Aircraft wireless remote launch control system

Abstract

The application discloses a wireless remote launching control system for aircrafts, which is divided into a remote control end device and a launching end device, and can realize wireless remote launching control for multiple aircrafts. A control computer at the remote control end issues a control instruction, which is transmitted to the launching end through a wireless data transmission module. The launching end controls the power on-off of the aircraft device and sets a logic address with the help of an intermediate controller, so as to realize launching control of the aircraft. The wireless remote control system solves the distance limitation of the wired launching control device and the laying of complex circuits. The device can meet the launching requirements of various aircrafts, and is simple to operate and high in universality.

Description

Technical Field

[0001] This invention relates to a wireless remote launch control system for aircraft, used for long-distance launch control. Background Technology

[0002] Existing wired launch control systems consist of a launch control box, a switching power supply, and spools. A single wired launch control system can only control the ignition of one aircraft at a time. Furthermore, the switching power supply is bulky and inconvenient for integrated installation, typically requiring on-site placement. Additionally, to meet the power supply control methods and capacity requirements of the aircraft, the wired launch control system includes multiple switching power supplies and multiple sets of spools. The laying and storage of the spools and launch control equipment requires significant time and manpower, impacting on-site progress. When using existing wired launch control systems for launch control, the selection of the launch location is greatly limited by the length of the spools. Summary of the Invention

[0003] The technical problem to be solved by this invention is to overcome the shortcomings of existing transmission control systems, such as short transmission distance, large site restrictions on the layout of transmission control devices, and complex configuration of the transmitter control system, and to solve the problem of long-distance transmission control.

[0004] The objective of this invention is achieved through the following technical solutions.

[0005] A wireless remote transmission and control system for an aircraft includes a remote control terminal and a transmitter terminal. The remote control terminal includes an AC power supply A1, a control computer A2, and a data transmission module A3. The transmitter terminal includes an AC power supply B1 and a transmitter control box B0; the transmitter control box B0 integrates a programmable switching power supply B2, the data transmission module B3, and an intermediate controller B4. Figure 1 As shown.

[0006] The AC power supply A1 of the remote control terminal provides a stable AC power supply for the remote control computer A2 and the data transmission module A3.

[0007] The remote control terminal control computer A2 is a control computer with an operating system installed. Control commands are issued through this computer, and the control commands are transmitted to the transmitter through the data transmission module A3. It can also receive commands transmitted back from the transmitter.

[0008] The remote control terminal data transmission module A3 includes data transmission radio 1, data transmission radio 2, data transmission antenna 1, and data transmission antenna 2. Data transmission radio 1 is connected to data transmission antenna 1, and data transmission radio 2 is connected to data transmission antenna 2. Data transmission radio 1 and data transmission radio 2 are redundantly designed, employ spread spectrum technology, and operate simultaneously in different frequency bands. The transmission power and transmission rate are adjustable in multiple levels.

[0009] The AC power supply B1 at the transmitting end provides a stable AC power supply to the programmable switching power supply B2 at the transmitting end, and the capacity of the power supply must be able to meet the maximum power requirements of the aircraft before launch.

[0010] The transmitter-side programmable switching power supply B2 is a dedicated programmable switching power supply with two output ports of different voltage levels. The first port provides operating power to the data transmission module B3 and the intermediate controller B4. When AC power is connected to the input terminal of the programmable switching power supply B2, the first port immediately outputs voltage. The second port provides DC power to the aircraft. When AC power is connected to the input terminal of the programmable switching power supply B2, a command to turn on the programmable switching power supply B2 must be issued by the remote control computer A2 before the second output port of the programmable switching power supply B2 can output voltage.

[0011] The transmitting data transmission module B3 includes data transmission radio three, data transmission radio four, data transmission antenna three, and data transmission antenna four. Data transmission radio three is connected to data transmission antenna three, and data transmission radio four is connected to data transmission antenna four. Data transmission radio three and four are redundantly designed, employing spread spectrum technology, with multi-level adjustable transmission power and transmission rate. Data transmission radio three and four operate simultaneously in different frequency bands.

[0012] The data transmission radio 1 of the remote control data transmission module A3 is paired with the data transmission radio 3 of the transmitter data transmission module B3, and the communication parameters such as operating frequency, channel, and address are consistent; the data transmission radio 2 of the remote control data transmission module A3 is paired with the data transmission radio 4 of the transmitter data transmission module B3, and the communication parameters such as operating frequency, channel, and address are consistent.

[0013] The intermediate controller B4 of the transmitter is a network relay with communication function. The number and capacity of contacts can meet the control requirements of two aircraft. It can also collect the departure signal of the aircraft and send it back to the remote control computer A2. After collecting the signal, the remote control computer A2 determines that the aircraft has been successfully launched.

[0014] In one embodiment of the present invention, the control computer A2 can be either a laptop computer or an industrial PC. If an industrial PC is selected, the control computer A2, the data transmission module A3, and its accessories can be integrated into the ground control station.

[0015] In one embodiment of the present invention, the control software of the wireless remote transmission control system is installed in the control computer A2, and the control computer A2 and the data transmission module A3 communicate via a bus to transmit data. Commands issued by the control computer A2 are transmitted through the data transmission module A3 to the transmitting end data transmission module B3.

[0016] In one embodiment of the present invention, the transmitting end data transmission module B3 transmits instructions to the remote control end programmable switching power supply B2 and intermediate controller B4 via bus communication. The data transmission module B3 sends the received control instructions to the programmable switching power supply B2 and intermediate controller B4. The programmable switching power supply B2 and intermediate controller B4 execute the control instructions belonging to their respective by identifying the instruction address.

[0017] In one embodiment of the present invention, the remote control terminal programmable switching power supply B2, data transmission module B3, and intermediate controller B4 are integrated and installed within the launch control box B0. All components are designed for wide temperature ranges, suitable for various extreme temperatures at the aircraft launch site. The programmable switching power supply B2 features a compact yet high-capacity design, saving installation space. The launch control box is designed as a standard aluminum casing, making it lightweight and portable. The components inside the box can be laid flat, facilitating heat dissipation, and the launch control box B0 can be integrated into a standard cabinet.

[0018] In one embodiment of the present invention, the generator control box B0 is equipped with an air switch with leakage protection, which can quickly and automatically cut off the power in the event of faults such as electric shock, short circuit, or overload. The generator control box B0 is also designed with a power indicator light and a test port, so that operators can promptly monitor the operating status of the generator control system.

[0019] In one embodiment of the present invention, the launch control box B0 and the aircraft C1 are connected by a launch control cable B5. The length of the launch control cable B5 is designed to be as short as possible while ensuring a safe launch distance, so as to reduce voltage drop. The conductors of the launch control cable B5 are made of high-temperature resistant material, and the cable sheath is made of fireproof tubing to prevent exhaust flame erosion and to enable the reuse of the launch control cable.

[0020] In one embodiment of the present invention, the control box B0 has a wired communication interface reserved for external communication, so that communication can still be carried out via wired means in extreme cases where wireless communication is not possible.

[0021] In one embodiment of the present invention, the launch control box B0 has a reserved communication expansion interface. Through expansion, multiple launch control boxes can be connected in parallel to realize the function of continuous launch of multiple aircraft.

[0022] In one embodiment of the present invention, the control system is designed with dedicated control software that is suitable for conventional operating systems and is designed in complete accordance with the control process sequence, which can effectively prevent misoperation.

[0023] Compared with the prior art, the present invention has the following advantages:

[0024] (1) When used as a single unit, this invention can realize automatic continuous launch control of two aircraft on the same control terminal;

[0025] (2) When the present invention is used in an extended manner, it can realize the automatic continuous launch control of multiple aircraft on the same control terminal;

[0026] (3) The wireless communication device of the present invention adopts a redundant configuration and operates in different frequency bands, which improves the anti-interference performance and improves the transmission success rate.

[0027] (4) The serial port of the transmitter data transmission module is directly connected to the intermediate relay. The launch of the aircraft is completed through logic address control. No microcontroller or computer control is required. It is simple, reliable and widely applicable.

[0028] (5) The present invention is flexible in its use, reducing the laying and storage of scattered equipment and cables, and making it easy to arrange the test site flexibly. The present invention can be used alone on the spot or integrated into a standard cabinet.

[0029] (6) The present invention can collect and display the status information of the transmitter signal at the remote control end in real time, and the control process is intuitive and easy to operate. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the components of a wireless remote transmission and control system. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0032] A wireless remote transmission and control system for aircraft enables power-on / off control and RT address setting of the aircraft via long-distance wireless communication, thereby facilitating aircraft launch. The wireless control system can be extended through communication to control the launch of multiple aircraft.

[0033] The technical solution of this invention is as follows: The remote control end includes an AC power supply A1, a control computer A2, and a data transmission module A3; the transmitting end includes an AC power supply B1 and a transmitter control box B0; the transmitter control box B0 integrates a programmable switching power supply B2, a data transmission module B3, and an intermediate controller B4; the transmitting end also includes a transmitter control cable B5. The remote control end sends control commands through the control computer A2, which are then transmitted to the transmitting end via the data transmission module A3 and the data transmission module B3. The programmable switching power supply B2 and the intermediate controller B4 at the transmitting end perform corresponding actions according to different commands, thereby realizing the power-on / off control of the aircraft and the RT address setting, thus realizing the launch of the aircraft.

[0034] The wireless remote transmission and control system is based on a wired transmission and control device, replacing cable transmission with a two-way data transmission module. The wireless remote transmission and control system includes remote control and transmitting equipment. The remote control equipment includes an AC power supply A1, a control computer A2, and a data transmission module A3; the transmitting equipment includes an AC power supply B1, a programmable switching power supply B2, a data transmission module B3, an intermediate controller B4, and a transmission and control cable B5, etc. Figure 1 As shown.

[0035] The remote control AC power supply A1 provides a stable AC power supply to the remote control computer A2 and the data transmission module A3.

[0036] The remote control computer A2 is equipped with the control software for the transmission and control system. Control commands are issued through this computer and transmitted to the transmitting end via the data transmission module. It can also receive commands transmitted back from the transmitting end. Control computer A2 can be either an industrial laptop or an industrial PC. If an industrial PC is chosen, control computer A2 and data transmission module A3 can be integrated into the ground control station.

[0037] The remote control data transmission module A3 includes data transmission radio 1, data transmission radio 2, data transmission antenna 1, and data transmission antenna 2. Data transmission radio 1 is connected to data transmission antenna 1, and data transmission radio 2 is connected to data transmission antenna 2. Data transmission radio 1 and data transmission radio 2 are redundantly designed, employing spread spectrum technology and operating simultaneously in different frequency bands. Their transmission power and transmission rate are multi-level adjustable. Data transmission module A3 communicates with the control computer A2 via a bus communication method.

[0038] The transmitter AC power supply B1 provides a stable AC operating power supply to the transmitter's programmable switching power supply B2, and the power supply capacity can meet the maximum power requirements of the aircraft before launch.

[0039] The transmitter-side programmable switching power supply B2 features a compact yet high-capacity design, significantly saving installation space and reducing the overall size of the enclosure. The programmable switching power supply B2 has two output ports with different voltage levels. The first port provides power to the transmitter data transmission module B3 and the intermediate controller B4; when AC power is connected to the input of the programmable switching power supply B2, the first port immediately outputs voltage. The second port provides DC power to the aircraft; when AC power is connected to the input of the programmable switching power supply B2, a command to turn on the programmable switching power supply A2 is required from the remote control computer A2 for the second output port of the programmable switching power supply A2 to output voltage and transmit the voltage value back to the remote control computer A2.

[0040] The transmitter data transmission module B3 includes data transmission radio three, data transmission radio four, data transmission antenna three, and data transmission antenna four. Data transmission radio three is connected to data transmission antenna three, and data transmission radio four is connected to data transmission antenna four. Data transmission radio three and data transmission radio four are redundantly designed, employ spread spectrum technology, and operate simultaneously in different frequency bands, with multi-level adjustable transmission power and transmission rate.

[0041] The intermediate controller B4 at the transmitter is a network relay with communication function. The number and capacity of its contacts can meet the control requirements of two aircraft. It can also collect the departure signal of the aircraft and send it back to the remote control computer A2. After collecting the signal, the remote control computer A2 determines that the launch was successful.

[0042] The transmitter's programmable switching power supply B2, data transmission module B3, and intermediate controller B4 are integrated into the launch control box B0. The launch control box B0 is equipped with a leakage protection circuit breaker, which can quickly and automatically cut off power in the event of electric shock, short circuit, overload, or other faults. The launch control box B0 also features power indicator lights and test ports, allowing operators to monitor the operational status of the launch control system. All equipment within the launch control box B0 is designed for wide temperature ranges, suitable for various extreme temperatures at the spacecraft launch site. The launch control box B0 is housed in a standard aluminum chassis and can be integrated into a standard server rack.

[0043] The launch control cable B5 is the connecting cable between the launch control box B0 and the aircraft. The length of the launch control cable B5 should be shortened as much as possible while ensuring a safe launch distance to reduce voltage drop.

[0044] The data transmission radio 1 of the remote control data transmission module A3 is paired with the data transmission radio 3 of the transmitter data transmission module B3, and the communication parameters such as operating frequency, channel, and address are consistent; the data transmission radio 2 of the remote control data transmission module A3 is paired with the data transmission radio 4 of the transmitter data transmission module B3, and the communication parameters such as operating frequency, channel, and address are consistent.

[0045] The controller box B0 has a reserved wired communication interface, so that communication can still be carried out via wired means in extreme cases where wireless communication is not possible.

[0046] The wireless remote control system is designed with a bus expansion port, which can be used to connect multiple intermediate controllers in parallel, enabling the use of a single remote control terminal to control the launch of multiple aircraft.

[0047] The control system is designed with dedicated control software that is compatible with conventional operating systems. The control software interface is simple and easy to understand and is designed in complete accordance with the control process sequence, which can effectively prevent misoperation.

[0048] The control software of the launch control system is installed in the remote control computer A2. Data transmission between control computer A2 and the data transmission module is achieved via bus communication. Commands issued by control computer A2 are transmitted through data transmission module A3 to the transmitter data transmission module B3. Transmitter data transmission module B3, transmitter programmable power supply B2, and intermediate controller B4 transmit commands via bus communication. Transmitter data transmission module B3 sends received control commands to programmable power supply B2 and intermediate controller B4. Programmable power supply B2 and intermediate controller B4 identify the command address and execute the corresponding control command, thereby completing the launch control of the aircraft.

[0049] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0050] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A wireless remote transmission control system for aircraft, characterized in that, It includes remote control and transmitting equipment; the remote control equipment includes AC power supply A1, control computer A2, and data transmission module A3; the transmitting equipment includes AC power supply B1 and transmitting control box B0; the transmitting control box B0 integrates programmable switching power supply B2, data transmission module B3, and intermediate controller B4. The remote control AC power supply A1 provides a stable AC power supply to the remote control computer A2 and the data transmission module A3. The remote control computer A2 is a control computer with an operating system installed. Control commands are issued through this computer, and the control commands are transmitted to the transmitter via the data transmission radio. It can also receive commands transmitted back from the transmitter. The remote control terminal data transmission module A3 includes data transmission radio 1, data transmission radio 2, data transmission antenna 1 and data transmission antenna 2; wherein data transmission radio 1 is connected to data transmission antenna 1, and data transmission radio 2 is connected to data transmission antenna 2. The remote control terminal data transmission module A3 data transmission radio 1 and data transmission radio 2 are redundantly designed, and data transmission radio 1 and data transmission radio 2 work simultaneously in different frequency bands. The transmitter AC power supply B1 provides a stable AC operating voltage for the transmitter's programmable switching power supply. The capacity of the power supply must be able to meet the maximum power requirements of the aircraft before launch. The transmitter-side programmable switching power supply B2 is a dedicated programmable switching power supply with two output ports of different voltage levels. The first port provides working power to the data transmission module B3 and the intermediate controller B4. When the switching power supply is powered by AC, the first port immediately outputs voltage. The second port provides DC power to the aircraft. When the input terminal of the switching power supply is connected to AC power, the second output port of the switching power supply can only output voltage after the remote control computer A2 issues a command to turn on the switching power supply. Transmitter data transmission module B3 includes data transmission radio three, data transmission radio four, data transmission antenna three, and data transmission antenna four; Data transmission radio 3 is connected to data transmission antenna 3, and data transmission radio 4 is connected to data transmission antenna 4. The transmitter data transmission module B3 and data transmission radio three and four are redundantly designed, and data transmission radio three and data transmission radio four work simultaneously in different frequency bands. The remote control data transmission module A3 data transmission radio 1 is paired with the transmitter data transmission module B3 data transmission radio 3 for use; the remote control data transmission module A3 data transmission radio 2 is paired with the transmitter data transmission module B3 data transmission radio 4 for use. The intermediate controller B4 at the transmitter is a network relay with communication function. The number and capacity of its contacts can meet the control requirements of two aircraft. It can also collect the departure signal of the aircraft and send it back to the remote control computer A2. After collecting the signal, the remote control computer A2 determines that the launch was successful.

2. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The specifications and models of data transmission antenna one and data transmission antenna two can be selected according to the control distance.

3. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The specifications and models of data transmission antenna three and data transmission antenna four can be selected according to the control distance.

4. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The control computer A2 and the data transmission module A3 communicate via a bus. Commands issued by the control computer A2 are transmitted through the data transmission module A3 to the transmitting end data transmission module B3.

5. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The transmitting end data transmission module B3 transmits commands to the remote control end programmable switching power supply B2 and intermediate controller B4 via bus communication. The data transmission module B3 sends the received control commands to the programmable switching power supply B2 and intermediate controller B4. The programmable switching power supply B2 and intermediate controller B4 execute the control commands belonging to their respective commands by identifying the command address.

6. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The control box B0 is equipped with an air switch with leakage protection, which can quickly and automatically cut off the power in the event of faults such as electric shock, short circuit, or overload.

7. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The launch control box B0 is connected to the aircraft C1 via launch control cable B5. The length of launch control cable B5 is designed to be as short as possible while ensuring a safe launch distance, so as to reduce voltage drop.

8. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The controller box B0 has reserved wired communication interface and communication expansion interface for external use.

9. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The remote control terminal data transmission module A3 and data transmission radio 1 and data transmission radio 2 adopt spread spectrum technology, and the transmission power and transmission rate are adjustable in multiple levels.

10. The aircraft wireless remote transmission control system according to claim 1, characterized in that, The transmitter data transmission module B3 and data transmission radios three and four adopt spread spectrum technology, and the transmission power and transmission rate are adjustable in multiple levels.

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