Method and device for controlling the separation of the post-boost portion of a launch vehicle

Abstract

The application discloses a control method and device for a tail section part after separation of a carrier rocket, and relates to the field of power supply of the carrier rocket. The method comprises the following steps: after separation of the tail section part, the power supply mode of a comprehensive controller is changed to be battery power supply, and the power supply mode of a rudder is changed to be combined power supply of a tail section battery and the battery; and the tail section part is controlled to fall into a specified area by the rudder. The tail section battery and the battery are additionally arranged in the tail section part, and corresponding power distribution modes are adopted, so that the rudder still has sufficient power to support work after separation of the tail section part, the tail section part is controlled to fall into the specified area, and thus the workload of safety management and control required by large-scale falling area is significantly reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of power supply for carrier rockets, in particular to a control method and device for a tail section of a carrier rocket after separation. BACKGROUND

[0002] In recent years, many countries in the world have invested a large amount of resources in the research of carrier rockets. With the testing and launching of various new models of carrier rockets, the problem of the substage debris falling area (hereinafter referred to as the falling area) has gradually attracted attention. At present, the falling area of the tail section of the carrier rocket is too large, and a large number of personnel need to be evacuated, and the corresponding safety management and control work of the falling area is heavy. SUMMARY

[0003] In view of the defects in the prior art, the technical problem solved by the present application is how to supply power to the tail section after separation, and thus achieve the purpose of controlling the tail section to fall into a specified area.

[0004] To achieve the above purpose, the control method for the tail section of a carrier rocket after separation provided by the present application includes a comprehensive controller, a rudder, a tail inertial unit, and a final stage battery for powering the comprehensive controller. The method includes the following steps: after the tail section is separated, the power supply mode of the comprehensive controller is changed to use a storage battery, and the power supply mode of the rudder is changed to use a tail battery and a storage battery combined power supply; the tail section is controlled to fall into a specified area by the rudder.

[0005] On the basis of the above technical solution, the process of changing the power supply mode of the comprehensive controller to use a storage battery and the power supply mode of the rudder to use a tail battery and a storage battery combined power supply after the tail section is separated includes: before separation, using the final stage battery to power the comprehensive controller and using the tail battery to power the rudder; during the power conversion period before the separation command is issued, adjusting the power supply mode of the comprehensive controller from the final stage battery to a combined power supply of the storage battery and the final stage battery; during the separation stage, adjusting the power supply mode of the comprehensive controller from the combined power supply of the storage battery and the final stage battery to the power supply of the storage battery; and after the specified time length of the separation command is issued, adjusting the power supply mode of the rudder from the tail battery to the combined power supply of the tail battery and the storage battery.

[0006] On the basis of the above technical solution, before using the storage battery for power supply, the method further includes the following steps: connecting a diode and a power distribution switch in series on the storage battery power supply line, and connecting a diode in series on the power supply line of the final stage battery and the tail battery; the process of using the storage battery for power supply includes closing the power distribution switch.

[0007] On the basis of the above technical solution, preferably, the method further includes the following step: during the process from the pre-separation stage to the falling stage, using the storage battery to power the tail inertial unit.

[0008] On the basis of the above technical solutions, the tail section further comprises a tail section telemetry system, and the method further comprises the following steps: using the final stage battery to supply power for the tail section telemetry system in the pre-separation stage, adjusting the power supply mode of the tail section telemetry system from the final stage battery to the combined power supply of the storage battery and the final stage battery in the power conversion period before the separation instruction is issued; and adjusting the power supply mode of the tail section telemetry system from the combined power supply of the storage battery and the final stage battery to the power supply of the storage battery during the separation stage.

[0009] The application provides a control device for a tail section of a launch vehicle after separation, wherein the tail section comprises a comprehensive controller, a rudder, a tail section inertial unit, and a final stage battery for supplying power to the comprehensive controller; the device comprises a launch control computer, a tail section battery and a storage battery for supplying power to the launch control computer, which are arranged in the tail section; the launch control computer is configured to: after the tail section is separated, change the power supply mode of the comprehensive controller to the power supply of the storage battery, and change the power supply mode of the rudder to the combined power supply of the tail section battery and the storage battery; and control the tail section to fall into a designated area through the rudder.

[0010] On the basis of the above technical solutions, the working process of the launch control computer comprises:

[0011] In the pre-separation stage, the output end of the final stage battery is connected to the input end of the comprehensive controller, and the output end of the tail section battery is connected to the input end of the rudder;

[0012] In the power conversion period before the separation instruction is issued, the output end of the storage battery is connected to the input end of the comprehensive controller;

[0013] During the separation stage, the power supply line between the final stage battery and the comprehensive controller is disconnected;

[0014] After the specified time length of the separation instruction is issued, the output end of the storage battery is connected to the input end of the rudder.

[0015] On the basis of the above technical solutions, diodes are connected in series on the power supply lines of the storage battery, the final stage battery and the tail section battery, and a power distribution switch is further connected in series on the power supply line of the storage battery, and the power distribution switch is configured to be closed when the power supply of the storage battery is needed and disconnected when the power supply of the storage battery is not needed.

[0016] On the basis of the above technical solutions, the storage battery is further configured to supply power to the tail section inertial unit during the process from the pre-separation stage to the falling stage.

[0017] On the basis of the above technical solutions, the device further comprises a tail section telemetry system, which is configured to periodically send data of the integrated controller and the launch control computer to a control terminal on the ground; the launch control computer is further configured to control the output end of the final stage battery to be connected to the input end of the tail section telemetry system before separation, and control the output end of the battery to be connected to the input end of the tail section telemetry system in a power conversion period before the separation instruction is issued; and during the separation stage, the power supply line between the final stage battery and the tail section telemetry system is disconnected.

[0018] Compared with the prior art, the application has the following advantages:

[0019] Compared with the prior art, the application has the following advantages:

[0020] At the same time, the application is provided with a diode on the battery power supply line to prevent short circuit when the battery is connected and powered, thereby improving the safety in use; at the same time, the application is provided with a power distribution switch for the battery power supply line to prevent the battery from consuming power when using the final stage battery or the tail section battery to charge itself during flight. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative effort.

[0022] Figure 1 The power supply schematic diagram of the integrated controller and the tail section telemetry system in the embodiment of the application;

[0023] Figure 2 The power supply schematic diagram of the rudder motor in the embodiment of the application. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the embodiments of the application more clear, the technical solutions in the embodiments of the application will be described clearly and completely in the following with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only some of the embodiments of the application, not all. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative effort belong to the scope of protection of the application.

[0025] The flow chart shown in the drawing is only an example and does not necessarily include all contents and operations / steps, nor does it have to be executed in the order described. For example, some operations / steps can be further divided, combined or partially merged, so the actual execution order can be changed according to actual conditions.

[0026] First, the development principle of the application is introduced.

[0027] It is found through research that the existing tail section is powered by the main battery of the rocket, and after separation, the power supply is cut off, and the work of the control unit cannot be continued; at the same time, the battery of the tail section is separated, and the remaining power is consumed, and the rudder cannot be effectively and continuously powered.

[0028] Therefore, it is necessary to ensure that the tail section still has enough power to support the rudder after separation, so as to control the tail section to fall into the specified area.

[0029] On this basis, the tail section in the embodiment of the application includes a comprehensive controller, a rudder, a tail inertial unit, and a final battery for powering the comprehensive controller; the control method of the tail section after the separation of the carrier rocket includes the following steps: after the separation of the tail section, the power supply mode of the comprehensive controller is changed to use the storage battery for power supply, and the power supply mode of the rudder is changed to use the tail battery and the storage battery for combined power supply; the tail section is controlled to fall into the specified area by the rudder.

[0030] Therefore, compared with the large falling area range of the tail section in the prior art, the tail battery and the storage battery are added to the tail section in the application, and through the corresponding power distribution mode, the rudder still has enough power to support the work of the tail section after the separation, so as to control the tail section to fall into the specified area, thereby significantly reducing the safety control workload required by the large falling area.

[0031] The power supply mode of each device of the tail section of the application is introduced below. First, the stages of the rocket separation are briefly described (the names of the stages and the transition order are prior art).

[0032] (1) The pre-separation stage includes the pre-launch stage (i.e. the stage before the launch of the rocket), the first active stage, the first sliding stage, etc.

[0033] (2) The (first) separation stage, i.e. the stage of separating the tail section, enters after the rocket separation command.

[0034] (3) The falling stage, i.e. the stage of the separated tail falling.

[0035] On this basis, to achieve that the tail section still has enough power after separation, the power distribution direction is: as much as possible to use the non-charged battery possessed by the rocket itself for power supply in the pre-separation stage, so as to ensure that the battery in the separated body has enough power after separation.

[0036] To this end, the specific flow of changing the power supply mode of the integrated controller to battery power supply and the power supply mode of the rudder to combined power supply of the tail section battery and the battery after separation in the tail section part in the above method comprises: in the pre-separation stage, the integrated controller is powered by the last battery, and the rudder is powered by the tail section battery; in the power conversion period before the separation instruction is issued (3 seconds before the separation instruction is issued in this embodiment), the power supply mode of the integrated controller is adjusted from the last battery to combined power supply of the battery and the last battery; in the separation stage, the power supply mode of the integrated controller is adjusted from combined power supply of the battery and the last battery to battery power supply; after the specified time (1 second in this embodiment) after the separation instruction is issued, the power supply mode of the rudder is adjusted from the tail section battery to combined power supply of the tail section battery and the battery.

[0037] Preferably, referring to FIGS. 1, 2 and 3, the method further comprises the following steps before the battery power supply is used: connecting a diode and a power distribution switch in series on the battery power supply line, and connecting a diode in series on the power supply lines of the last battery and the tail section battery; the flow of using the battery power supply in the above method comprises: closing the power distribution switch. Figure 1 Figure 2 Therefore, the diode for preventing short circuit when the battery is connected and powered is arranged on the battery power supply line, and the use safety is improved; at the same time, the power distribution switch is arranged on the battery power supply line to prevent the battery from consuming power when the last battery or the tail section battery is used to charge the battery during flight.

[0038] Preferably, the method further comprises the following steps: in the process from the pre-separation stage to the falling stage, the battery is used to power the tail section inertial unit, and the battery is used here because the battery can support the rudder to control the tail section part to land and has enough power after separation through the above process; on this basis, a dedicated battery is not needed to be additionally arranged for the tail section inertial unit.

[0039] Preferably, the tail section part further comprises a tail section telemetry system, which comprises a tail section telemetry central unit, a tail section encoder, a telemetry power amplifier, a chain detection transmitting antenna, a chain detection receiving antenna and a tail section telemetry transmitting antenna; the method further comprises the following steps: in the pre-separation stage, the last battery is used to power the tail section telemetry system, and in the power conversion period before the separation instruction is issued, the power supply mode of the tail section telemetry system is adjusted from the last battery to combined power supply of the battery and the last battery; in the separation stage, the power supply mode of the tail section telemetry system is adjusted from combined power supply of the battery and the last battery to battery power supply.

[0040] Preferably, the tail section part further comprises a tail section telemetry system, which comprises a tail section telemetry central unit, a tail section encoder, a telemetry power amplifier, a chain detection transmitting antenna, a chain detection receiving antenna and a tail section telemetry transmitting antenna; the method further comprises the following steps: in the pre-separation stage, the last battery is used to power the tail section telemetry system, and in the power conversion period before the separation instruction is issued, the power supply mode of the tail section telemetry system is adjusted from the last battery to combined power supply of the battery and the last battery; in the separation stage, the power supply mode of the tail section telemetry system is adjusted from combined power supply of the battery and the last battery to battery power supply.

[0041] ​The control device for the tail section part of the carrier rocket in the embodiment of the application, the tail section part comprising a comprehensive controller, a rudder, a tail inertial unit, and a final stage battery for powering the comprehensive controller; the device comprising a launch control computer, a tail battery and a storage battery (a lithium battery pack is used in the embodiment) for powering the launch control computer, which are arranged in the tail section part.

[0042] Preferably, the working flow of the launch control computer comprises:

[0043] In the pre-separation stage, the output end of the control final stage battery is connected to the input end of the comprehensive controller (i.e., the final stage battery is used to power the comprehensive controller), and the output end of the control tail battery is connected to the input end of the rudder (i.e., the tail battery is used to power the rudder);

[0044] In the power conversion period (3 seconds before the separation instruction is issued in the embodiment) before the separation instruction is issued, the output end of the storage battery is connected to the input end of the comprehensive controller (i.e., the power supply mode of the comprehensive controller is adjusted from the final stage battery to the joint power supply of the storage battery and the final stage battery);

[0045] In the process of the separation stage, the power supply line between the final stage battery and the comprehensive controller is disconnected (i.e., the power supply mode is adjusted from the joint power supply of the storage battery and the final stage battery to the power supply of the storage battery);

[0046] After the specified time length (1 second in the embodiment) after the separation instruction is issued, the output end of the storage battery is connected to the input end of the rudder (i.e., the power supply mode of the rudder is adjusted from the tail battery to the joint power supply of the tail battery and the storage battery).

[0047] Preferably, as shown in Figure 1 and Figure 2 , a diode is connected in series on the power supply line of the storage battery, the final stage battery and the tail battery, and a power distribution switch is further connected in series on the power supply line of the storage battery, which is used to close when the storage battery needs to be powered and to disconnect when the storage battery does not need to be powered, so as to prevent the storage battery from consuming the power in the flight process when the final stage battery or the tail battery is used to charge the storage battery.

[0048] Preferably, the storage battery in the device is further used to power the tail inertial unit in the process from the pre-separation stage to the falling stage.

[0049] Preferably, the device further comprises a tail section telemetry system, which comprises a tail section telemetry central unit, a tail section transducer, a telemetry power amplifier, a chain detection transmitting antenna, a chain detection receiving antenna and a tail section telemetry transmitting antenna; the tail section telemetry system is configured to periodically send data of the integrated controller and the launch control computer to a control terminal on the ground. The launch control computer is further configured to control the output end of the final stage battery to be connected to the input end of the tail section telemetry system before separation (i.e., the final stage battery is used to supply power to the tail section telemetry system), control the output end of the battery to be connected to the input end of the tail section telemetry system in the power conversion period before the separation instruction is issued (i.e., the power supply mode of the tail section telemetry system is adjusted from the final stage battery to the joint power supply of the battery and the final stage battery), and disconnect the power supply line between the final stage battery and the tail section telemetry system during the separation stage (i.e., the power supply mode of the tail section telemetry system is adjusted from the joint power supply of the battery and the final stage battery to the power supply of the battery).

[0050] Those of ordinary skill in the art will appreciate that all or certain steps in the methods disclosed above and functional modules / units in the systems and devices can be implemented as software, firmware, hardware, and appropriate combinations thereof. In hardware implementations, the division between the functional modules / units mentioned in the above description does not necessarily correspond to the division of physical components; for example, one physical component can have multiple functions, or one function or step can be performed by several physical components in cooperation. Certain physical components or all physical components can be implemented as software executed by a processor, such as a central processing unit, a digital signal processor, or a microprocessor, or as hardware, or as an integrated circuit, such as an application-specific integrated circuit. Such software can be distributed on computer-readable storage media, which can include computer-readable storage media (or non-transitory media) and communication media (or transitory media).

[0051] As is well known to those of ordinary skill in the art, the term computer-readable storage media includes volatile and non-volatile, removable and non-removable media implemented in any method or technology for storage of information such as computer readable instructions, data structures, program modules or other data. Computer-readable storage media includes, but is not limited to, RAM, ROM, EEPROM, flash memory or other memory technology, CD-ROM, digital versatile disks (DVD) or other optical disk storage, magnetic cassettes, magnetic tapes, magnetic disk storage or other magnetic storage devices, or any other medium that can be used to store the desired information and can be accessed by a computer. In addition, it is well known to those of ordinary skill in the art that communication media typically includes computer-readable instructions, data structures, program modules or other data in modulated data signals such as carrier waves or other transport mechanisms, and can include any information delivery medium.

[0052] For example, the computer readable storage medium can be an internal storage unit of the electronic device of the aforementioned embodiments, such as a hard disk or a memory of the electronic device. The computer readable storage medium can also be an external storage device of the electronic device, such as a plug-in hard disk, a smart media card (SMC), a secure digital (SD) card, a flash card, or the like.

[0053] The above merely provides the specific implementation of the embodiments of the present application, but the protection scope of the embodiments of the present application is not limited to this. Any person skilled in the art can easily think of various equivalent modifications or replacements within the technical range disclosed by the embodiments of the present application, and these modifications or replacements should be covered in the protection scope of the embodiments of the present application. Therefore, the protection scope of the embodiments of the present application should be subject to the protection scope of the claims.

Claims

1. A control method for the tail section of a launch vehicle after separation, wherein the tail section includes an integrated controller, servo motors, a tail section inertial navigation system, and a final-stage battery for powering the integrated controller; characterized in that, The method includes the following steps: Before separation, the final stage battery powers the integrated controller, and the tail stage battery powers the servo motor. During the power conversion cycle before the separation command is issued, the power supply mode of the integrated controller is changed from the final stage battery to a combination of the battery and the final stage battery. During the separation phase, the power supply mode of the integrated controller is changed from a combination of the battery and the final stage battery to battery power. After a specified time after the separation command is issued, the power supply mode of the servo motor is changed from the tail stage battery to a combination of the tail stage battery and the battery. The tail section is controlled by a servo motor to fall into the designated area. Before using battery power, the process includes the following steps: connecting a diode and a power distribution switch in series on the battery power supply line, and connecting a diode in series on the power supply lines of the final battery and the last battery; the process of using battery power includes: closing the power distribution switch.

2. The control method for the tail section of a launch vehicle after separation as described in claim 1, characterized in that, The method also includes the following steps: during the pre-separation phase to the descent phase, a battery is used to power the tail section inertial navigation system.

3. The control method for the tail section of a launch vehicle after separation as described in claim 1 or 2, characterized in that: The tail section also includes a tail section telemetry system. The method further includes the following steps: in the pre-separation stage, the tail section telemetry system is powered by the final stage battery; during the power conversion cycle before the separation command is issued, the power supply mode of the tail section telemetry system is changed from the final stage battery to a combination of battery and final stage battery; during the separation stage, the power supply mode of the tail section telemetry system is changed from a combination of battery and final stage battery to battery power.

4. A control device for the tail section of a launch vehicle after separation, the tail section comprising an integrated controller, servo motors, a tail section inertial navigation system, and a final-stage battery for powering the integrated controller; characterized in that: The device includes a launch control computer located in the tail section, a tail section battery, and a storage battery for powering the launch control computer. The launch control computer is used to: control the output of the final stage battery to be connected to the input of the integrated controller, and control the output of the tail stage battery to be connected to the input of the servo motor in the pre-separation stage. During the power conversion cycle before the separation command is issued, the output terminal of the control battery is connected to the input terminal of the integrated controller; During the separation phase, disconnect the power supply lines between the final stage battery and the integrated controller; After a specified time has elapsed since the separation command was issued, the output terminal of the control battery is connected to the input terminal of the servo motor. After the tail section is separated, the power supply method of the integrated controller is changed to battery power, and the power supply method of the servo motor is changed to a combination of tail section battery and battery; the tail section is controlled by the servo motor to fall into the designated area. Each of the power supply lines for the storage battery, the final stage battery, and the tail stage battery has a diode connected in series. A power distribution switch is also connected in series on the power supply line for the storage battery. The power distribution switch is used to: close when the storage battery is needed and open when the storage battery is not needed.

5. The control device for the tail section of a launch vehicle after separation as described in claim 4, characterized in that: The battery is also used to power the tail section inertial navigation system during the pre-separation phase to the descent phase.

6. The control device for the tail section of a launch vehicle after separation as described in claim 4 or 5, characterized in that: The device also includes a tail-end telemetry system, which is used to periodically send data from the integrated controller and the launch control computer to the ground control terminal. The launch control computer is also used to control the output of the final stage battery to be connected to the input of the tail-end telemetry system before separation, and to control the output of the battery to be connected to the input of the tail-end telemetry system during the power conversion cycle before the separation command is issued. During the separation phase, the power supply lines between the final stage battery and the tail-end telemetry system are disconnected.

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