The hybrid power supply module includes a relay control power supply circuit and a converging module direct power supply circuit. The control power supply module includes a relay control power supply circuit, wherein the relay control power supply circuit adopts a magnetic latching relay.

[0050] like Figure 2 As shown, the pyrotechnic control main module includes a battery negative bus main switch, an analog separation circuit, an arrow electrical separation locking circuit, a first group of battery positive bus main switches, an pyrotechnic detonation current detection circuit and an pyrotechnic drive circuit, and the main and standby circuits work in hot backup. The first group of battery positive bus main switches are connected to the pyrotechnic drive circuit, and the battery negative bus main switch is connected to the pyrotechnic drive circuit. The battery negative bus main switch and the first group of battery positive bus main switches use magnetic latching relays, and the pyrotechnic drive circuit uses MOS tubes. The pyrotechnic control main module receives the ground analog separation command, generates arrow electrical analog separation, arrow mechanical analog separation signal, and analog separation indication signal, wherein the arrow electrical separation signal is used as the battery negative line main switch locking signal, the arrow mechanical analog separation signal is sent to the management unit and the GNC unit, and the analog separation indication signal is sent to the ground for collection. Before the arrow electrical separation, the battery negative bus main switch is in a locked state to prevent the pyrotechnic from detonating prematurely; after the arrow electrical separation, the battery negative bus main switch is unlocked. The pyrotechnic detonation current is collected by a current Hall sensor, and the Hall sensor output is expanded by a sample-and-hold circuit and sent to a comprehensive electronic collection. The pyrotechnic drive output is connected to the pyrotechnic bridge wire and the instrument, and the pyrotechnic safety is ensured by the instrument protection plug. The pyrotechnic control master module is the basic configuration, which supplies power to the pyrotechnic control slave module. Figure 3 As shown, the pyrotechnic control slave module includes the second group of battery positive bus master switches and pyrotechnic drive circuits, and the second group of battery negative bus master switches are implemented by the pyrotechnic control master module. The 29V working power supply and battery bus of the pyrotechnic control slave module are input through the inter-board connector and output by the pyrotechnic control master module. Among them, the battery positive bus master switch and the pyrotechnic drive circuit are both main and standby sets. The main channel of the battery positive bus master switch is connected to the main circuit of the pyrotechnic drive circuit; the backup channel of the battery positive bus master switch is connected to the backup circuit of the pyrotechnic drive circuit, and the main and standby circuits work in hot backup. The pyrotechnic drive output is connected to the pyrotechnic bridge wire and the instrument meter, and the pyrotechnic safety is ensured by the instrument meter protection plug. The pyrotechnic control slave module is an pyrotechnic control function expansion module, which can be configured in quantity according to task requirements.

[0051] like Figure 4 As shown in the figure, the hybrid power supply module uses a magnetic latching relay as the control power switch. The relay switch control OC gate command is provided externally, and the resistance voltage division analog quantity telemetry of the relay power supply output is collected externally. The external power supply bus input passes through the confluence module as the relay input and direct power supply output, and at the same time, the control power supply module is powered through the inter-board connector.

[0052] like Figure 5 As shown, the control power supply module adopts a magnetic latching relay as the control power supply power switch. The control power supply module is powered by the hybrid power supply module through the inter-board connector. The relay switch control OC gate instruction is provided externally. The resistance voltage division analog quantity telemetry of the relay power supply output is collected externally. The control power supply module is used as an expansion module, and its quantity can be configured according to the number of distribution circuits required.

[0053] The present invention adopts a modular and universal design, which can realize the flexible expansion of control resources, solve the problems of diverse interfaces and poor universality of distribution unit products, and reduce the development cycle and R&D cost of single-machine products through standardized design. It is suitable for power distribution control and pyrotechnic control of spacecraft such as deep space probes.

[0054] 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 power distribution system for deep space exploration missions, characterized in that: It includes an pyrotechnic control master module, an pyrotechnic control slave module, a hybrid power supply module and a control power supply module; The pyrotechnic control master module is connected to the pyrotechnic control slave module, and the pyrotechnic control master module supplies power to the pyrotechnic control slave module; The hybrid power supply module is connected to the control power supply module, and the hybrid power supply module supplies power to the control power supply module; The pyrotechnic control main module includes a battery negative busbar master switch, a first group of battery positive busbar master switches, a first pyrotechnic drive circuit, an arrow electrical separation locking circuit, an arrow electrical simulation separation circuit, an arrow mechanical simulation separation circuit and a pyrotechnic detonation current detection circuit; The battery negative bus master switch is respectively connected to the first pyrotechnic device driving circuit, the pyrotechnic device detonation current detection circuit and the device-arrow electrical separation locking circuit; The first battery group positive busbar master switch is connected to the first pyrotechnic device drive circuit; The device-arrow electrical separation locking circuit is connected to the device-arrow electrical simulation separation circuit; The device-arrow electrical simulation separation circuit and the device-arrow mechanical simulation separation circuit are both used to connect a separation plug; The battery negative bus master switch is connected to the pyrotechnic control slave module; The pyrotechnic control slave module includes a second group of battery positive busbar master switches and a second pyrotechnic drive circuit; The second battery group positive busbar master switch is connected to the second pyrotechnic device drive circuit; The second battery group positive busbar master switch is connected to the battery negative busbar master switch; The hybrid power supply module comprises a first relay-controlled power supply circuit and a confluence module direct power supply circuit; The first relay control power supply circuit is connected to the direct power supply circuit of the convergence module, and the first relay control power supply circuit and the direct power supply circuit of the convergence module are both connected to the control power supply module; The control power supply module includes a second relay control power supply circuit, and the second relay control power supply circuit is connected to the hybrid power supply module.

2. The power distribution system for deep space exploration missions according to claim 1, characterized in that: The battery negative busbar master switch and the first group of battery positive busbar master switch both use magnetic latching relays.

3. The power distribution system for deep space exploration missions according to claim 1, characterized in that: The first pyrotechnic device driving circuit adopts MOS tube.

4. The power distribution system for deep space exploration missions according to claim 1, characterized in that: The pyrotechnic device detonation current detection circuit adopts a Hall current sensor.

5. The power distribution system for deep space exploration missions according to claim 1, characterized in that: The device-arrow electrical simulation separation circuit, the device-arrow mechanical simulation separation circuit and the device-arrow electrical separation locking circuit all use electromagnetic relays.

6. The power distribution system for deep space exploration missions according to claim 1, characterized in that: The main switch of the positive busbar of the second battery group adopts a magnetic latching relay.

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