A wireless transmission energy emitting and controlling device and a method thereof

Abstract

The application relates to a wireless transmission energy control device and a wireless transmission energy control method, and solves the problems of multiple missile cable transmission, large weight and large occupied space of the energy control device. The device comprises an energy control management module and an energy control execution module, the energy control execution module comprises a sending end and at least one receiving end, the sending end comprises a first coupling coil and a first wireless transceiver module, and the receiving end comprises a second coupling coil and a second wireless transceiver module; the energy control management module is used for receiving a missile instruction and sending the instruction to the sending end; the sending end is used for receiving an external current and transmitting electric energy to the corresponding receiving end through the coupling effect of the first / second coupling coil, and transmitting the missile instruction to the corresponding receiving end through wireless communication between the first / second transceiver modules; and the receiving end is used for controlling the corresponding missile system according to the missile instruction. The number of cables and the occupied space are reduced, and the maintenance difficulty of the weapon equipment is reduced.

Description

Technical Field

[0001] This invention relates to the field of weapon system launch and control technology, and in particular to a wireless power transmission launch and control device and method. Background Technology

[0002] The launch control system (RCS) is a crucial component of a weapon system, connecting the command and control system with the missile system. Typically, the RCS handles pre-launch checks and launch control for multiple missiles. With increasing informatization, the demands on weapon equipment are constantly rising. Currently, command information and power supply are transmitted from the RCS to the missiles via cables. As the payload and number of missiles required increase, the amount of cable between the RCS and the missiles needs to be continuously increased. These cables not only increase the weight of the weapon system but also occupy significant space, hindering the rational layout of the equipment relative to the missiles. Furthermore, the large number of cables complicates installation for operators and increases the difficulty of equipment maintenance.

[0003] Currently, the launch control unit (CCU) is connected to the missiles via cables, with one CCU connecting multiple missiles. Command and control system instructions and power supply are transmitted to the missiles via these cables. As the number of missiles controlled by a single CCU increases, two methods can be used. One is to directly add cables between the CCU and the missiles, installing all cables before launch; the other is to not change the existing cables but instead create multiple sets of cables, connecting the CCU to the next set of missiles after each launch. Both methods require additional cables. The former consumes a significant amount of space, hindering efficient missile layout and making installation and maintenance more difficult. The latter requires personnel to replace a set of cables after each launch, resulting in time consumption and low automation.

[0004] To address the problems of numerous, heavy, and space-consuming cables, complex personnel operation, and difficult weapon maintenance associated with a single launch control device for launching multiple missiles, there is an urgent need to find a new launch control device that significantly reduces the weight and space occupied by the cables. Summary of the Invention

[0005] Based on the above analysis, the present invention aims to provide a wireless transmission and control device and method for launching and controlling multiple missiles, in order to solve the problems of existing launch and control devices having many cables, large weight, large space occupation, complex personnel operation, and high maintenance difficulty when launching multiple missiles.

[0006] On one hand, embodiments of the present invention provide a wireless transmission and power transmission control device, including a transmission control management module and a transmission control execution module. The transmission control execution module includes a transmitting end and at least one receiving end. The transmitting end includes a first coupling coil and a first wireless transceiver module, and the receiving end includes a second coupling coil and a second wireless transceiver module.

[0007] The launch control management module is used to receive the launch command and send the launch command to the sending end;

[0008] The transmitting end is used to receive external current and transmit electrical energy to the corresponding receiving end through the coupling effect of the first coupling coil and the second coupling coil, and to transmit the launch command to the corresponding receiving end through wireless communication between the first transceiver module and the second transceiver module.

[0009] The receiving end is used to control the corresponding missile system according to the instructions on the missile.

[0010] Furthermore, the transmitting end also includes an input end and an inverter circuit;

[0011] The input terminal is connected to the inverter circuit and is used to receive external DC current.

[0012] The inverter circuit is connected to the first coupling coil and is used to invert the external DC current to generate AC current.

[0013] The first coupling coil transmits the alternating current to the second coupling coil based on the coupling effect between the alternating current and the second coupling coil.

[0014] Furthermore, the receiving end also includes a rectifier circuit and a relay;

[0015] The rectifier circuit is connected to the second coupling coil and is used to receive the AC current transmitted by the second coupling coil and convert the AC current into DC current.

[0016] The relay is connected to the rectifier circuit and is used to transmit the DC current to the corresponding missile system.

[0017] Furthermore, the control device also includes a moving mechanism. The control execution module includes a transmitting end and multiple receiving ends. The moving mechanism receives control commands and moves the transmitting end to the corresponding receiving end based on the control commands.

[0018] Furthermore, the multiple receiving terminals are located at the lower end of the missile box, which includes multiple missile tubes, and one receiving terminal controls the missile system in one missile tube.

[0019] Furthermore, the first coupling coil is located on the side of the transmitting end corresponding to the receiving end, and the second coupling coil is located on the side of the receiving end corresponding to the transmitting end.

[0020] Furthermore, the areas of the first coupling coil and the second coupling coil are equal, and when the first coupling coil couples with the corresponding second coupling coil of the receiving end, the corresponding areas of the two are greater than or equal to 70% of the area of ​​the first coupling coil.

[0021] Furthermore, the distance between the transmitting end and the corresponding receiving end ranges from 5mm to 40mm.

[0022] Furthermore, the receiving end is also used to receive the onboard feedback generated by the missile system after performing corresponding operations according to the onboard command, and to transmit the onboard feedback to the sending end via wireless communication using the second transceiver module;

[0023] The transmitting end is also used to receive the onboard feedback and send the onboard feedback to the launch control management module;

[0024] The launch control management module is used to receive the onboard feedback and send the onboard feedback to the command and control system.

[0025] On the other hand, embodiments of the present invention provide a wireless transmission and power transmission control method for a transmission control device. The transmission control device includes a transmission control management module and a transmission control execution module. The transmission control execution module includes a transmitting end and at least one receiving end. The transmitting end includes a first coupling coil and a first wireless transceiver module, and the receiving end includes a second coupling coil and a second wireless transceiver module. The transmission control method includes:

[0026] The launch control management module receives the launch command and sends the launch command to the sending end;

[0027] The transmitting end receives external current and transmits electrical energy to the corresponding receiving end through the coupling effect of the first coupling coil and the second coupling coil. The transmitting end also transmits the launch command to the corresponding receiving end through wireless communication between the first transceiver module and the second transceiver module.

[0028] The receiving end controls the corresponding missile system according to the instructions on the missile.

[0029] Compared with the prior art, the present invention can achieve at least the following beneficial effects:

[0030] This application employs a launch control execution module comprising a transmitter and at least one receiver. Electrical energy is transmitted to the receiver via the coupling between the first coupling coil of the transmitter and the second coupling coil of the receiver. Onboard commands are transmitted to the corresponding receiver via wireless communication between the first transceiver module of the transmitter and the second transceiver module of the receiver. This allows for the control of the missile system through the corresponding receiver. This technical solution reduces the weight and space occupied by a large number of cables, facilitates a more rational layout of the launch control device and missile system, reduces the difficulty of weapon maintenance, lowers the complexity of personnel operation, and improves the degree of automation.

[0031] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained from what is particularly pointed out in the description and drawings. Attached Figure Description

[0032] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0033] Figure 1 This is a flowchart illustrating the transmission of onboard commands / power / feedback between the launch control device and the corresponding missile system in one embodiment of this application.

[0034] Figure 2 This is a schematic diagram of the control execution module structure in one embodiment of this application;

[0035] Figure 3 This is a schematic diagram of a transmitter and multiple receivers in one embodiment of this application. Detailed Implementation

[0036] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which form part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0037] A specific embodiment of the present invention discloses a wireless transmission and power control device; please refer to [link to relevant documentation]. Figure 1The launch control device includes a launch control management module and a launch control execution module. The launch control execution module includes a transmitting end and at least one receiving end. The transmitting end includes a first coupling coil and a first wireless transceiver module, and the receiving end includes a second coupling coil and a second wireless transceiver module. The launch control management module is used to receive onboard commands and transmit the onboard commands to the transmitting end. The transmitting end is used to receive external current and transmit electrical energy to the corresponding receiving end through the coupling effect of the first coupling coil and the second coupling coil, and to transmit the onboard commands to the corresponding receiving end through wireless communication between the first transceiver module and the second transceiver module. The receiving end is used to control the corresponding missile system according to the onboard commands.

[0038] Compared with existing technologies, the wireless power transmission device provided in this embodiment, by splitting the launch control execution module into a transmitting end and at least one receiving end, transmits electrical energy to the receiving end through the coupling effect of the first coupling coil of the transmitting end and the second coupling coil of the receiving end, and transmits missile commands to the corresponding receiving end through wireless communication between the first transceiver module of the transmitting end and the second transceiver module of the receiving end, and then controls the corresponding missile system through the corresponding receiving end, reduces the weight and space occupied by a large number of cables, is more conducive to the rational layout of the launch control device and the missile system, reduces the maintenance difficulty of weapon equipment, reduces the complexity of personnel operation, and improves the degree of automation.

[0039] Specifically, the onboard command is sent from the command and control system to the launch control management module, and the launch control management module and the command and control system are connected by a cable; optionally, the number of cables is 1; furthermore, the launch control management module and the launch control execution module are connected by a cable; optionally, the number of cables is 1.

[0040] In one specific embodiment, please refer to Figure 2 The transmitting end further includes an input end and an inverter circuit; the input end is connected to the inverter circuit and is used to receive external DC current; the inverter circuit is connected to the first coupling coil and is used to invert the external DC current to generate AC current; the first coupling coil, based on the coupling effect between the AC current and the second coupling coil, transmits the AC current to the second coupling coil.

[0041] Specifically, the external DC current can be a 220V DC current. The inverter circuit converts the 220V DC current into a 220V AC current and transmits it to the first coupling coil. After receiving the 220V AC current, the first coupling coil will couple with the corresponding second coupling coil, transmitting the 220V AC current to the second coupling coil. That is, the transmission of electrical energy from the transmitting end to the receiving end is completed.

[0042] In one specific embodiment, the receiving end further includes a rectifier circuit and a relay; the rectifier circuit is connected to the second coupling coil and is used to receive the AC current transmitted by the second coupling coil and convert the AC current into DC current; the relay is connected to the rectifier circuit and is used to transmit the DC current to the corresponding missile system.

[0043] Specifically, the second coupling coil receives 220V AC current and transmits it to the rectifier circuit. The rectifier circuit converts the 220V AC current into 28V DC current and transmits it to the corresponding missile system through a relay. Furthermore, there is a power transmission channel between the rectifier circuit and each missile system. The number of relays matches the number of power transmission channels, with each channel corresponding to one relay. When the missile's onboard command is a power-on command, the controller at the receiving end, based on the missile system information specified in the power-on command (i.e., the corresponding missile system), controls the relay in the corresponding power transmission channel to close, thus enabling the corresponding power transmission channel to conduct and transmit power to the corresponding missile system, energizing it.

[0044] In one specific embodiment, the transmitting end further includes a controller and a power supply circuit. The power supply circuit converts the external DC current into the voltage and current required by the controller and the first wireless transceiver module, respectively, and transmits them to the controller and the first wireless transceiver module. Under the control of the controller, the first wireless transceiver module receives the onboard commands sent to the transmitting end by the launch control management module, and transmits the onboard commands to the corresponding receiving end via wireless communication. Further, the corresponding receiving end refers to the receiving end corresponding to the missile system specified in the onboard command information. For example, if the onboard command specifies missile system number 1, then the corresponding receiving end is the receiving end that controls missile system number 1.

[0045] In one specific embodiment, the receiving end further includes a controller and a connector. Under the control of the controller, the second wireless transceiver module of the receiving end receives onboard commands transmitted wirelessly from the first wireless transceiver module. The receiving end controls the corresponding missile system based on the onboard commands. When the onboard commands are missile communication test commands, missile self-test test commands, parameter configuration commands, or launch commands, the receiving end sends the corresponding commands to the corresponding missile system through the connector.

[0046] Optionally, the onboard commands can be power-on commands, missile communication test commands, missile self-test commands, parameter configuration commands, and launch commands. After the receiving end powers on the corresponding missile system according to the power-on command, it then performs pre-launch checks and launch control on the corresponding missile system according to the subsequent missile self-test commands, parameter configuration commands, and launch commands.

[0047] In one specific embodiment, please refer to Figure 3 The control device further includes a moving mechanism. The control execution module includes a transmitting end and multiple receiving ends. The moving mechanism receives control commands and moves the transmitting end to the corresponding receiving end based on the control commands.

[0048] Specifically, the mobile mechanism receives control instructions from the command and control system. These instructions include specific information about the receiver corresponding to the transmitter. The control instructions instruct the mobile mechanism to match the transmitter with the corresponding receiver, preparing for subsequent missile-borne commands launched based on the command and control system, and using the transmitter and the corresponding receiver to control the corresponding missile system.

[0049] The moving mechanism aligns the transmitter with a corresponding receiver among multiple receivers. This allows the system to control multiple missile launches by sequentially moving the transmitter to the appropriate receiver position according to control commands. For example, when launching missiles 1, 2, 3, and 4, each located in a different missile tube (corresponding to a different receiver), the moving mechanism can sequentially move the transmitter to the receiver corresponding to missile 1, missile 2, missile 3, and missile 4, completing the launch of missiles 1, 2, 3, and 4. This design further solves the problems of numerous, heavy, and space-consuming cables in multiple missile launch systems, reducing operational complexity and increasing automation.

[0050] In one specific embodiment, please continue to see Figure 3 The multiple receivers are located at the lower end of the missile box, which contains multiple missile tubes. Each receiver controls the missile system in one missile tube.

[0051] Optionally, a receiver is positioned corresponding to the location of the missile tube it controls. This arrangement allows for a shorter cable length between the receiver and the corresponding missile system, which is beneficial for the rational layout and utilization of space.

[0052] In one specific embodiment, the first coupling coil is located on the side of the transmitting end corresponding to the receiving end, and the second coupling coil is located on the side of the receiving end corresponding to the transmitting end.

[0053] Furthermore, the first coupling coil is located at the center of the side of the transmitting end corresponding to the receiving end, and the second coupling coil is located at the center of the side of the receiving end corresponding to the transmitting end.

[0054] Furthermore, both the first and second coupling coils are planar coupling coil structures. Optionally, the first coupling coil has a spiral shape from the center of the side of the transmitting end corresponding to the receiving end outwards, or it has multiple circles with gradually increasing radii from the center of the side of the transmitting end corresponding to the receiving end outwards. Optionally, the second coupling coil has a spiral shape from the center of the side of the receiving end corresponding to the transmitting end outwards, or it has multiple circles with gradually increasing radii from the center of the side of the receiving end corresponding to the transmitting end outwards. The number of turns, turn spacing, and other parameters of the first and second coupling coils can be designed according to actual requirements.

[0055] In one specific embodiment, the areas of the first coupling coil and the second coupling coil are equal, and when the first coupling coil is coupled with the second coupling coil of the corresponding receiving end, the corresponding areas of the two are greater than or equal to 70% of the area of ​​the first coupling coil.

[0056] In one specific embodiment, the distance between the transmitting end and the corresponding receiving end ranges from 5mm to 40mm. Optionally, the distance between the transmitting end and the corresponding receiving end is 20mm.

[0057] In one specific embodiment, the receiving end is further configured to receive onboard feedback generated by the missile system after performing corresponding operations according to onboard instructions, and transmit the onboard feedback to the sending end via wireless communication using the second transceiver module; the sending end is further configured to receive the onboard feedback and send the onboard feedback to the launch control management module; the launch control management module is configured to receive the onboard feedback and send the onboard feedback to the command and control system.

[0058] A specific embodiment of the present invention discloses a wireless transmission power control method. This method is used in a launch control device, which includes a launch control management module and a launch control execution module. The launch control execution module includes a transmitting end and at least one receiving end. The transmitting end includes a first coupling coil and a first wireless transceiver module, and the receiving end includes a second coupling coil and a second wireless transceiver module. The launch control method includes: the launch control management module receiving an onboard command and transmitting the onboard command to the transmitting end; the transmitting end receiving external current and transmitting electrical energy to the corresponding receiving end through the coupling effect of the first and second coupling coils; and transmitting the onboard command to the corresponding receiving end through wireless communication between the first and second transceiver modules; the receiving end controlling the corresponding missile system according to the onboard command.

[0059] Compared with existing technologies, this application uses the coupling effect of the first coupling coil at the transmitting end and the second coupling coil at the receiving end to transmit electrical energy to the receiving end. The onboard commands are transmitted to the corresponding receiving end through wireless communication between the first transceiver module at the transmitting end and the second transceiver module at the receiving end. The corresponding receiving end then controls the corresponding missile system. This technical solution reduces the weight and space occupied by a large number of cables, is more conducive to the rational layout of the launch control device and the missile system, reduces the maintenance difficulty of weapon equipment, reduces the complexity of personnel operation, and improves the degree of automation.

[0060] The specific implementation process of this embodiment can be found in the above-described device embodiment, and will not be repeated here. Since this embodiment is based on the same principle as the above-described device embodiment, this method also has the corresponding technical effects of the above-described device embodiment.

[0061] Those skilled in the art will understand that all or part of the processes of the methods described in the above embodiments can be implemented by a computer program instructing related hardware, and the program can be stored in a computer-readable storage medium. The computer-readable storage medium may be a disk, optical disk, read-only memory, or random access memory, etc.

[0062] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A wireless power transmission and control device, characterized in that, It includes a transmission control management module, a transmission control execution module, and a moving mechanism. The transmission control execution module includes a transmitting end and multiple receiving ends. The transmitting end includes a first coupling coil and a first wireless transceiver module. The receiving end includes a second coupling coil and a second wireless transceiver module. The launch control management module is used to receive the launch command and send the launch command to the sending end; The transmitting end is used to receive external current and transmit electrical energy to the corresponding receiving end through the coupling effect of the first coupling coil and the second coupling coil, and to transmit the launch command to the corresponding receiving end through wireless communication between the first wireless transceiver module and the second wireless transceiver module. The receiving end is used to control the corresponding missile system according to the onboard instructions. When launching multiple missiles, the moving mechanism moves the transmitting end sequentially to the position corresponding to the corresponding receiving end according to the control command, thereby realizing the control of the multiple missile system.

2. The launch control device according to claim 1, characterized in that, The transmitting end also includes an input end and an inverter circuit; The input terminal is connected to the inverter circuit and is used to receive external DC current. The inverter circuit is connected to the first coupling coil and is used to invert the external DC current to generate AC current. The first coupling coil transmits the alternating current to the second coupling coil based on the coupling effect between the alternating current and the second coupling coil.

3. The launch control device according to claim 2, characterized in that, The receiving end also includes a rectifier circuit and a relay; The rectifier circuit is connected to the second coupling coil and is used to receive the AC current transmitted by the second coupling coil and convert the AC current into DC current. The relay is connected to the rectifier circuit and is used to transmit the DC current to the corresponding missile system.

4. The launch control device according to claim 1, characterized in that, The multiple receivers are located at the lower end of the missile box, which contains multiple missile tubes. Each receiver controls the missile system in one missile tube.

5. The launch control device according to claim 1, characterized in that, The first coupling coil is located on the side of the transmitting end corresponding to the receiving end, and the second coupling coil is located on the side of the receiving end corresponding to the transmitting end.

6. The launch control device according to claim 5, characterized in that, The areas of the first coupling coil and the second coupling coil are equal. When the first coupling coil is coupled with the second coupling coil of the corresponding receiving end, the corresponding areas of the two are greater than or equal to 70% of the area of ​​the first coupling coil.

7. The launch control device according to claim 1, characterized in that, The distance between the transmitting end and the corresponding receiving end ranges from 5mm to 40mm.

8. The launch control device according to claim 1, characterized in that, The receiving end is also used to receive the onboard feedback generated by the missile system after performing corresponding operations according to the onboard command, and to transmit the onboard feedback to the sending end via wireless communication using the second wireless transceiver module; The transmitting end is also used to receive the onboard feedback and send the onboard feedback to the launch control management module; The launch control management module is used to receive the onboard feedback and send the onboard feedback to the command and control system.

9. A method for controlling wireless power transmission, characterized in that, This method is used in a transmission control device, which includes a transmission control management module, a transmission control execution module, and a moving mechanism. The transmission control execution module includes a transmitting end and multiple receiving ends. The transmitting end includes a first coupling coil and a first wireless transceiver module, and the receiving end includes a second coupling coil and a second wireless transceiver module. The emission control method includes: The launch control management module receives the launch command and sends the launch command to the sending end; The transmitting end receives external current and transmits electrical energy to the corresponding receiving end through the coupling effect of the first coupling coil and the second coupling coil. The transmitting end also transmits the launch command to the corresponding receiving end through wireless communication between the first wireless transceiver module and the second wireless transceiver module. The receiving end controls the corresponding missile system according to the onboard instructions; When launching multiple missiles, the moving mechanism moves the transmitting end sequentially to the position corresponding to the corresponding receiving end according to the control command, thereby realizing the control of the multiple missile system.

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