Overwater anti-sinking emergency control system for water aircraft

Abstract

The utility model discloses an on-water anti-sinking emergency control system for a water surface aircraft, which comprises a controller, a plurality of water leakage sensors arranged in a fuselage of the water surface aircraft and used for detecting the water seepage state inside the water surface aircraft, and a damage detection device used for detecting whether the fuselage is damaged or not, the controller can receive signals of the water leakage sensor and the damage detection device in real time, and when the water leakage sensor signal detected by the controller indicates that water enters the water surface aircraft and the damage detection device signal indicates that the bottom of the fuselage of the water surface aircraft is damaged; the controller controls the inflation device to inflate the air bag connected to the water surface aircraft body so that the water surface aircraft can float. The system is installed on the aircraft, can rapidly detect whether the aircraft enters water or not, rapidly works after the aircraft body enters water, prevents the aircraft from further entering water and sinking, improves the take-off and landing safety of the aircraft on the water surface, and reduces the loss caused by water entering and sinking of the aircraft.

Description

Technical Field

[0001] The utility model belongs to the technical field of water surface aircrafts, and particularly relates to an emergency control system for preventing water surface aircrafts from sinking. Background Art

[0002] When a water surface aircraft takes off and lands on water, due to various reasons, there is a risk of damage to the aircraft body during the takeoff and landing stage. Since the aircraft floats on the water surface, after the bottom is damaged, water will enter the aircraft body, and in severe cases, it will even cause the entire aircraft to sink to the bottom of the water.

[0003] Generally, for existing single-hull water surface aircrafts, anti-sinking designs are carried out from the fuselage structure, and multi-section sealed cabins are used for waterproof design, that is, multiple sealed cabins are used at the bottom of the lower cabin. When the water impact load is too large during the water landing of the aircraft or other reasons cause damage to the lower part of the fuselage and water enters the aircraft body, the water will only enter a certain section of the sealed cabin, and the other intact sealed cabins will not continue to let water in due to being separated, thus ensuring that the aircraft still has sufficient buoyancy on the water, and further preventing the aircraft from continuing to sink, which can effectively reduce the economic losses caused by the entry of water into the aircraft body and equipment.

[0004] For existing common double-float water surface aircrafts, sealed cabin structures are also designed in the floats. Even if there is a small damage to the floats, like the single-hull aircraft, the sealed cabins of the floats still have buoyancy and will not let water in completely to cause the aircraft to lose buoyancy.

[0005] For some single-hull water surface aircrafts, due to limited internal space utilization of the fuselage size or other reasons, effective sealed cabins cannot be designed. When water enters the aircraft body after the bottom is damaged, ground operators cannot immediately determine whether the aircraft has taken in water, resulting in the inability to carry out emergency rescue in a timely manner. If the aircraft takes in a large amount of water, it is necessary for the surrounding support personnel to approach the aircraft in need of rescue by boat and then use ropes for rescue. This rescue process is relatively complex, requires high personnel quality, and has poor timeliness.

[0006] Particularly, for unmanned water surface aircrafts, when the aircraft touches down on the water surface, due to the influence of wind and water surges, and the control effect of the unmanned flight control system, the state of the aircraft during takeoff and touchdown is not stable, resulting in the bottom of the aircraft hitting the water surface heavily, thus causing the aircraft body to crack, water seepage to occur, and there is a further risk of sinking. Since the operators of general unmanned aircrafts are on the ground or on a boat at a certain distance nearby, and the aircraft touches down on the water surface, they cannot rush to the scene to check the state of the aircraft in a timely manner, which is very likely to delay the rescue opportunity. In addition, even if there are emergency rescue personnel around, since the damage is generally at the bottom of the aircraft, people cannot immediately know from the naked eye that the bottom of the aircraft body is cracked. By the time it is found that the aircraft is starting to sink, the rescue difficulty will increase greatly, resulting in the sinking of the aircraft.

[0007] In addition, the design of externally hanging buoyancy devices on aircraft is commonly used on conventional helicopters and multi-rotor aircraft, generally for use in water takeoffs and landings after modification. However, this will affect the external shape and flight performance of the aircraft, and it is not suitable for all types of aircraft. Summary of the Invention

[0008] Purpose of the Invention

[0009] Aiming at the problem that during the normal flight of a water surface aircraft, especially during the test flight phase, landing or other reasons may cause damage to the fuselage, resulting in the water surface aircraft sinking in water, the present invention provides an emergency anti-sinking control system for water surface aircraft on water.

[0010] Technical Solution of the Invention

[0011] An emergency anti-sinking control system for water surface aircraft on water includes a controller, a plurality of leakage sensors arranged inside the fuselage of the water surface aircraft for detecting the internal water seepage state of the water surface aircraft body, and a damage detection device for detecting whether the fuselage is damaged. The controller can receive the signals of the leakage sensors and the damage detection device in real time. When the signal of the leakage sensor detected by the controller indicates that water has entered the water surface aircraft and the signal of the damage detection device shows that the bottom of the water surface aircraft fuselage is damaged, the controller controls the inflation device to inflate the airbag connected to the water surface aircraft fuselage to make the water surface aircraft float.

[0012] Preferably, leakage sensors are arranged at multiple different heights inside the fuselage of the water surface aircraft.

[0013] Preferably, the damage detection device adopted includes a strain gauge and a resistance wire.

[0014] Preferably, the damage detection device is arranged in the middle and front of the inner bottom surface of the water surface aircraft fuselage.

[0015] Preferably, the inflation device includes a compressed gas tank fixed inside the fuselage of the water surface aircraft. The compressed gas tank is connected to the airbag through a trachea, and the controller controls the opening or closing of the compressed gas tank by controlling the valve on the compressed gas tank.

[0016] Preferably, a one-way valve is arranged on the trachea.

[0017] Preferably, the airbag in the non-inflated state is connected to the bottom side of the water surface aircraft through a rope.

[0018] Preferably, for an unmanned water surface aircraft, when the signal of the leakage sensor detected by the controller indicates that water has entered the water surface aircraft and the signal of the damage detection device shows that the bottom of the water surface aircraft fuselage is damaged, the control system can generate a water inlet warning and transmit the warning to the ground station through the on-board data link.

[0019] Preferably, the controller also determines whether the surface vehicle is on the water surface by receiving the height signal of the surface vehicle.

[0020] Preferably, the height signal of the surface vehicle is obtained by a height measurement system on board the surface vehicle.

[0021] Advantages of the present utility model: The system installed on the aircraft can quickly detect whether the aircraft is flooded, and after the fuselage of the aircraft is flooded, it can work quickly to prevent the aircraft from further flooding and sinking, improve the safety of takeoff and landing of the surface vehicle, and reduce the losses caused by the flooding and sinking of the aircraft. It can avoid underwater salvage, reduce the risk of water ingress into on-board electronic equipment, etc., and reduce property losses. Description of the Drawings

[0022] Figure 1 It is a block diagram of the composition of an emergency anti-sinking control system for a surface vehicle of the control system of the present utility model.

[0023] Figure 2 It is the control logic of an emergency anti-sinking control system for a surface vehicle of the control system of the present utility model. Detailed Embodiments

[0024] The present utility model is realized by the following technical solutions.

[0025] An emergency anti-sinking control system for a surface vehicle includes a power supply, a water leakage sensor, a damage detection device, a controller, an inflation device, and an airbag.

[0026] Among them, the power supply is used to provide independent power supply for the controller, water leakage sensor, valve, etc. in this control system, and generally uses battery power supply.

[0027] The water leakage sensor is used to detect the water seepage state inside the body of the surface vehicle. A plurality of water leakage sensors are attached to the inner bottom of the fuselage, and the water leakage sensors can be attached at different heights of the bottom of the ship to feedback on different water inlet heights.

[0028] The damage detection device is used to more accurately judge the water inlet situation. The damage detection device is a sensor for detecting the damage of the fuselage attached to the middle and front parts of the inner bottom surface of the fuselage. The sensor is a strain gauge or a resistance wire, etc. When there is a huge deformation or damage at the part of the bottom of the ship where the damage detection device is set, the signal of the strain gauge changes compared with the whole vehicle state, or the resistance wire breaks causing the signal to change. At this time, the controller can judge that the fuselage is damaged according to the signal of the damage detection device.

[0029] The controller is used to collect the signals of the water leakage sensor and the damage detection device, and make a judgment based on the above signals whether to control the inflation device to start inflating.

[0030] The inflating device is used to inflate the airbag. The inflating device includes a compressed gas cylinder and an air pipe. The compressed gas cylinder is installed and fixed inside the airframe. Compressed gas is stored in the gas cylinder. After the controller controls the valve on the compressed gas cylinder to open, the airbag is supplied with gas through the compressed gas cylinder. A one-way valve is provided on the pipeline between the compressed gas cylinder and the airbag to ensure that the gas is supplied to the airbag unidirectionally and the gas will not flow back.

[0031] After the airbag is inflated, it floats on the water surface, providing buoyancy by itself. The airbag is connected to the fuselage by a rope to prevent the aircraft from sinking further. When the airbag is in the non-inflated state, it is compressed and installed on the side of the bottom of the airframe without affecting the aerodynamic and hydrodynamic shapes of the aircraft. The number of airbags depends on the actual shape of the aircraft to ensure that the aircraft can remain horizontal relying on the airbags on the water.

[0032] The controller also determines whether the surface aircraft is on the water surface by receiving the height signal of the surface aircraft. The height signal of the surface aircraft can be obtained through the height measurement system on board the surface aircraft, such as GPS, Beidou, or radio altimeter, millimeter wave radar, etc.

[0033] The working logic of this control system is that when it is detected and determined by the altimeter that the aircraft is on the water surface, and the water detection sensor detects water ingress, and at the same time the airframe damage detection device detects airframe damage, and it is determined that there is a risk of further sinking and sinking of the surface aircraft, the control system makes the control device work, and the compressed gas cylinder releases compressed air to the airbags around the fuselage through the connecting air pipe. The airbags instantaneously expand when inflated, and the buoyancy of the airbags is sufficient to prevent the aircraft from sinking.

[0034] For an unmanned surface aircraft, the controller generates a water ingress warning and transmits the warning to the ground station through the on-board data link. The command personnel notify the personnel to rescue the aircraft, and at the same time the emergency control system starts to work to inflate the airbags to make the aircraft float.

[0035] The above embodiments are only for illustrating the technical concept and features of the present invention. The purpose is to enable those skilled in the art to understand the content of the present invention and implement it accordingly, and it cannot be used to limit the protection scope of the present invention. Any equivalent transformation or modification made according to the spirit and essence of the present invention should be covered within the protection scope of the present invention. The technologies, shapes, and structures not described in detail in the present invention are all well-known technologies.

Claims

1. An emergency control system for preventing a water surface vehicle from sinking in water, characterized in that, It includes a controller, several leakage sensors disposed inside the fuselage of the surface vehicle for detecting the internal water seepage state of the surface vehicle body, and a damage detection device for detecting whether the fuselage is damaged. The controller can receive the signals of the leakage sensors and the damage detection device in real time. When the signal of the leakage sensor detected by the controller indicates that water has entered the surface vehicle and the signal of the damage detection device shows that the bottom of the surface vehicle fuselage is damaged, the controller controls the inflation device to inflate the airbag connected to the surface vehicle fuselage to make the surface vehicle float.

2. The emergency control system for preventing sinking of a surface aircraft on water according to claim 1, characterized in that Leakage sensors are disposed at multiple different heights inside the fuselage of the surface vehicle.

3. The emergency control system for preventing sinking of a water surface aircraft according to claim 1, wherein, The adopted damage detection device includes a strain gauge and a resistance wire.

4. The emergency control system for preventing a watercraft from sinking on water of a watercraft as claimed in claim 1, wherein, The damage detection device is disposed in the middle and front of the inner bottom surface of the surface vehicle fuselage.

5. The emergency control system for preventing water surface aircraft from sinking on water according to claim 1, characterized in that, The inflation device includes a compressed gas tank fixed inside the surface vehicle fuselage. The compressed gas tank is connected to the airbag through an air pipe. The controller controls the opening or closing of the compressed gas tank by controlling the valve on the compressed gas tank.

6. The water anti-sinking emergency control system of a water surface aircraft according to claim 5, characterized in that, A one-way valve is disposed on the air pipe.

7. The water anti-sinking emergency control system of a watercraft as claimed in claim 5, wherein The non-inflated airbag is connected to the bottom side of the surface vehicle through a rope.

8. The emergency control system for preventing a water surface aircraft from sinking on water according to claim 1, characterized in that, For an unmanned surface vehicle, when the signal of the leakage sensor detected by the controller indicates that water has entered the surface vehicle and the signal of the damage detection device shows that the bottom of the surface vehicle fuselage is damaged, the control system can generate a water ingress warning and transmit the warning to the ground station through the on-board data link.

9. The water anti-sinking emergency control system for a water surface aircraft according to claim 1, characterized in that, The controller also judges whether the surface vehicle is on the water surface by receiving the height signal of the surface vehicle.

10. The emergency control system for preventing the water surface aircraft from sinking on water according to claim 9, characterized in that, The height signal of the surface vehicle is obtained through the height measurement system on board the surface vehicle.

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