Oil receiving device, cooperation method and aircraft

Abstract

The invention provides an oil receiving device, a cooperation method and an aircraft, the oil receiving device comprises an oil receiving hose, and the oil receiving hose comprises an oil receiving pipeline; the posture adjusting hydraulic pipe is wound on the oil receiving pipeline, and the posture adjusting hydraulic pipe is used for changing the shape of the oil receiving pipeline to be in butt joint with an oil filling pipe; the pressure supply pipe is wound on the oil supply pipeline, the pressure supply pipe is attached to the posture adjusting hydraulic pipe, the pressure supply pipe is connected with a hydraulic system of the aircraft, and the pressure supply pipe provides driving force for the posture adjusting hydraulic pipe to change the shape of the oil supply pipeline; the purposes that the weight is reduced, the gravity center influence is reduced, the application range is expanded, stability is improved, air docking is more accurate and faster, take-off and landing are not affected, and hovering refueling can be achieved are achieved.

Description

Technical Field

[0001] The present application belongs to the technical field of low-altitude aircraft, and specifically relates to a refueling device, a coordination method and an aircraft. Background Art

[0002] Helicopters can take off and land vertically without relying on a runway, and have broad uses and development prospects. However, when manned helicopters are performing missions such as long-distance rescue, they have long flight times and high fuel requirements, and often the fuel tank capacity is unable to meet mission requirements.

[0003] Helicopter aerial refueling technology enables helicopters to perform longer-range and longer-duration missions. For example, when performing long-distance transportation, emergency rescue and other missions at sea, if aerial refueling technology can be used to extend the hovering time and operating radius, the mission scope and response speed can be effectively expanded.

[0004] The first problem to be solved in helicopter aerial refueling is the helicopter aerial refueling device. The length of the helicopter refueling pipe must be outside the rotor radius. Generally speaking, the length of the aerial refueling pipe is 1 meter outside the rotor. According to relevant information, the weight of the entire helicopter refueling equipment is between 200 kg and 300 kg. The helicopter refueling rod itself is heavy and the length is still very long after extension. A refueling rod that is too long will affect the stability of daily flight and is also easily damaged during takeoff and landing.

[0005] The refueling boom is located in front of the helicopter, which also means that it is impossible to use the existing hard refueling pipe to perform rapid refueling through hovering hot refueling on offshore platforms or land oil depots. It is necessary to land for refueling or to hang the refueling pipe on the helicopter for refueling. This task has many procedures, takes a long time, and uses a lot of fuel.

[0006] At present, similar products of deformable hoses include snake-like robots, which have high freedom of movement and are suitable for adjusting shape and position in space to match the docking of refueling pipes. However, there are problems such as difficult to control serial structures, large number of mechanical joints and control servos, and heavy weight. In addition, the motor load-bearing efficiency of multi-section robotic arms is low, and the load-bearing capacity of the motor increases linearly with the number of joints, the number of motors, and the distance to the base. The motor at the root has a heavy load-bearing capacity and a large size, making it difficult to maintain a tubular stroke and causing a serious increase in weight. Summary of the invention

[0007] Purpose of the invention: To solve the problems of traditional helicopters carrying hard-pipe refueling, such as heavy weight of the hard refueling pipe, great impact on the center of gravity, excessively long refueling pipe which has a great impact on flight stability, difficulty in air docking, easy damage during takeoff and landing, and inability to hover for refueling.

[0008] In a first aspect, the present application provides an oil receiving device, the oil receiving device comprising an oil receiving hose, the oil receiving hose comprising:

[0009] Oil receiving pipeline;

[0010] An attitude adjustment hydraulic pipe is wound around the oil receiving pipe, and the attitude adjustment hydraulic pipe is used to change the shape of the oil receiving pipe to connect with the oil filling pipe;

[0011] A pressure supply pipe is wound around the oil receiving pipe, the pressure supply pipe is fitted with the attitude adjustment hydraulic pipe, the pressure supply pipe is connected to the hydraulic system of the aircraft, and the pressure supply pipe provides the attitude adjustment hydraulic pipe with a driving force to change the shape of the oil receiving pipe.

[0012] Preferably, the posture adjustment hydraulic pipe is divided into multiple sections of closed pipes.

[0013] Preferably, the oil receiving device further comprises:

[0014] A segmented pressure control valve, arranged between the pressure supply pipe and the attitude adjustment hydraulic pipe;

[0015] Wherein, each closed pipe section of the posture adjustment hydraulic pipe can be connected to the refueling pipe by adjusting the shape of the oil receiving pipe according to the refueling docking position requirements under the regulation of the segmented pressure control valve through the hydraulic pressure.

[0016] Preferably, the attitude adjustment hydraulic pipe is wound around the oil receiving pipeline in a spiral manner; and the pressure supply pipe is wound around the oil receiving pipeline in a spiral manner.

[0017] Preferably, at least one set of the attitude adjustment hydraulic pipe, the pressure supply pipe and the segmented pressure control valve is installed on the oil receiving pipeline.

[0018] Preferably, the oil receiving device further comprises:

[0019] An interface locking mechanism is arranged on the refueling interface of the oil receiving pipeline;

[0020] When the docking is completed, the refueling pipe and the oil receiving pipeline are locked by the movement of the interface locking mechanism.

[0021] Preferably, the oil receiving device further comprises:

[0022] The magnetic induction probe is arranged at the refueling interface of the oil receiving pipeline, and the magnetic induction probe is used to identify the distance information of the refueling pipe.

[0023] Preferably, the oil receiving device further comprises:

[0024] An image recognition device is arranged at the refueling interface of the oil receiving pipeline, and is used to observe the relative spatial position of the refueling pipe and the status of the refueling equipment.

[0025] Preferably, the attitude adjustment hydraulic pipe and the pressure supply pipe together form a spiral line wound around the oil receiving pipe, and the ratio of the pitch of the spiral line to the diameter of the oil receiving pipe is more than twice.

[0026] Preferably, the ratio of the length of each closed pipe section of the posture adjustment hydraulic pipe to the pitch of the spiral line is a first preset value.

[0027] Preferably, the first preset value is between 0.8 and 1.5.

[0028] Preferably, there is a staggered distance between the closed pipe sections of adjacent posture adjustment hydraulic pipes, and the staggered distance value is a second preset value.

[0029] Preferably, the second preset value is 0.1-0.3 times the pitch of the helix.

[0030] Preferably, the refueling equipment includes a refueling ship, a refueling machine and a ground oil depot; the refueling ship includes a deck refueling interface, the refueling machine includes a refueling pipe, and the ground oil depot includes a ground refueling interface.

[0031] In a second aspect, the present application further provides an aircraft, the aircraft comprising the refueling device as described above, the refueling device being arranged at the center of gravity position of the belly of the aircraft.

[0032] Preferably, the oil receiving device is detachably arranged at the center of gravity of the belly of the aircraft.

[0033] In a third aspect, the present application further provides a collaborative method, the method comprising:

[0034] The magnetic induction probe identifies the distance information of the fuel pipe;

[0035] The image recognition device obtains the relative spatial position of the refueling pipe and the status of the refueling equipment;

[0036] Based on the distance information, the relative spatial position of the refueling pipe and the refueling equipment, determine the spatial position and distance requirement for docking between the aircraft and the refueling equipment, and analyze the safety of the surrounding environment;

[0037] If the surrounding environment is safe, based on the spatial position and distance requirements for docking between the aircraft and the refueling equipment, the hydraulic pressure is used to control the attitude and adjust the hydraulic pipe to adjust the shape of the oil receiving pipe to achieve docking with the refueling pipe.

[0038] Preferably, the method further comprises:

[0039] When the docking is completed, the refueling pipe and the refueling pipe are locked by the interface locking mechanism.

[0040] Preferably, the method of adjusting the shape of the oil receiving pipe by adjusting the attitude of the hydraulic pipe through hydraulic pressure control based on the spatial position and distance requirements of the aircraft and the refueling equipment to achieve docking with the refueling pipe includes:

[0041] Based on the spatial position and distance requirements for docking between the aircraft and the refueling equipment, each closed pipe section of the attitude adjustment pipe changes the shape of the refueling pipe to dock with the refueling pipe through hydraulic pressure under the regulation of the segmented pressure control valve.

[0042] Preferably, the refueling equipment includes a refueling ship, a refueling machine and a ground oil depot; the refueling ship includes a deck refueling interface, the refueling machine includes a refueling pipe, and the ground oil depot includes a ground refueling interface.

[0043] This application has the following technical effects:

[0044] The present application proposes a refueling device, a coordination method and an aircraft, which, through a new helicopter refueling mode, solve the problems existing in traditional helicopter refueling with a hard pipe, such as the heavy weight of the hard refueling pipe, the great influence on the center of gravity, the excessively long refueling pipe which has a great influence on the flight stability, the difficulty of docking in the air, and the easy damage during takeoff and landing.

[0045] Accordingly, the refueling device, coordination method and aircraft proposed in the present application achieve the purpose of reducing weight, reducing the impact of the center of gravity, expanding the scope of application, improving stability, making air docking more accurate and faster, and not affecting takeoff and landing, and being able to hover for refueling. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 This is a schematic diagram of a traditional helicopter aerial refueling provided by an embodiment of the present application;

[0047] Figure 2 This is a schematic diagram of a helicopter and a tanker docking provided by an embodiment of the present application;

[0048] Figure 3 This is a schematic diagram of a helicopter docking with a ship deck or the ground provided in an embodiment of the present application;

[0049] Figure 4 It is a structural schematic diagram of an oil receiving hose provided in an embodiment of the present application;

[0050] Figure 5 It is a schematic diagram of a segmented pressure control valve, a posture adjustment hydraulic pipe, and a pressure supply pipe connected to each other provided in an embodiment of the present application;

[0051] Figure 6 It is a flow chart of a collaborative refueling method provided in an embodiment of the present application. DETAILED DESCRIPTION

[0052] The present application provides an oil receiving device, the oil receiving device comprising an oil receiving hose, the oil receiving hose comprising:

[0053] Oil receiving pipeline;

[0054] An attitude adjustment hydraulic pipe is wound around the oil receiving pipe, and the attitude adjustment hydraulic pipe is used to change the shape of the oil receiving pipe to connect with the oil filling pipe;

[0055] A pressure supply pipe is wound around the oil receiving pipe, the pressure supply pipe is fitted with the attitude adjustment hydraulic pipe, the pressure supply pipe is connected to the hydraulic system of the aircraft, and the pressure supply pipe provides the attitude adjustment hydraulic pipe with a driving force to change the shape of the oil receiving pipe.

[0056] The refueling device proposed in this application solves the problems of traditional helicopters carrying hard-pipe refueling, such as heavy weight of the hard refueling pipe, great impact on the center of gravity, excessively long refueling pipe that has a great impact on flight stability, difficulty in air docking, easy damage during takeoff and landing, and inability to hover for refueling, through a new helicopter refueling mode.

[0057] Accordingly, the refueling device proposed in the present application achieves the purpose of reducing weight, reducing the influence of the center of gravity, expanding the scope of application, improving stability, making air docking more accurate and faster, and not affecting takeoff and landing, and being able to hover for refueling.

[0058] Wherein, the posture adjustment hydraulic pipe is divided into multiple sections of closed pipes.

[0059] In other embodiments of the present application, the oil receiving device further includes:

[0060] A segmented pressure control valve, arranged between the pressure supply pipe and the attitude adjustment hydraulic pipe;

[0061] Wherein, each closed pipe section of the posture adjustment hydraulic pipe can be connected to the refueling pipe by adjusting the shape of the oil receiving pipe according to the refueling docking position requirements under the regulation of the segmented pressure control valve through the hydraulic pressure.

[0062] Wherein, the attitude adjustment hydraulic pipe is wound around the oil receiving pipeline in a spiral manner; and the pressure supply pipe is wound around the oil receiving pipeline in a spiral manner.

[0063] In other embodiments of the present application, at least one set of the attitude adjustment hydraulic pipe, the pressure supply pipe and the segmented pressure control valve is installed on the oil receiving pipeline.

[0064] In other embodiments of the present application, the oil receiving device further includes:

[0065] An interface locking mechanism is arranged on the refueling interface of the oil receiving pipeline;

[0066] When the docking is completed, the refueling pipe and the oil receiving pipeline are locked by the movement of the interface locking mechanism.

[0067] In other embodiments of the present application, the oil receiving device further includes:

[0068] The magnetic induction probe is arranged at the refueling interface of the oil receiving pipeline, and the magnetic induction probe is used to identify the distance information of the refueling pipe.

[0069] In other embodiments of the present application, the oil receiving device further includes:

[0070] An image recognition device is arranged at the refueling interface of the oil receiving pipeline, and is used to observe the relative spatial position of the refueling pipe and the status of the refueling equipment.

[0071] In a feasible implementation, the attitude adjustment hydraulic pipe and the pressure supply pipe together form a spiral line wound around the oil receiving pipe, and the ratio of the pitch of the spiral line to the diameter of the oil receiving pipe is more than twice.

[0072] Wherein, the ratio of the length of each closed pipe section of the posture adjustment hydraulic pipe to the pitch of the spiral line is a first preset value.

[0073] In a feasible implementation, the first preset value is between 0.8 and 1.5.

[0074] In other embodiments of the present application, there is a staggered distance between the closed pipe sections of adjacent posture adjustment hydraulic pipes, and the staggered distance value is a second preset value.

[0075] In a feasible implementation, the second preset value is 0.1-0.3 times the pitch of the helix.

[0076] In other embodiments of the present application, the refueling equipment includes a refueling ship, a refueling machine and a ground oil depot; the refueling ship includes a deck refueling interface, the refueling machine includes a refueling pipe, and the ground oil depot includes a ground refueling interface.

[0077] The refueling device proposed in this application solves the problems of traditional helicopters carrying hard-pipe refueling, such as heavy weight of the hard refueling pipe, great impact on the center of gravity, excessively long refueling pipe that has a great impact on flight stability, difficulty in air docking, easy damage during takeoff and landing, and inability to hover for refueling, through a new helicopter refueling mode.

[0078] Accordingly, the refueling device proposed in the present application achieves the purpose of reducing weight, reducing the influence of the center of gravity, expanding the scope of application, improving stability, making air docking more accurate and faster, and not affecting takeoff and landing, and being able to hover for refueling.

[0079] In other embodiments of the present application, the present application further provides an aircraft, the aircraft comprising the refueling device as described above, the refueling device being arranged at the center of gravity of the belly of the aircraft.

[0080] Furthermore, the oil receiving device is detachably arranged at the center of gravity of the belly of the aircraft.

[0081] The aircraft proposed in this application solves the problems of traditional helicopters carrying hard-pipe refueling, such as heavy weight of the hard refueling pipe, great impact on the center of gravity, excessively long refueling pipe that has a great impact on flight stability, difficulty in air docking, easy damage during takeoff and landing, and inability to hover for refueling, through a new helicopter refueling mode.

[0082] The present application proposes an aircraft that achieves the purpose of reducing weight, reducing the impact of the center of gravity, expanding the scope of application, improving stability, making air docking more accurate and faster, and not affecting takeoff and landing, and being able to hover and refuel.

[0083] In other embodiments of the present application, the present application further provides a collaborative method, the method comprising:

[0084] The magnetic induction probe identifies the distance information of the fuel pipe;

[0085] The image recognition device obtains the relative spatial position of the refueling pipe and the status of the refueling equipment;

[0086] Based on the distance information, the relative spatial position of the refueling pipe and the refueling equipment, determine the spatial position and distance requirement for docking between the aircraft and the refueling equipment, and analyze the safety of the surrounding environment;

[0087] If the surrounding environment is safe, based on the spatial position and distance requirements for docking between the aircraft and the refueling equipment, the hydraulic pressure is used to control the attitude and adjust the hydraulic pipe to adjust the shape of the oil receiving pipe to achieve docking with the refueling pipe.

[0088] Furthermore, the method further comprises:

[0089] When the docking is completed, the refueling pipe and the refueling pipe are locked by the interface locking mechanism.

[0090] Furthermore, based on the spatial position and distance requirements of the aircraft and the refueling equipment, the hydraulic pressure is used to control the attitude of the hydraulic pipe to adjust the shape of the refueling pipe to achieve the docking of the refueling pipe, including:

[0091] Based on the spatial position and distance requirements for docking between the aircraft and the refueling equipment, each closed pipe section of the attitude adjustment pipe changes the shape of the refueling pipe to dock with the refueling pipe through hydraulic pressure under the regulation of the segmented pressure control valve.

[0092] Furthermore, the refueling equipment includes a refueling ship, a refueling machine and a ground oil depot; the refueling ship includes a deck refueling interface, the refueling machine includes a refueling pipe, and the ground oil depot includes a ground refueling interface.

[0093] A collaborative method proposed in this application solves the problems of traditional helicopters carrying hard-pipe refueling, such as heavy weight of the hard refueling pipe, great impact on the center of gravity, excessively long refueling pipe that has a great impact on flight stability, difficulty in air docking, easy damage during takeoff and landing, and inability to hover for refueling, through a new helicopter refueling mode.

[0094] Accordingly, a collaborative method proposed in the present application achieves the purpose of reducing weight, reducing the impact of the center of gravity, expanding the scope of application, improving stability, making air docking more accurate and faster, and ensuring that takeoff and landing are not affected, and being able to hover and refuel.

[0095] In other embodiments of this application, please refer to Figure 2 and Figure 3 The present invention proposes a low-altitude aircraft coordination method, including a tanker 1, a refueling helicopter 2, a refueling pipe 3, a refueling hose 4, a refueling ship 5, and a ship deck refueling interface 6.

[0096] A collaborative method proposed in this application solves the problems of traditional helicopters carrying hard-pipe refueling, such as heavy weight of the hard refueling pipe, great impact on the center of gravity, excessively long refueling pipe that has a great impact on flight stability, difficulty in air docking, easy damage during takeoff and landing, and inability to hover for refueling, through a new helicopter refueling mode.

[0097] A collaborative method proposed in this application achieves the purpose of reducing weight, reducing the impact of the center of gravity, expanding the scope of application, improving stability, making air docking more accurate and faster, and ensuring that takeoff and landing are not affected, and being able to hover and refuel.

[0098] In other embodiments of this application, please refer to Figure 4 The oil receiving hose 4 includes an oil receiving pipeline 41, a posture adjustment hydraulic pipe 42, a pressure supply pipe 43, a segmented pressure control valve 44, a magnetic induction probe 45, an image recognition device 46, and an interface locking mechanism 47.

[0099] Please note that Figure 1 The traditional helicopter aerial refueling mode uses a long hard pipe on the nose of the helicopter to receive oil, and a refueling machine with a hose in front to deliver oil. There are problems such as the hard refueling pipe is heavy, has a great impact on the center of gravity, the overly long refueling pipe has a great impact on flight stability, is difficult to dock in the air, and is easily damaged during takeoff and landing.

[0100] The present invention adopts a deformable hose to refuel the helicopter, which can be removed when refueling is not required, thereby reducing weight and expanding airborne space.

[0101] When refueling, the hose can change its shape through the attitude adjustment hydraulic pipe to connect with the refueling pipe. It is easier to operate and lighter in weight. The shape of the hose can be quickly adjusted as the flight status changes, which makes the refueling connection better and the flight safer.

[0102] It should be noted that currently similar products to deformable hoses include snake-like robots, which have a high degree of freedom of movement, but have problems with the large number and weight of mechanical joints and control servos, which limits the number of joints.

[0103] The refueling hose 4 used in the present invention includes a refueling pipeline 41, an attitude adjustment hydraulic pipe 42, a pressure supply pipe 43, and a segmented pressure control valve 44. The deformation of the refueling hose 4 is achieved by sharing the hydraulic power on the helicopter. The hydraulic drive of the refueling hose is used to eliminate and reduce the weight of the mechanical device and the torsion servo motor, so that the refueling hose of the helicopter does not need to be carried on the nose all the time. At the same time, the weight of the refueling hose is greatly reduced. The refueling hose is connected to the hydraulic system of the refueling helicopter 2 through the pressure supply pipe 43 to realize the input of the hose deformation driving force.

[0104] Among them, the attitude adjustment hydraulic pipe 42 and the pressure supply pipe 43 are installed in a spiral manner on the oil receiving pipeline 41. The attitude adjustment hydraulic pipe 42 is divided into multiple sections. Each section can adjust the shape of the oil receiving hose according to the requirements of the refueling docking position under the regulation of the segmented pressure control valve 44 through hydraulic pressure, so that the helicopter refueling pipe becomes flexible and light, can be installed at the center of gravity of the belly of the aircraft, and has little impact on the balance of the whole machine.

[0105] Among them, the refueling helicopter 2 adopts a hose refueling method, so that the helicopter can not only dock with the existing hose refueling machine, but also dock with the existing high-flow hard pipe refueling machine, and can directly dock with the ship deck or ground oil depot, which expands the objects of helicopter refueling and expands the scope of application of helicopter aerial refueling.

[0106] In a feasible implementation, the oil receiving hose 4 includes an oil receiving pipeline 41 , an attitude adjustment hydraulic pipe 42 , a pressure supply pipe 43 , a segmented pressure control valve 44 , a magnetic induction probe 45 , an image recognition device 46 , and an interface locking mechanism 47 .

[0107] Among them, the oil receiving pipeline 41 is in the middle of the oil receiving hose 4, and its outer portion is spirally installed with an attitude adjustment hydraulic pipe 42, a pressure supply pipe 43, and a segmented pressure control valve 44. The attitude adjustment hydraulic pipe 42, the pressure supply pipe 43, and the segmented pressure control valve 44 form a spiral line to control the shape of the oil receiving hose 4, and the deformation driving force is provided by the hydraulic system of the helicopter 2. The attitude adjustment hydraulic pipe 42 is divided into multiple sections of closed pipes, and each section of the closed pipe is connected to the pressure supply pipe 43 through a segmented pressure control valve 44, which can independently adjust the pressure of the section, thereby controlling the shape change of the attitude adjustment hydraulic pipe 42, and driving the oil receiving hose 4 to adjust its shape according to the position of the refueling pipe to better receive oil.

[0108] In other embodiments of this application, please refer to Figure 4 One or more sets of attitude adjustment hydraulic pipes 42, pressure supply pipes 43 and segmented pressure control valves 44 can be installed on the oil receiving hose 4. Fewer sets can reduce the weight of the oil pipes, and more sets can more flexibly adjust the shape of the oil pipes.

[0109] See also Figure 4 and Figure 6 The front part of the oil receiving hose 4 is the refueling interface, on which are installed a magnetic induction probe 45, an image recognition device 46, and an interface locking mechanism 47. The magnetic induction probe 45 can better identify the distance information of the refueling pipe, and the image recognition device 46 can comprehensively observe the relative spatial position of the refueling pipe and the condition of the refueling machine or refueling equipment. The combination of the two can more accurately and quickly determine the spatial position and distance requirements for docking with the refueling facilities, as well as analyze the safety of the surrounding environment, and assist in the safe and fast completion of the refueling collaborative task. When the docking is completed, the movement and locking of the interface locking mechanism 47 are used to achieve the stable locking of the oil delivery pipe and the oil receiving pipe, thereby ensuring the stability of the docking.

[0110] In other embodiments of this application, please refer to Figure 5 The segmented pressure control valve 44 is interconnected with the attitude adjustment hydraulic pipe 42 and the pressure supply pipe 43 to provide pressure for each segment of the attitude adjustment hydraulic pipe. The attitude adjustment hydraulic pipe 42 and the pressure supply pipe 43 are interconnected to form a spiral line installed on the oil receiving pipeline 41, and the ratio of its pitch to the diameter of the oil receiving pipeline 41 is more than 2 times.

[0111] In a feasible implementation, the ratio of the length of the closed pipe section of each posture adjustment hydraulic pipe to the pitch is between 0.8-1.5.

[0112] In a feasible implementation, there is a certain staggered distance between the closed pipe sections of adjacent attitude adjustment hydraulic pipes, and the distance value is represented by dh in the figure, and the value of dh is 0.1-0.3 times the pitch.

[0113] A low-altitude aircraft coordination method proposed in this application solves the problems of traditional helicopters carrying hard-pipe refueling, such as heavy weight of the hard refueling pipe, great impact on the center of gravity, excessively long refueling pipe that has a great impact on flight stability, difficulty in air docking, easy damage during takeoff and landing, and inability to hover for refueling, through a new helicopter refueling mode.

[0114] Accordingly, a low-altitude aircraft coordination method of the present application achieves the purpose of reducing weight, reducing the impact of the center of gravity, expanding the scope of application, improving stability, making air docking more accurate and faster, and ensuring that takeoff and landing are not affected, and being able to hover and refuel.

[0115] In other embodiments of the present application, the present application provides a refueling device, a coordination method and an aircraft, wherein the refueling device includes a refueling hose, and the refueling hose includes: a refueling pipeline; an attitude adjustment hydraulic pipe, which is wound around the refueling pipeline, and the attitude adjustment hydraulic pipe is used to change the shape of the refueling pipeline to connect with the refueling pipe; a pressure supply pipe, which is wound around the refueling pipeline, and the pressure supply pipe is fitted with the attitude adjustment hydraulic pipe, and the pressure supply pipe is connected to the hydraulic system of the aircraft, and the pressure supply pipe provides the attitude adjustment hydraulic pipe with a driving force to change the shape of the refueling pipeline.

[0116] The present application provides a refueling device, a coordination method and an aircraft, which achieve the purpose of reducing weight, reducing the influence of the center of gravity, expanding the scope of application, improving stability, making air docking more accurate and faster, and not affecting takeoff and landing, and being able to hover for refueling.

[0117] In other embodiments of this application, please refer to Figure 6 The collaborative process involved in the present invention is that when the helicopter 2 determines that aerial refueling is needed according to the flight mission and the remaining fuel situation during flight, the refueling demand is coordinated with the tanker or ship or ground base, and the route is adjusted according to the positions of both parties. The helicopter approaches the tanker (ship or ground base) on the route. At the same time, the relative spatial position of the refueling pipe can be fully observed through the image recognition device 46, and the distance information of the refueling pipe can be further identified through the magnetic induction probe 45. The azimuth distance of the refueling pipe is determined through comprehensive judgment, and the segmented pressure control valve 44 is segmented. The pressure adjustment causes the attitude adjustment hydraulic pipe 42 to change its shape, which further drives the oil receiving pipe 41 to change its shape to adapt to the docking requirements of the refueling port. After the docking adjustment is completed, it is locked through the interface locking mechanism 47 to start aerial refueling and receiving.

[0118] A low-altitude aircraft coordination method proposed in the present invention solves the problems existing in traditional helicopters carrying hard-pipe refueling, such as heavy weight of the hard refueling pipe, great influence on the center of gravity, excessively long refueling pipe having great influence on flight stability, difficulty in mid-air docking, and easy damage during takeoff and landing, through a new helicopter refueling mode.

[0119] This application achieves:

[0120] 1. Changing from a metal hard pipe to a flexible hose with a variable shape reduces the problem of heavy weight of the traditional helicopter refueling hard pipe;

[0121] 2. The position of the refueling pipe has been adjusted from the original position of the nose away from the center of gravity to the belly of the aircraft, reducing the impact of the refueling device on the center of gravity of the helicopter;

[0122] 3. Refueling through a deformable hose expands the scope of helicopter refueling to ships and ground bases in addition to tankers, expanding the scope of use;

[0123] 4. The docking is done through a self-deformed hose, which avoids frequent docking adjustments caused by weather reasons or aircraft aerodynamic interference. The hose can automatically change its shape to adapt to the position adjustment, and the stability of refueling docking is improved;

[0124] 5. The refueling hose can be automatically deformed for docking, making aerial docking more accurate and faster;

[0125] 6. The refueling pipe position has been adjusted from the original position where the nose is far away from the center of gravity to the belly of the aircraft, reducing the impact of the external refueling pipe on takeoff and landing;

[0126] 7. The deformation driving force of the helicopter oil receiving pipe directly adopts the existing hydraulic device of the helicopter, which simplifies the deformation driving servo device, further reduces the weight and improves reliability.

Claims

1. An oil receiving device, characterized in that: The oil receiving device comprises an oil receiving hose, and the oil receiving hose comprises: Oil receiving pipeline; An attitude adjustment hydraulic pipe is wound around the oil receiving pipe, and the attitude adjustment hydraulic pipe is used to change the shape of the oil receiving pipe to connect with the oil filling pipe; A pressure supply pipe is wound around the oil receiving pipe, the pressure supply pipe is fitted with the attitude adjustment hydraulic pipe, the pressure supply pipe is connected to the hydraulic system of the aircraft, and the pressure supply pipe provides the attitude adjustment hydraulic pipe with a driving force to change the shape of the oil receiving pipe.

2. The oil receiving device according to claim 1, characterized in that: The posture adjustment hydraulic pipe is divided into multiple sections of closed pipes.

3. The oil receiving device according to claim 2, characterized in that: The oil receiving device also includes: A segmented pressure control valve, arranged between the pressure supply pipe and the attitude adjustment hydraulic pipe; Wherein, each closed pipe section of the posture adjustment hydraulic pipe can be connected to the refueling pipe by adjusting the shape of the oil receiving pipe according to the refueling docking position requirements under the regulation of the segmented pressure control valve through the hydraulic pressure.

4. The oil receiving device according to claim 3, characterized in that: The attitude adjustment hydraulic pipe is wound around the oil receiving pipeline in a spiral manner; and the pressure supply pipe is wound around the oil receiving pipeline in a spiral manner.

5. The oil receiving device according to claim 4, characterized in that: At least one set of the attitude adjustment hydraulic pipe, the pressure supply pipe and the segmented pressure control valve is installed on the oil receiving pipeline.

6. The oil receiving device according to claim 1, characterized in that: The oil receiving device also includes: An interface locking mechanism is arranged on the refueling interface of the oil receiving pipeline; When the docking is completed, the refueling pipe and the oil receiving pipeline are locked by the movement of the interface locking mechanism.

7. The oil receiving device according to claim 6, characterized in that: The oil receiving device also includes: The magnetic induction probe is arranged at the refueling interface of the oil receiving pipeline, and the magnetic induction probe is used to identify the distance information of the refueling pipe.

8. The oil receiving device according to claim 7, characterized in that: The oil receiving device also includes: An image recognition device is arranged at the refueling interface of the oil receiving pipeline, and is used to observe the relative spatial position of the refueling pipe and the status of the refueling equipment.

9. The oil receiving device according to claim 5, characterized in that: The attitude adjustment hydraulic pipe and the pressure supply pipe together form a spiral line wound on the oil receiving pipeline, and the ratio of the pitch of the spiral line to the diameter of the oil receiving pipeline is more than twice.

10. The oil receiving device according to claim 9, characterized in that: The ratio of the length of each closed pipe section of the posture adjustment hydraulic pipe to the pitch of the helical line is a first preset value.

11. The oil receiving device according to claim 10, characterized in that: The first preset value is between 0.8 and 1.

5.

12. The oil receiving device according to claim 11, characterized in that: There is a staggered distance between the closed pipe sections of adjacent posture adjustment hydraulic pipes, and the staggered distance value is a second preset value.

13. The oil receiving device according to claim 12, characterized in that: The second preset value is 0.1-0.3 times the pitch of the helix.

14. The oil receiving device according to claim 8, characterized in that: The refueling equipment includes a refueling ship, a refueling machine and a ground oil depot; the refueling ship includes a deck refueling interface, the refueling machine includes a refueling pipe, and the ground oil depot includes a ground refueling interface.

15. An aircraft, characterized in that: The aircraft comprises the refueling device according to any one of claims 1 to 14, and the refueling device is arranged at the center of gravity of the belly of the aircraft.

16. The aircraft according to claim 15, characterized in that The oil receiving device is detachably arranged at the center of gravity of the belly of the aircraft.

17. A collaborative method, characterized in that: The method comprises: The magnetic induction probe identifies the distance information of the fuel pipe; The image recognition device obtains the relative spatial position of the refueling pipe and the status of the refueling equipment; Based on the distance information, the relative spatial position of the refueling pipe and the refueling equipment, determine the spatial position and distance requirement for docking between the aircraft and the refueling equipment, and analyze the safety of the surrounding environment; If the surrounding environment is safe, based on the spatial position and distance requirements for docking between the aircraft and the refueling equipment, the hydraulic pressure is used to control the attitude and adjust the hydraulic pipe to adjust the shape of the oil receiving pipe to achieve docking with the refueling pipe.

18. The method according to claim 17, characterized in that The method further comprises: When the docking is completed, the refueling pipe and the refueling pipe are locked by the interface locking mechanism.

19. The method according to claim 17, characterized in that Based on the spatial position and distance requirements of the aircraft and the refueling equipment, the shape of the refueling pipe is adjusted by adjusting the hydraulic pipe through the hydraulic pressure control attitude to achieve the docking of the refueling pipe, including: Based on the spatial position and distance requirements for docking between the aircraft and the refueling equipment, each closed pipe section of the attitude adjustment pipe changes the shape of the refueling pipe to dock with the refueling pipe through hydraulic pressure under the regulation of the segmented pressure control valve.

20. The method according to claim 17, characterized in that The refueling equipment includes a refueling ship, a refueling machine and a ground oil depot; the refueling ship includes a deck refueling interface, the refueling machine includes a refueling pipe, and the ground oil depot includes a ground refueling interface.

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