A sensor and method for collecting water test flight data of amphibious aircraft

Abstract

The present invention belongs to the technical field of aircraft flight test, and specifically relates to a sensor and method for collecting water flight test data of amphibious aircraft. The sensor includes a splash-proof housing, the splash-proof housing includes a trumpet-shaped pipe, a cylindrical pipe connected to the trumpet-shaped pipe is provided on the top of the trumpet-shaped pipe, two small tubes are provided on the cylindrical pipe, the two small tubes are respectively connected to the cylindrical pipe, an internal circuit is installed inside the cylindrical pipe, and a double-pin electrode is connected to the bottom of the internal circuit. The sensor for collecting water flight test data of the present invention is based on the principle that non-pure water is conductive, and uses the double-pin electrode to detect whether conductive water exists. When water is present, the double-pin electrode is connected, and when no water is present, the double-pin electrode is disconnected. By converting the electrical signal into a digital signal indicating whether the electrode is connected or disconnected, the sensor can be used to indicate the water surface status when the aircraft is collecting water flight test data. At the same time, the pilot can judge whether the aircraft is connected to water or out of water based on the signal.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft flight test, and in particular relates to a sensor and a method for collecting water flight test data of an amphibious aircraft. Background Art

[0002] During the water test flight of amphibious aircraft, the collection of test flight data is often a difficult task with many uncertainties, which requires careful deployment and precise implementation. Among them, the aircraft water test flight data collection technology is a key technology, which is directly related to the quality and safety of the aircraft water test flight.

[0003] Water test flight data collection technology is to collect aircraft-related data during the amphibious aircraft's taxiing or take-off and landing phases on the water. The key point is to determine whether the amphibious aircraft is in contact with the water surface and whether it has left the water surface.

[0004] Existing techniques for determining whether an aircraft is in the water taxiing or liftoff phase often rely on test pilots looking through observation windows or windshields, which is relatively inefficient. Furthermore, the operating environment of amphibious aircraft is inherently more complex and variable than that of land-based aircraft. Traditional methods for determining whether an aircraft is in the water taxiing or liftoff phase distract test pilots, impacting flight safety and hindering the collection of water test data. Summary of the Invention

[0005] The purpose of the present invention is to provide a sensor and measurement method for collecting water test flight data of amphibious aircraft, which has a simple structure, strong functionality, high reliability, and is easy to install and maintain, and measures whether the hull of an amphibious aircraft is in contact with the water surface and whether it leaves the water surface.

[0006] The technical solution of the present invention:

[0007] A sensor for collecting data from water test flights of amphibious aircraft includes a splash-proof housing, the splash-proof housing including a trumpet-shaped pipe, a cylindrical pipe connected to the trumpet-shaped pipe is provided on the top of the trumpet-shaped pipe, two small tubes are provided on the cylindrical pipe, and the two small tubes are respectively connected to the cylindrical pipe. An internal circuit is installed inside the cylindrical pipe, and a double-pin electrode is connected to the bottom of the internal circuit.

[0008] Furthermore, the sensor is installed on the bottom of the aircraft hull through a cylindrical pipe, with the large mouth of the trumpet-shaped pipe facing forward along the course, and the small mouth of the trumpet-shaped pipe facing backward along the course.

[0009] Furthermore, the outlets of the two small tubes are oriented in the same direction as the small opening of the trumpet-shaped pipe, that is, toward the rear along the course.

[0010] Furthermore, the internal circuit includes an adjustable resistor, a sensor power supply, a relay and a capacitor. Any one electrode piece of the double-foot electrode is connected to the adjustable resistor, the adjustable resistor is connected to the aircraft surface status indication system through a signal cable, the other electrode piece of the double-foot electrode is connected to the relay, the positive pole of the sensor power supply is connected to the aircraft surface status indication system, and the negative pole is also connected to the aircraft surface status indication system through the relay, and the capacitor is connected in parallel at both ends of the relay.

[0011] Furthermore, the outer surface of the internal circuit is covered with a waterproof shell.

[0012] The method for a sensor used for collecting water test flight data of an amphibious aircraft is based on the principle that impure water is conductive, and uses a two-foot electrode to detect whether conductive water exists. When there is water inside the splash-proof housing, the two-foot electrode is connected, the relay is closed, the sensor power supply is connected to the aircraft water surface status indication system, and the sensor power supply outputs a high level to the aircraft water surface status indication system; when there is no water or very little water inside the splash-proof housing, the two-foot electrode is disconnected, the relay is disconnected, the sensor power supply is disconnected from the aircraft water surface status indication system, and the sensor power supply outputs a low level to the aircraft water surface status indication system; the water surface status indication system converts the level signal input by the sensor power supply into a digital signal of 1 or 0, and indicates whether the two-foot electrode is connected or disconnected through the digital signal, further indicating the water surface status of the aircraft during water test flight data collection. The test pilot determines whether the aircraft is connected to water or leaving water based on the digital signal, providing support for data collection work for the aircraft performing water test flight scientific research tasks.

[0013] Furthermore, when the level signal output by the sensor power supply to the aircraft surface status indication system is unstable, a capacitor is connected in parallel to both ends of the relay.

[0014] Furthermore, when the sensitivity of the level signal output by the sensor power supply to the aircraft surface status indication system is low, the sensitivity of the output level signal is improved by adjusting the resistance value of the adjustable resistor.

[0015] The beneficial effects of the present invention include providing a sensor and method for collecting data from amphibious aircraft on-water flight tests. The sensor for collecting data from water flight tests is based on the principle that impure water is conductive. It uses two-legged electrodes to detect the presence of conductive water. In the presence of water, the two-legged electrodes are connected, and in the absence of water, the two-legged electrodes are disconnected. By converting the electrical signal into a digital signal to indicate whether the electrodes are connected or disconnected, the sensor can be used to indicate the water surface status when the aircraft is collecting data from water flight tests. At the same time, the pilot can determine whether the aircraft is entering or leaving the water based on the signal, providing support for the aircraft to perform data collection for water flight test scientific research tasks. The sensor can be installed on the bottom of the amphibious aircraft, but the specific installation location and installation method are determined based on the actual situation of the aircraft. At the same time, when the amphibious aircraft takes off, a large amount of splashing will be generated on the water surface. To prevent the occurrence of false signals due to water contact, a splash-proof housing is used to prevent false signals. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the splash-proof housing of the sensor for collecting water test flight data of the present invention. Figure 1 ;

[0017] Figure 2 This is a schematic diagram of the splash-proof housing of the sensor for collecting water test flight data of the present invention. Figure 2 ;

[0018] Figure 3 This is a schematic diagram of the double-foot electrode shape of the sensor for collecting water test flight data of the present invention;

[0019] Figure 4 This is a schematic diagram of the installation position of the two-legged electrodes of the sensor for collecting water test flight data of the present invention;

[0020] Figure 5 This is a schematic diagram of the internal circuit of a sensor for collecting water test flight data according to the present invention;

[0021] Among them, 1. trumpet-shaped pipe, 2. cylindrical pipe, 3. small tube, 4. internal circuit, 5. double-foot electrode. DETAILED DESCRIPTION

[0022] The following is a further detailed description of the specific embodiments of the present invention, such as the shapes and structures of the various components involved, the relative positions and connection relationships between the various parts, the functions and working principles of the various parts, the manufacturing process and the operation and use methods, etc., through the description of the embodiments with reference to the accompanying drawings, so as to help those skilled in the art to have a more complete, accurate and in-depth understanding of the concept and technical solution of the present invention:

[0023] One embodiment of the present invention is a sensor for collecting water test flight data of an amphibious aircraft, comprising a splash-proof housing, an internal circuit, and two-foot electrodes.

[0024] Splash-proof housing Figure 1 、 2 As shown, it includes a trumpet-shaped pipe 1, which is arranged horizontally. A cylindrical pipe 2 connected to the trumpet-shaped pipe 1 is provided on the top of the trumpet-shaped pipe 1. The cylindrical pipe 2 is arranged perpendicular to the trumpet-shaped pipe 1. This makes it convenient to install the sensor to the bottom of the aircraft hull through the cylindrical pipe 2. The trumpet-shaped pipe 1 is parallel to the water surface, which can more accurately determine whether the aircraft hull has left the water surface.

[0025] like Figure 1 、 2 As shown, two small tubes 3 are provided on the cylindrical pipe 2, and the two small tubes 3 are respectively connected to the cylindrical pipe 2. The two small tubes 3 are also kept parallel to the water surface. When too much water enters the trumpet-shaped pipe 1 and the cylindrical pipe 2, the two small tubes 3 can discharge the excess water from the inside of the sensor structure. The outlets of the two small tubes 3 are set at the rear of the course, and will not be affected by wind resistance during drainage, so that the excess water can be better discharged.

[0026] like Figure 4 As shown, an internal circuit 4 is installed inside the cylindrical pipe 2. The internal circuit 4 is bonded to the inner wall of the cylindrical pipe 2 by bonding. The internal circuit 4 is installed at the upper end of the cylindrical pipe 2, and the lower end is used to install a double-foot electrode 5, which is connected to the internal circuit 4.

[0027] In the present invention, a mounting base can also be included, which is installed on the top of the cylindrical pipe 2 of the sensor. The entire sensor structure is installed to the bottom of the hull through the mounting base and can be installed in a detachable manner such as screws, which is convenient for subsequent replacement and maintenance of the sensor. After the installation is completed, the large mouth of the trumpet-shaped pipe 1 faces forward along the course, and the small mouth of the trumpet-shaped pipe 1 faces backward along the course. The outlets of the two small tubes 3 are oriented in the same direction as the small mouth of the trumpet-shaped pipe 1, both facing backward along the course.

[0028] like Figure 5 As shown, the internal circuit 4 includes an adjustable rheostat, a sensor power supply, a relay and a capacitor. Any one electrode piece of the double-foot electrode 5 is connected to the adjustable rheostat, and the adjustable rheostat is connected to the aircraft surface status indication system through a signal cable. The other electrode piece of the double-foot electrode 5 is connected to the relay. The positive electrode of the sensor power supply is connected to the aircraft surface status indication system, and the negative electrode is also connected to the aircraft surface status indication system through the relay. The capacitor is connected in parallel at both ends of the relay. The internal circuit determines whether the aircraft hull has left the water surface by judging the level signal provided by the sensor power supply to the aircraft surface status indication system.

[0029] When an amphibious aircraft is about to leave the water during takeoff, the amount of water entering the large opening of trumpet-shaped pipe 1 gradually decreases. Due to the guidance of the small opening of trumpet-shaped pipe 1, the amount of water between two-legged electrodes 5 changes accordingly, and the impedance between two-legged electrodes 5 changes. Two-legged electrodes 5 are connected to internal circuit 4. When the impedance changes, the voltage at the two trigger terminals of the relay changes. When the resistance of the adjustable rheostat is adjusted to a certain value, the relay closes, and the sensor outputs a high-voltage signal. The capacitor connected to the relay stabilizes the sensor output signal, and the adjustable rheostat adjusts the sensitivity of the sensor output.

[0030] In the present invention, the outer surface of the internal circuit 4 is covered with a waterproof shell. The waterproof shell can be a protective shell made of a flexible material, such as a shell made of silicone, plastic and other materials, or a layer of waterproof material coating can be set on the outside of the internal circuit 4 to protect the components of the internal circuit 4 from being damaged due to water ingress.

[0031] The method for detecting whether an aircraft leaves the water surface using the sensor of the present invention is as follows:

[0032] Based on the principle that non-pure water can conduct electricity, a two-foot electrode 5 is used to detect whether there is conductive water. When there is water inside the splash-proof shell, the two-foot electrode 5 is connected, the relay is closed, the sensor power supply is connected to the aircraft water surface status indication system, and the sensor power supply outputs a high level to the aircraft water surface status indication system; when there is no water or very little water inside the splash-proof shell, the two-foot electrode 5 is disconnected, the relay is disconnected, the sensor power supply is disconnected from the aircraft water surface status indication system, and the sensor power supply outputs a low level to the aircraft water surface status indication system; the water surface status indication system converts the level signal input by the sensor power supply into a digital signal 1 or 0, and indicates whether the two-foot electrode 5 is connected or disconnected through the digital signal, and further indicates the water surface status of the aircraft during water test flight data collection. The test pilot determines whether the aircraft is connected to water or leaving water based on the digital signal, providing support for the aircraft to perform water test scientific research mission data collection work.

[0033] When the level signal output by the sensor power supply to the aircraft surface status indication system is unstable, the capacitor is connected in parallel to both ends of the relay. When the sensitivity of the level signal output by the sensor power supply to the aircraft surface status indication system is low, the sensitivity of the output level signal is improved by adjusting the resistance value of the adjustable resistor.

[0034] Specifically, the signals output by the sensors used to collect data from the water test flight include the following processes:

[0035] Step 1: When the aircraft is stationary and gliding at low speed on the water surface, the amount of water between the two-foot electrodes 5 is large, the impedance is small, the relay is closed, and the sensor outputs a high voltage;

[0036] Step 2: When the aircraft is gliding on the water surface at high speed, the aircraft is about to leave the water surface, the amount of water between the two-foot electrodes 5 decreases, and the impedance between the two-foot electrodes 5 gradually increases. When the water amount decreases to a certain level, the relay pops open and the sensor outputs a low voltage;

[0037] Step 3: When the aircraft completely leaves the water surface, there is almost no water between the electrodes 5 of the two feet, the impedance between the electrodes 5 of the two feet is large, the relay pops open, and the sensor outputs a low voltage.

[0038] The present invention is described above by way of example in conjunction with the accompanying drawings. It is obvious that the specific implementation of the present invention is not limited to the above-mentioned method. As long as various non-substantial improvements are made using the method concept and technical solution of the present invention, or the concept and technical solution of the present invention are directly applied to other occasions without improvement, they are all within the scope of protection of the present invention.

Claims

1. A sensor for collecting water test flight data of amphibious aircraft, characterized in that: The invention comprises a splash-proof shell, wherein the splash-proof shell comprises a trumpet-shaped pipe, a cylindrical pipe connected to the trumpet-shaped pipe is provided on the top of the trumpet-shaped pipe, two small tubes are provided on the cylindrical pipe, the two small tubes are connected to the cylindrical pipe respectively, an internal circuit is installed inside the cylindrical pipe, and a two-pin electrode is connected to the bottom of the internal circuit; the sensor is installed at the bottom of the aircraft hull through the cylindrical pipe, the large mouth of the trumpet-shaped pipe faces forward along the course, and the small mouth of the trumpet-shaped pipe faces backward along the course; the outlets of the two small tubes face the same direction as the small mouth of the trumpet-shaped pipe, that is, both face backward along the course; the internal circuit comprises an adjustable resistor, a sensor power supply, a relay and a capacitor Any one electrode piece of the double-foot electrode is connected to an adjustable rheostat, which is connected to the aircraft surface status indication system through a signal cable. The other electrode piece of the double-foot electrode is connected to a relay. The positive electrode of the sensor power supply is connected to the aircraft surface status indication system, and the negative electrode is also connected to the aircraft surface status indication system through a relay. The capacitor is connected in parallel at both ends of the relay. When the level signal output by the sensor power supply to the aircraft surface status indication system is unstable, the capacitor is connected in parallel to both ends of the relay. When the sensitivity of the level signal output by the sensor power supply to the aircraft surface status indication system is low, the sensitivity of the output level signal is improved by adjusting the resistance value of the adjustable rheostat.

2. The sensor for collecting water test flight data of an amphibious aircraft according to claim 1, characterized in that: The outer surface of the internal circuit is covered with a waterproof shell.

3. The method for collecting data of an amphibious aircraft water test flight using a sensor according to any one of claims 1 to 2, characterized in that: Based on the principle that impure water can conduct electricity, a two-foot electrode is used to detect whether there is conductive water. When there is water inside the splash-proof shell, the two-foot electrode is connected, the relay is closed, the sensor power supply is connected to the aircraft water surface status indication system, and the sensor power supply outputs a high level to the aircraft water surface status indication system; when there is no water or very little water inside the splash-proof shell, the two-foot electrode is disconnected, the relay is disconnected, the sensor power supply is disconnected from the aircraft water surface status indication system, and the sensor power supply outputs a low level to the aircraft water surface status indication system; the water surface status indication system converts the level signal input by the sensor power supply into a digital signal 1 or 0, and indicates whether the two-foot electrode is connected or disconnected through the digital signal, and further indicates the water surface status of the aircraft during water test flight data collection. The test pilot determines whether the aircraft is connected to water or leaving water based on the digital signal, providing support for the aircraft to perform data collection work for water test flight scientific research tasks.

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