CN117519265A - Automatic flight control system and method for vertical track angle of airplane - Google Patents
Automatic flight control system and method for vertical track angle of airplane Download PDFInfo
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- CN117519265A CN117519265A CN202311515772.4A CN202311515772A CN117519265A CN 117519265 A CN117519265 A CN 117519265A CN 202311515772 A CN202311515772 A CN 202311515772A CN 117519265 A CN117519265 A CN 117519265A
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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 133
- 238000000034 method Methods 0.000 title claims abstract description 22
- 230000006641 stabilisation Effects 0.000 claims description 3
- 238000011105 stabilization Methods 0.000 claims description 3
- 238000004132 cross linking Methods 0.000 description 4
- 230000009194 climbing Effects 0.000 description 2
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Abstract
The invention discloses an automatic flight control system and method for an aircraft vertical track angle. The flight control computer is used for receiving the expected track inclination angle value, the track inclination angle modal entering signal and the actuating mechanism state signal; calculating the minimum track inclination angle of each navigation segment and a control instruction; outputting track inclination modal state quantity, control instructions, minimum track inclination of each navigation section, predicted arrival points and current track inclination signals; judging the mode entering condition, running the track dip angle mode control law, and automatically switching to a high interception control law; the automatic flight control board is used for setting a desired track inclination angle value, outputting a track inclination angle modal entering signal, and receiving a track inclination angle modal state quantity and a minimum track inclination angle of each flight segment; the expected track inclination angle value is set by referring to the minimum track inclination angle of each navigation section; and the executing mechanism is used for receiving the control instruction, driving the control surface to deflect and outputting the state signal of the executing mechanism. The invention simplifies the operation procedure of the existing automatic flight control system.
Description
Technical Field
The invention belongs to the technical field of automatic flight control of aviation technology, and relates to an automatic flight control system and method for an aircraft vertical track angle.
Background
When an aircraft flies along a route, the aircraft often needs to fly at a fixed altitude through a specific waypoint, and the aircraft executes a flight plan of 'A land, B land and C land', as shown in fig. 1, the waypoint information comprises longitude and latitude coordinates and the altitude information of the waypoint.
An ideal aircraft vertical trajectory, regardless of the earth's curvature, is a collection of line segments that point to the projection of the next waypoint at the next altitude, with the projection of the starting waypoint at the starting altitude as an endpoint. To realize such a vertical trajectory, the direction of the aircraft speed needs to be controlled to be always kept on the trajectory, however, the vertical trajectory is difficult to accurately control in actual flight due to factors such as real-time changes of the aircraft airspeed, the climbing/falling performance characteristics of the aircraft, the external atmosphere environment and the like. The existing automatic flight control system mostly adopts pilots to manually plan the aircraft height changing process according to the distance information of the waypoints and combining the flight experience and the aircraft characteristics, manually bind proper expected vertical speed/target height, timely and actively switch on and enter a vertical speed or height preselected mode of an autopilot, and indirectly realize the control of the vertical flight path of the aircraft through the vertical speed or height preselected longitudinal control mode functions and the like. Therefore, in the control process of the existing automatic flight control system, the setting of the system function modes is different from the actual use scene, a great deal of manual intervention work is still required for a pilot in actual flight, navigation parameters are manually calculated, proper control modes are selected according to conditions, and the like, and a great deal of effort is still required for the pilot to control and monitor the system. The existing system is not high in automation and intelligent level, and the functional mode setting needs to be comprehensively optimized further so as to simplify the operation flow of the system and further reduce the burden of pilots.
Disclosure of Invention
The invention aims to provide an automatic flight control system and method for an aircraft vertical track angle. The invention overcomes the defects of the existing automatic flight control system and simplifies the operation procedure of the existing automatic flight control system.
The technical proposal is that. An automatic flight control system for an aircraft vertical track angle comprises a flight control computer, an automatic flight control board and an executing mechanism;
the flight control computer is used for receiving the expected track inclination angle value, the track inclination angle modal entering signal and the actuating mechanism state signal; calculating the minimum track inclination angle of each navigation segment and a control instruction; outputting track inclination modal state quantity, control instructions, minimum track inclination of each navigation section, predicted arrival points and current track inclination signals; judging the mode entering condition, running the track dip angle mode control law, and automatically switching to a high interception control law;
the automatic flight control board is used for setting a desired track inclination angle value, outputting a track inclination angle modal entering signal, and receiving a track inclination angle modal state quantity and a minimum track inclination angle of each flight segment; the expected track inclination angle value is set by referring to the minimum track inclination angle of each navigation section;
and the executing mechanism is used for receiving the control instruction, driving the control surface to deflect and outputting the state signal of the executing mechanism.
In the automatic flight control system for the vertical track angle of the airplane, the minimum track dip angle settlement process of each flight section is as follows: and the flight control computer calculates the distance and the height difference of the waypoints according to the waypoint information, and then calculates the minimum track inclination angle of each navigation section.
In the automatic flight control system for the vertical track angle of the airplane, the calculation formula of the track inclination angle by taking the climbing of the airplane as positive is as follows:
wherein D is the distance between the waypoints, and DeltaH is the altitude difference between the waypoints.
In the aircraft vertical track angle automatic flight control system, the settlement process of the control instruction is as follows: the flight control computer calculates the current track inclination angle signal in real time according to the aircraft sky-direction speed signal and the ground speed signal, calculates the track inclination angle deviation by combining the expected track inclination angle value, and then operates the track inclination angle modal control law by combining the aircraft real-time state information and the actuator state signal fed back by the actuator to calculate the control instruction.
In the automatic flight control system for the vertical track angle of the airplane, the automatic flight control board is also used for displaying the expected track inclination angle value.
In the automatic flight control system for the vertical track angle of the airplane, the automatic flight control board is also provided with the mode button with the indicator lamp, and the automatic flight control board lights the indicator lamp after receiving the modal state quantity of the track inclination angle so as to ensure that the pilot confirms that the mode has entered.
A control method of an aircraft vertical track angle automatic flight control system as described above, comprising the steps of:
step 1: the flight control computer calculates the minimum track dip angle of each navigation section according to the navigation path point information;
step 2: the flight control computer sends the calculated minimum track inclination angle of each flight segment to an automatic flight control board for display, and the flight control board is used for reference when setting the expected track inclination angle;
step 3: setting an expected track inclination angle value through an automatic flight control board, and sending the expected track inclination angle value to a flight control computer by the automatic flight control board;
step 4: after receiving the expected track inclination angle value sent by the automatic flight control board, the flight control computer calculates and predicts the arrival point by combining with the altitude difference information of the waypoint;
step 5: pressing a mode button on the automatic flight control board to generate a track dip angle mode entering signal, sending the signal to the flight control computer, and after judging that the mode entering condition is met, the flight control computer operates the track dip angle mode control law and sends the track dip angle mode state quantity to the automatic flight control board, and the automatic flight control board lights an indicator lamp after receiving the track dip angle mode state quantity for a pilot to confirm that the mode has entered;
step 6: the flight control computer calculates the current track inclination angle signal in real time according to the aircraft sky-direction speed signal and the ground speed signal, calculates the track inclination angle deviation by combining the expected track inclination angle value sent by the automatic flight control board, operates the track inclination angle modal control law by combining the aircraft real-time state information sent by the sensor and the actuator state signal fed back by the actuator, and sends a calculation control instruction to the actuator.
The control method of the aircraft vertical track angle automatic flight control system further comprises the following step 7: the actuating mechanism acts after receiving a control instruction sent by the flight control computer, drives the control surface to deflect to generate aerodynamic force, and the aircraft changes the attitude of the aircraft under the action of the aerodynamic force, so that the real-time track inclination angle value of the aircraft is changed.
The control method of the aircraft vertical track angle automatic flight control system further comprises the following step 8: the flight control computer automatically switches to a height interception control law when the real-time height is close to the preselected height by combining the preselected height signal sent by the automatic flight control board through the real-time height signal of the aircraft sent by the sensor, and sends a control instruction to the executing mechanism to gradually level the aircraft, so that the function of automatic interception and stabilization at the preselected height is realized.
Advantageous effects
The invention discloses an automatic flight control system for an aircraft vertical track angle, which overcomes the defects that the existing automatic flight control system has different function modes and actual use scenes, a pilot still needs a large amount of manual intervention work in actual flight, and occupies a large amount of energy control and monitoring systems of the pilot, and the existing system has insufficient automation and intelligent level. In addition, an automatic flight control system capable of automatically controlling the aircraft to fly according to the preset vertical track is provided, the operation program of the existing automatic flight control system is simplified, and the burden of a pilot is further reduced.
After the pilot finishes setting the route point parameters, the system can automatically calculate the minimum track inclination angle of each flight segment and display the minimum track inclination angle through the cockpit display equipment, so that the pilot can conveniently and subsequently operate the system, the pilot refers to the minimum track inclination angle calculated by the system, the expected track inclination angle value is set in the automatic flight control board, the flight control computer can calculate the predicted arrival point in real time in the setting process, and display the predicted arrival point through the cockpit display equipment, so that the pilot can know the modal control effect in advance, after the pilot presses a button on the automatic flight control board to enter the mode, the system can automatically control the aircraft to fly according to the expected track inclination angle value, the automatic flight function of the aircraft vertical track angle is realized, when the aircraft flies to the preselected height, the preselected height can be automatically intercepted and maintained, the whole process is easy to operate, and the information display is clear.
Drawings
FIG. 1 is a schematic illustration of a flight plan;
FIG. 2 is a schematic diagram of the composition of the present system;
fig. 3 is a schematic diagram of track pitch definition.
Detailed Description
The invention relates to an automatic flight control system for an aircraft vertical track angle, which is described in detail with reference to the accompanying drawings:
example 1. An aircraft vertical track angle automatic flight control system, as shown in figures 1-3, comprises a flight control computer 1, an automatic flight control board 2 and an actuating mechanism 3.
The flight control computer is a core device of the system, is crosslinked with external navigation equipment and receives waypoint information sent by the navigation equipment; cross-linking with an external sensor, and receiving real-time altitude signals, sky-direction speed signals, ground speed signals and real-time state information of the aircraft sent by the sensor; cross-linking with the automatic flight control board, receiving expected track inclination angle value and modal entering signal sent by the automatic flight control board, and providing track inclination angle modal state quantity for the automatic flight control board; cross-linking with the executing mechanism, receiving the executing mechanism state signal sent by the executing mechanism, and providing a control instruction for the executing mechanism; cross-linking with an external cockpit display system, and providing minimum track dip angle, predicted arrival point and current track dip angle signals of each flight segment for the cockpit display system. The flight control computer is also responsible for resolving the distance and the altitude difference between the route points, the minimum track inclination angle of each route section, the predicted arrival point, the current track inclination angle signal and the control instruction. Meanwhile, the flight control computer is responsible for judging the mode entering condition, running track dip angle mode control law and automatically switching to a high-level interception control law.
The automatic flight control board is a display control part of the automatic flight control system, acquires a desired track inclination angle value set by a pilot and a track inclination angle mode entering signal generated by the pilot pressing an automatic flight control board mode button, receives a track inclination angle mode state quantity sent by a flight control computer, displays the desired track inclination angle value set by the pilot, and lights a button lamp according to the track inclination angle mode state quantity signal sent by the flight control computer.
The executing mechanism is an executing device of the system, receives a control instruction sent by the flight control computer, drives the control surface to deflect, and sends an executing mechanism state signal to the flight control computer.
The control method of the system comprises the following steps:
1. the flight control computer acquires the waypoint information comprising longitude and latitude coordinates and altitude information, which is set before the pilot flies, through the navigation equipment.
2. The flight control computer calculates the distance and the height difference of the waypoints according to the waypoint information sent by the navigation equipment, and then calculates the minimum track inclination angle of each navigation section, the track inclination angle defines and shows an opinion figure 3, and the aircraft climbs positively. The track dip angle solution formula is as follows:
3. the flight control computer sends the calculated minimum track inclination angle of each navigation segment to a display system for display, and the minimum track inclination angle is used for reference when a pilot sets the expected track inclination angle.
4. The pilot sets the expected track inclination angle value through the automatic flight control board, and the automatic flight control board sends the expected track inclination angle value to the flight control computer and simultaneously displays the expected track inclination angle value on the automatic flight control board.
5. After receiving the expected track inclination angle value sent by the automatic flight control board, the flight control computer calculates the predicted arrival point by combining with the altitude difference information of the waypoints, and displays the predicted arrival point on a cockpit display system for a pilot to confirm the expected control effect.
6. The pilot generates a track dip angle mode entering signal by pressing a mode button of the automatic flight control board, the automatic flight control board sends the mode entering signal to the flight control computer, the flight control computer operates the track dip angle mode control law after judging that the mode entering condition is met, and sends a track dip angle mode state quantity to the automatic flight control board, and the automatic flight control board lights a button lamp after receiving the track dip angle mode state quantity so as to ensure that the pilot confirms that the mode has entered.
7. The flight control computer calculates the current track inclination angle signal in real time according to the aircraft sky-direction speed signal and the ground speed signal sent by the sensor, calculates the track inclination angle deviation by combining the expected track inclination angle value sent by the automatic flight control board, and operates the track inclination angle modal control law by combining the real-time aircraft state information sent by the sensor and the actuator state signal fed back by the actuator, and sends a calculation control instruction to the actuator. And the flight control computer simultaneously sends the calculated current track inclination angle signal to the cockpit display equipment for display, so that a pilot knows the effect of controlling the aircraft to fly automatically by the automatic flight control system.
8. The actuating mechanism acts after receiving a control instruction sent by the flight control computer, drives the control surface to deflect to generate aerodynamic force, and the aircraft changes the attitude of the aircraft under the action of the aerodynamic force, so that the real-time track inclination angle value of the aircraft is changed.
9. The flight control computer automatically switches to a height interception control law when the real-time height is close to the preselected height by combining the preselected height signal sent by the automatic flight control board through the real-time height signal of the aircraft sent by the sensor, and sends a control instruction to the executing mechanism to gradually level the aircraft, so that the function of automatic interception and stabilization at the preselected height is realized.
Claims (9)
1. An automatic flight control system for an aircraft vertical track angle is characterized by comprising a flight control computer, an automatic flight control board and an executing mechanism;
the flight control computer is used for receiving the expected track inclination angle value, the track inclination angle modal entering signal and the actuating mechanism state signal; calculating the minimum track inclination angle of each navigation segment and a control instruction; outputting track inclination modal state quantity, control instructions, minimum track inclination of each navigation section, predicted arrival points and current track inclination signals; judging the mode entering condition, running the track dip angle mode control law, and automatically switching to a high interception control law;
the automatic flight control board is used for setting a desired track inclination angle value, outputting a track inclination angle modal entering signal, and receiving a track inclination angle modal state quantity and a minimum track inclination angle of each flight segment; the expected track inclination angle value is set by referring to the minimum track inclination angle of each navigation section;
and the executing mechanism is used for receiving the control instruction, driving the control surface to deflect and outputting the state signal of the executing mechanism.
2. The aircraft vertical track angle automatic flight control system according to claim 1, wherein the minimum track pitch settlement process for each leg is as follows: and the flight control computer calculates the distance and the height difference of the waypoints according to the waypoint information, and then calculates the minimum track inclination angle of each navigation section.
3. The aircraft vertical track angle automatic flight control system of claim 1, wherein the aircraft climb is positive and the track inclination is calculated as follows:
wherein D is the distance between the waypoints, and DeltaH is the altitude difference between the waypoints.
4. The aircraft vertical track angle automatic flight control system of claim 1, wherein the settling process of the control instructions is as follows: the flight control computer calculates the current track inclination angle signal in real time according to the aircraft sky-direction speed signal and the ground speed signal, calculates the track inclination angle deviation by combining the expected track inclination angle value, and then operates the track inclination angle modal control law by combining the aircraft real-time state information and the actuator state signal fed back by the actuator to calculate the control instruction.
5. The aircraft vertical track angle automatic flight control system of claim 1, wherein the automatic flight control panel is further configured to display a desired track pitch value.
6. The aircraft vertical track angle automatic flight control system according to claim 1, wherein the automatic flight control board is further provided with a mode button with an indicator lamp, and the automatic flight control board lights the indicator lamp after receiving the track inclination mode state quantity for a pilot to confirm that a mode has entered.
7. A method of controlling an aircraft vertical track angle automatic flight control system according to any one of claims 1 to 6, comprising the steps of:
step 1: the flight control computer calculates the minimum track dip angle of each navigation section according to the navigation path point information;
step 2: the flight control computer sends the calculated minimum track inclination angle of each flight segment to an automatic flight control board for display, and the flight control board is used for reference when setting the expected track inclination angle;
step 3: setting an expected track inclination angle value through an automatic flight control board, and sending the expected track inclination angle value to a flight control computer by the automatic flight control board;
step 4: after receiving the expected track inclination angle value sent by the automatic flight control board, the flight control computer calculates and predicts the arrival point by combining with the altitude difference information of the waypoint;
step 5: pressing a mode button on the automatic flight control board to generate a track dip angle mode entering signal, sending the signal to the flight control computer, and after judging that the mode entering condition is met, the flight control computer operates the track dip angle mode control law and sends the track dip angle mode state quantity to the automatic flight control board, and the automatic flight control board lights an indicator lamp after receiving the track dip angle mode state quantity for a pilot to confirm that the mode has entered;
step 6: the flight control computer calculates the current track inclination angle signal in real time according to the aircraft sky-direction speed signal and the ground speed signal, calculates the track inclination angle deviation by combining the expected track inclination angle value sent by the automatic flight control board, operates the track inclination angle modal control law by combining the aircraft real-time state information sent by the sensor and the actuator state signal fed back by the actuator, and sends a calculation control instruction to the actuator.
8. The method of controlling an aircraft vertical track angle automatic flight control system according to claim 7, further comprising step 7: the actuating mechanism acts after receiving a control instruction sent by the flight control computer, drives the control surface to deflect to generate aerodynamic force, and the aircraft changes the attitude of the aircraft under the action of the aerodynamic force, so that the real-time track inclination angle value of the aircraft is changed.
9. The method of controlling an aircraft vertical track angle automatic flight control system according to claim 7, further comprising step 8: the flight control computer automatically switches to a height interception control law when the real-time height is close to the preselected height by combining the preselected height signal sent by the automatic flight control board through the real-time height signal of the aircraft sent by the sensor, and sends a control instruction to the executing mechanism to gradually level the aircraft, so that the function of automatic interception and stabilization at the preselected height is realized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311515772.4A CN117519265A (en) | 2023-11-15 | 2023-11-15 | Automatic flight control system and method for vertical track angle of airplane |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202311515772.4A CN117519265A (en) | 2023-11-15 | 2023-11-15 | Automatic flight control system and method for vertical track angle of airplane |
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| CN117519265A true CN117519265A (en) | 2024-02-06 |
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| CN202311515772.4A Pending CN117519265A (en) | 2023-11-15 | 2023-11-15 | Automatic flight control system and method for vertical track angle of airplane |
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- 2023-11-15 CN CN202311515772.4A patent/CN117519265A/en active Pending
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