Aircraft wireless remote emission control system

Abstract

An aircraft wireless remote emission control system is divided into a remote control end device and an emission end device and can achieve wireless remote emission control over a plurality of aircrafts. A computer is controlled at a remote control end to send out a control instruction, the control instruction is transmitted to a transmitting end through a wireless data transmission module, and the transmitting end carries out power supply on-off control and logic address setting on aircraft equipment by means of an intermediate controller, so that transmitting control of an aircraft is realized. The wireless remote control system solves the limitation of a wired launch control device on the distance and the laying of a complex circuit. The device can meet the launching requirements of various aircrafts and is easy to operate and high in universality.

Description

Technical Field

[0001] The invention relates to an aircraft wireless remote launch control system, which is used for long-distance launch control. Background Art

[0002] The existing wired launch control device consists of a launch control box, a switching power supply, a bobbin, etc. A set of wired launch control devices can only control the ignition of one aircraft at a time. In addition, the switching power supply is large in size and not convenient for integrated installation, so the switching power supply is usually placed on the spot. In addition, in order to meet the aircraft power supply control method and power consumption requirements, the wired launch control device includes multiple switching power supplies and multiple sets of bobbins. The laying and storage of bobbins and launch control equipment requires a lot of time and human resources, affecting the on-site progress. When using the existing wired launch control device for launch control, the choice of launch position is greatly affected by the limitation of the bobbin length. Summary of the invention

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

[0004] The purpose of the present invention is achieved through the following technical solutions.

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

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

[0007] The remote control computer A2 is a control computer with an operating system installed. Control instructions are sent through the computer, and the control instructions are transparently transmitted to the transmitter through the data transmission module A3, and the instructions sent back by the transmitter can be received.

[0008] The remote control end data transmission module A3 includes a data transmission radio station 1, a data transmission radio station 2, a data transmission antenna 1 and a data transmission antenna 2. The data transmission radio station 1 is connected to the data transmission antenna 1, and the data transmission radio station 2 is connected to the data transmission antenna 2. The data transmission radio station 1 and the data transmission radio station 2 are redundantly designed, adopt the spread spectrum technology, work in different frequency bands at the same time, and the transmission power and transmission rate are adjustable in multiple levels.

[0009] The transmitting end AC power supply B1 provides a stable AC power supply for the transmitting end programmable switch power supply B2, and the capacity of the power supply needs to be able to meet the maximum power requirement before the aircraft is launched.

[0010] The transmitting end program-controlled switch power supply B2 is a dedicated program-controlled switch power supply, which has two output ports with different voltage levels. The first port provides working power to the data transmission module B3 and the intermediate controller B4, and the first port immediately outputs voltage when the input terminal of the program-controlled switch power supply B2 is connected to AC power; the second port provides DC power to the aircraft, and when the input terminal of the program-controlled switch power supply B2 is connected to AC power, the remote control computer A2 needs to issue an instruction to turn on the program-controlled switch power supply B2, and the second output port of the program-controlled switch power supply B2 can output voltage.

[0011] The transmitting end data transmission module B3 includes a data transmission radio station 3, a data transmission radio station 4, a data transmission antenna 3 and a data transmission antenna 4. The data transmission radio station 3 is connected to the data transmission antenna 3, and the data transmission radio station 4 is connected to the data transmission antenna 4. The data transmission radio station 3 and the data transmission radio station 4 are redundantly designed, using spread spectrum technology, and the transmission power and transmission rate are multi-level adjustable. The data transmission radio station 3 and the data transmission radio station 4 work simultaneously and in different frequency bands.

[0012] The digital transmission radio station 1 of the remote control end digital transmission module A3 is paired with the digital transmission radio station 3 of the transmitting end digital transmission module B3, and the communication parameters such as working frequency, channel, address, etc. are consistent; the digital transmission radio station 2 of the remote control end digital transmission module A3 is paired with the digital transmission radio station 4 of the transmitting end digital transmission module B3, and the communication parameters such as working frequency, channel, address, etc. are consistent.

[0013] The transmitting end intermediate controller B4 is a network relay with communication function. The number and capacity of contacts can meet the control requirements of two aircraft, and can collect the aircraft departure signal and transmit it back to the remote control computer A2. After the remote control computer A2 collects the signal, it determines that the aircraft launch is successful.

[0014] In one embodiment of the present invention, the control computer A2 can be a laptop or an industrial computer. If an industrial computer is selected, the control computer A2 and 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 use bus communication to transmit data. The command issued by the control computer A2 is transparently transmitted to the transmitting end data transmission module B3 through the data transmission module A3.

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

[0017] In one embodiment of the present invention, the remote control end program-controlled switch power supply B2, the data transmission module B3, and the intermediate controller B4 are integrated and installed in the launch control box B0. All components are designed with a wide temperature range and are suitable for various extreme temperatures at the launch site of the aircraft. The program-controlled switch power supply B2 is designed with a small volume and large capacity to save installation space. The launch control box is designed as a standard aluminum shell chassis, which is light and easy to carry. The components in the box can be laid flat, which is conducive to heat dissipation, and the launch control box B0 can be integrated into a standard cabinet.

[0018] In one embodiment of the present invention, 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 electric shock, short circuit, overload, etc. The control box B0 is also designed with a power indicator light and a test port, which is convenient for operators to timely grasp the operating status of the control system.

[0019] In one embodiment of the present invention, the launch control box B0 is connected to the aircraft C1 through a launch control cable B5. The length of the launch control cable B5 is designed to be as short as possible under the premise of ensuring the safe launch distance to reduce the voltage drop. The conductor of the launch control cable B5 is made of high temperature resistant material, and the cable jacket is made of a fireproof casing to prevent tail flame ablation and realize the reuse of the launch control cable.

[0020] In one embodiment of the present invention, the transmission and control box B0 reserves a wired communication interface for external use, so that communication can still be carried out in a wired manner in extreme circumstances where wireless communication cannot be achieved.

[0021] In one embodiment of the present invention, the launch control box B0 reserves a communication expansion interface, through which multiple launch control boxes can be connected in parallel to achieve the function of continuous launch of multiple aircraft.

[0022] In one embodiment of the present invention, the launch control system is designed with dedicated launch control software, which is applicable to conventional operating systems and is designed completely in accordance with the launch control process sequence, thereby effectively preventing misoperation.

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

[0024] (1) When the present invention is used alone, it can realize automatic and continuous launch control of two aircrafts on the same control terminal;

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

[0026] (3) The wireless communication device of the present invention adopts redundant configuration and works in different frequency bands, thereby improving anti-interference performance and the transmission success rate;

[0027] (4) The serial port of the transmitting end data transmission module is directly connected to the intermediate relay, and the aircraft launch is completed through logical address control, without the need for microcontroller or computer control. It is simple, reliable and widely applicable.

[0028] (5) The present invention is flexible in use, reduces the laying and storage of scattered equipment and cables, and facilitates flexible layout of the test site. The present invention can be used alone on site or integrated into a standard cabinet for use;

[0029] (6) The present invention can collect the status information of the transmitting end signal at the remote control end and display it in real time, and the control process is intuitive and easy to operate. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a schematic diagram of the wireless remote launch control system. DETAILED DESCRIPTION

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

[0032] A wireless remote launch control system for aircraft, which realizes power-on and power-off control of the aircraft and RT address setting through long-distance wireless communication control, thereby realizing the launch of the aircraft. The wireless launch control system can realize the launch control of multiple aircraft through communication expansion.

[0033] The technical solution of the present invention is: the remote control end includes an AC power supply A1, a control computer A2, and a data transmission module A3, and the transmitting end includes an AC power supply B1 and a transmitting control box B0; the transmitting control box B0 integrates a programmable switch power supply B2, a data transmission module B3, and an intermediate controller B4; the transmitting end also includes a transmitting control cable B5, and a control instruction is issued by the control computer A2 at the remote control end, and the instruction is transparently transmitted to the transmitting end through the data transmission module A3 and the data transmission module B3, and the programmable switch power supply B2 and the intermediate controller B4 of the transmitting end perform corresponding actions according to different instructions, thereby realizing the power on and off control of the aircraft and the RT address setting, thereby realizing the launch of the aircraft.

[0034] The wireless remote transmission control system is based on the wired transmission control device, and uses a two-way data transmission module instead of cable transmission. The wireless remote transmission control system includes a remote control end and a transmitter end device. The remote control end device includes an AC power supply A1, a control computer A2, and a data transmission module A3; the transmitter end device includes an AC power supply B1, a programmable switch power supply B2, a data transmission module B3, an intermediate controller B4, and a transmission control cable B5. Figure 1 shown.

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

[0036] The control computer A2 at the remote end is installed with the control software of the control system. The control instructions are sent through the computer, and the control instructions are transparently transmitted to the transmitter through the data transmission module, and the instructions sent back by the transmitter can be received. The control computer A2 can choose to use an industrial laptop or an industrial computer. If an industrial computer is selected, the control computer A2 and the data transmission module A3 can be integrated into the ground control station.

[0037] The remote control end data transmission module A3 includes a data transmission radio station 1, a data transmission radio station 2, a data transmission antenna 1 and a data transmission antenna 2. The data transmission radio station 1 is connected to the data transmission antenna 1, and the data transmission radio station 2 is connected to the data transmission antenna 2. The data transmission radio station 1 and the data transmission radio station 2 are redundantly designed, using spread spectrum technology, and working in different frequency bands at the same time. The transmission power and transmission rate are multi-level adjustable. The data transmission module A3 and the control computer A2 use bus communication to transmit data.

[0038] The transmitting end AC power supply B1 provides a stable AC working power supply for the transmitting end programmable switch power supply B2. The capacity of the power supply can meet the maximum power requirement of the aircraft before launch.

[0039] The transmitting end programmable switch power supply B2 adopts a small volume and large capacity design, which can greatly save installation space and reduce the box volume. The programmable switch power supply B2 has two output ports with different voltage levels. The first route provides working power to the transmitting end data transmission module B3 and the intermediate controller B4. When the input end of the programmable switch power supply B2 is connected to AC power, the first route immediately has voltage output; the second route provides DC power to the aircraft. When the input end of the programmable switch power supply B2 is connected to AC power, the remote control computer A2 needs to issue an instruction to turn on the programmable switch power supply A2. Only then can the second output port of the programmable switch power supply A2 output voltage and transmit the output voltage value back to the remote control computer A2.

[0040] The transmitting end data transmission module B3 includes data transmission radio station 3, data transmission radio station 4, data transmission antenna 3 and data transmission antenna 4. Among them, data transmission radio station 3 is connected to data transmission antenna 3, and data transmission radio station 4 is connected to data transmission antenna 4. Data transmission radio station 3 and data transmission radio station 4 are redundant designs, using spread spectrum technology, working in different frequency bands at the same time, and the transmission power and transmission rate are multi-level adjustable.

[0041] The intermediate controller B4 at the transmitting end is a network relay with communication function. The number and capacity of contacts can meet the control requirements of two aircrafts, and can collect the departure signal of the aircraft and transmit it back to the remote control computer A2. After the remote control computer A2 collects the signal, it determines that the launch is successful.

[0042] The transmitting end program-controlled switch power supply B2, data transmission module B3, and intermediate controller B4 are integrated and installed in the launch control box B0. The launch 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 electric shock, short circuit, overload and other faults. The launch control box B0 is also designed with a power indicator light and a test port, which is convenient for operators to grasp the operating status of the launch control system in time. The equipment in the launch control box B0 adopts a wide temperature design, which is suitable for various extreme temperatures at the launch site of the aircraft. The launch control box B0 is designed as a standard aluminum shell chassis and can be integrated into a standard cabinet.

[0043] The launch control cable B5 is a connecting cable between the launch control box B0 and the aircraft. The length of the launch control cable B5 is shortened as much as possible under the premise of ensuring that the safe launch distance is met, so as to reduce the voltage drop.

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

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

[0046] The wireless remote launch and control system is designed with a bus expansion port, through which multiple intermediate controllers can be connected in parallel, realizing the function of controlling the launch of multiple aircraft with one remote control terminal.

[0047] The dispatch control system is designed with dedicated dispatch control software, which is suitable for conventional operating systems. The dispatch control software interface is simple and easy to understand, and is designed completely in accordance with the dispatch 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. The control computer A2 and the data transmission module use bus communication to transmit data. The command issued by the control computer A2 is transparently transmitted to the transmitting end data transmission module B3 through the data transmission module A3. The transmitting end data transmission module B3 transmits commands to the transmitting end program-controlled switch power supply B2 and the intermediate controller B4 through bus communication. The transmitting end data transmission module B3 sends the received control command to the program-controlled switch power supply B2 and the intermediate controller B4. The program-controlled switch power supply B2 and the intermediate controller B4 execute their respective control commands by identifying the command address, thereby completing the launch control of the aircraft.

[0049] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

[0050] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. An aircraft wireless remote launch control system, characterized in that: It includes remote control end and transmitting end equipment; the remote control end equipment includes AC power supply A1, control computer A2, and data transmission module A3, and the transmitting end equipment includes AC power supply B1 and transmitting control box B0; the transmitting control box B0 integrates programmable switch power supply B2, data transmission module B3, and intermediate controller B4; The remote control end AC power supply A1 provides a stable AC power supply for 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. The control instructions are sent through the computer, and the control instructions are transparently transmitted to the transmitter through the data transmission radio. The remote control computer A2 can also receive the instructions sent back by the transmitter. The remote control end data transmission module A3 includes a data transmission radio station 1, a data transmission radio station 2, a data transmission antenna 1 and a data transmission antenna 2; wherein the data transmission radio station 1 is connected to the data transmission antenna 1, and the data transmission radio station 2 is connected to the data transmission antenna 2; The remote control end data transmission module A3 data transmission radio station 1 and data transmission radio station 2 are redundantly designed. Data transmission radio station 1 and data transmission radio station 2 work simultaneously and in different frequency bands. The transmitter AC power supply B1 provides a stable AC working voltage for the transmitter's programmable switch power supply. The power supply capacity must be able to meet the maximum power required before the aircraft is launched. The transmitting end program-controlled switch power supply B2 is a dedicated program-controlled switch power supply, which has two output ports with different voltage levels; the first port provides working power to the data transmission module B3 and the intermediate controller B4, and the first port immediately outputs voltage when the switch power supply is connected to AC power; the second port provides DC power to the aircraft, and when the switch power supply input terminal is connected to AC power, the remote control computer A2 needs to issue an instruction to turn on the switch power supply, and the second output port of the switch power supply can output voltage; The transmitting end data transmission module B3 includes a data transmission radio station three, a data transmission radio station four, a data transmission antenna three and a data transmission antenna four; Wherein, digital transmission radio station 3 is connected to digital transmission antenna 3, and digital transmission radio station 4 is connected to digital transmission antenna 4; The transmitting end data transmission module B3 data transmission radio station 3 and data transmission radio station 4 are designed as redundant. Data transmission radio station 3 and data transmission radio station 4 work simultaneously and in different frequency bands. The remote control end data transmission module A3 data transmission radio station 1 is paired with the transmitter end data transmission module B3 data transmission radio station 3; the remote control end data transmission module A3 data transmission radio station 2 is paired with the transmitter end data transmission module B3 data transmission radio station 4; The intermediate controller B4 at the transmitting end is a network relay with communication function. The number and capacity of contacts can meet the control requirements of two aircrafts, and can collect the departure signal of the aircraft and transmit it back to the remote control computer A2. After the remote control computer A2 collects the signal, it determines that the launch is successful.

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

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

4. The aircraft wireless remote launch control system according to claim 1, characterized in that: The control computer A2 and the data transmission module A3 use bus communication to transmit data. The command issued by the control computer A2 is transparently transmitted to the transmitting end data transmission module B3 through the data transmission module A3.

5. The aircraft wireless remote launch control system according to claim 1, characterized in that: The transmitting end data transmission module B3 and the remote control end programmable switch power supply B2 and the intermediate controller B4 transmit instructions through bus communication. The data transmission module B3 sends the received control instructions to the programmable switch power supply B2 and the intermediate controller B4. The programmable switch power supply B2 and the intermediate controller B4 execute their respective control instructions by identifying the instruction address.

6. The aircraft wireless remote launch 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 case of electric shock, short circuit, overload and other faults.

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

8. The aircraft wireless remote launch control system according to claim 1, characterized in that: The control box B0 reserves wired communication interface and communication expansion interface for external use.

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

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

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