阅读说明：本技术 一种油动涵道式飞行器的燃料储存装置及控制方法 (Fuel storage device of oil-driven ducted aircraft and control method ) 是由 何旭东 于 2021-01-12 设计创作，主要内容包括：本发明公开了一种油动涵道式飞行器的燃料储存装置及控制方法,包括：涵道和至少两个油箱；所述油箱之间通过管路连接；至少一个油箱通过管路与发动机连接,并串联有一个油泵；所述油箱设置于所述涵道的内部,并沿周向均匀分布；所述油箱上部设有加油口,所述加油口对应所述涵道的壳体处设有开口,并在所述开口处安装有可拆卸的加油口盖；所述加油口盖内设有泄压口；所述泄压口内安装有电磁阀,所述电磁阀与所述飞控系统电连；本发明优点在于,利用涵道式飞行器的涵道作为燃料箱箱体,充分利用涵道内部空间,结合设计的电磁阀控制结构,较好的解决了分体式油箱质量平衡问题。(The invention discloses a fuel storage device of an oil-driven ducted aircraft and a control method, wherein the fuel storage device comprises the following components: a duct and at least two oil tanks; the oil tanks are connected through pipelines; at least one oil tank is connected with the engine through a pipeline and is connected with an oil pump in series; the oil tanks are arranged inside the duct and are uniformly distributed along the circumferential direction; an oil filling port is arranged at the upper part of the oil tank, an opening is formed in the position, corresponding to the shell of the duct, of the oil filling port, and a detachable oil filling port cover is installed at the opening; a pressure relief opening is formed in the oil filler cap; an electromagnetic valve is arranged in the pressure relief port and electrically connected with the flight control system; the invention has the advantages that the culvert of the culvert type aircraft is used as the fuel tank body, the inner space of the culvert is fully utilized, and the quality balance problem of the split type fuel tank is better solved by combining the designed electromagnetic valve control structure.)

1. A fuel storage device for an oil-driven ducted aircraft, comprising: a duct (7) and at least two oil tanks (1); the duct (7) is formed by combining an inner shell and an outer shell, and a clamping cavity is arranged between the two shells;

the oil tank is characterized in that the oil tanks (1) are connected through a pipeline (5); at least one oil tank (1) is connected with an engine (11) through a pipeline (5) and is connected with an oil pump (6) in series; the oil pump (6) is electrically connected with the flight control system;

the oil tanks (1) are arranged in the clamping cavities of the ducts (7) and are uniformly distributed along the circumferential direction; an oil filling port (2) is formed in the upper portion of the oil tank (1), an opening is formed in the position, corresponding to the shell of the duct (7), of the oil filling port (2), and a detachable oil filling port cover (8) is installed at the opening;

a pressure relief opening (9) is formed in the oil filler cover (8), and the inside of the oil tank (1) is communicated with the outside through the pressure relief opening (9); an electromagnetic valve is arranged in the pressure relief opening (9), and the electromagnetic valve controls the opening and closing of the pressure relief opening (9); the electromagnetic valve is electrically connected with the flight control system.

2. A fuel storage device according to claim 1, characterized in that the vertical cross-sectional outer contour of the upper part of the fuel tank (1) corresponds to the vertical cross-sectional outer contour of the housing of the duct (7), and the upper part of the fuel tank (1) rests against the upper part of the clamping cavity.

3. A fuel storage device according to claim 1 or 2, characterized in that the lower part of the fuel tank (1) is in a V-shaped contracted configuration; the included angle of the two side surfaces of the V-shaped contraction structure is less than or equal to 60 degrees.

4. The fuel storage device of claim 3, wherein the V-shaped constriction is in a segmented constriction pattern; wherein the included angle of two side faces of the upper section close to the oil tank (1) is 90-61 degrees, and the included angle of two side faces of the lower section close to the oil tank is 45-58 degrees.

5. A fuel storage device according to claim 1, characterized in that all fuel tanks (1) are connected in series; the fuel outlet (3) is arranged at the bottom of the oil tank (1) at the starting end, the fuel inlet (4) and the fuel outlet (3) are arranged at the bottoms of the other oil tanks (1), and the fuel inlet (4) and the fuel outlet (3) of each oil tank (1) are respectively connected with the fuel outlet (3) and the fuel inlet (4) of the adjacent oil tank (1) through the pipeline (5); the fuel outlet (3) of the fuel tank (1) at the end is connected with the engine (11) through a pipeline (5).

6. The fuel storage device according to claim 5, wherein an oil pump (6) is connected in series on the pipeline (5) between two adjacent oil tanks (1), and the oil pump (6) is electrically connected with the flight control system.

7. Fuel storage device according to claim 6, characterized in that a level gauge is mounted inside the tank (1), said level gauge being electrically connected to said flight control system.

8. The control method of a fuel storage device according to any one of claims 1 to 7, characterized by comprising the steps of:

s1, fuel filling stage

S11, filling fuel through the fuel filling port (2) of each fuel tank (1);

s12, after filling, adjusting the switch of the electromagnetic valve in each pressure relief opening (9) by the flight control system to level the fuel quantity stored in each fuel tank (1);

s2 engine feeding stage

S21, the oil pump (6) between the engine (11) and the oil tank (1) works, and fuel is pumped into the engine (11) from the oil tank (1);

and S22, adjusting the opening and closing of each pressure relief opening (9) at the same time of the step S21, and keeping the discharging amount of each oil tank (1) the same.

Technical Field

The invention relates to the field of aircraft design, in particular to a fuel storage device of an oil-driven ducted aircraft and a control method.

Background

Under the environment of rapid development of various aircraft applications, the requirements on aircraft mounting and endurance are higher and higher. The power sources of the aircraft driven by electric energy are usually a brushless motor and a lithium battery, and the electric energy aircraft cannot meet the requirements of long-time flight and large-mass mounting due to the limitation of a battery technology; the power source of the oil-driven aircraft is a fuel engine, gasoline, kerosene and the like, the fuel engine has higher power than a brushless motor under the same diameter of a paddle disk, and meanwhile, the mass energy density and the volume energy density of the gasoline and the kerosene are far higher than those of a lithium battery, so that the oil-driven aircraft can well solve the limit on the endurance and the mounting of the aircraft.

The oil-driven ducted aircraft can take off and land, hover and fly autonomously in a small space; the lift-increasing effect of the duct enables the power required by the ducted aircraft to obtain the same lift force under the same size of blades to be smaller, and the flight time and the mounting capacity can be obviously improved; the ring expansion function of the duct enables the flight safety margin of the duct aircraft to be remarkably reduced, and the duct aircraft is suitable for completing environment interactive operation tasks; the inner wall of the duct has the rectifying effect on the airflow between the paddles, so that the noise can be effectively reduced.

At present, fuel storage of the existing oil-driven ducted aircraft is an externally-mounted fuel tank, the weight of the aircraft is increased by the externally-mounted fuel tank, the flying safety margin of the ducted aircraft is increased by the extra volume, and the externally-mounted fuel tank can influence the flow field around the ducted aircraft and reduce the flying efficiency in the flying process.

Chinese patent CN101746505A discloses a single-thrust disc type unmanned aerial vehicle, wherein the main body is a duct, and oil tanks are installed in the left and right cavities of the duct, and the oil tanks supply oil to the engine during take-off. Above-mentioned design has solved the oil tank and has set up the problem, provides an oil tank and installs in the technical scheme of duct inner chamber, but does not solve the balanced problem of oil tank fuel feeding, wherein just there are two oil tank fuel feeding differences, leads to whole focus skew, and this does not do benefit to flight control. In the same way, Chinese patent CN203428026U discloses a small ducted aircraft: the aircraft comprises a culvert fuselage, a landing gear, a flight control cabin, a mission equipment cabin, an engine, a propeller system, an oil tank and a control plane; the flight control cabin is fixedly connected to one side of the engine, and the task equipment cabin is fixedly connected to the other side of the engine; the lower part of the engine is fixedly connected with the upper part of the ducted fuselage, and the lower part of the ducted fuselage is fixedly connected with the undercarriage; the propeller system, the oil tank and the control surface are positioned inside the ducted fuselage. The oil tank is arranged inside the ducted fuselage, but the problem of oil supply leveling is not really solved.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the fuel storage device and the method of the oil-driven ducted aircraft are needed to be provided, the externally-hung integrated oil tank can be arranged in the inner cavity of the duct in a split mode, and meanwhile the problem of balance among the oil tanks is solved.

The technical scheme adopted by the invention for solving the technical problem is as follows:

a fuel storage device for an oil-driven ducted aircraft, comprising: a duct and at least two oil tanks; the duct is formed by combining an inner shell and an outer shell, and a clamping cavity is arranged between the two shells;

the oil tanks are connected through pipelines; at least one oil tank is connected with the engine through a pipeline and is connected with an oil pump in series; the oil pump is electrically connected with the flight control system;

the oil tanks are arranged in the clamping cavity of the duct and are uniformly distributed along the circumferential direction; an oil filling port is arranged at the upper part of the oil tank, an opening is formed in the position, corresponding to the shell of the duct, of the oil filling port, and a detachable oil filling port cover is installed at the opening;

a pressure relief opening is formed in the oil filler cover, and the inside of the oil tank is communicated with the outside through the pressure relief opening; an electromagnetic valve is arranged in the pressure relief opening and controls the opening and closing of the pressure relief opening; the electromagnetic valve is electrically connected with the flight control system.

Furthermore, the outer contour of the vertical section of the upper part of the oil tank is consistent with the outer contour of the vertical section of the ducted shell in shape, and the upper part of the oil tank abuts against the upper part of the clamping cavity.

Furthermore, the lower part of the oil tank is of a V-shaped contraction structure; the included angle of the two side surfaces of the V-shaped contraction structure is less than or equal to 60 degrees.

Further, the V-shaped contraction structure is in a segmented contraction mode; wherein the included angle of two side faces close to the upper section of the oil tank is 90-61 degrees, and the included angle of two side faces close to the lower section is 45-58 degrees.

Further, all the oil tanks are connected in series; the fuel inlet and the fuel outlet of each oil tank are respectively connected with the fuel outlet and the fuel inlet of the adjacent oil tank through the pipelines; the fuel outlet of the fuel tank at the tail end is connected with the engine through a pipeline.

Furthermore, an oil pump is connected in series on a pipeline between two adjacent oil tanks, and the oil pump is electrically connected with the flight control system.

Furthermore, a liquid level meter is installed inside the oil tank, and the liquid level meter is electrically connected with the flight control system.

On the other hand, the invention also provides a control method based on the fuel storage device, which comprises the following specific steps:

s1, fuel filling stage

S11, filling fuel through the oil filling ports of the oil tanks;

s12, after filling, adjusting the switch of the electromagnetic valve in each pressure relief opening by the flight control system to level the fuel quantity stored in each fuel tank;

s2 engine feeding stage

S21, an oil pump between the engine and the oil tank works to pump fuel into the engine from the oil tank;

and S22, adjusting the opening and closing conditions of the pressure relief ports while the step S21 is carried out, and keeping the discharging amount of each oil tank the same.

The invention has the following advantages:

the culvert of the culvert type aircraft is used as a fuel tank body, the inner space of the culvert is fully utilized, the influence of an external hanging type on the volume and the flow field of the culvert aircraft is overcome, and the quality balance problem of the split type fuel tank is better solved by further combining the designed pressure relief port and electromagnetic valve control structure; furthermore, the V-shaped bottom structure is adopted, so that when the aircraft flies obliquely at a large angle, the fuel liquid level can still be ensured to be higher than the outlet, and the condition that air is sucked into the engine to cause lean oil combustion and even parking in the air is avoided.

Drawings

In order to illustrate the embodiments of the present invention more clearly, the drawings that are needed in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only one or several embodiments of the present invention, and that other drawings can be obtained by those skilled in the art without inventive effort.

The location and number of identical structures shown in the drawings are merely for convenience in describing the invention and do not indicate or imply that the structures referred to must have a particular orientation, number of distributions and are therefore not to be considered limiting.

FIG. 1 is a front view of a fuel tank according to the present invention;

FIG. 2 is a perspective view of the installation site of the present invention (with the duct partially cut away);

fig. 3 is a schematic perspective view of the present invention.

In the figure:

1-an oil tank; 2-oil filling port; 3-a fuel outlet; 4-a fuel inlet; 5-pipeline; 6-an oil pump; 7-a duct; 8-a filler cap; 9-a pressure relief port; 10-a linker arm; 11-an engine; 101-a first tank; 102-a second tank; 103-a third oil tank; 104-a fourth tank; 501-a first pipeline; 502-a second conduit; 503-a third line; 504-fourth line; 505-a fifth pipeline; 601-a first oil pump; 602-a second oil pump; 603-a third oil pump; 604-fourth oil pump.

Detailed Description

Specific embodiments of the present invention are described below with reference to specific figures 1-3.

Referring to fig. 1 and 3, a fuel storage device of an oil-driven ducted aircraft includes: the duct 7 and the four oil tanks 1 are respectively a first oil tank 101, a second oil tank 102, a third oil tank 103 and a fourth oil tank 104. The duct 7 is formed by combining an inner shell and an outer shell, and a clamping cavity is arranged between the two shells. The engine 11 is fixed right above the duct 7 through the connecting arm 10, the axes of the engine and the duct are overlapped, and an output shaft of the engine 11 is connected with a blade arranged below the engine and used as a power source of the aircraft.

Four oil tanks 1 are arranged inside the clamping cavity of the duct 7 and are uniformly distributed along the circumferential direction.

Preferably, as shown in fig. 2, the outer contour of the vertical section of the upper part of the oil tank 1 is consistent with the outer contour of the vertical section of the housing of the bypass 7, and the upper part of the oil tank 1 is abutted against the upper part of the clamping cavity, so that the space can be fully utilized and the voyage can be improved. Further, the lower part of the oil tank 1 is designed to be in a V-shaped shrinkage structure as shown in figure 1, and the included angle of two side surfaces of the V-shaped shrinkage structure is kept to be less than or equal to 60 degrees; the design aims to ensure that the bottom oil outlet is still covered by fuel oil when the aircraft performs large maneuvering actions, such as inclined forward flight, and the integral inclined angle is less than 60 degrees, so that air is not sucked into an engine to cause lean combustion. Further, in order to increase the oil storage capacity of the oil tank 1, the V-shaped contraction structure is designed into a sectional contraction mode; wherein, the included angle of two side surfaces of the upper section close to the oil tank 1 is 90-61 degrees, and the specific design is 80 degrees, namely the included angle of two sides and the bottom surface is 50 degrees; the included angle of the two side surfaces of the lower section is 45-58 degrees, the specific design is 55.76 degrees, namely the included angle of the two sides and the bottom surface is 62.12 degrees, so that the whole oil storage capacity can be increased, the short-time large-angle inclination can be ensured, and the oil supply can still be produced.

The oil tanks 1 are connected through pipelines 5; a first oil tank 101, a fourth oil tank 104, a third oil tank 103 and a second oil tank 102 are arranged in sequence. Preferably, as shown in connection with fig. 3, all the tanks 1 are connected in series; the bottom of a first oil tank 101 at the starting end is provided with a fuel outlet 3, the bottom of each of the other oil tanks 1 is provided with a fuel inlet 4 and a fuel outlet 3, and the fuel inlet 4 and the fuel outlet 3 of each oil tank 1 are respectively connected with the fuel outlet 3 and the fuel inlet 4 of the adjacent oil tank 1 through a pipeline 5; the fuel outlet 3 of the second fuel tank 102 at the end is connected to the engine 11 through a first pipe 501, and a fourth oil pump 604 is connected in series to the pipe. The first oil tank 101 and the fourth oil tank 104 are connected through a fourth pipeline 504 and are connected in series with a first oil pump 601; the fourth oil tank 104 and the third oil tank 103 are connected through a third pipeline 503 and are connected in series with a second oil pump 602; the third oil tank 103 and the second oil tank 102 are connected by a second pipeline 502, and are connected in series with a third oil pump 603. Each oil pump 6 is electrically connected with the flight control system. The inside of the oil tank 1 is also provided with a liquid level meter (not shown in the figure), and the liquid level meter is also electrically connected with the flight control system. Further, for the sake of overall aesthetic appearance and protection of the fuel line, the end of the first line 501 is not directly connected to the engine 11, but is connected in series to the fifth line 505. The fifth pipeline 505 is arranged in the connecting arm 10, only penetrates out of the tail end of the connecting arm 10, and is connected with an oil inlet of the engine 11.

The upper part of the oil tank 1 is provided with an oil filling port 2, the shell of the oil filling port 2 corresponding to the duct 7 is provided with an opening, and a detachable oil filling port cover 8 is arranged at the opening; preferably, the shape of the oil filler cap 8 is designed to be consistent with that of the opening, so that the surface of the oil filler cap 8 forms a continuous curved surface, and the purpose is that the overall pneumatic shape of the duct 7 is not damaged after the oil filler cap 8 is installed. A pressure relief port 9 is formed in the oil filler cover 8, and the inside of the oil tank 1 is communicated with the outside through the pressure relief port 9; an electromagnetic valve is arranged in the pressure relief opening 9 and controls the opening and closing of the pressure relief opening 9; the electromagnetic valve is electrically connected with the flight control system. The design aim is that the liquid level meter feeds back real-time fuel quantity in each oil tank 1 to a flight control system, and the flight control system controls an electromagnetic brake and an oil pump 6. The opening and closing of the pressure relief opening 9 are controlled by the electromagnetic gate, when the pressure relief opening is opened, air flows in, balance of pressure inside and outside the oil tank 1 is guaranteed, and fuel can be normally pumped out.

The invention provides a control method of a fuel storage device based on the above embodiment, which comprises the following steps:

s1, fuel filling stage

S11, filling fuel through the oil filling port 2 of each oil tank 1;

s12, after filling is completed, calculating the oil quantity in each oil tank through a liquid level meter, feeding the oil quantity back to the flight control system, and adjusting the electromagnetic valve switch and each oil pump 6 to work by the flight control system so as to balance the oil quantity of each oil tank 1 and ensure that the oil quantity of each oil tank is equal; if when the liquid level in the first oil tank 101 is higher than that in the second oil tank 102, the pressure relief ports 9 of the oil filler caps 8 of the first oil tank 101 and the second oil tank 102 are opened, the rest of the pressure relief ports 9 are closed, the fourth oil pump 604 is closed, the rest of the oil pumps 6 are operated, at this time, the pressure relief ports 9 of the oil filler caps 8 of the first oil tank 101 are filled with air, the pressure relief ports 9 of the oil filler caps 8 of the second oil tank 102 are exhausted, the pressure relief ports 9 of the oil filler caps 8 of the fourth oil tank 104 and the third oil tank 103 are closed, the liquid level is unchanged, the fuel oil sequentially passes through the fourth oil tank 104 and the third oil tank 103 from the first oil tank 101 and finally flows into the second oil tank 102, all the pressure relief ports 9 are closed when the.

S2 engine feeding stage

S21, operating all oil pumps 6 to pump fuel from the oil tank 1 into the engine 11;

s22, opening the pressure relief ports 9 of the oil filler caps 8 of all the oil tanks 1 while the step S21 is carried out, and enabling each pressure relief port 9 to intake air to ensure that the fuel oil is normally pumped out.

S23, in the flight process, the liquid level meters in the oil tanks feed back real-time oil quantity to the flight control system, the flight control system controls the revolution number of each oil pump 6 and the opening and closing of the electromagnetic gate 9 to ensure that the oil quantity of each oil tank is always equal in long-time flight, if the oil quantity of the fourth oil tank 104 is more than that of other oil tanks 1, the revolution number of the second oil pump 602 is accelerated, the revolution numbers of the other oil pumps 6 are unchanged, normal oil supply of an engine is ensured, the oil quantity output of the fourth oil tank 104 is increased, the output of the other oil tanks; if the oil quantity of the first oil tank 101 is less than that of the other oil tanks 1, at this time, the pressure relief port 9 of the oil filler cap 8 of the first oil tank 101 is closed, the oil pump 601 stops operating, the first oil tank 101 cannot input fuel, the output of the other oil tanks is unchanged, and the oil quantities of the oil tanks are gradually equal.

At unmanned aerial vehicle flight in-process specifically, when the fuselage need take place the large angle slope to a certain direction, the aircraft focus can be changed to this moment fuel oil mobility, if aircraft 45 slope flight to first oil tank 101 is located the below, and third oil tank 103 is located the top, and fourth oil tank 104 and second oil tank 102 are located the circumstances about for example. When the oil mass is full, whole focus remains unchanged basically, nevertheless along with fuel consumption, fuel plane perpendicular to gravity direction, the top gets into the air, and unmanned aerial vehicle focus moves down below under this gesture. Corresponding to this kind of condition, flight control system feeds back the oil tank oil mass according to the level gauge, and accelerometer, gyroscope feedback unmanned aerial vehicle self gesture according to above-mentioned S23 method, control each oil tank output, initiatively cause the oil mass difference, guarantee that unmanned aerial vehicle focus is unchangeable, reduce control plane burden, guarantee unmanned aerial vehicle flight stability.

Although the present invention has been described in detail with reference to examples, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the invention as defined in the appended claims.