CN112373704A - System for realizing emergency control of airplane by controlling engine thrust and airplane - Google Patents
System for realizing emergency control of airplane by controlling engine thrust and airplane Download PDFInfo
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- CN112373704A CN112373704A CN202011283596.2A CN202011283596A CN112373704A CN 112373704 A CN112373704 A CN 112373704A CN 202011283596 A CN202011283596 A CN 202011283596A CN 112373704 A CN112373704 A CN 112373704A
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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 claims abstract description 64
- 230000007935 neutral effect Effects 0.000 claims abstract description 10
- 230000004044 response Effects 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 3
- 244000208734 Pisonia aculeata Species 0.000 claims description 2
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000002650 habitual effect Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000013178 mathematical model Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000009420 retrofitting Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
- B64D31/02—Initiating means
- B64D31/04—Initiating means actuated personally
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a system for realizing emergency control of an airplane by controlling the thrust of an engine and the airplane, wherein the system comprises: the cockpit control panel emergency switch can respond to the operation of starting the emergency switch by an operator when a flight control fault occurs, instruct the flight control computer to switch from an autonomous control law to a backup control law, and control and adjust the symmetric thrust and the differential thrust of the engine so as to maintain the flight height and the course of the airplane; a sidestick capable of being overridden when manipulated away from neutral such that the flight control computer controls and adjusts the engine's symmetric thrust and differential thrust in accordance with the manipulation of the sidestick. The invention can provide the manual control authority necessary for the pilot and a reliable and easy-to-operate manual control mode, so that the pilot can timely intervene in emergency control of the airplane when the pilot faces some special emergency conditions such as emergency obstacle avoidance, missed approach and the like, and the safety of the airplane under the emergency control condition is improved.
Description
Technical Field
The invention relates to the technical field of emergency flight control of an aircraft, in particular to a system for realizing emergency control of the aircraft by controlling engine thrust and the aircraft comprising the system.
Background
In the history of civil aviation, a plurality of serious flight accidents caused by serious flight control faults such as failure of a conventional control surface, loss of flight control capability and the like occur. The modern airplane flight control system and the propulsion system both adopt a digital electronic control scheme, so that the high integration of the flight control system and the propulsion system becomes possible.
By using the emergency flight control technology which only controls the thrust of the engine as a backup control strategy, a certain emergency control capability can be provided for the airplane when the conventional control surface of the airplane fails. This is of great importance for the safety of large aircraft.
The prior art has proposed some solutions in this respect, however, the existing solutions are deficient in terms of the operations involved in emergency control and the setting of control authorities, and thus the existing solutions can help to some extent the aircraft to maintain altitude, heading, etc. in emergency situations, but they excessively limit the control authorities of the pilot in some necessary situations, such as the need for emergency barriers, missed flights, etc., which are not conducive to ensuring the safety of aircraft flight in some special emergency situations.
Accordingly, there is a need to provide a new system for emergency control of an aircraft by controlling engine thrust to at least partially alleviate or solve the above-mentioned problems and deficiencies with existing solutions.
Disclosure of Invention
The invention aims to overcome the defect that the safety of airplane flight cannot be effectively guaranteed under some special emergency conditions due to the fact that the control authority of a pilot is excessively limited in the conventional system and method for realizing the emergency control of the airplane, and provides a novel system for realizing the emergency control of the airplane by controlling the thrust of an engine and the airplane.
The invention solves the technical problems through the following technical scheme:
the invention provides a system for realizing emergency control of an aircraft by controlling thrust of an engine, wherein the aircraft comprises a flight control computer, a FADEC and engines on two sides of the aircraft, the flight control computer is configured to be capable of controlling the engines through the FADEC, and the system is characterized in that the flight control computer is configured with a main control law and a backup control law, and the system comprises:
a cockpit control panel emergency switch configured to instruct the flight control computer to switch from the main control law to the backup control law in response to an operation of an operator to turn on the cockpit control panel emergency switch when a flight control fault occurs, and to respectively control the engine to adjust a symmetric thrust and a differential thrust of the engine according to the backup control law and aircraft state information of the aircraft to maintain a flight altitude and a course of the aircraft;
a sidestick configured to be in a neutral position when not subject to an external force and to effect an override when maneuvered away from the neutral position such that the flight control computer controls the engine to adjust a symmetric thrust and a differential thrust of the engine, respectively, based on operator manipulation of the sidestick and the aircraft state information.
According to one embodiment of the invention, the sidebar is configured to be able to cause the flight control computer to control the engine to increase the symmetric thrust of the engine when steered for pullback and to reduce the symmetric thrust of the engine when steered for pushforward.
According to an embodiment of the invention, the sidebar is configured to be able to cause the flight control computer to control the engine to increase the differential thrust of the engine when steered to tilt to the left and right.
According to one embodiment of the invention, the sidebar is configured to be automatically restored to the neutral position when not manipulated by an external force for a preset period of time.
According to an embodiment of the invention, the system further comprises:
a roll control knob, the flight control computer further configured to adjust the symmetric thrust and the differential thrust of the engine according to a position of the roll control knob to control the aircraft to perform a roll maneuver.
According to an embodiment of the invention, the system further comprises:
a track angle control knob, said flight control computer further configured to adjust a symmetric thrust and a differential thrust of said engine according to a position of said track angle control knob to control said aircraft to change its track angle.
According to an embodiment of the invention, the system further comprises:
an auto landing intervention button, the flight control computer further configured to control the engine to adjust a symmetric thrust and a differential thrust of the engine to control the aircraft to implement an auto landing in response to the auto landing intervention button being pressed.
According to one embodiment of the invention, the flight control fault comprises a complete failure of a hydraulic system of the aircraft or a complete failure of a control plane control of the aircraft.
According to one embodiment of the invention, the cockpit control panel emergency switch, the roll control knob, the track angle control knob and the automatic landing intervention button are integrated on a cockpit control panel of the aircraft.
The invention also provides an aircraft, characterized in that the aircraft comprises a system for emergency control of the aircraft by controlling the thrust of the engine as described above.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
according to the system for realizing the emergency control of the airplane by controlling the thrust of the engine and the airplane, the necessary manual control authority of a pilot and a reliable and easily-operated manual control mode can be provided, so that the pilot can timely intervene in the emergency control of the airplane when facing some special emergency conditions such as emergency obstacle avoidance, missed approach and the like, and the safety of the airplane under the emergency control condition is improved.
Drawings
Fig. 1 is a schematic diagram of a system for emergency control of an aircraft by controlling engine thrust in accordance with a preferred embodiment of the present invention.
Fig. 2 is another schematic diagram of a system for emergency control of an aircraft by controlling engine thrust in accordance with a preferred embodiment of the present invention.
Description of the reference numerals
11: side lever
12: emergency switch for control panel of cockpit
13: rolling control knob
14: track angle control knob
15: automatic landing intervention button
2: flight control computer
3：FADEC
4: engine
5: aircraft state information
Detailed Description
The following detailed description of the preferred embodiments of the present invention, taken in conjunction with the accompanying drawings, is intended to be illustrative, and not restrictive, and it is intended that all such modifications and equivalents be included within the scope of the present invention.
In the following detailed description, directional terms, such as "left", "right", "upper", "lower", "front", "rear", and the like, are used with reference to the orientation as illustrated in the drawings. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting.
A system for emergency control of an aircraft by controlling the thrust of the engine 4 according to a preferred embodiment of the invention is shown in fig. 1-2. The aircraft comprises a flight control computer 2, a FADEC3 and engines 4 on both sides of the aircraft, the flight control computer 2 is configured to be able to control the engines 4 via the FADEC3, and is configured with a main control law and a backup control law.
It will be understood by those skilled in the art that the control laws, which are collectively referred to as control law, and the algorithms for which the flight control system forms control commands, describe the functional relationship between the controlled state variables and the system input signals, may generally represent a mathematical model of the flight control system. For a flight control system, the control laws are related to the working modes of the system, and one working mode corresponds to one control law. On this basis, the primary control law in this context can be understood as the control law of the aircraft in the normal state, and the backup control law can be understood as the emergency control law of the aircraft in the event of a flight control fault, such as a complete failure of the hydraulic system of the aircraft or a complete failure of the control surface control of the aircraft.
Referring to fig. 1-2, the system includes a cockpit control panel emergency switch 12 and a sidebar 11. The cockpit control panel emergency switch 12 is configured to instruct the flight control computer 2 to switch from the autonomous control law to the backup control law in response to an operation of an operator for turning on the cockpit control panel emergency switch 12 when a flight control fault occurs, and respectively control the engine 4 to adjust the symmetric thrust and the differential thrust of the engine 4 according to the backup control law and the aircraft state information 5 of the aircraft so as to maintain the flight altitude and the heading of the aircraft. Among other things, a flight control fault as referred to herein includes a complete failure of the hydraulic system of the aircraft or a complete failure of the control plane control of the aircraft.
The sidestick 11 is then configured to be in a neutral position when not subject to external forces and to effect an override when manipulated out of the neutral position such that the flight control computer 2 controls the engine 4 to adjust the symmetric thrust and the differential thrust of the engine 4, respectively, based on the operator's manipulation of the sidestick 11 and the aircraft state information 5.
Compared with the conventional flight control system, the solution according to the above embodiment of the present invention, the manual control manner of controlling the engine 4 by using the sidebar 11 can be set to be substantially equivalent to the conventional manual control of the control surface, and the control of the engine 4 by using the cockpit control panel emergency switch 12 can be configured to be substantially equivalent to the conventional automatic flight control manner based on the thrust control of the engine 4.
On this basis, as shown in fig. 1-2, according to some preferred embodiments of the present invention, control means such as a roll control knob 13, a track angle control knob 14, an automatic landing intervention button 15, etc. may also be introduced, which may also be configured to complement some automatic flight control means for emergency control. The control functions involved with the ROLL control knob 13 (e.g., "ROLL switch" shown in fig. 2), track angle control knob 14 (e.g., "PITCH switch" shown in fig. 2), automatic Landing intervention button 15 (e.g., "Approach and pulling switch" shown in fig. 2) will be described in detail below.
It should be understood that aircraft state information, as referred to herein, may primarily include inertial navigation information, which is typically obtained from an inertial reference system of the aircraft, which may specifically include information such as the angles of the three axes of the aircraft, angular velocities, angular accelerations, etc., and aircraft state information, which may also include atmospheric data information, which may generally be obtained from an atmospheric system, which may specifically include information such as airspeed, angle of attack, sideslip angle, etc.
It should also be understood that the cockpit control panel emergency switch 12, roll control knob 13, track angle control knob 14, and automatic landing intervention button 15 may be integrated on the aircraft's native cockpit control panel. Therefore, the scheme according to some preferred embodiments of the present invention can be implemented by only multiplexing or improving the original flight control device and allowing the backup control law to operate in the flight control computer 2 of the original airplane without adding new devices. This will allow the solution according to the invention to be used for retrofitting existing aircraft and their flight control systems without significantly increasing their cost and thus with better economy.
The solution according to the above embodiment of the present invention introduces the authority logic of the side stick 11 and the cockpit control board, and by manipulating the emergency switch or the knob on the cockpit control board, the flight control computer 2 can automatically control the aircraft based on the corresponding automatic control mode, such as controlling the attitude and track of the aircraft, and by manipulating the side stick 11, the manual override can be performed, and the direct control of the engine 4 of the aircraft by manipulation of the side stick 11 can be realized.
The cockpit control panel emergency switch 12 may be specifically designed in the form of an automatic control intervention Button (e.g., "Engage Button" shown in fig. 2), and when the automatic control intervention Button is pressed, an automatic control intervention command is triggered.
According to some preferred embodiments of the present invention, the control functions involved in the roll control knob 13, the track angle control knob 14, the automatic landing intervention button 15 are substantially designed such that the flight control computer 2 is further configured to:
the symmetrical thrust and the differential thrust of the engine 4 can be adjusted according to the position of the roll control knob 13 so as to control the aircraft to execute the roll action;
the symmetrical thrust and the differential thrust of the engine 4 can be adjusted according to the position of the track angle control knob 14 so as to control the aircraft to change the track angle; and
the engine 4 can be controlled in response to the automatic landing intervention button 15 being pressed to adjust the symmetric thrust and the differential thrust of the engine 4 to control the aircraft to carry out an automatic landing.
According to some preferred embodiments of the present invention, the sidebar 11 is configured to be able to cause the flight control computer 2 to control the engine 4 to increase the symmetric thrust of the engine 4 when it is manoeuvred back, and to cause the flight control computer 2 to control the engine 4 to decrease the symmetric thrust of the engine 4 when it is manoeuvred front.
According to some preferred embodiments of the present invention, the sidebar 11 is configured to be able to cause the flight control computer 2 to control the engine 4 to increase the differential thrust of the engine 4 when manipulated to tilt to the left and right.
According to some preferred embodiments of the present invention, the side bar 11 is configured to automatically return to the neutral position when not manipulated by an external force for a preset period of time.
According to the solution of the above described preferred embodiment of the invention, it will be possible for the pilot to have a sense of his relative habitual or familiar handling when using the sidestick 11 for manual control.
The system for realizing the emergency control of the airplane by controlling the thrust of the engine according to the preferred embodiment of the invention can provide the necessary manual control authority for the pilot and the manual control mode which is reliable and easy to operate by the pilot, so that the pilot can timely intervene in the emergency control of the airplane when the pilot faces some special emergency situations such as emergency obstacle avoidance, missed approach and the like. Such a system for emergency control of an aircraft would help to improve the safety of the aircraft in emergency control situations.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (10)
1. A system for emergency control of an aircraft by controlling engine thrust, the aircraft comprising a flight control computer, a FADEC and engines on both sides of the aircraft, the flight control computer being configured to be able to control the engines via the FADEC, characterized in that the flight control computer is configured with a primary control law and a backup control law, and in that the system comprises:
a cockpit control panel emergency switch configured to instruct the flight control computer to switch from the main control law to the backup control law in response to an operation of an operator to turn on the cockpit control panel emergency switch when a flight control fault occurs, and to respectively control the engine to adjust a symmetric thrust and a differential thrust of the engine according to the backup control law and aircraft state information of the aircraft to maintain a flight altitude and a course of the aircraft;
a sidestick configured to be in a neutral position when not subject to an external force and to effect an override when maneuvered away from the neutral position such that the flight control computer controls the engine to adjust a symmetric thrust and a differential thrust of the engine, respectively, based on operator manipulation of the sidestick and the aircraft state information.
2. The emergency flight control system of claim 1, wherein the sidebar is configured to enable the flight control computer to control the engine to increase a symmetric thrust of the engine when manipulated for pullback and to enable the flight control computer to control the engine to decrease a symmetric thrust of the engine when manipulated for pushforward.
3. The emergency flight control system of claim 1, wherein the sidebar is configured to enable the flight control computer to control the engine to increase a differential thrust of the engine when manipulated to tilt to the left and right.
4. The emergency flight control system of claim 1, wherein the sidebar is configured to be automatically restored to the neutral position when not manipulated by external forces for a preset length of time.
5. The emergency flight control system of claim 1, further comprising:
a roll control knob, the flight control computer further configured to adjust the symmetric thrust and the differential thrust of the engine according to a position of the roll control knob to control the aircraft to perform a roll maneuver.
6. The emergency flight control system of claim 5, further comprising:
a track angle control knob, said flight control computer further configured to adjust a symmetric thrust and a differential thrust of said engine according to a position of said track angle control knob to control said aircraft to change its track angle.
7. The emergency flight control system of claim 6, further comprising:
an auto landing intervention button, the flight control computer further configured to control the engine to adjust a symmetric thrust and a differential thrust of the engine to control the aircraft to implement an auto landing in response to the auto landing intervention button being pressed.
8. The emergency flight control system of claim 1, wherein the flight control fault comprises a complete failure of a hydraulic system of the aircraft or a complete failure of control surface control of the aircraft.
9. The emergency flight control system of claim 7, wherein the cockpit control panel emergency switch, the roll control knob, the track angle control knob, and the automatic landing intervention button are integrated on a cockpit control panel of the aircraft.
10. An aircraft, characterized in that it comprises a system for emergency control of an aircraft by controlling engine thrust according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011283596.2A CN112373704A (en) | 2020-11-17 | 2020-11-17 | System for realizing emergency control of airplane by controlling engine thrust and airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011283596.2A CN112373704A (en) | 2020-11-17 | 2020-11-17 | System for realizing emergency control of airplane by controlling engine thrust and airplane |
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| Publication Number | Publication Date |
|---|---|
| CN112373704A true CN112373704A (en) | 2021-02-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011283596.2A Pending CN112373704A (en) | 2020-11-17 | 2020-11-17 | System for realizing emergency control of airplane by controlling engine thrust and airplane |
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Application publication date: 20210219 |