CN113978742B - Oiling system, water oiling aircraft and oiling method - Google Patents
Oiling system, water oiling aircraft and oiling method Download PDFInfo
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- CN113978742B CN113978742B CN202111240883.XA CN202111240883A CN113978742B CN 113978742 B CN113978742 B CN 113978742B CN 202111240883 A CN202111240883 A CN 202111240883A CN 113978742 B CN113978742 B CN 113978742B
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 title claims abstract description 107
- 238000000034 method Methods 0.000 title claims abstract description 38
- 239000000446 fuel Substances 0.000 claims abstract description 20
- 239000000945 filler Substances 0.000 claims abstract description 12
- 229910000831 Steel Inorganic materials 0.000 claims description 17
- 239000010959 steel Substances 0.000 claims description 17
- 238000006073 displacement reaction Methods 0.000 claims description 15
- 230000008569 process Effects 0.000 claims description 14
- 230000001133 acceleration Effects 0.000 claims description 11
- 238000007789 sealing Methods 0.000 claims description 8
- 230000008859 change Effects 0.000 claims description 6
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 239000003921 oil Substances 0.000 description 87
- 230000001276 controlling effect Effects 0.000 description 11
- 239000002828 fuel tank Substances 0.000 description 11
- 239000000295 fuel oil Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 210000001503 joint Anatomy 0.000 description 4
- 238000005096 rolling process Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- 238000003860 storage Methods 0.000 description 3
- 230000002411 adverse Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 210000002445 nipple Anatomy 0.000 description 2
- 230000036544 posture Effects 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Classifications
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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
- B64D39/00—Refuelling during flight
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Loading And Unloading Of Fuel Tanks Or Ships (AREA)
Abstract
The invention discloses a refueling system, a water refueling aircraft and a refueling method. Comprising the following steps: a fueling tank (1) for storing fuel to be supplied to the helicopter; a fueling control system (2) for controlling start/stop of fueling; a fueling line (12) for delivering fuel; a filler line reel (4) for reeling in/unreeling a filler line (12); a refuel line reel control system (3) for controlling the refuel line reel (4) to reel/reel the refuel line (12); the pressure refueling pipeline connector (9) is arranged at the tail end of the externally-placed refueling pipeline (12) and is used for realizing the connection between the refueling pipeline (12) and a helicopter oil receiving system. The invention adopts the mode that the seaplane flies to a preset sea area, floats on the sea surface or sails at a low speed and flies cooperatively with the helicopter to finish the aerial refueling of the helicopter, thereby reducing the operation difficulty of the aerial refueling of the helicopter and improving the timeliness and economy of the refueling.
Description
Technical Field
The invention belongs to the technical field of helicopter aerial refueling, and particularly relates to a refueling system, a water refueling aircraft and a refueling method.
Background
The helicopter can take off and land independently of a runway, can hover in the sky, is widely used in various aerial work activities, and particularly plays an irreplaceable role in various rescue activities. Due to the flight mode characteristics and the limit of the volume of the oil tank, the helicopter utilizes the self oil tank to fly for a short range and a short dead time, and the flight radius is about 200-300 km generally, so that the effectiveness of the helicopter in the rescue of middle and high sea maritime is seriously restricted. In order to improve the range and the dead time of the helicopter, a relay oiling means of the helicopter is required to be provided.
At present, the following methods are adopted for the development of refueling of a helicopter in the middle and open sea:
a land-based fixed wing aircraft is utilized to refuel a helicopter by adopting a plug-taper pipe type aerial refuel system. This technology has been implemented and applied in the united states, but due to the difficulty of operation and high safety risks, practical applications are not numerous, and other helicopter manufacturers have not followed. The following problems are mainly solved: the method has the advantages that the land-based fixed-wing aircraft has high flight speed, the helicopter has low flight speed, the speed of the Liu Jigu fixed-wing aircraft and the helicopter are difficult to match in the collaborative oiling process, and the requirement on the pilot to control the aircraft speed is high and the difficulty is high. The swing radius of the main rotor wing of the helicopter is large, the oil receiving plug on the helicopter cannot be arranged above the rotor wing, the oil receiving plug can be abutted with the refueling taper sleeve of the land-based fixed-wing aircraft only by extending far from the fuselage below the main rotor wing, the adverse effects on the heading and pitching stability of the helicopter caused by transverse force generated when the oil receiving plug is abutted with the refueling taper sleeve are quite remarkable, and the difficulty of controlling the attitude of the aircraft by a helicopter pilot is greatly increased. According to the method, the downward gas washing flow interference generated by the main rotor wing of the helicopter is caused, the positions, the directions and other postures of the refueling taper sleeve are changed all the time, in the butt joint process, the difficulty of the butt joint of the oil receiving plug and the refueling taper sleeve of the helicopter is further increased, the transverse force on the oil receiving plug is also increased, and adverse effects are further brought to the heading and pitching stability of the helicopter. The change of the postures of the oiling taper sleeve, such as position, direction and the like, causes the irregular swing of the oiling pipeline, so that the possibility of collision between the oiling pipeline and the main rotor wing of the helicopter is increased, and the accident that the main rotor wing of the helicopter cuts the oiling pipeline occurs for many times in actual oiling.
And (3) filling the helicopter in a mode of establishing a fuel oil replenishing point on the island. The technology is a more traditional mode, is mature and has small risk, but is not used much at present due to large construction investment, low use efficiency and poor economy. The following problems are mainly solved: the method has the advantages that the method is wide in open sea areas in China, if the refueling coverage of a helicopter is ensured, the quantity of island reef supply points to be built is large, and although resources required by each island reef supply point are fewer, the total early construction cost is quite large. The maintenance cost after the use of the ground and control system is also high in enterprise due to the fact that the quantity is large, the natural environment is bad, the island reef supply points are scattered, the distance between the island and the island is large, and the island reef supply points are supplied with the island by themselves inevitably and long in period and huge in cost due to the fact that the distance is long. The number of times and the place distribution of the rescue tasks are relatively dispersed by lifting and developing the four sides of the island, so that the utilization rate of a plurality of island reef supplementing points is quite low, and the total economical efficiency is reduced.
And (5) refueling from the large ship through the pipeline in a hovering refueling mode. The technology is realized and applied abroad, the actual machine operation is realized in China, but the helicopter cannot be ensured to be refueled timely and effectively, and the following problems are mainly solved: the method comprises the steps that a large number of ships can perform the fuel oil supply task of a helicopter on the sea for a long time in China, and large-scale coverage is difficult to achieve, so that when the helicopter needs to be refueled, available refueled ships are not available around the ships. The marine accident occurs when the sea area is far away from the refueling ship, the marine accident cannot reach the sea area in time, quick deployment is difficult to realize, and finally the helicopter cannot supply fuel in time.
Disclosure of Invention
The purpose of the invention is that: a fueling system, a water fueling aircraft, and a fueling method are provided. The invention adopts the mode that the seaplane flies to a preset sea area, floats on the sea surface or sails at a low speed and flies cooperatively with the helicopter to finish the aerial refueling of the helicopter, thereby reducing the operation difficulty of the aerial refueling of the helicopter and improving the timeliness and economy of the refueling.
The technical scheme of the invention is as follows: a fueling system comprising:
the fuel tank is used for filling fuel and is used for storing fuel filled into the helicopter;
a fueling control system for controlling start/stop of fueling;
a fueling line for delivering fuel;
a refuel line reel for reeling/unreeling the refuel line;
the oiling pipeline reel control system is used for controlling the oiling pipeline reel to reel/unreel the oiling pipeline;
the pressure refueling pipeline connector is arranged at the tail end of the externally-placed refueling pipeline and is used for realizing the connection between the refueling pipeline and a helicopter oil receiving system.
The foregoing refueling system further includes:
the oiling pipe frame follow-up control system is used for controlling the oiling pipe frame to always point to the helicopter oil receiving system;
the oiling pipe frame is used for supporting an externally-placed oiling pipe line close to the oiling system;
the oiling pipeline telescopic follow-up system is used for compensating displacement fluctuation caused by the change between the oiling system and the helicopter oil receiving system in the oiling process;
the oiling pipe frame, the oiling pipe frame follow-up control system and the oiling pipe line telescopic follow-up system act together to finally realize the stress relief of the externally-discharged oiling pipe line.
The foregoing refueling system further includes:
and the oiling pipeline safety device is used for timely disconnecting the connection between the oiling system and the helicopter oil receiving system when the stress borne by the externally-placed oiling pipeline exceeds the preset safety stress.
In the foregoing fueling system, the fueling pipeline safety device is structured as follows: a stress concentration groove arranged on the externally placed oil filling pipeline; during the refueling process, when the stress of the externally placed refueling pipeline exceeds the preset safety stress, the externally placed refueling pipeline is disconnected at the stress concentration groove.
In the oiling system, the self-sealing valves are arranged on the oiling pipelines at the two ends of the stress concentration groove.
An aircraft refueled on water is provided with the refueled system.
In the above-mentioned water refueling plane, the refueling system is installed in the middle of the body of the water refueling plane, and the middle of the body of the water refueling plane is provided with the flap for the unfolding work of the refueling system.
The refueling method of the above-mentioned water refueling aircraft comprises the following steps:
a) The water refueling aircraft reaches a preset sea area, and the helicopter to be refueled reaches the upper part of the preset sea area and is positioned above the water refueling aircraft;
b) The helicopter cooperates with the water refueling plane to ensure that the position of the helicopter and the water refueling plane are relatively fixed;
c) The oiling pipeline of the oiling system in the water oiling aircraft is outwards put through the oiling pipeline reel, so that the pressure oiling pipeline nozzle is connected with the helicopter oil receiving system, and oiling can be performed;
d) And after the oiling is completed, the pressure oiling pipeline nozzle is uncoupled from the oil receiving system of the helicopter, and the helicopter is uncoupled from the water oiling plane.
In the step c of the method for fueling the water-based fueling aircraft, the method for connecting the pressure fueling pipeline nozzle with the helicopter fueling receiving system is as follows: the helicopter lowers the hoisting steel rope to the position of a refueling system of the water refueling aircraft; the pressure oiling pipeline connector is fixed on the hoisting steel rope, and after the helicopter withdraws the hoisting steel rope, the pressure oiling pipeline connector is inserted into the helicopter oil receiving system to realize connection.
In the step c of the refueling method of the above-mentioned water refueling aircraft, in the refueling process, the following control system of the refueling pipeline frame senses pitching signals, rolling signals and helicopter azimuth signals given by the water refueling aircraft and controls the azimuth of the refueling pipeline frame to stably point to the helicopter oil receiving system; the oiling pipeline telescopic follow-up system senses axial displacement and axial acceleration signals of the oiling pipeline, which are acquired by a displacement sensor and an acceleration sensor arranged on the oiling pipeline frame, and controls the extension/retraction of the oiling pipeline on the oiling pipeline frame; ensuring the stress of the oiling pipeline within a safe range until the oiling amount meets the requirement.
The invention has the advantages that: the invention adopts the mode that the seaplane flies to a preset sea area, floats on the sea surface or sails at a low speed and flies cooperatively with the helicopter to finish the aerial refueling of the helicopter, thereby reducing the operation difficulty of the aerial refueling of the helicopter and improving the timeliness and economy of the refueling.
The invention adopts the way that the oil filling system is arranged on the water plane, and the oil filling system is connected with the oil receiving system of the helicopter for filling oil, and the oil filling system is internally provided with a system for relieving the stress of the oil filling pipeline and a safety device for ensuring the oil filling safety.
According to the invention, the helicopter and the water refueling plane are cooperated, so that the helicopter can timely obtain fuel oil supplement in the middle and high sea areas needing refueling and in the offshore areas far away from the land-based refueling points, and the range and the dead time of the helicopter are effectively improved.
Compared with the traditional plug-taper pipe type air refueling system, the speed matching difficulty between the refueling machine and the oil receiving machine is reduced during refueling, and therefore the operation difficulty and the safety risk are reduced.
According to the invention, the helicopter is positioned above the water refueling aircraft during refueling, so that the interference of the helicopter rotor wing to the refueling process is avoided, and the convenience and safety of refueling operation are further improved.
According to the invention, a fixed fuel oil replenishing facility is not required to be established at sea during oiling, so that compared with a mode of establishing a replenishing point on an island, the hardware investment is reduced, and the use efficiency and the economy are further improved.
The invention can quickly reach the sea area where the helicopter needs to refuel when refuel, overcomes the shortboards which have small number of ships and cannot reach the preset sea area in time, and improves the timeliness and effectiveness of refuel.
The invention designs the oiling pipe frame, the oiling pipe frame follow-up control system and the oiling pipe line telescopic follow-up system, and the oiling pipe frame and the oiling pipe line telescopic follow-up system act together in the oiling process to realize the stress relief of the externally-discharged oiling pipe line; the reliability and the safety of the oiling process are improved.
The invention designs the oil filling pipeline safety device, when the stress overload on the oil filling pipeline exceeds the preset safety stress, the oil filling pipeline can be automatically disconnected at the oil filling pipeline safety device, and in the mode, the safety accident that the water oil filling aircraft and the helicopter are mutually pulled to finally cause the aircraft to be damaged due to the fact that the connection between the water oil filling aircraft and the helicopter cannot be timely disconnected in the oil filling process can be prevented; meanwhile, the self-sealing valves on the two sides of the oil filling pipeline safety device are automatically closed when disconnected, so that oil leakage is reduced, and environmental pollution is avoided.
The invention designs the independent fuel tank for refueling, which can finish refueling the helicopter without using the self-fuel of the water refueling aircraft, thereby ensuring the range and the endurance of the water refueling aircraft.
The invention designs an independent fueling control system for controlling the starting/stopping of fueling, reduces the control requirement of a pilot of the water fueling aircraft on the fueling system in the fueling process, ensures that the pilot only needs to concentrate on the control of the water fueling aircraft, and improves the safety of the aircraft.
Drawings
Fig. 1 is a principal constitution and operation schematic diagram of the water-based refueling aircraft refueling system of the present invention.
Reference numerals:
1-refuelling fuel tank, 2-refuelling control system, 3-refuelling pipeline reel control system, 4-refuelling pipeline reel, 5-refuelling pipeline frame follow-up control system, 6-refuelling pipeline frame, 7-refuelling pipeline telescopic follow-up system, 8-refuelling pipeline safety device, 9-pressure refuelling pipeline nipple, 10-helicopter pressure refuelling nipple, 11-helicopter fuel tank, 12-refuelling pipeline, 13-stress concentration groove, 14-self-sealing valve.
Detailed Description
The invention is further illustrated by the following figures and examples, which are not intended to be limiting.
Example 1. A fueling system, see fig. 1, comprising:
a fueling tank 1 for storing fuel to be supplied to the helicopter;
a fueling control system 2 for controlling start/stop of fueling;
a fueling line 12 for delivering fuel;
a filler line reel 4 for reeling in/unreeling a filler line 12;
a fueling line reel control system 3 for controlling the fueling line reel 4 to reel/reel the fueling line 12;
the pressure refueling pipeline connector 9 is arranged at the tail end of the externally-placed refueling pipeline 12 and is used for realizing the connection of the refueling pipeline 12 and a helicopter oil receiving system.
Further comprises:
the oiling line frame follow-up control system 5 is used for controlling the oiling line frame 6 to always point to the helicopter oiling system;
a filler neck 6 for supporting an outgoing filler neck 12 adjacent the fueling system;
the oiling pipeline telescopic follow-up system 7 is used for compensating displacement fluctuation caused by the change between the oiling system and the helicopter oil receiving system in the oiling process;
the oiling pipe frame 6, the oiling pipe frame follow-up control system 5 and the oiling pipe line telescopic follow-up system 7 are combined to act together, and finally the stress of the externally-discharged oiling pipe line 12 is relieved.
Further comprises:
the refuel line safety device 8 is used for timely disconnecting the connection between the refuel system and the helicopter oil receiving system when the stress on the refuel line 12 which is externally placed exceeds the preset safety stress.
The aforementioned refuel line safety device 8 has the structure: a stress concentration groove 13 provided on the outwardly-disposed refueling line 12; during refueling, the outwardly displaced refuel line 12 breaks at the stress riser 13 when the stresses experienced by the refuel line exceed a predetermined safety stress.
Specifically, self-sealing flaps 14 are provided on the filler pipe line 12 at both ends of the stress concentration tank 13.
An on-water refueling aircraft is provided with the refueling system, and the concrete structure is as follows:
the middle part of the body of the water refuelling aircraft is provided with the refuelling system, and the middle part of the body of the water refuelling aircraft is provided with a flap used for the refuelling system to work.
The refueling method of the above-mentioned water refueling aircraft comprises the following steps:
a) The water refueling aircraft reaches a preset sea area, and the helicopter to be refueled reaches the upper part of the preset sea area and is positioned above the water refueling aircraft;
b) The helicopter cooperates with the water refueling plane to ensure that the position of the helicopter and the water refueling plane are relatively fixed;
c) The refueling pipeline 12 of the internal refueling system of the water refueling aircraft is outwards placed through the refueling pipeline reel 4, so that the pressure refueling pipeline nozzle 9 is connected with the helicopter oil receiving system, and the refueling can be performed;
d) And after the oiling is completed, the pressure oiling pipeline nozzle 9 is uncoupled from the oil receiving system of the helicopter, and the helicopter is uncoupled from the water oiling plane.
In step c, the method for connecting the pressure refueling pipeline nozzle 9 with the helicopter oil receiving system is as follows: the helicopter lowers the hoisting steel rope to the position of a refueling system of the water refueling aircraft; the pressure refueling pipeline connector 9 is fixed on a hoisting steel rope, and after the helicopter withdraws the hoisting steel rope, the pressure refueling pipeline connector 9 is inserted into a helicopter oil receiving system to realize connection.
In the step c, in the oiling process, the oiling pipe frame follow-up control system 5 senses pitching signals, rolling signals and helicopter azimuth signals given by the water oiling machine and controls the azimuth of the oiling pipe frame 6 to stably point to the helicopter oil receiving system; the oiling line telescopic follower system 7 senses axial displacement and axial acceleration signals of the oiling line, which are acquired by a displacement sensor and an acceleration sensor arranged on the oiling line frame 6, and controls the extension/retraction of the oiling line 12 on the oiling line frame 6; ensuring the stress of the oiling pipeline within a safe range until the oiling amount meets the requirement.
Example 2. A water refueled aircraft, see fig. 1, includes a water craft body and a refueled system.
The structure of the seaplane body comprises: the middle part of the water plane body is provided with a cover for the expansion work of the oiling system, and the middle part of the water plane body is provided with the oiling system for oiling the helicopter.
The structure of the oiling system comprises: the device comprises a fuel tank for filling, a filling control system, a filling pipeline reel control system, a filling pipeline frame follow-up control system, a filling pipeline telescopic follow-up system 7, a filling pipeline safety device and a pressure filling pipeline nozzle. The oiling control system controls starting and stopping of oiling; the fueling pipeline is used for delivering fuel; the oiling pipeline reel is used for winding and unwinding the oiling pipeline; the oiling pipe frame, the oiling pipe frame follow-up control system and the oiling pipe frame telescopic follow-up system 7 are jointly used for slowing down the stress of the oiling pipe, so that the phenomenon that the stability and the operability of the water oiling aircraft and the helicopter are affected or the structural damage of the water oiling aircraft and the helicopter is caused is prevented. The oil filling pipeline safety device is used for preventing the connection between the oil filling machine and the oil receiving machine from being disconnected in time when a dangerous situation occurs, and reducing fuel leakage. The pressure refueling pipeline connector is used for connecting a refueling pipeline with a helicopter pressure refueling system.
The oiling mode of the water plane oiling machine comprises the following steps:
the water plane arrives and falls in a preset sea area, and the helicopter arrives above the preset water area.
The helicopter cooperates with the seaplane to ensure the relative position between the helicopter and the seaplane.
The water plane refueling pipeline is connected with the helicopter pressure refueling system.
The water plane refuels to the helicopter, so that the pipeline stress is ensured to be within a safe range until the refuel amount meets the requirement.
The fueling line is disconnected from the helicopter pressure fueling system.
And (3) finishing oiling, and removing coordination between the helicopter and the seaplane.
Example 3. A water powered aircraft, see fig. 1, includes a fueling system and a water powered aircraft body.
A fueling system. The operating principle of the oiling system is as follows: the fuel tank for refueling is connected with the refueling control system by adopting an oil conveying pipeline; the oiling control system is connected with the pressure oiling pipeline connector by adopting an oiling pipeline, and an oiling pipeline safety device is arranged on the oiling pipeline close to the pressure oiling pipeline connector. The refuel line passes through a refuel line reel, a refuel line stand, and a refuel line telescoping follower system 7. Before refueling, a pressure refueling pipeline connector and a helicopter pressure refueling connector are connected. During refueling, fuel in the fuel tank for refueling enters the helicopter fuel tank through the fuel delivery pipeline, the refueling control system, the refueling pipeline safety device, the pressure refueling pipeline connector and the helicopter pressure refueling connector. The refueling power is provided by a refueling control system. In the oiling process, the oiling pipe frame always points to the helicopter, so that the swing between the oiling pipe frame and the helicopter is reduced; the length from the refueling pipeline frame to the refueling pipeline between helicopters is controlled by a refueling pipeline telescopic follow-up system 7 according to the axial displacement and the axial acceleration of the refueling pipeline.
The fuel tank for refueling is used for storing fuel, and is divided into 1 refueling tank and 4 oil storage tanks which are symmetrically arranged near the gravity center of the aircraft, and communicating pipes are arranged between the tanks. The hydraulic oil filling device has the capabilities of single-point pressure oil filling and gravity oil filling, and the pressure oil filling connector is the same as that of a main oil tank of an aircraft. The oil tank is located below the 4 oil storage tanks and is connected with a communicating pipe with a one-way valve in each oil storage tank.
The oiling control system is used for realizing oiling, controlling starting and stopping of oiling, regulating oiling flow and pressure, monitoring the working state of the system and protecting the working of the system according to the requirement. The oiling power adopts an explosion-proof motor to drive an oil pump; a coarse oil filter and a fine oil filter are arranged in the pipeline, so that the pollution degree of the fuel oil is ensured to meet the requirements of the helicopter; pressure sensors are arranged before and after the oil pump and the oil filter; a flowmeter is arranged at the rear end of the oil filling pipe; a safety pipeline is arranged between the oil pump outlet and the fuel tank; the control panel is arranged to monitor the working state of the system, control the starting and stopping of the oil pump, and provide protection of overpressure, oil filter blockage, emergency stop and the like of the system.
The fueling pipeline realizes the connection of a water fueling aircraft fueling system and a helicopter pressure fueling joint and conveys fuel. One end of the hose is connected with an outlet of the oiling control system, the other end of the hose is connected with the pressure oiling pipeline nozzle, and a safety device with a self-sealing valve is arranged on a pipeline close to the pressure oiling pipeline nozzle.
The refuelling pipeline is stored and stored on the water refuelling aircraft by adopting a refuelling pipeline reel, and the refuelling pipeline reel of the current general aircraft pressure refuelling vehicle is adopted.
The oiling pipeline reel control system realizes starting and stopping of the oiling pipeline reel and direction change, and adopts the current general oiling pipeline reel control system of the aircraft pressure oiling vehicle.
The oil filling pipe frame is used for controlling the azimuth of the oil filling pipe. The oil filling pipe frame comprises 4 upright posts and four square frames with different sizes, wherein the upper square frame is smaller, the lower square frame is larger, and the 4 upright posts and the four square frames with different sizes form a truss with a rectangular frustum shape with a small upper part and a large lower part. The lower part of the truss is connected with a base through an electric control device, and the base is fixed on the water plane structure. The oiling pipe frame is provided with three groups of guide wheels, and each group is provided with three guide wheels which are the same and are installed at an angle of 120 degrees; the guide wheel is provided with a groove, and the shape of the groove is coordinated with the shape of the oiling pipeline; the oiling pipeline passes through a cavity formed by surrounding the three guide wheels, and a slight gap exists; the upper part of the oiling pipe frame truss is provided with an oiling pipe line telescopic follow-up system 7.
The oil filling pipe frame follow-up control system senses pitching signals, rolling signals and helicopter azimuth signals given by the water oil filling aircraft, and is provided with a gyro stabilizing device which is cooperated with the electric control device to control and stabilize azimuth direction of the oil filling pipe frame, so that position change of the oil filling pipe frame and the helicopter is reduced, and stress on the oil filling pipe frame is reduced. The electric control device is provided by a water plane.
The oiling line telescopic follow-up system 7 consists of three groups of driving wheels closely contacted with the oiling line and an electric control action device for driving the driving wheels. Each group of driving wheels is provided with three driving wheels which are the same and are installed at an angle of 120 degrees; the driving wheel is provided with a groove, and the shape of the groove is coordinated with the shape of the oiling pipeline; the oiling pipeline passes through a cavity formed by surrounding the three guide wheels; the tension adjusting device is arranged on the driving wheel to ensure that the driving wheel is tightly contacted with the oiling pipeline to generate power for driving the oiling pipeline to stretch out and draw back. The oiling line telescopic follow-up system 7 is also provided with an oiling line displacement sensor, an acceleration sensor and the like for collecting the displacement and the acceleration of the oiling line, and is used for providing control input for an electric control action device of the oiling line telescopic follow-up system 7, controlling the working state of an action part of the oiling line telescopic follow-up system 7 to realize the displacement compensation of the oiling line, and reducing the stress on the oiling line.
When the stress overload on the oiling pipeline exceeds a specified value, a safety device with a self-sealing valve is arranged on a pipeline close to the pressure oiling pipeline connector to work, the connection between the oiling pipeline and the pressure oiling pipeline connector is disconnected, and meanwhile, the oiling pipeline outlet is closed, so that the connection between the oiling machine and the oil receiving machine can not be disconnected in time when a dangerous situation is met, and the fuel leakage is reduced.
A seaplane body. The water plane body is started up according to the use and maintenance requirements of the oil filling system to structurally arrange related covers; an aircraft energy interface is introduced according to the energy requirement of the oiling system, a related information display interface is designed according to the system state display requirement, and a fixed point is designed according to the weight, the gravity center and the installation requirement.
The oil filling mode of the water oil filling aircraft is developed according to the following procedures:
the water refueled aircraft flies to a preset sea area to wait for landing: the water refueling plane receives a command of refueling the helicopter at sea, completes corresponding flight preparation, flies to a preset airspace, judges that the water surface condition meets the requirements of taking off and landing of the water plane and refueling operation, and falls to a preset sea area to wait for the arrival of the helicopter.
An aircraft refueling system for expanding water to refuel: and (3) checking that the state of the oiling system is good, the oil product meets the requirements of the helicopter, opening the oiling system working port cover in the middle of the helicopter body, releasing the fixation of the pressure oiling pipeline nozzle, and expanding the oiling pipeline control system.
Helicopter arrives at specified airspace: the helicopter flies to the appointed airspace according to the command, and the airspace meteorological conditions and the air flow interference between the water refueling aircrafts are judged to accord with the refueling cooperative conditions.
The helicopter and the water refueling plane are cooperated with each other: the helicopter and the water refueled aircraft keep uninterrupted communication and mutual visual observation, and control of the helicopter and the water refueled aircraft is adjusted in a coordinated manner.
The water refueled aircraft emits refueled pipeline: the water refueled aircraft take-up reel control system pays out the refueled line, confirming payout of about 10 meters. Starting the oiling pipeline control system, unfolding the oiling pipeline frame, checking and confirming that the oiling pipeline frame points to the helicopter, and adjusting the oiling pipeline frame in a follow-up way. The oil filling pipeline telescopic follow-up system 7 is started, and the oil filling pipeline telescopic follow-up system is checked and confirmed to work normally and can be adjusted in a follow-up mode.
The oiling pipeline is in butt joint with an oil receiving joint of the helicopter: the helicopter flies to the position about 20 meters above the oil filling pipeline frame of the water oil filling aircraft, and the position relation and the motion state among the helicopter are confirmed to meet the requirements of the lifting pressure oil filling pipeline nozzle. The helicopter starts the winch to put down the lifting steel rope, the water refueling aircraft connects the lifting steel rope with the pressure refueling pipeline connector, the helicopter lifts the pressure refueling pipeline connector, the pressure refueling pipeline connector is in butt joint with the helicopter pressure refueling connector, the connection state is checked to be good, and the lifting steel rope is disconnected with the pressure refueling pipeline connector.
The helicopter is separated from the water refueling plane and kept: the helicopter notifies the water refueled aircraft that the pressure refueled pipeline nozzle is connected, and the water refueled aircraft again confirms that the refueled system, particularly the pipeline control system, works well and feeds back to the helicopter. The helicopter slowly moves to the rear of the side of the water refueling aircraft, reaches a position which is not less than 50 meters away from the rear of the side of the water refueling aircraft, and keeps the position unchanged from the water refueling aircraft.
The helicopter completes the oiling inspection: the helicopter carries out refueling pre-inspection, and notifies the water refueling aircraft that the helicopter can refuel after confirming that the helicopter pressure refueling system is normal.
Starting and fueling of the water fueling aircraft: starting a refueling control system after the water refueling aircraft receives the notification that refueling is possible; the fuel enters the helicopter fuel tank from the fueling tank, the fueling pipeline safety device, the pressure fueling pipeline nozzle and the helicopter pressure fueling connector. The helicopter observes the refueling state and confirms that the state of the pressure refueling pipeline nozzle and the pipeline is not abnormal. And after the oil quantity meets the requirement, notifying the water refueling aircraft to close the refueling control system, and finishing refueling.
The oiling pipeline is disconnected with the helicopter oil receiving joint: the helicopter connects the lifting steel rope with the pressure refueling pipeline connector, and separates the pressure refueling pipeline connector from the helicopter pressure refueling connector. And checking whether fuel oil leaks or not, and whether the connection between the hoisting steel rope and the pressure refueling pipeline connector is good or not.
Recovering pressure refueling pipeline connector of water refueling aircraft: the helicopter flies to the position about 20 meters above the oil filling pipeline frame of the water oil filling aircraft, and the position relation and the motion state among the helicopter are confirmed to meet the requirements of the lifting pressure oil filling pipeline nozzle. The helicopter starts the winch to put down the hoisting steel rope, and puts down the pressure refueling pipeline connecting nozzle. The water refueling aircraft separates the hoisting steel rope from the pressure refueling pipeline nozzle. The helicopter withdraws the hoisting steel rope.
In the oiling method, the pipeline frame follow-up control system senses pitching signals, rolling signals and helicopter azimuth signals given by the water oiling aircraft, and the gyro stabilizing device is cooperated with the electric control device to control the azimuth of the oiling pipeline frame to stably point to the helicopter. The oiling line telescopic servo system 7 senses stress, axial displacement and axial acceleration signals of the oiling line, which are acquired by the stress sensor, the displacement sensor and the acceleration sensor, and controls the oiling line to rapidly and accurately extend and retract on the oiling line frame.
In the oiling method, when the stress overload on the oiling pipeline exceeds a specified value, a safety device with a self-sealing valve is arranged on a pipeline close to the pressure oiling pipeline connector to work, the connection between the oiling pipeline and the pressure oiling pipeline connector is disconnected, and meanwhile, the oiling pipeline outlet is closed, so that the connection between the oiling machine and the oil receiving machine can not be disconnected in time when a dangerous situation is met, and the fuel leakage is reduced.
The water refueled aircraft draws in the refueling system: a water refueled aircraft launch reel control system withdraws a refueled line. The refuel line control system and refuel line telescoping follower system 7 are closed. And (5) folding the oiling pipe frame. And fixing the pressure refueling pipeline connector. The inspection pressure refueling pipeline connector is fixed, the refueling pipeline is accommodated, and the refueling pipeline frame is well fixed. And closing the working port cover of the oiling system in the middle of the airframe.
And (5) solving the cooperation of the water refueling plane and the helicopter, and ending the refueling task.
The above description of embodiments only shows embodiments of the invention, which are described in more detail and are not to be construed as limiting the scope of the invention. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention.
Claims (9)
1. A fueling system for a water-fuelled aircraft comprising:
a fueling tank (1) for storing fuel to be supplied to the helicopter;
a fueling control system (2) for controlling start/stop of fueling;
a fueling line (12) for delivering fuel;
a filler line reel (4) for reeling in/unreeling a filler line (12);
a refuel line reel control system (3) for controlling the refuel line reel (4) to reel/reel the refuel line (12);
the pressure refueling pipeline connector (9) is arranged at the tail end of the externally-placed refueling pipeline (12) and is used for realizing the connection between the refueling pipeline (12) and a helicopter oil receiving system;
the oiling pipe frame follow-up control system (5) is used for controlling the oiling pipe frame (6) to always point to the helicopter oil receiving system;
a filler neck (6) for supporting an outgoing filler neck (12) adjacent to the filler system;
the oiling pipeline telescopic follow-up system (7) is used for compensating displacement fluctuation caused by the change of the position between the oiling system and the helicopter oil receiving system in the oiling process;
the oiling pipe frame (6), the oiling pipe frame follow-up control system (5) and the oiling pipe line telescopic follow-up system (7) are combined to realize the stress relief of the externally-discharged oiling pipe line (12);
the oiling control system (2), the oiling pipe frame follow-up control system (5) and the oiling pipe frame telescopic follow-up system (7) are all arranged on the oiling machine.
2. A fueling system as recited in claim 1, further comprising:
and the oiling pipeline safety device (8) is used for timely disconnecting the connection between the oiling system and the helicopter oil receiving system when the stress borne by the externally-placed oiling pipeline (12) exceeds the preset safety stress.
3. A refuelling system according to claim 2, characterized in that the refuelling line safety device (8) is configured as: a stress concentration groove (13) arranged on the externally-placed refueling pipeline (12); during the refueling process, when the stress on the externally placed refueling pipeline (12) exceeds the preset safety stress, the externally placed refueling pipeline is disconnected at the stress concentration groove (13).
4. A refuelling system according to claim 3, characterized in that the refuelling line (12) at both ends of the stress concentrating groove (13) is provided with a self-sealing flap (14).
5. A water refuelling aircraft characterised in that a refuelling system according to any one of claims 1 to 4 is installed.
6. The water refuelling aircraft of claim 5, wherein the refuelling system is mounted in the middle of the body of the water refuelling aircraft, and a flap for the refuelling system to operate is provided in the middle of the body of the water refuelling aircraft.
7. A method of refuelling a water refuelling aircraft provided with a refuelling system according to any one of claims 1 to 4, comprising the steps of:
a) The water refueling aircraft reaches a preset sea area, and the helicopter to be refueled reaches the upper part of the preset sea area and is positioned above the water refueling aircraft;
b) The helicopter cooperates with the water refueling plane to ensure that the position of the helicopter and the water refueling plane are relatively fixed;
c) The oiling pipeline (12) of the internal oiling system of the water oiling aircraft is outwards put through the oiling pipeline reel (4), so that the pressure oiling pipeline nozzle (9) is connected with the oil receiving system of the helicopter, and oiling can be performed;
d) And after oiling is completed, the pressure oiling pipeline nozzle (9) is decoupled from the oil receiving system of the helicopter, and the helicopter is decoupled from the water oiling plane.
8. A method of refuelling an aircraft on water according to claim 7, wherein in step c the method of coupling the pressure refuelling line nozzle (9) to the helicopter oil receiving system is: the helicopter lowers the hoisting steel rope to the position of a refueling system of the water refueling aircraft; the pressure refueling pipeline connector (9) is fixed on a hoisting steel rope, and after the helicopter withdraws the hoisting steel rope, the pressure refueling pipeline connector (9) is inserted into the helicopter oil receiving system to realize connection.
9. The method for fueling the water-based fueling aircraft as set forth in claim 7 wherein in step c, during fueling, the fueling-pipeline-frame-follow-up control system (5) senses pitch signals, roll signals and helicopter azimuth signals from the water-based fueling aircraft and controls the azimuth of the fueling-pipeline-frame (6) to be stably directed to the helicopter fueling-receiving system; the oiling pipeline telescopic follow-up system (7) senses axial displacement and axial acceleration signals of the oiling pipeline, which are acquired by a displacement sensor and an acceleration sensor arranged on the oiling pipeline frame (6), and controls the extension/retraction of the oiling pipeline (12) on the oiling pipeline frame (6); ensuring the stress of the oiling pipeline within a safe range until the oiling amount meets the requirement.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR1018852A (en) * | 1949-04-01 | 1953-01-14 | Flight Refueling Ltd | Improvements to equipment for towing and refueling airplanes in flight |
| US20030136874A1 (en) * | 2001-12-10 | 2003-07-24 | Gjerdrum David Michael | Method for safer mid-air refueling |
| US20180016026A1 (en) * | 2016-07-15 | 2018-01-18 | Sikorsky Aircraft Corporation | Perception enhanced refueling system |
| US10640215B2 (en) * | 2016-09-20 | 2020-05-05 | Textron Innovations Inc. | Modular refueling systems for aircraft |
| CN109533357A (en) * | 2018-11-14 | 2019-03-29 | 中国直升机设计研究所 | A kind of easily broken self-sealing joint for helicopter fuel tank anti-crash |
| CN109592057B (en) * | 2018-12-07 | 2021-12-31 | 天津津航计算技术研究所 | Vision servo-based aerial refueling machine oil receiving implementation method |
| EP3686109B1 (en) * | 2019-01-24 | 2020-12-30 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | An en route fluid transmitting apparatus |
| CN110127067A (en) * | 2019-03-01 | 2019-08-16 | 清华大学 | Combined type VTOL high speed fixed-wing unmanned flight's platform |
| CN112009699B (en) * | 2020-08-17 | 2021-09-14 | 台州学院 | Oil-driven model aeroplane and model ship unmanned helicopter with air refueling function |
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