An alarm system for an aircraft atmospheric sensor warm-up anomaly

Abstract

The application belongs to the technical field of the design of an abnormal opening alarm of an aircraft atmospheric sensor warming, and particularly relates to an alarm system for the abnormal opening of an aircraft atmospheric sensor warming, comprising an atmospheric sensor, a wheel load information acquisition device, an inertial navigation device, an atmospheric data computer, a central alarm computer and a display control unit. The existing devices on the aircraft are utilized, and no new device is needed, so that the alarm can be timely performed when the atmospheric sensor is automatically warmed abnormally, the crew or ground service personnel are prompted to disconnect the atmospheric sensor warming, and the atmospheric sensor damage or personnel injury caused by untimely discovery is avoided.

Description

Technical Field

[0001] This application belongs to the field of aircraft atmospheric sensor heating abnormal activation alarm design technology, specifically relating to an alarm system for an aircraft atmospheric sensor heating abnormal activation. Background Technology

[0002] To meet the high reliability and safety requirements of modern large aircraft, their air data systems generally employ a redundancy design. These systems typically consist of multiple air data computers, each equipped with dedicated air sensors such as a total pressure sensor, a static pressure sensor, and a total temperature sensor. During operation, a heating control box controls and monitors the heating status of each air sensor. The logic for automatic heating activation is usually related to indicated airspeed and wheel load.

[0003] The external parking environment of aircraft is harsh, frequently exposed to strong winds, heavy rain, and other severe weather. Although the externally mounted atmospheric sensors are protected by shields, condensation from the air can still seep into the sensors during prolonged periods of operation, affecting pressure measurements. Strong winds, in particular, can significantly impact pressure readings. In severe cases, both condensation and strong winds can cause the atmospheric data computer to receive incorrect pressure information and calculate an incorrect indicated airspeed. When the incorrect indicated airspeed exceeds a set threshold, it can trigger an malfunction in automatic heating. If ground crew fails to detect this in time, the atmospheric sensors will remain under heating for extended periods, potentially causing damage. Furthermore, the high temperatures generated by the heated sensors can pose a safety hazard to ground crew members.

[0004] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0005] The purpose of this application is to provide an alarm system for abnormal activation of the heating of an aircraft atmospheric sensor. It utilizes existing equipment on the aircraft without the need for additional equipment, making it simple to implement. When the automatic heating of the atmospheric sensor is abnormally activated, it can promptly issue an alarm to prompt the flight crew or ground staff to disconnect the atmospheric sensor heating, thus avoiding damage to the atmospheric sensor or injury to personnel due to delayed detection.

[0006] The technical solution of this application is:

[0007] An alarm system for abnormal activation of an aircraft atmospheric sensor heating includes an atmospheric sensor, a wheel-borne information acquisition device, an inertial navigation device, an atmospheric data computer, a central alarm computer, and a display control unit.

[0008] Atmospheric sensors, wheel-borne information acquisition equipment, and inertial navigation equipment are connected to an atmospheric data computer;

[0009] The atmospheric sensor includes a total pressure sensor and a static pressure sensor. The atmospheric data computer collects total pressure data through the total pressure sensor and the static pressure sensor. static pressure Calculate indicated airspeed ;

[0010] The atmospheric data computer collects wheel-mounted status data through wheel-mounted information acquisition equipment;

[0011] Atmospheric data computers collect combined ground speed data via inertial navigation equipment. ;

[0012] Atmospheric data computer connects to central alarm computer, combined with ground speed Less than or equal to the ground speed threshold And indicated airspeed greater than or equal to the airspeed threshold Or, combined ground speed Less than or equal to the ground speed threshold When the wheel load status is "airborne", the atmospheric data computer outputs an alarm message "atmospheric sensor abnormal heating on" to the central alarm computer.

[0013] The central alarm computer is connected to the display control unit and outputs an alarm message "Atmospheric sensor abnormal heating on" to the display control unit. The display control unit then displays the alarm message.

[0014] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, the atmospheric sensor, wheel-borne information acquisition equipment, and inertial navigation equipment are connected to an atmospheric data computer via a bus.

[0015] The atmospheric data computer is connected to the central alarm computer via a bus;

[0016] The central alarm computer is connected to the display control unit via a bus.

[0017] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, when the Mach number is ≤1, the indicated airspeed is calculated. for:

[0018] ;

[0019] When Mach number > 1, calculate indicated airspeed. for:

[0020] ;

[0021] in,

[0022] Atmospheric pressure at sea level;

[0023] The speed of sound at sea level;

[0024] It represents the adiabatic index.

[0025] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, the standard atmospheric pressure at sea level is... Take 101.3 kPa;

[0026] The speed of sound at sea level Take 340.294 m / s;

[0027] Insulation Index Take 1.4.

[0028] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, when the M number is ≤1, it meets the following condition: ;

[0029] When M > 1, the following conditions are met: .

[0030] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, the wheel-mounted information acquisition device is a device for acquiring wheel-mounted status, such as a bus interface unit, a data concentrator, or a flight control computer. The atmospheric data computer acquires the wheel-mounted status through the wheel-mounted information acquisition device, which is a voting value of multiple wheel-mounted statuses.

[0031] According to at least one embodiment of this application, in the above-described alarm system for abnormal activation of aircraft atmospheric sensor heating, the inertial navigation equipment is redundantly configured.

[0032] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, the airspeed threshold... 120km / h;

[0033] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, the ground speed threshold... Take 70km / h.

[0034] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, both the atmospheric sensor and the atmospheric data computer are redundant configurations, and each atmospheric data computer corresponds to a dedicated atmospheric sensor.

[0035] According to at least one embodiment of this application, the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating also includes a heating control box.

[0036] The heating control box is connected to the atmospheric data computer;

[0037] Indicative airspeed greater than or equal to the airspeed threshold When the vehicle is in "air" or the airborne status is controlled by the atmospheric data computer, the heating control box automatically heats the atmospheric sensor.

[0038] According to at least one embodiment of this application, in the above-mentioned alarm system for abnormal activation of aircraft atmospheric sensor heating, the display control unit is connected to the heating control box. When it receives the alarm information of "abnormal activation of atmospheric sensor heating", it triggers a warning level alarm and controls the heating control box to disconnect the heating of the atmospheric sensor.

[0039] This application has at least the following beneficial technical effects:

[0040] This invention provides an alarm system for abnormal activation of the heating of an aircraft atmospheric sensor. It utilizes existing equipment on the aircraft without the need for additional equipment, making it simple to implement. When the automatic heating of the atmospheric sensor is abnormally activated, it can promptly issue an alarm, prompting the flight crew or ground staff to disconnect the atmospheric sensor heating, thus preventing damage to the atmospheric sensor or injury to personnel due to delayed detection. Attached Figure Description

[0041] Figure 1 This is a schematic diagram of an alarm system for abnormal activation of an aircraft atmospheric sensor heating, provided in an embodiment of this application.

[0042] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0043] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0044] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0045] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0046] An alarm system for abnormal activation of an aircraft's atmospheric sensor heating, such as Figure 1 As shown, it includes a heating control box, an atmospheric sensor, a wheel-borne information acquisition device, an inertial navigation device, an atmospheric data computer, a central alarm computer, and a display control unit.

[0047] The heating control box, atmospheric sensor, wheel-borne information acquisition equipment, and inertial navigation equipment are connected to the atmospheric data computer, specifically via a bus connection.

[0048] The atmospheric sensor includes a total pressure sensor and a static pressure sensor. The atmospheric data computer collects total pressure data through the total pressure sensor and the static pressure sensor. static pressure Calculate indicated airspeed .

[0049] When Mach number ≤ 1, calculate indicated airspeed. for:

[0050] ;

[0051] When Mach number > 1, calculate indicated airspeed. for:

[0052] ;

[0053] in,

[0054] The standard atmospheric pressure at sea level is typically taken as 101.3 kPa.

[0055] The speed of sound at sea level is typically taken as 340.294 m / s;

[0056] The adiabatic index is usually taken as 1.4.

[0057] When M ≤ 1, the following conditions are met: ;

[0058] When M > 1, the following conditions are met: .

[0059] The wheel-borne information acquisition device is a bus interface unit, data concentrator, or flight control computer, etc., that collects wheel-borne status. The atmospheric data computer collects wheel-borne status through the wheel-borne information acquisition device, and this wheel-borne status is the voting value of multiple wheel-borne statuses.

[0060] The inertial navigation system is redundant; the atmospheric data computer collects combined ground velocity data through the inertial navigation system. .

[0061] Indicative airspeed greater than or equal to the airspeed threshold When the vehicle is in "airborne" condition, or when the airborne status is controlled by the air data computer, the heating control box automatically heats the air sensors. Among these parameters is the airspeed threshold. The speed is usually 120 km / h.

[0062] The atmospheric data computer is connected to the central alarm computer via a bus, combining ground speed data. Less than or equal to the ground speed threshold And indicated airspeed greater than or equal to the airspeed threshold Or, combined ground speed Less than or equal to the ground speed threshold When the wheel load status is "airborne," the atmospheric data computer outputs an alarm message "Ambient air sensor abnormal heating activated" to the central alarm computer. Among these, the ground speed threshold... A speed of 70 km / h is usually acceptable.

[0063] The central alarm computer is connected to the display control unit via a bus and outputs an "Atmospheric sensor abnormal heating on" alarm message to the display control unit. The display control unit displays the "Atmospheric sensor abnormal heating on" alarm message to prompt the crew or ground personnel to disconnect the atmospheric sensor heating to avoid damage to the atmospheric sensor or injury to personnel due to delayed detection.

[0064] The display control unit is connected to the heating control box. When it receives the alarm message "Atmospheric sensor abnormal heating on", it triggers a warning alarm and controls the heating control box to disconnect the heating of the atmospheric sensor.

[0065] Both the atmospheric sensors and the atmospheric data computer are redundant configurations, and each atmospheric data computer corresponds to a dedicated atmospheric sensor.

[0066] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. An alarm system for abnormal activation of an aircraft atmospheric sensor heating, characterized in that, Includes atmospheric sensors, wheel-borne information acquisition equipment, inertial navigation equipment, atmospheric data computer, central alarm computer, and display control unit; Atmospheric sensors, wheel-borne information acquisition equipment, and inertial navigation equipment are connected to an atmospheric data computer. The atmospheric sensor includes a total pressure sensor and a static pressure sensor. The atmospheric data computer collects total pressure data through the total pressure sensor and the static pressure sensor. static pressure Calculate indicated airspeed ; The atmospheric data computer collects wheel-mounted status data through wheel-mounted information acquisition equipment; Atmospheric data computers collect combined ground speed data via inertial navigation equipment. ; Atmospheric data computer connects to central alarm computer, combined with ground speed Less than or equal to the ground speed threshold And indicated airspeed greater than or equal to the airspeed threshold Or, combined ground speed Less than or equal to the ground speed threshold Furthermore, when the wheel load status is "airborne", the atmospheric data computer outputs an alarm message "atmospheric sensor abnormal heating on" to the central alarm computer; The central alarm computer is connected to the display control unit and outputs an "Atmospheric sensor abnormal heating on" alarm message to the display control unit. The display control unit then displays the "Atmospheric sensor abnormal heating on" alarm message.

2. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 1, characterized in that, Atmospheric sensors, wheel-borne information acquisition equipment, and inertial navigation equipment are connected to an atmospheric data computer via a bus. The atmospheric data computer is connected to the central alarm computer via a bus; The central alarm computer is connected to the display control unit via a bus.

3. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 2, characterized in that, When Mach number ≤ 1, calculate indicated airspeed. for: ； When Mach number > 1, calculate indicated airspeed. for: ； in, Atmospheric pressure at sea level; The speed of sound at sea level; It represents the adiabatic index.

4. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 3, characterized in that, sea ​​level standard atmospheric pressure Take 101.3 kPa; The speed of sound at sea level Take 340.294 m / s; Insulation Index Take 1.

4.

5. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 4, characterized in that, When M ≤ 1, the following conditions are met: ; When M > 1, the following conditions are met: .

6. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 5, characterized in that, The wheel-borne information acquisition equipment is a bus interface unit, a data concentrator, or a flight control computer. The air data computer collects wheel-borne status through the wheel-borne information acquisition equipment, which is a voting value for multiple wheel-borne statuses.

7. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 6, characterized in that, The inertial navigation system is redundant.

8. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 7, characterized in that, airspeed threshold Take 20km / h.

9. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 8, characterized in that, Ground speed threshold Take 70km / h.

10. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 9, characterized in that, Both the atmospheric sensors and the atmospheric data computer are redundant configurations, with each atmospheric data computer corresponding to a dedicated atmospheric sensor.

11. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 10, characterized in that, It also includes a heating control box; The heating control box is connected to the atmospheric data computer; Indicative airspeed greater than or equal to the airspeed threshold When the vehicle is in "air" or the airborne status is controlled by the atmospheric data computer, the heating control box automatically heats the atmospheric sensor.

12. The alarm system for abnormal activation of aircraft atmospheric sensor heating according to claim 11, characterized in that, The display control unit is connected to the heating control box. When it receives the alarm message "Atmospheric sensor abnormal heating on", it triggers a warning level alarm and controls the heating control box to disconnect the heating of the atmospheric sensor.

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