CN118144984A - Backup flight control method, device and system suitable for civil branch passenger plane - Google Patents
Backup flight control method, device and system suitable for civil branch passenger plane Download PDFInfo
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- CN118144984A CN118144984A CN202410098515.3A CN202410098515A CN118144984A CN 118144984 A CN118144984 A CN 118144984A CN 202410098515 A CN202410098515 A CN 202410098515A CN 118144984 A CN118144984 A CN 118144984A
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 245
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000004364 calculation method Methods 0.000 claims description 14
- 238000012545 processing Methods 0.000 claims description 8
- 238000011022 operating instruction Methods 0.000 claims description 6
- 238000012423 maintenance Methods 0.000 claims description 4
- 238000012544 monitoring process Methods 0.000 claims description 3
- 230000003862 health status Effects 0.000 claims 1
- 238000012360 testing method Methods 0.000 claims 1
- 238000001514 detection method Methods 0.000 description 9
- 230000008569 process Effects 0.000 description 6
- 238000013461 design Methods 0.000 description 4
- 230000006870 function Effects 0.000 description 4
- 230000000007 visual effect Effects 0.000 description 3
- 238000004590 computer program Methods 0.000 description 2
- 230000000994 depressogenic effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
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- 239000003381 stabilizer Substances 0.000 description 1
Classifications
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B9/00—Safety arrangements
- G05B9/02—Safety arrangements electric
- G05B9/03—Safety arrangements electric with multiple-channel loop, i.e. redundant control systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
- B64C13/505—Transmitting means with power amplification using electrical energy having duplication or stand-by provisions
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Abstract
The invention provides a backup flight control method, a device and a system suitable for civil branch airliners, which belong to the technical field of flight control, wherein a backup flight control computer receives a switch on-off signal of a backup flight control system pre-position switch in a cockpit in real time, and when the pre-position switch is in a pre-position state, the backup flight control computer is connected with a power supply of an independent storage battery of the backup control system; the backup flight control computer is started and receives the control instruction in real time to obtain an actuator control instruction; the backup flight control computer receives a switch on-off signal from the enabling switch in real time and rapidly outputs an actuator control instruction to the actuator when the enabling switch is in an enabling state; the actuator controls the control surface based on the actuator control instruction to control the aircraft to fly. According to the invention, when the pilot monitors that the main flight control system cannot safely control the aircraft, the pilot can quickly switch to the backup flight control system, so that stable control of the aircraft attitude is realized.
Description
Technical Field
The invention relates to the technical field of flight control, in particular to a backup flight control method, device and system suitable for civil branch passenger plane.
Background
Flight control systems are complex and critical systems on modern civil aircraft, critical to aircraft safety. In the existing fly-by-wire flight control system, the individual machine type also has a backup flight control system which is independent of the main flight control system and controls part of control surfaces of the aircraft to maintain the attitude of the aircraft. For example, in a flight control system of an aircraft, a backup flight control mode of controlling a spoiler and a horizontal stabilizer is adopted, but it is difficult for the aircraft to ensure that the Minimum Acceptable Control (MAC) requirement is met, and safe landing of the aircraft cannot be ensured. In an aircraft flight control system, a backup flight control method for providing electric energy by adopting a hydraulic system causes the equipment to be too complex, and increases the number of the aircraft equipment.
In addition, a backup flight control system is proposed in the related art, and the backup control system starts to provide control for the right backup controller after the failure of the main controller, but always sends a control command, the control terminal of the aircraft control surface actuator selects and judges signals, and the backup controller is activated by mistake under the condition that the main controller is still effective, so that the normal control of the main controller on the actuator is interfered. In the related art, a backup flight control system is also proposed, but a core component backup control computer of the backup control system is too complex and is in a cold backup state, and when the backup control computer needs to be started quickly in an emergency, the equipment cannot be connected quickly and effectively.
Disclosure of Invention
In order to solve the problem that the main controller is activated by mistake under the condition that the main controller is still effective in the related art, which leads to the interference of the main controller to the normal control of an actuator, the invention provides a backup flight control method, a device and a system suitable for civil branch line airliners, which are simple and reliable, adopt a hot backup state and prevent the false activation, and the technical scheme is as follows:
In a first aspect, there is provided a back-up flight control system for a residential branch line passenger aircraft, comprising: the control system comprises a cockpit instruction sensor, a backup flight control system switch in the cockpit, a backup control system independent storage battery, a backup flight control computer, an actuator and a control surface, wherein the backup flight control computer is connected with the cockpit instruction sensor, the backup flight control system switch in the cockpit, the backup control system independent storage battery and the actuator, the backup control system independent storage battery provides power for the backup flight control computer,
A switch of a backup flight control system in the cockpit sends a switch on-off signal for indicating the state of the switch to a backup flight control computer; the switch of the backup flight control system in the cockpit comprises a pre-position switch and an enabling switch, and the pre-position switch indicates the backup flight control computer to work when being in a pre-position state; the enabling switch is in an enabling state and indicates the backup flight control computer to output an actuator control instruction;
the backup flight control computer receives a manipulation instruction from the cockpit instruction sensor;
the backup flight control computer sends an actuator control instruction to the actuator;
the actuator controls the control surface based on an actuator control instruction sent by the backup control computer.
Further, the backup flight control computer is connected with the main flight control equipment, and the backup flight control computer also sends a status signal for indicating the operation of the backup flight control system to the main flight control equipment so that a driver can acquire the operation status of the backup flight control system in real time, and the backup flight control computer does not receive the signal of the main flight control equipment, so that the backup flight control computer can work independently as much as possible and is prevented from being influenced by the main flight control equipment.
Further, the actuator also transmits back a monitoring signal for indicating the working state of the control surface to the backup flight control computer, so that a driver can conveniently acquire the working state of the control surface in real time.
Optionally, the backup flight control computer comprises: the system comprises a power demodulation module, an instruction receiving and transmitting module and a control law calculation module;
The power demodulation module is used for processing the current provided by the independent storage battery of the backup control system, converting the current into a secondary power supply required by the operation of the power demodulation module, and simultaneously converting part of the current into a power supply which can normally work by the cockpit command sensor and a power supply for driving the actuator to work; the backup flight control computer supplies power to the cockpit command sensor and the actuator, so that the complexity of system design can be reduced;
The command receiving and transmitting module is used for processing the control command acquired by the cockpit command sensor, converting the control command into data which can be used by the control law calculation module, and simultaneously processing the actuator control command calculated by the control law calculation module and converting the actuator control command into a signal which can be identified by the actuator;
And the control law calculation module is used for calculating the control law of the instruction from the instruction receiving and transmitting module to obtain an actuator control instruction, and outputting the actuator control instruction to the actuator through the instruction receiving and transmitting module. The control law design is simple and visual enough, only the full stroke of the actuator control instruction corresponds to the full stroke of the cockpit instruction sensor, and no feedback is introduced.
Wherein the main flight control device includes: the computer is controlled by the fly-away computer,
The flight control computer is used for receiving a state signal which is sent by the backup flight control computer and used for indicating the backup flight control system, so that a driver can acquire the working state of the backup flight control system in real time.
In a second aspect, there is provided a method of back-up flight control for a civil branch line passenger aircraft for use in the system of any of the first aspects, the method comprising:
The backup flight control computer receives a switch on-off signal of a pre-position switch of the backup flight control system in the cockpit in real time, judges whether the pre-position switch is in a pre-position state, and the backup control system independently provides a power supply for the backup flight control computer through a storage battery;
When the pre-position switch is in a pre-position state, the backup flight control computer is connected to a power supply of an independent storage battery of the backup control system;
the backup flight control computer is started, and receives an operating instruction from the cockpit instruction sensor in real time to obtain an actuator control instruction;
The backup flight control computer receives a switch on-off signal of an enabling switch of the backup flight control system in the cockpit in real time and judges whether the enabling switch is in an enabling state;
When the enabling switch is in an enabling state, the backup flight control computer rapidly outputs an actuator control instruction to the actuator in real time;
the actuator controls the control surface based on the actuator control instruction to control the aircraft to fly.
Compared with cold backup, the invention can quickly start the backup flight control system under the condition that the main flight control equipment cannot normally control the flight, namely under the emergency condition, thereby realizing the purpose of quickly and stably controlling the attitude of the airplane.
Further, after the backup flight control computer is started, the backup flight control computer performs self-checking, and the self-health state is uploaded to a maintenance display interface of the driver through the main flight control system, so that the driver can conveniently acquire the self-checking condition of the backup flight control computer.
When the whole power supply is started, the aircraft power supply supplies power to the independent storage battery of the backup control system. Regardless of the state of the backup flight control system, the aircraft power supply supplies power to the backup control system independent storage battery, and the step runs through the whole process. Therefore, the independent storage battery of the backup control system is always supplied with power, the quality of the independent storage battery can be ensured, meanwhile, the backup control computer can be supplied with power at any time, and the backup control computer can work at any time.
In a third aspect, there is provided a back-up flight control apparatus for a civil branch line passenger aircraft, comprising:
The judging module is used for receiving the switch on-off signal of the pre-position switch of the backup flight control system in the cockpit in real time and judging whether the pre-position switch is in a pre-position state or not;
the access module is used for accessing the power supply of the independent storage battery of the backup control system when the pre-position switch is in a pre-position state;
The acquisition module is used for starting and receiving the control instruction from the cockpit instruction sensor in real time to obtain an actuator control instruction;
the judging module is also used for receiving the switch on-off signal of the enabling switch of the backup flight control system in the cockpit in real time and judging whether the enabling switch is in an enabling state or not;
and the output module is used for rapidly outputting the control instruction of the actuator to the actuator in real time when the enabling switch is in an enabling state so as to facilitate the control surface of the actuator to be controlled.
In a fourth aspect, there is provided a back-up flight control apparatus for a civil branch line passenger aircraft, comprising:
A processor;
A memory for storing the processor-executable instructions;
wherein the processor is configured to:
receiving a switch on-off signal of a pre-position switch of a backup flight control system in the cockpit in real time, and judging whether the pre-position switch is in a pre-position state;
When the pre-position switch is in a pre-position state, the power supply of the independent storage battery of the backup control system is connected;
starting and receiving an operating instruction from a cockpit instruction sensor in real time to obtain an actuator control instruction;
Receiving a switch on-off signal of an enabling switch of a backup flight control system in the cockpit in real time and judging whether the enabling switch is in an enabling state;
When the enabling switch is in an enabling state, an actuator control instruction is quickly output to the actuator in real time, so that the control surface of the actuator is controlled by the actuator.
In a fifth aspect, there is provided a computer-readable storage medium having stored thereon a computer program which, when executed by a processor, performs the functions performed by the modules of the third aspect.
The invention realizes a backup flight control system completely independent of the main flight control system, when a pilot monitors that the main flight control system cannot safely control the aircraft, the pilot can quickly switch to the backup flight control system to realize stable control on the attitude of the aircraft, and then the pilot can select to restart the main flight control computer continuously in the air, and emergency landing can be realized through the backup flight control system, so that the flight safety is ensured.
Drawings
FIG. 1 is a schematic diagram of a backup control system architecture according to an embodiment of the present invention;
Fig. 2 is a schematic diagram of a manipulation flow for switching from a primary flight control system to a backup flight control system according to an embodiment of the present invention.
Detailed Description
The invention is described in further detail below with reference to specific embodiments and figures.
An embodiment of the present invention provides a backup flight control system for a residential branch line airliner, as shown in fig. 1, comprising:
The cockpit command sensor 1, the switch 2 of the backup flight control system in the cockpit, the independent storage battery 3 of the backup control system, the backup flight control computer 4, the actuator and the control surface 5 connected with the actuator,
The cockpit command sensor 1 is connected with the backup flight control computer 4 through a hard wire, the backup flight control computer 4 provides power for the cockpit command sensor 1, and the cockpit command sensor 1 sends an angular displacement sensor RVDT signal or a linear displacement sensor LVDT signal to the backup flight control computer 4.
The switch 2 of the backup flight control system in the cockpit is connected with the backup flight control computer 4 through a hard wire, and sends a switch on-off signal for indicating the switch state to the backup flight control computer 4.
The back-up flight control system switch 2 in the cockpit comprises a pre-position switch and an enabling switch. The pre-position switch has two states, namely a pre-position state and a non-pre-position state, and the pre-position state is used for indicating the backup flight control computer to work. The enabling switch has two states, namely an enabling state and a non-enabling state, and the enabling state is used for indicating the backup flight control computer to output an actuator control command. The backup flight control computer 4 outputs an actuator control instruction to the actuator when detecting that the pre-position switch is in a pre-position state and the enabling switch is in an enabling state; otherwise, the output of the actuator control command is prohibited. Wherein the override switch and the enable switch may be depressed by the driver. The override switch is typically always in the "override state" and the enable switch is depressed when the pilot determines that the primary flight control device is not properly controlling the flight.
In one embodiment, the cockpit may be provided with one or more pre-position switches, one or more enable switches.
The cockpit command sensor 1 and the backup flight control system switch 2 in the cockpit are mutually independent and are only spatially positioned in the cockpit, and no signal crosslinking exists.
The independent storage battery 3 of the backup control system is connected with the backup flight control computer 4 through a power connection wire to provide needed power for the backup flight control computer 4.
The backup flight control computer 4 is connected with the actuators through a bus such as an actuator bus ADB, the backup flight control computer 4 sends actuator control instructions to the actuators, and the actuators transmit back internal monitoring signals for indicating the working state of the control surface to the backup flight control computer 4.
The backup flight control computer 4 is connected with the main flight control device 6 through a bus, such as an intra-system bus SIB, and the backup flight control computer 4 sends a status signal for indicating the operation of the backup flight control system to the main flight control device 6, does not receive any signal of the main flight control device 6, and ensures that the backup flight control computer 4 works independently as much as possible and is not influenced by the main flight control device 6.
The backup flight control computer 4 also sends a status signal to the flight control computer of the primary flight control device 6 for indicating the operation of the backup flight control system, so that the pilot obtains the operation status of the backup flight control system in real time.
Specifically, the backup flight control computer 4 includes: the system comprises a power demodulation module, an instruction receiving and transmitting module and a control law calculation module;
the power demodulation module is used for processing the current provided by the independent storage battery 3 of the backup control system, converting the current into a secondary power supply required by the operation of the power demodulation module, and converting part of the current into a power supply which can normally work by the cockpit command sensor 1 and a power supply for driving the operation of the actuator.
The command receiving and sending module is used for processing the control command acquired by the cockpit command sensor 1 and converting the control command into data which can be used by the control law calculation module. And meanwhile, the actuator control instruction calculated by the control law calculation module is processed and converted into a signal which can be identified by the actuator.
And the control law calculation module is used for calculating the control law of the instruction from the instruction receiving and transmitting module to obtain an actuator control instruction, and outputting the actuator control instruction to the actuator through the instruction receiving and transmitting module. The control law design is simple and visual enough, only the full stroke of the actuator control instruction corresponds to the full stroke of the cockpit instruction sensor, and no feedback is introduced.
The main flight control device 6 includes: a flight control computer and an actuator controller.
The flight control computer collects the control instruction of the cockpit instruction sensor 1 and the instruction of external equipment, and sends the control instruction to the actuator controller, and the control surface is controlled by the actuator controller. The function of the main flight control device 6 is the same as that of the related art, and will not be described again.
In the embodiment of the invention, the flight control computer is also used for receiving the state signal which is sent by the backup flight control computer 4 and used for indicating the backup flight control system, so that a driver can acquire the working state of the backup flight control system in real time.
An embodiment of the present invention provides a backup flight control method suitable for a civil branch line airliner, as shown in fig. 2, including the steps of:
Step 1, the driver judges whether the pre-position switch is required to be set in a pre-position state or a non-pre-position state, and whether the enabling switch is required to be set in an enabling state or a non-enabling state.
The pre-position switch is set to be in a pre-position state when defaulting, and when a driver judges that the backup flight control system is not required to be accessed at all or perceives that an actuator control instruction of the backup flight control system is accessed to a control surface abnormally in the flight process, the backup flight control computer can be forcibly closed by shifting the pre-position switch to be in a non-pre-position state.
The enabling switch is set to be in a non-enabling state when defaults, and when a driver judges that an actuator control instruction of the flight control system needs to be backed up is accessed to the control surface, the enabling switch can be set to be in the enabling state.
And step 2, receiving the discrete quantity (switch on-off signal) of a pre-position switch of the backup flight control system in the cockpit in real time by the backup flight control computer.
Step 3, the backup flight control computer judges whether the pre-position switch is in a pre-position state or not based on the discrete quantity (switch on-off signal) of the pre-position switch; step 5 is executed when the preset switch is in the preset state, and step 2 is returned when the preset switch is in the non-preset state.
And 4, when the whole power supply is started, the aircraft power supply is required to supply power to the independent storage battery of the backup control system no matter what state the backup flight control system is in, and the step penetrates through the whole method flow. In the embodiment of the invention, the independent storage battery of the backup control system is always supplied with power, so that the quality of the independent storage battery can be ensured, and meanwhile, the backup control computer can be ensured to be supplied with power at any time, and can work at any time.
And step 5, the backup flight control computer is connected with a power supply of an independent storage battery of the backup control system, and then step 6 is performed.
And 6, starting the backup flight control computer, performing self-checking, and rapidly checking the functions of clock synchronization, algebraic operation, logic operation, storage and the like of the chip. And uploading the self health state to a maintenance display interface of the driver through the main flight control system after the self-checking is finished. Step 7 is then entered.
And step 7, receiving an operation instruction from a cockpit instruction sensor in real time by the backup flight control computer, calculating a control law in the FPGA of the backup flight control computer to obtain an actuator control instruction capable of meeting basic operation, and entering the step 8 without outputting the actuator control instruction.
And 8, receiving the discrete quantity (switch on-off signal) of the enabling switch of the backup flight control system in the cockpit in real time by the backup flight control computer, and entering a step 9 for judgment.
And 9, the backup flight control computer judges whether the enabling switch is in an enabling state or not in real time based on the discrete quantity (switch on-off signal) of the enabling switch. When the enable switch is in the "enable state", step 10 is performed; when the enable switch is not in the "enable state", the process returns to step 8.
And step 10, the backup flight control computer rapidly outputs the self-calculated actuator control instruction to the actuator in real time.
And 11, controlling the control surface by the actuator through the actuator control instruction of the backup flight control computer received in real time so as to rapidly control the movement of the aircraft.
Compared with cold backup, the invention can quickly start the backup flight control system under the condition that the main flight control equipment cannot normally control the flight, namely under the emergency condition, thereby realizing the purpose of quickly and stably controlling the attitude of the airplane.
In one embodiment, before the operation of the route begins, the driver/ground crew is powered on the ground through the whole machine, and as the pre-position switch of the backup flight control system in the cockpit is always in a pre-position state, the power supply charges the independent storage battery of the backup system at the moment, the independent storage battery of the backup control system supplies power to the backup flight control computer, the backup flight control computer is started, and then the power-on self-detection is performed. After the self-detection is completed, the self-detection result is transmitted through a flight control computer in the main flight control equipment and displayed on a cockpit screen (a driver maintenance display interface), and is in an available state when the self-detection result is normal and in an unavailable state when the self-detection result is abnormal. The backup flight control computer then enters a "standby state".
In the standby state, the backup flight control computer receives the control instruction information of the driver from the cockpit, calculates the control instruction of the control surface position through a control law calculation module written in the complex electronic hardware FPGA in advance, and does not output the control instruction. In the control law calculation module, the control law design is simple and visual enough, only the full stroke of the control command of the cockpit corresponds to the full stroke of the control surface, and no feedback is introduced.
In the whole flight process, if the main flight control system is not found to obviously work abnormally or the condition that the aircraft cannot be safely operated does not occur, the backup flight control system enabling switch in the cockpit defaults to be in a non-enabling state, and the backup flight control computer is in a standby state until the flight is finished. The pilot can manually place the flight pre-position switch in a non-pre-position state, and the backup flight control computer is powered off. The driver can also be independent of the pre-position switch of the backup flight control system in the cockpit, and when the electric quantity of the independent storage battery of the backup control system is consumed, the backup flight control computer is automatically powered off.
In one embodiment, before the course operation begins, the driver/ground crew powers up on the ground via the all-purpose machine, and the driver/ground crew observes that the backup flight control system pre-position switch in the cockpit is in a "non-pre-position state" according to a manual procedure, or that the backup flight control computer is not activated via the cockpit display. At the moment, a pre-position switch of a backup flight control system in the cockpit is manually placed in a pre-position state, an on-board power supply charges an independent storage battery of the backup control system, the independent storage battery of the backup control system supplies power to a backup flight control computer, and the backup flight control computer is started and then is electrified for self-detection. And after the self-detection is finished, transmitting a self-detection result through a flight control computer and displaying the self-detection result on a screen of the cockpit. The backup flight control computer then enters a "standby state".
In the whole flight process, the pilot finds out that the main flight control equipment obviously works abnormally, or the situation that the aircraft cannot be safely operated occurs. The driver quickly and manually sets the enabling switch of the backup flight control system in the cockpit to be in an enabling state, and the backup flight control computer can quickly output a control instruction to the actuator to control the control surface because the control instruction of the control surface is always calculated by the backup flight control computer, so that the control of the aircraft is quickly taken over, and meanwhile, the screen of the cockpit is displayed to be in a working state.
After the pilot stabilizes the aircraft attitude through the backup flight control system, the flight control computer and the actuator controller of the main flight control equipment can be restarted. When the flight control computer and the actuator controller of the main flight control equipment can work normally, the enabling switch of the backup flight control system in the cockpit is set to be in a non-enabling state, and at the moment, the flight control computer of the main flight control equipment continues to work, so that the aircraft can safely land.
When the flight control computer and the actuator controller of the main flight control equipment are restarted for a plurality of times, the flight control computer and the actuator controller of the main flight control equipment can not work normally, and the backup flight control system can be adopted to continue flying until safe landing.
When the whole aircraft is powered down in the flight process, a driver can set a backup flight control system enabling switch in the cockpit to be in an enabling state, at the moment, the backup flight control computer is provided with a backup control system independent storage battery for supplying power, and the backup control system independent storage battery is provided with sufficient electric quantity, so that the aircraft can stand until the aircraft is immediately lowered.
In one embodiment, during the flight, the driver observes the cockpit screen to find that the backup flight control system is abnormally connected, and the backup flight control system pre-position switch in the cockpit can be manually set to be in a non-pre-position state, so that the backup flight control computer is powered off and normal flight is not influenced.
An embodiment of the present invention also provides a backup flight control apparatus adapted for a civil branch line airliner for backing up a flight control computer, the apparatus comprising:
The judging module is used for receiving the switch on-off signal of the pre-position switch of the backup flight control system in the cockpit in real time and judging whether the pre-position switch is in a pre-position state or not;
the access module is used for accessing the power supply of the independent storage battery of the backup control system when the pre-position switch is in a pre-position state;
The acquisition module is used for starting and receiving the control instruction from the cockpit instruction sensor in real time to obtain an actuator control instruction;
the judging module is also used for receiving the switch on-off signal of the enabling switch of the backup flight control system in the cockpit in real time and judging whether the enabling switch is in an enabling state or not;
and the output module is used for rapidly outputting the control instruction of the actuator to the actuator in real time when the enabling switch is in an enabling state so as to facilitate the control surface of the actuator to be controlled.
An embodiment of the present invention also provides a backup flight control apparatus adapted for a civil branch line airliner for backing up a flight control computer, the apparatus comprising:
A processor;
A memory for storing the processor-executable instructions;
wherein the processor is configured to:
receiving a switch on-off signal of a pre-position switch of a backup flight control system in the cockpit in real time, and judging whether the pre-position switch is in a pre-position state;
When the pre-position switch is in a pre-position state, the power supply of the independent storage battery of the backup control system is connected;
starting and receiving an operating instruction from a cockpit instruction sensor in real time to obtain an actuator control instruction;
Receiving a switch on-off signal of an enabling switch of a backup flight control system in the cockpit in real time and judging whether the enabling switch is in an enabling state;
When the enabling switch is in an enabling state, an actuator control instruction is quickly output to the actuator in real time so that the control surface of the control surface is controlled by the actuator
An embodiment of the present invention further provides a computer-readable storage medium, on which a computer program is stored, where the program, when executed by a processor, implements functions implemented by a judging module, an accessing module, an acquiring module, and an outputting module in a backup flight control device suitable for a civil branch line passenger aircraft.
An embodiment of the present invention also provides a backup flight control apparatus adapted for a civil branch line airliner for backing up a flight control computer, the apparatus comprising:
A processor;
A memory for storing the processor-executable instructions;
wherein the processor is configured to:
receiving a switch on-off signal of a pre-position switch of a backup flight control system in the cockpit in real time, and judging whether the pre-position switch is in a pre-position state;
When the pre-position switch is in a pre-position state, the power supply of the independent storage battery of the backup control system is connected;
starting and receiving an operating instruction from a cockpit instruction sensor in real time to obtain an actuator control instruction;
Receiving a switch on-off signal of an enabling switch of a backup flight control system in the cockpit in real time and judging whether the enabling switch is in an enabling state;
When the enabling switch is in an enabling state, an actuator control instruction is quickly output to the actuator in real time, so that the control surface of the actuator is controlled by the actuator.
The foregoing has outlined rather broadly the more detailed description of the invention in order that the detailed description thereof that follows may be better understood, and in order that the present invention may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. In addition, the invention is not fully described in the conventional technology.
Claims (10)
1. A backup flight control system for a residential branch line passenger aircraft, comprising: the control system comprises a cockpit instruction sensor, a backup flight control system switch in the cockpit, a backup control system independent storage battery, a backup flight control computer, an actuator and a control surface, wherein the backup flight control computer is connected with the cockpit instruction sensor, the backup flight control system switch in the cockpit, the backup control system independent storage battery and the actuator, the backup control system independent storage battery provides power for the backup flight control computer,
A switch of a backup flight control system in the cockpit sends a switch on-off signal for indicating the state of the switch to a backup flight control computer; the switch of the backup flight control system in the cockpit comprises a pre-position switch and an enabling switch, and the pre-position switch indicates the backup flight control computer to work when being in a pre-position state; the enabling switch is in an enabling state and indicates the backup flight control computer to output an actuator control instruction; the backup flight control computer receives a manipulation instruction from the cockpit instruction sensor; the backup flight control computer sends an actuator control instruction to the actuator; the actuator controls the control surface based on an actuator control instruction sent by the backup control computer.
2. The system of claim 1, wherein the backup flight control computer is coupled to the primary flight control device, the backup flight control computer further transmitting a status signal to the primary flight control device indicating operation of the backup flight control system.
3. The system of claim 1, wherein the actuator further transmits back to the backup flight control computer a monitoring signal indicative of the operating condition of the control surface.
4. The system of claim 1, wherein the backup flight control computer comprises: the system comprises a power demodulation module, an instruction receiving and transmitting module and a control law calculation module;
The power demodulation module is used for processing the current provided by the independent storage battery of the backup control system, converting the current into a secondary power supply required by the operation of the power demodulation module, and simultaneously converting part of the current into a power supply which can normally work by the cockpit command sensor and a power supply for driving the actuator to work;
The command receiving and transmitting module is used for processing the control command acquired by the cockpit command sensor, converting the control command into data which can be used by the control law calculation module, and simultaneously processing the actuator control command calculated by the control law calculation module and converting the actuator control command into a signal which can be identified by the actuator;
And the control law calculation module is used for calculating the control law of the instruction from the instruction receiving and transmitting module to obtain an actuator control instruction, and outputting the actuator control instruction to the actuator through the instruction receiving and transmitting module.
5. The system of claim 1, wherein the primary flight control device comprises: the computer is controlled by the fly-away computer,
The flight control computer is used for receiving a state signal which is sent by the backup flight control computer and used for indicating the backup flight control system.
6. A method of backup flight control for a civil branch line airliner, for use in the system of any one of claims 1 to 5, the method comprising:
The backup flight control computer receives a switch on-off signal of a pre-position switch of the backup flight control system in the cockpit in real time, judges whether the pre-position switch is in a pre-position state, and the backup control system independently provides a power supply for the backup flight control computer through a storage battery;
When the pre-position switch is in a pre-position state, the backup flight control computer is connected to a power supply of an independent storage battery of the backup control system;
the backup flight control computer is started, and receives an operating instruction from the cockpit instruction sensor in real time to obtain an actuator control instruction;
The backup flight control computer receives a switch on-off signal of an enabling switch of the backup flight control system in the cockpit in real time and judges whether the enabling switch is in an enabling state;
When the enabling switch is in an enabling state, the backup flight control computer rapidly outputs an actuator control instruction to the actuator in real time;
the actuator controls the control surface based on the actuator control instruction to control the aircraft to fly.
7. The method of claim 6, wherein after the backup flight control computer is started, the backup flight control computer performs a self-test and uploads its health status to the pilot maintenance display interface via the primary flight control system.
8. The method of claim 6, wherein the aircraft power supply supplies power to the backup control system independent battery when the full power source is started.
9. A backup flight control apparatus for a commercial branch line passenger aircraft, comprising:
The judging module is used for receiving the switch on-off signal of the pre-position switch of the backup flight control system in the cockpit in real time and judging whether the pre-position switch is in a pre-position state or not;
the access module is used for accessing the power supply of the independent storage battery of the backup control system when the pre-position switch is in a pre-position state;
The acquisition module is used for starting and receiving the control instruction from the cockpit instruction sensor in real time to obtain an actuator control instruction;
the judging module is also used for receiving the switch on-off signal of the enabling switch of the backup flight control system in the cockpit in real time and judging whether the enabling switch is in an enabling state or not;
and the output module is used for rapidly outputting the control instruction of the actuator to the actuator in real time when the enabling switch is in an enabling state so as to facilitate the control surface of the actuator to be controlled.
10. A backup flight control apparatus for a commercial branch line passenger aircraft, comprising:
A processor;
A memory for storing the processor-executable instructions;
wherein the processor is configured to:
receiving a switch on-off signal of a pre-position switch of a backup flight control system in the cockpit in real time, and judging whether the pre-position switch is in a pre-position state;
When the pre-position switch is in a pre-position state, the power supply of the independent storage battery of the backup control system is connected;
starting and receiving an operating instruction from a cockpit instruction sensor in real time to obtain an actuator control instruction;
Receiving a switch on-off signal of an enabling switch of a backup flight control system in the cockpit in real time and judging whether the enabling switch is in an enabling state;
When the enabling switch is in an enabling state, an actuator control instruction is quickly output to the actuator in real time, so that the control surface of the actuator is controlled by the actuator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410098515.3A CN118144984A (en) | 2024-01-24 | 2024-01-24 | Backup flight control method, device and system suitable for civil branch passenger plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410098515.3A CN118144984A (en) | 2024-01-24 | 2024-01-24 | Backup flight control method, device and system suitable for civil branch passenger plane |
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| Publication Number | Publication Date |
|---|---|
| CN118144984A true CN118144984A (en) | 2024-06-07 |
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| CN202410098515.3A Pending CN118144984A (en) | 2024-01-24 | 2024-01-24 | Backup flight control method, device and system suitable for civil branch passenger plane |
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| Country | Link |
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| CN (1) | CN118144984A (en) |
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- 2024-01-24 CN CN202410098515.3A patent/CN118144984A/en active Pending
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