A separation control box for a satellite deployer suitable for long-term on-orbit operation

Abstract

The present invention discloses a separation control box suitable for a satellite deployer running on orbit for a long time. The separation control box can collect the temperature of the deployer, heat the deployer, control the deployment unlocking device to unlock, charge the satellite battery, perform secondary conversion on the power provided by the carrier to be suitable for the satellite deployer, receive the carrier's instructions, and provide the carrier with telemetry signals of the satellite and deployer status. The separation control box includes an electrical interface connecting the carrier and the satellite deployer, which can receive the power signal provided by the carrier; there are four-way temperature collection in the separation control box, which can collect the temperature of the upper and lower surfaces of the deployer, the deployer bottom plate and the electrical box, and return them to the carrier; there are four-way thermal control component heating control circuits inside the deployer, which can heat the deployer; the separation control box can receive separation instructions from the carrier.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, in particular to a separation control box for a satellite deployer that operates on-orbit for a long time. Background Art

[0002] The Picosat Orbital Deployer (POD) is a satellite-rocket separation mechanism, mainly used for the separation of cubic satellites. The function of the satellite deployer is to reliably connect the satellite and the carrier, realize the satellite release in space, and complete the deployment. The satellite deployer needs to receive the separation signal from the rocket, spacecraft, upper stage and other carriers to realize the release of the satellite. The carrier is directly electrically connected to the satellite deployer, and a large number of cables need to be connected. It is easy for the cables to get tangled during the separation of the satellite from the deployer, causing the satellite to be unable to separate normally. Secondly, for satellites that have long-term separation requirements after being in orbit, the satellite needs to be charged. Usually, the power input provided by the carrier does not meet the power amplitude required by the satellite battery. At the same time, in this process, the environment of the satellite deployer is unknown, and the temperature of the satellite cannot be determined, so it may affect the normal working state of the satellite after release. Summary of the invention

[0003] The object of the present invention is to provide a separation control box for a satellite deployer that is suitable for long-term on-orbit operation, so as to solve the problems raised in the above-mentioned background technology.

[0004] To achieve the above object, the present invention provides the following technical solutions:

[0005] A separation control box for a satellite deployer for long-term on-orbit operation comprises a shell, and the shell is provided with 5 interfaces, wherein:

[0006] Interface 1, used to connect the satellite deployer and carrier;

[0007] Interface 2, connected with the separation mechanism;

[0008] Interface three, connecting with satellite;

[0009] Interface 4, connected with the satellite deployer;

[0010] Interface five is the ground survey interface.

[0011] As a further technical solution of the present invention: a grounding pile is installed on the shell.

[0012] As a further technical solution of the present invention: the shell contains a secondary power conversion circuit for receiving the carrier power supply input and completing the secondary power conversion of the deployer control box.

[0013] As a further technical solution of the present invention: the shell contains a hatch device unlocking circuit for receiving a release instruction carried out, providing an unlocking current signal to the unlocking mechanism, and ensuring smooth unlocking of the hatch.

[0014] As a further technical solution of the present invention: the shell contains a temperature collection circuit for receiving a release instruction carried out, providing an unlocking current signal to the unlocking mechanism, and ensuring smooth unlocking of the hatch.

[0015] As a further technical solution of the present invention: the shell contains a satellite battery charging interface for charging the satellite.

[0016] As a further technical solution of the present invention: the shell contains a temperature and separation status telemetry circuit for remotely measuring the temperature of the satellite deployer and the satellite separation status, and returning the temperature and separation status to the carrier.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The separation control box of the present invention includes an electrical interface connecting the carrier and the satellite deployer, which can receive the power signal provided by the carrier; the separation control box has four-way temperature acquisition, which can collect the temperature of the upper and lower surfaces of the deployer, the deployer bottom plate and the electrical box, and return it to the carrier; the deployer is provided with a four-way thermal control component heating control circuit inside, which can heat the deployer; the separation control box can receive the separation instruction from the carrier, control the unlocking device on the deployer, realize the unlocking of the deployer to complete the satellite release, and return the telemetry signal. Through this separation control box, various signal transmission and conversion between the carrier and the satellite deployer (POD) can be carried out. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is the structure diagram of the separation control box.

[0020] Figure 2 This is the electrical block diagram of the separation control box.

[0021] Figure 1 Middle: 1-interface 1, 2-interface 2, 3-interface 3, 4-interface 4, 5-interface 5, 6-grounding pile, 7-shell. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] like Figure 1 and2 As shown, a separation control box for a satellite deployer that is suitable for long-term in-orbit operation includes a shell 7, and the shell 7 is provided with 5 electrical interfaces, namely: interface 1, interface 2, interface 3, interface 4, and interface 5. The shell 7 is also provided with a grounding post 6. The separation control box serves as a connection channel between the carrier and the satellite deployer, and receives power and transmits remote control and telemetry data with the carrier. During satellite deployment, satellite separation control and signal remote control, and deployer temperature telemetry are performed. Secondary power is provided to convert into satellite batteries for charging. Figure 2 .

[0024] The separation control box is connected to the carrier through interface 1 to realize the power input provided by the carrier; transmit the satellite and carrier separation switch command; remotely measure the temperature of the upper and lower surfaces, bottom plate, and electrical box of the satellite deployer; remotely measure the deployment status of the satellite deployer door; remotely measure the separation status of the satellite and push plate; and remotely measure the separation switch status.

[0025] The separation control box is connected to the deployer through interface 2. When the separation control box receives the separation command issued by the spacecraft, it energizes the unlocking device to achieve unlocking and release the satellite; collects the deployment status of the satellite deployer hatch; and collects the status of the satellite and the push plate.

[0026] The separation control box is connected to the satellite via interface 3 to charge the battery.

[0027] The separation control box is connected to the satellite deployer via interface four 4: to collect the temperature of the satellite deployer; when the temperature is too low, the satellite deployer is heated.

[0028] The interface 5 of the separation control box is a ground measurement interface, which can be used to remotely measure the heater status and the secondary power conversion.

[0029] Here’s how it works:

[0030] Power Conversion:

[0031] The power conversion module converts the input power into the power required by the control circuit. The secondary power module adopts a two-way main and standby design, which is a hot backup design. When the main part fails, it automatically switches to the backup output to ensure the normal power supply of the DCDC module.

[0032] Satellite deployer temperature collection and control:

[0033] Temperatures are collected on the upper surface of the satellite deployer, the lower surface of the satellite deployer, the bottom plate of the satellite deployer, and the electrical box of the satellite deployer. The separate control box collects analog signals. When the temperature is too low, the heating mode is turned on to heat the satellite deployer to ensure that the temperature of the satellite deployer is within the working range.

[0034] Satellite battery charging:

[0035] The given power input is converted into the power required by the satellite battery through the power conversion circuit inside the separation control box, and the satellite battery is charged through the interface.

[0036] Device unlock:

[0037] The separation control box receives the release command from the carrier and provides an unlocking current signal to the unlocking mechanism to ensure that the hatch is unlocked smoothly.

[0038] Embodiment 2, based on the embodiment, the separation control box of the present design is further provided with a thermal control component and a thermal control component heating device inside, which are used for heating control of the bottom, upper surface, lower surface and electrical box of the deployer door panel.

[0039] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.

[0040] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A separation control box for a satellite deployer for long-term on-orbit operation, comprising a housing, characterized in that: The housing is provided with 5 interfaces, among which: Interface 1, used to connect the separation mechanism and the carrier; Interface 2, used to connect the separation mechanism and the satellite deployer; Interface three, connecting with satellite; Interface 4, connected with the satellite deployer; Interface five is the ground measurement interface; The shell contains a secondary power conversion circuit for accepting the carrier power supply input and completing the secondary power conversion of the deployer control box. The shell contains a door device unlocking circuit for receiving the carrier release command, providing an unlocking current signal to the unlocking mechanism, and ensuring that the door is unlocked smoothly. The shell contains a temperature acquisition circuit for receiving the carrier release command, providing an unlocking current signal to the unlocking mechanism, and ensuring that the door is unlocked smoothly. The shell contains a satellite battery charging interface for charging the satellite. The shell contains a temperature and separation status telemetry circuit for telemetering the satellite deployer temperature and the satellite separation status, and returning the temperature and separation status to the carrier.

2. According to claim 1, a separation control box for a satellite deployer suitable for long-term on-orbit operation is characterized in that: A grounding pile is installed on the shell.

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