CN113734449B - Aircraft attack angle protection threshold design method - Google Patents
Aircraft attack angle protection threshold design method Download PDFInfo
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- CN113734449B CN113734449B CN202010412354.2A CN202010412354A CN113734449B CN 113734449 B CN113734449 B CN 113734449B CN 202010412354 A CN202010412354 A CN 202010412354A CN 113734449 B CN113734449 B CN 113734449B
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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
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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Abstract
The aircraft attack angle protection threshold design method comprises an attack angle protection controller, an attack angle sensor, a pushrod, a steering column, a wing deicing switch, a tail wing deicing switch, a deicing controller, a wing deicing execution mechanism, a tail wing deicing execution mechanism and a total temperature sensor, wherein the attack angle protection controller determines an attack angle protection threshold by judging the states of the wing deicing switch, the tail wing deicing switch, the wing deicing execution mechanism, the tail wing deicing execution mechanism and the total temperature sensor, and reduces the attack angle of an aircraft by pushing the steering column forward through the pushrod when the attack angle of the aircraft reaches the attack angle protection threshold.
Description
Technical Field
The application relates to the field of aircraft design, belongs to the technology of flight control systems, and particularly relates to an aircraft attack angle protection threshold design method.
Background
As is well known, the operation profile of a transport aircraft mostly experiences icing weather conditions, in airworthiness regulations, aircraft design departments are also required to consider icing as a normal environmental condition, under the icing condition, aerodynamic characteristics of the aircraft are changed, available flight attitude is limited in a certain range, a typical attitude limiting condition is limiting of an attack angle of the aircraft, and the available attack angle under the icing condition is properly reduced, otherwise, the aircraft can enter a stall condition and cannot maintain lift force, but the available attack angle cannot be so small as to seriously influence flight performance and cannot safely fly, so that an aircraft attack angle protection threshold design method is required to be designed, and the pilot is effectively and reliably helped to get out of a state that the aircraft approaches stall.
The traditional aircraft is also provided with an attack angle protection threshold design under icing conditions, but most of the aircraft is judged to be in icing conditions or non-icing conditions, and compared with the aircraft icing conditions which can be normally deicing and the aircraft icing conditions which can not be normally deicing, the available attack angles of the aircraft can be distinguished, the prior art can not deal with the complex icing conditions of the aircraft by using only one attack angle protection threshold, and the mismatching of the attack angle protection threshold and the aircraft conditions can cause potential safety hazards of flight.
Disclosure of Invention
The invention aims to provide a design method of an aircraft attack angle protection threshold, which can provide corresponding aircraft attack angle protection thresholds for different icing states of an aircraft, thereby ensuring flight safety and meeting flight performance.
An aircraft attack angle protection threshold design method comprises an attack angle protection controller, an attack angle sensor, a pusher, a steering column, a wing deicing switch, a tail wing deicing switch, a deicing controller, a wing deicing execution mechanism, a tail wing deicing execution mechanism and a total temperature sensor, and is characterized by comprising the following contents: the aircraft comprises an incidence angle protection controller, a steering column, a wing deicing switch, a tail deicing switch, a wing deicing actuating mechanism, a tail deicing actuating mechanism, a nose angle sensor, a tail temperature sensor, a nose angle protection controller, a nose angle protection threshold and a nose angle protection threshold.
The angle of attack protection controller has built-in ice type judgement module and angle of attack protection threshold storage module, ice type judgement module judges the icing condition of aircraft according to deicing controller and total temperature sensor's signal, angle of attack threshold storage module embeds the angle of attack threshold value under the different icing conditions of aircraft, angle of attack protection threshold storage module starts the angle of attack threshold value that corresponds in icing condition according to the icing condition of aircraft, compare the angle of attack threshold value that corresponds in icing condition with the aircraft angle of attack sensor real-time signal that angle of attack protection controller received simultaneously, if angle of attack sensor's real-time signal is greater than or equal to angle of attack protection threshold value, angle of attack protection threshold storage module will send instruction forward steering column to the push rod ware until angle of attack sensor's real-time signal is less than angle of attack protection threshold value, if angle of attack sensor's real-time signal is less than angle of attack protection threshold value, angle of attack protection threshold storage module keeps the no instruction state.
The ice type judging module divides the icing state of the aircraft into a non-icing state, a road icing state and a failure icing state.
The temperature signal of the total temperature sensor received by the ice type judging module is larger than a preset temperature, and the ice type judging module sets the aircraft to be in a non-icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism and the empennage deicing executing mechanism are in working states, and the ice type judging module sets the aircraft to be in a road icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism or the empennage deicing executing mechanism is in a non-working state, and the ice type judging module sets the aircraft to be in a failure icing state; if the temperature signal is smaller than or equal to the preset temperature, but the states of the wing deicing switch and the tail wing deicing switch are not opened, and the ice type judging module sets the aircraft to be in a non-icing state.
The attack angle protection threshold storage module stores attack angle protection threshold values of the aircraft in different icing conditions, wherein the attack angle protection threshold values comprise a non-icing condition attack angle protection threshold, a road icing condition attack angle protection threshold and a failure icing condition attack angle protection threshold, and the attack angle protection threshold values correspond to the non-icing condition, the road icing condition and the failure icing condition of the aircraft respectively.
The angle of attack protection controller has built-in ice type judgement module and angle of attack protection threshold storage module, ice type judgement module judges the icing condition of aircraft according to deicing controller and total temperature sensor's signal, angle of attack threshold storage module embeds the angle of attack threshold value under the different icing conditions of aircraft, angle of attack protection threshold storage module starts the angle of attack threshold value that corresponds in icing condition according to the icing condition of aircraft, compare the angle of attack threshold value that corresponds in icing condition with the aircraft angle of attack sensor real-time signal that angle of attack protection controller received simultaneously, if angle of attack sensor's real-time signal is greater than or equal to angle of attack protection threshold value, angle of attack protection threshold storage module will send instruction forward steering column to the push rod ware until angle of attack sensor's real-time signal is less than angle of attack protection threshold value, if angle of attack sensor's real-time signal is less than angle of attack protection threshold value, angle of attack protection threshold storage module keeps the no instruction state.
The ice type judging module divides the icing state of the aircraft into a non-icing state, a road icing state and a failure icing state.
The temperature signal of the total temperature sensor received by the ice type judging module is larger than a preset temperature, and the ice type judging module sets the aircraft to be in a non-icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism and the empennage deicing executing mechanism are in working states, and the ice type judging module sets the aircraft to be in a road icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism or the empennage deicing executing mechanism is in a non-working state, and the ice type judging module sets the aircraft to be in a failure icing state; if the temperature signal is smaller than or equal to the preset temperature, but the states of the wing deicing switch and the tail wing deicing switch are not opened, and the ice type judging module sets the aircraft to be in a non-icing state.
The attack angle protection threshold storage module stores attack angle protection threshold values of the aircraft in different icing conditions, wherein the attack angle protection threshold values comprise a non-icing condition attack angle protection threshold, a road icing condition attack angle protection threshold and a failure icing condition attack angle protection threshold, and the attack angle protection threshold values correspond to the non-icing condition, the road icing condition and the failure icing condition of the aircraft respectively.
The temperature signal of the total temperature sensor received by the ice type judging module is larger than a preset temperature, and the ice type judging module sets the aircraft to be in a non-icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism and the empennage deicing executing mechanism are in working states, and the ice type judging module sets the aircraft to be in a road icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism or the empennage deicing executing mechanism is in a non-working state, and the ice type judging module sets the aircraft to be in a failure icing state; if the temperature signal is smaller than or equal to the preset temperature, but the states of the wing deicing switch and the tail wing deicing switch are not opened, and the ice type judging module sets the aircraft to be in a non-icing state.
The attack angle protection threshold storage module stores attack angle protection threshold values of the aircraft in different icing conditions, wherein the attack angle protection threshold values comprise a non-icing condition attack angle protection threshold, a road icing condition attack angle protection threshold and a failure icing condition attack angle protection threshold, and the attack angle protection threshold values correspond to the non-icing condition, the road icing condition and the failure icing condition of the aircraft respectively.
The invention has the beneficial effects that: 1) The method designs different attack angle protection thresholds of the aircraft under different icing conditions, so that the attack angle threshold is matched with the aircraft state as much as possible, thereby ensuring the flight safety and meeting the flight performance. 2) The attack angle protection controller comprehensively judges the icing state of the aircraft through the total temperature sensor and the deicing controller, presets attack angle thresholds under different icing states, compares the attack angle thresholds under different icing states with the real-time attack angle of the aircraft, and controls the attack angle of the aircraft according to a comparison result.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
Fig. 1 is a schematic illustration of an aircraft angle of attack protection threshold design configuration.
Fig. 2 is a schematic diagram of the working logic of the ice type judging module.
Fig. 3 is a logic schematic diagram of an attack angle protection threshold storage module.
Detailed Description
Referring to the attached drawings, the design configuration of the aircraft attack angle protection threshold design method is shown in fig. 1, the aircraft attack angle protection threshold design method comprises an attack angle protection controller, an attack angle sensor, a push rod device, a steering column, a wing deicing switch, a tail wing deicing switch, a deicing controller, a wing deicing executing mechanism, a tail wing deicing executing mechanism and a total temperature sensor, wherein the attack angle protection controller is connected with the steering column through the push rod device, the wing deicing switch, the tail wing deicing switch, the wing deicing executing mechanism and the tail wing deicing executing mechanism are connected with the attack angle protection controller through the deicing controller, and the attack angle sensor and the total temperature sensor are directly connected with the attack angle protection controller. The attack angle protection controller determines an attack angle protection threshold by judging states of the wing deicing switch, the tail wing deicing switch, the wing deicing execution mechanism, the tail wing deicing execution mechanism and the total temperature sensor, and reduces the attack angle of the aircraft by pushing the steering column forward through the pusher when the attack angle of the aircraft reaches the attack angle protection threshold.
The ice type judging module judges the icing state of the aircraft according to the signals of the deicing controller and the total temperature sensor, and divides the icing state of the aircraft into a non-icing state, a road icing state and a failure icing state. The temperature signal of the total temperature sensor received by the ice type judging module is larger than a preset temperature, and the ice type judging module sets the aircraft to be in a non-icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism and the empennage deicing executing mechanism are in working states, and the ice type judging module sets the aircraft to be in a road icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism or the empennage deicing executing mechanism is in a non-working state, and the ice type judging module sets the aircraft to be in a failure icing state; if the temperature signal is smaller than or equal to the preset temperature, but the states of the wing deicing switch and the tail wing deicing switch are not opened, and the ice type judging module sets the aircraft to be in a non-icing state.
The temperature signal of the total temperature sensor received by the ice type judging module is larger than a preset value, the preset temperature value is 10 degrees, and the ice type judging module sets the aircraft to be in a non-icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism and the empennage deicing executing mechanism are in working states, and the ice type judging module sets the aircraft to be in a road icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism or the empennage deicing executing mechanism is in a non-working state, and the ice type judging module sets the aircraft to be in a failure icing state; if the temperature signal is smaller than or equal to the preset temperature, but the states of the wing deicing switch and the tail wing deicing switch are not opened, and the ice type judging module sets the aircraft to be in a non-icing state.
If the temperature signal of the total temperature sensor is greater than 10 ℃, the ice type judging module sets the aircraft in a non-icing state, if the wing deicing switch is opened or the tail wing deicing switch is opened, the wing deicing executing mechanism functions normally and the tail wing deicing executing mechanism functions normally, the ice type judging module sets the aircraft in a road icing state, and otherwise, the aircraft is set in a failure icing state.
The working logic of the attack angle protection threshold storage module is shown in fig. 3, and the attack angle protection threshold storage module stores attack angle protection threshold values of the aircraft in different icing states, wherein the attack angle protection threshold values comprise a non-icing state attack angle protection threshold, a road icing state attack angle protection threshold and a failure icing state attack angle protection threshold, and the attack angle protection threshold values correspond to the non-icing state, the road icing state and the failure icing state of the aircraft respectively. The angle of attack protection threshold storage module starts the angle of attack threshold corresponding to the icing state according to the icing state of the aircraft, compares the angle of attack threshold corresponding to the icing state with the real-time signal of the aircraft angle of attack sensor received by the angle of attack protection controller, and if the real-time signal of the angle of attack sensor is greater than or equal to the angle of attack protection threshold, the angle of attack protection threshold storage module sends a command to the pushrod device to push the steering column until the real-time signal of the angle of attack sensor is less than the angle of attack protection threshold, and if the real-time signal of the angle of attack sensor is less than the angle of attack protection threshold, the angle of attack protection threshold storage module maintains the non-command state.
The angle of attack protection threshold storage module is used for storing different angle of attack protection thresholds of the aircraft in a non-icing state, an icing state of a route and a failure icing state, if the ice type judgment module is used for setting the aircraft in the non-icing state, the angle of attack protection threshold storage module is used for starting the angle of attack protection threshold of the non-icing state, the ice type judgment module is used for setting the aircraft in the icing state of the route, the angle of attack protection threshold storage module is used for starting the angle of attack protection threshold of the icing state of the route, otherwise, the angle of attack protection threshold of the failure icing state is started, the angle of attack protection controller receives a real-time signal of the angle of attack sensor, the angle of attack protection threshold storage module of the angle of attack protection controller compares the real-time signal of the angle of attack sensor with the angle of attack protection threshold, if the real-time signal of the angle of attack sensor is larger than or equal to the angle of attack protection threshold, the angle of attack protection threshold storage module is used for sending a command to the push rod until the real-time signal of the angle of attack sensor is smaller than the angle of attack protection threshold by 2 degrees, and if the real-time signal of the angle of attack sensor is smaller than the angle of attack protection threshold, and the angle of attack protection threshold storage module is kept in a non-command state.
Assume that: the total temperature sensor signals are 9 ℃, the wing deicing switch is opened, the empennage deicing switch is opened, the wing deicing executing mechanism is failed, the empennage deicing executing mechanism is normal, the total temperature sensor temperature signals are 9 ℃, the wing deicing switch is opened, the empennage deicing switch is opened, the ice type judging module sets the aircraft to be in a road icing state or a failure icing state, the wing deicing executing mechanism is failed, the empennage deicing executing mechanism is normal in function, and the ice type judging module sets the aircraft to be in the failure icing state.
Assume that: the real-time signal of the attack angle sensor is 12 degrees, the attack angle protection threshold value of the invalid icing state is 12 degrees, the ice type judging module sets the attack angle protection threshold value of the aircraft in the road icing state, the attack angle protection threshold storage module starts the attack angle protection threshold value of the invalid icing state, the real-time signal of the attack angle sensor is 12 degrees, the attack angle protection threshold value of the invalid icing state is 12 degrees, the real-time signal of the attack angle sensor is equal to the attack angle protection threshold value, and the attack angle protection threshold storage module sends an instruction to the pusher to push the driving rod.
Claims (3)
1. An aircraft attack angle protection threshold design method comprises an attack angle protection controller, an attack angle sensor, a pusher, a steering column, a wing deicing switch, a tail wing deicing switch, a deicing controller, a wing deicing execution mechanism, a tail wing deicing execution mechanism and a total temperature sensor, and is characterized by comprising the following contents: the angle of attack protection controller is connected with the steering column through a pushrod, the wing deicing switch, the tail deicing switch, the wing deicing actuating mechanism and the tail deicing actuating mechanism are connected with the angle of attack protection controller through the deicing controller, the angle of attack protection controller determines an angle of attack protection threshold by judging the states of the wing deicing switch, the tail deicing switch, the wing deicing actuating mechanism, the tail deicing actuating mechanism and the tail deicing actuating mechanism, and pushes the steering column forwards through the pushrod when the angle of attack of the aircraft reaches the angle of attack protection threshold, the angle of attack protection controller has a built-in ice type judging module and an angle of attack protection threshold storage module, the ice type judging module judges the icing state of the aircraft according to the signals of the deicing controller and the tail deicing actuating mechanism, the angle of attack protection threshold storage module has the angle of attack threshold under different icing states of the aircraft, the angle of attack protection threshold storage module starts the angle of attack threshold corresponding to the icing state of the aircraft according to the icing state of the aircraft, and simultaneously pushes the angle of attack protection controller to reduce the angle of attack by the pushrod when the angle of the aircraft reaches the angle of attack protection threshold, the angle of attack protection controller has a built-in ice type judging module and the ice type protecting threshold storage module judges the icing state of the aircraft according to the signals of the deicing controller and the total temperature sensor, if the angle of the aircraft is smaller than the aircraft, the angle of attack protection threshold is not stored in real-time, and the angle of the aircraft is stored in real-time signal is stored in the protection module when the angle of attack protection module is not equal to the angle of attack protection threshold, the attack angle protection threshold value comprises a non-icing state attack angle protection threshold, a road icing state attack angle protection threshold and a failure icing state attack angle protection threshold, and the non-icing state, the road icing state and the failure icing state of the aircraft are respectively corresponding to the non-icing state, the road icing state and the failure icing state of the aircraft.
2. The aircraft angle of attack protection threshold design method of claim 1, wherein the ice type determination module classifies an icing condition of the aircraft into a non-icing condition, a road icing condition, and a failure icing condition.
3. The method for designing an aircraft attack angle protection threshold according to claim 2, wherein the temperature signal of the total temperature sensor received by the ice type judging module is greater than a predetermined temperature, and the ice type judging module sets the aircraft in a non-icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism and the empennage deicing executing mechanism are in working states, and the ice type judging module sets the aircraft to be in a road icing state; if the temperature signal is smaller than or equal to the preset temperature, the wing deicing switch and the empennage deicing switch are turned on at the same time, the wing deicing executing mechanism or the empennage deicing executing mechanism is in a non-working state, and the ice type judging module sets the aircraft to be in a failure icing state; if the temperature signal is smaller than or equal to the preset temperature, but the states of the wing deicing switch and the tail wing deicing switch are not opened, and the ice type judging module sets the aircraft to be in a non-icing state.
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| CN202010412354.2A CN113734449B (en) | 2020-05-15 | 2020-05-15 | Aircraft attack angle protection threshold design method |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06206593A (en) * | 1993-01-08 | 1994-07-26 | Mitsubishi Heavy Ind Ltd | Anti-icing and de-icing device for aircraft |
| CN109878740A (en) * | 2019-03-25 | 2019-06-14 | 上海工程技术大学 | The anti-icing and de-icing device and method of a kind of turboprop aircraft wing, empennage |
| US10336463B2 (en) * | 2017-11-02 | 2019-07-02 | Embraer S.A. | Aircraft stall warning/protection with time-varying maximum angle of attack settings for icing conditions |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012040446A1 (en) * | 2010-09-24 | 2012-03-29 | Heaton Clifford D | Airplane wing |
| US8789793B2 (en) * | 2011-09-06 | 2014-07-29 | Airbus Operations S.L. | Aircraft tail surface with a leading edge section of undulated shape |
| JP6114075B2 (en) * | 2013-03-07 | 2017-04-12 | 三菱航空機株式会社 | Aircraft warning system and aircraft |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06206593A (en) * | 1993-01-08 | 1994-07-26 | Mitsubishi Heavy Ind Ltd | Anti-icing and de-icing device for aircraft |
| US10336463B2 (en) * | 2017-11-02 | 2019-07-02 | Embraer S.A. | Aircraft stall warning/protection with time-varying maximum angle of attack settings for icing conditions |
| CN109878740A (en) * | 2019-03-25 | 2019-06-14 | 上海工程技术大学 | The anti-icing and de-icing device and method of a kind of turboprop aircraft wing, empennage |
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