Combined vented vehicle experimental model, experimental system and use method

Abstract

The application relates to a combined ventilation navigation body experimental model, an experimental system and a use method, and belongs to the technical field of ocean engineering experiments. The application solves the problem that, in the existing drag reduction design of the ventilation navigation body, the ventilation assembly and the force measuring device are independently arranged at different positions on the navigation body, and extra resistance is easily generated. The supporting wing is fixed on the top of the model main body, the force sensor is fixed on the top of the supporting wing through a connecting assembly, the force sensor and the connecting assembly are located in the sensor mounting hole, the upper part of the force sensor is fixed to the cover plate through the supporting sheet, and the lower surface of the connecting assembly and the lower surface of the cover plate are located on the same horizontal plane. The ventilation assembly and the force measuring device for measuring the resistance of the navigation body during navigation are combined and arranged, the two requirements of ventilation and force measurement are combined together, the influence of the external pipeline on the flow field is avoided, and the resistance of the navigation body during navigation can be more accurately and conveniently measured.

Description

Technical Field

[0001] This invention relates to a combined ventilated vehicle experimental model, experimental system, and method of use, belonging to the field of marine engineering experimental technology. Background Technology

[0002] As humanity increasingly values ​​the ocean, various new types of marine vehicles are constantly being developed. However, when these vehicles travel at high speeds in the sea, they inevitably experience significant pressure drag and frictional drag, severely impacting their navigation efficiency. Especially as the speed of the vehicle increases, the pressure at certain points on the surface may fall below the saturated vapor pressure of water at the current temperature, leading to cavitation. This not only causes cavitation erosion on the outer surface of the vehicle, but the pulsation and breakup of cavitation bubbles also generate intense cavitation noise, severely affecting the vehicle's stealth capabilities. In modern scientific, military, engineering, and environmental research, drag reduction technology for underwater vehicles is becoming increasingly important. The main goal of this technology is to reduce the frictional resistance between the underwater vehicle and the water flow to improve its navigation performance and efficiency. For example, underwater vehicles typically rely on battery power, so energy efficiency is crucial for endurance. Reducing drag can extend the endurance of underwater vehicles and reduce the need for frequent recharging. Therefore, how to utilize drag reduction technology to improve the performance and energy efficiency of underwater vehicles has broad potential value in military, marine science, and industrial applications.

[0003] Drag reduction technology for underwater vehicles is one of the core directions in the field of underwater vehicle hydrodynamics. Traditional drag reduction methods mostly involve underwater vehicle shape design, selection of low-drag materials, and hydrophobic surface coatings, but these methods have relatively low drag reduction efficiency. Artificial ventilation, on the other hand, involves encasing the surface of the vehicle in a cavity, altering the density of the surrounding fluid medium, thereby significantly reducing drag during navigation. However, the ventilation process requires precise control to ensure efficient operation of the underwater vehicle at different depths and speeds. In existing drag reduction research on ventilated vehicles, the ventilation components and force-measuring devices (such as force sensors) used to measure the drag experienced by the vehicle during navigation are independently arranged in different locations on the vehicle. The presence of the ventilation components and force-measuring devices affects the flow field, generates additional drag, causes additional vibration of the vehicle, and severely impacts the precise control of ventilation at different water depths and flow velocities.

[0004] Therefore, there is an urgent need for an experimental model of a ventilated vehicle that combines a ventilation component with a force-measuring device (such as a force sensor) to measure the resistance experienced by the vehicle during navigation. This would enable the vehicle to navigate in a stable flow field while accurately measuring the resistance it experiences during navigation. This would allow for precise control of the vehicle's ventilation and reduce the negative impact of the ventilation structure on the cavitation flow of the vehicle. Summary of the Invention

[0005] The present invention aims to solve the above-mentioned technical problems and provides a combined ventilated vehicle experimental model, experimental system and usage method.

[0006] The technical solution adopted by the present invention to solve the above-mentioned technical problems is as follows:

[0007] A combined ventilated airborne experimental model includes a model body, a force sensor, a support wing, a connecting assembly, a cover plate, and a sealing cover. The support wing is fixed to the top of the model body, and the force sensor is fixed to the top of the support wing via the connecting assembly. The cover plate has a sensor mounting hole, and both the force sensor and the connecting assembly are located within the sensor mounting hole. The upper part of the force sensor is fixed to the cover plate via a support plate. The lower surface of the connecting assembly is at the same horizontal plane as the lower surface of the cover plate. The sealing cover is located above the sensor mounting hole and is fixed to the cover plate. The cover plate is the top plate of the test section of a circulating water tunnel. Guide holes are provided through the top of the sealing cover, the interior of the connecting assembly, and the interior of the support wing from top to bottom. A wire hole is also provided on the sealing cover.

[0008] A combined ventilated flight vehicle experimental model includes a model body, a force sensor, a support wing, a connecting assembly, a cover plate, and a sealing cover. The support wing is fixed to the top of the model body. The force sensor is fixed to the top of the support wing via the connecting assembly. The cover plate has a sensor mounting hole. The force sensor and the connecting assembly are both located within the sensor mounting hole, with the upper part of the force sensor fixed to the cover plate via a support piece. The lower surface of the connecting assembly is at the same horizontal plane as the lower surface of the cover plate. The sealing cover is positioned above the sensor mounting hole and fixed to the cover plate. The cover plate is fixed to the inner wall of the test section top plate. The top of the sealing cover is fixed to the inner wall of the test section top plate, or the sealing cover is sealed and inserted through the test section top plate. Guide holes are provided from top to bottom in the top of the sealing cover, the interior of the connecting assembly, and the interior of the support wing. A wire hole is also provided on the sealing cover.

[0009] Furthermore, the main body of the model includes a head, a middle section pipe, a tail, a venting connector, and a fairing. The head is located at one end of the middle section pipe and there is a gap between the head and the middle section pipe. The tail is threadedly installed at the other end of the middle section pipe. One end of the venting connector is threaded into one end of the head, and the other end of the venting connector is threaded into one end of the middle section pipe. An annular cavity is formed between the outer wall of the middle part of the venting connector and the inner wall of one end of the middle section pipe. The venting connector has a first vent hole arranged along its axial direction and several second vent holes arranged radially and communicating with the first vent hole. One end of the fairing is fixedly fitted onto the head, and there is a gap between the inner wall of the other end and the outer wall of the middle section pipe. The first vent hole, the second vent hole, the annular cavity, the gap between the head and the middle section pipe, and the gap between the fairing and the middle section pipe are sequentially connected.

[0010] Furthermore, the number of second vents is eight, and they are evenly distributed around the circumference.

[0011] Furthermore, one end of the ventilator is fixed inside the first ventilator via a quick-connect ventilator plug.

[0012] Furthermore, the connecting assembly includes an upper connector and a lower connector that are fixed together by bolts in parallel. The lower connector is fixed to the support wing, the force sensor is fixed to the upper connector, and there is a gap between the upper connector and the sensor mounting hole.

[0013] Furthermore, the sealing cover includes a side baffle and a top plate, wherein the side baffle has a rectangular structure, and the top plate is fixed to the top of the side baffle by several bolts, and the side baffle and the cover plate are sealed and fixed together.

[0014] Furthermore, a rubber pad is installed between the top plate and the side baffle.

[0015] An experimental system employing the aforementioned combined ventilated airborne vehicle experimental model includes the combined ventilated airborne vehicle experimental model, an air pump, a high-pressure air tank, an air pipe, a gas flow meter, a gas regulating valve, a data acquisition instrument, and a data terminal. The air pump and the high-pressure air tank are connected via a pipeline. One end of the air pipe is connected to the high-pressure air tank, and the other end is sequentially installed inside a sealing cover, a connecting component, and a support wing, and is connected to the main body of the model. The gas regulating valve and the gas flow meter are installed on the air pipe, and the force sensor is connected to the data terminal via wires and the data acquisition instrument.

[0016] A method of using the above-mentioned experimental system includes the following steps:

[0017] Step 1: Assemble the experimental system and then fix the assembled experimental system in the test section of the circulating water tunnel;

[0018] Step 2: The experiment begins by adjusting the flow rate of the high-pressure gas tank through the gas regulating valve, reading the flow rate in real time through the gas flow meter, and measuring and collecting the resistance of the vehicle through the data acquisition instrument and data terminal.

[0019] Step 3: After the experiment, save and process the drag data of the main body of the airborne vehicle model, turn off the data acquisition instrument and the computer in sequence, and remove the entire combined ventilated airborne vehicle experimental model from the test section.

[0020] Compared with the prior art, the present invention has the following advantages:

[0021] In this invention, the ventilation component is combined with a force measuring device for measuring the resistance experienced by the vehicle during navigation, thus combining the two needs of ventilation and force measurement. This avoids the influence of external pipelines on the flow field and enables more accurate and convenient measurement of the resistance experienced by the vehicle during navigation.

[0022] In this invention, the ventilator is inserted inside the support wing, and the force sensor is placed inside the cover plate. This allows the ventilator components and force measuring devices of the experimental model of the vehicle to be centrally arranged. Only the support wing is set on the surface of the main body of the model for support and connection, reducing redundant structures. This effectively reduces the influence of the external structure of the main body of the model on the flow field, reduces resistance, and further enables precise control of the ventilator under different water depths and flow velocities. Attached Figure Description

[0023] Figure 1 This is a three-dimensional structural schematic diagram of the experimental model of the combined ventilated vehicle body in this invention;

[0024] Figure 2 This is a schematic diagram of the main sectional view of the model body;

[0025] Figure 3 This is a schematic diagram of the structural composition of the experimental system of the present invention.

[0026] In the picture:

[0027] 1. Model body; 1-1. Head; 1-2. Middle section pipe fittings; 1-3. Tail; 1-4. Ventilation connector; 1-41. First vent; 1-42. Second vent; 1-5. Fairing; 2. Force sensor; 3. Support wing; 4-1. Upper connector; 4-2. Lower connector; 4-3. Groove; 5. Cover plate; 6-1. Side baffle; 6-2. Top plate; 6-3. Rubber pad; 8. Air pump; 9. High-pressure gas tank; 10. Ventilation pipe; 11. Gas flow meter; 12. Gas regulating valve; 13. Data acquisition instrument; 14. Final data. Detailed Implementation

[0028] Combination Figures 1-3This description aims to clearly and completely illustrate the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] It should be noted that the descriptions of "left," "right," "left side," "right side," "upper part," "lower part," "top," and "bottom" in this invention are defined based on the orientation or positional relationships shown in the accompanying drawings. They are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the described structure must be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0030] In the description of this invention, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0031] Specific implementation method one: Combining Figures 1-3 This embodiment describes a combined ventilated airborne experimental model, comprising a model body 1, a force sensor 2, a support wing 3, a connecting assembly, a cover plate 5, and a sealing cover. The support wing 3 is fixedly mounted on the top of the model body 1. The force sensor 2 is fixedly mounted on the top of the support wing 3 via the connecting assembly. The cover plate 5 has a sensor mounting hole. The force sensor 2 and the connecting assembly are both located within the sensor mounting hole, and the upper part of the force sensor 2 is fixedly connected to the cover plate 5 via a support plate. The lower surface of the connecting assembly and the lower surface of the cover plate 5 are at the same horizontal plane. The sealing cover is positioned above the sensor mounting hole and is fixedly connected to the cover plate 5. The cover plate 5 is the test section top plate 6-2 of a circulating water tunnel. Guide holes are provided through the top of the sealing cover, the interior of the connecting assembly, and the interior of the support wing 3 from top to bottom. A wire hole is also provided on the sealing cover.

[0032] The main body of the model 1 is the model of the ship, which is a rotating structure.

[0033] The support wing 3 adopts the NACA0012 airfoil to reduce the drag effect of the support wing 3 during the experiment.

[0034] The ventilation pipe 10 passes through each guide hole in sequence and enters the interior of the model body 1 for ventilation.

[0035] A wire passes through a wire hole and connects to force sensor 2 for data transmission.

[0036] The support wing 3 is fixedly mounted on the rear of the model body 1. The support wing 3 is fixed to the model body 1 and to the connecting components by welding.

[0037] The cover plate 5 is the test section top plate 6-2 of the circulating water tunnel. The lower surface of the connecting component and the lower surface of the cover plate 5 are set at the same horizontal plane to ensure the flow stability of water in the test section of the circulating water tunnel.

[0038] The force sensor 2 is a waterproof sensor.

[0039] The upper inner wall of the sensor mounting hole is machined with steps to facilitate the installation and removal of the force sensor 2.

[0040] During the experiment, the resistance experienced by the vehicle is transmitted to the force sensor 2 sequentially through the support wing 3 and the connecting component. The connecting component and the force sensor 2 themselves do not directly contact the cover plate 5, so they will not affect the transmission of the resistance experienced by the vehicle during the experiment. Furthermore, the ventilation pipe 10 used for ventilation is a flexible hose structure, which further ensures that it will not affect the transmission of the resistance experienced by the vehicle during the experiment.

[0041] The support plate is fixedly installed on the top of the force sensor 2 by several bolts. The support plate protrudes from the four corners of the force sensor 2 and rests on the inner wall of the sensor mounting hole of the cover plate 5, and is fixed by several bolts.

[0042] In this invention, the ventilation component is combined with a force measuring device for measuring the resistance experienced by the vehicle during navigation, thus combining the two needs of ventilation and force measurement. This avoids the influence of external pipelines on the flow field and enables more accurate and convenient measurement of the resistance experienced by the vehicle during navigation.

[0043] In this invention, the ventilator 10 is inserted inside the support wing 3, and the force sensor 2 is placed inside the cover plate 5. This allows the ventilator components and force measuring devices of the experimental model of the vehicle to be centrally arranged. Only the support wing 3 is set on the surface of the model body 1 for support and connection, reducing redundant structures. This effectively reduces the influence of the external structure of the model body 1 on the flow field, reduces resistance, and further enables precise control of the vehicle's ventilation under different water depths and flow velocities.

[0044] Specific Implementation Method Two: Combining Figures 1-3This embodiment describes a combined ventilated airborne experimental model, comprising a model body 1, a force sensor 2, a support wing 3, a connecting assembly, a cover plate 5, and a sealing cover. The support wing 3 is fixedly mounted on the top of the model body 1. The force sensor 2 is fixedly mounted on the top of the support wing 3 via the connecting assembly. The cover plate 5 has a sensor mounting hole. The force sensor 2 and the connecting assembly are both located within the sensor mounting hole, and the upper part of the force sensor 2 is fixedly connected to the cover plate 5 via a support piece. The lower surface of the connecting assembly and the lower surface of the cover plate 5 are on the same horizontal plane. The sealing cover is positioned above the sensor mounting hole and fixedly connected to the cover plate 5. The cover plate 5 is fixedly mounted on the inner wall of the test section top plate 6-2. The top of the sealing cover is fixedly mounted on the inner wall of the test section top plate 6-2, or the sealing cover is sealed and inserted into the test section top plate 6-2. Guide holes are provided through the top of the sealing cover, the interior of the connecting assembly, and the interior of the support wing 3 from top to bottom. A wire hole is also provided on the sealing cover.

[0045] The main body of the model 1 is the model of the ship, which is a rotating structure.

[0046] The support wing 3 adopts the NACA0012 airfoil to reduce the drag effect of the support wing 3 during the experiment.

[0047] The ventilation pipe 10 passes through each guide hole in sequence and enters the interior of the model body 1 for ventilation.

[0048] A wire passes through a wire hole and connects to force sensor 2 for data transmission.

[0049] The support wing 3 is fixedly mounted on the rear of the model body 1. The support wing 3 is fixed to the model body 1 and to the connecting components by welding.

[0050] The cover plate 5 is fixedly installed on the inner wall of the test section top plate 6-2, and the top of the sealing cover is fixedly installed on the inner wall of the test section top plate 6-2 or the sealing cover is sealed and installed on the test section top plate 6-2, which facilitates the installation and disassembly of the entire test model of the vehicle body in the circulating water tunnel test section.

[0051] The lower surface of the connecting component is on the same horizontal plane as the lower surface of the cover plate 5 to ensure the flow stability of water in the circulating water tunnel test section.

[0052] The force sensor 2 is a waterproof sensor.

[0053] The upper inner wall of the sensor mounting hole is machined with steps to facilitate the installation and removal of the force sensor 2.

[0054] During the experiment, the resistance experienced by the vehicle is transmitted to the force sensor 2 sequentially through the support wing 3 and the connecting component. The connecting component and the force sensor 2 themselves do not directly contact the cover plate 5, so they will not affect the transmission of the resistance experienced by the vehicle during the experiment. Furthermore, the ventilation pipe 10 used for ventilation is a flexible hose structure, which further ensures that it will not affect the transmission of the resistance experienced by the vehicle during the experiment.

[0055] The support plate is fixedly installed on the top of the force sensor 2 by several bolts. The support plate protrudes from the four corners of the force sensor 2 and rests on the inner wall of the sensor mounting hole of the cover plate 5, and is fixed by several bolts.

[0056] In this invention, the ventilation component is combined with a force measuring device for measuring the resistance experienced by the vehicle during navigation, thus combining the two needs of ventilation and force measurement. This avoids the influence of external pipelines on the flow field and enables more accurate and convenient measurement of the resistance experienced by the vehicle during navigation.

[0057] In this invention, the ventilator 10 is inserted inside the support wing 3, and the force sensor 2 is placed inside the cover plate 5. This allows the ventilator components and force measuring devices of the experimental model of the vehicle to be centrally arranged. Only the support wing 3 is set on the surface of the model body 1 for support and connection, reducing redundant structures. This effectively reduces the influence of the external structure of the model body 1 on the flow field, reduces resistance, and further enables precise control of the vehicle's ventilation under different water depths and flow velocities.

[0058] The main body 1 of the model includes a head 1-1, a middle section pipe 1-2, a tail 1-3, a venting connector 1-4, and a fairing 1-5. The head 1-1 is located at one end of the middle section pipe 1-2 and there is a gap between the head 1-1 and the middle section pipe 1-2. The tail 1-3 is threadedly installed at the other end of the middle section pipe 1-2. One end of the venting connector 1-4 is threaded into one end of the head 1-1, and the other end of the venting connector 1-4 is threaded into one end of the middle section pipe. The outer wall of the middle part of the venting connector 1-4 is flush with the inner wall of one end of the middle section pipe 1-2. An annular cavity is formed between the two parts. The venting connector 1-4 has a first vent hole 1-41 arranged axially and several second vent holes 1-42 arranged radially and communicating with the first vent hole 1-41. One end of the fairing 1-5 is fixedly fitted onto the head 1-1, and there is a gap between the inner wall of the other end and the outer wall of the middle section pipe 1-2. The first vent hole 1-41, the second vent hole 1-42, the annular cavity, the gap between the head 1-1 and the middle section pipe 1-2, and the gap between the fairing 1-5 and the middle section pipe 1-2 are sequentially connected. With this design, the head 1-1 and the tail 1-3 are installed at both ends of the middle section pipe 1-2 by a threaded connection, which can meet the different needs of high-speed cavitation and low-speed ventilated vehicles. Different types of head 1-1 can be replaced according to actual experimental needs, such as a low-speed fully autonomous passage head or a high-speed ventilated head with a cavitation disc. The venting connector 1-4 enables a detachable connection between the head section 1-1 and the middle section pipe 1-2, facilitating not only the replacement of the head section 1-1 but also the adjustment of the distance between them. The fairing 1-5 is integrated with the head section 1-1 into a single structure.

[0059] One end of the vent pipe 10 extends into the middle section pipe fitting 1-2 and communicates with the first vent hole 1-41. The first vent hole 1-41 is the air inlet, and several second vent holes 1-42 are the air outlets. The more second vent holes 1-42 there are, the better the ventilation effect.

[0060] The first vent 1-41, the second vent 1-42, the annular cavity, the gap between the head 1-1 and the middle section pipe 1-2, and the gap between the fairing 1-5 and the middle section pipe 1-2 are sequentially connected and together form a gas passage to achieve uniform circumferential ventilation.

[0061] The interior of the middle section pipe 1-2 is hollow to reduce the weight of the aircraft itself.

[0062] The number of second vent holes 1-42 is eight, and they are evenly distributed around the circumference. This design, by arranging eight vent holes evenly around the circumference, can make the pressure in the air chamber between the vent connector and the fairing more uniform, resulting in more uniform gas ejection from the circumferential air gaps.

[0063] One end of the vent pipe 10 is fixed in the first vent hole 1-41 via a quick-connect vent pipe connector. This design makes installation simpler and faster while ensuring a tight seal for ventilation, preventing air leakage that could lead to errors in the gas flow rate read from the flow meter.

[0064] The connecting assembly includes an upper connector 4-1 and a lower connector 4-2, which are bolted together in parallel. The lower connector 4-2 is fixed to the support wing 3, and the force sensor 2 is fixed to the upper connector 4-1. Both the upper connector 4-1 and the lower connector 4-2 have gaps between themselves and the sensor mounting holes. This design allows for welding as the connection between the lower connector 4-2 and the support wing 3. Both the upper connector 4-1 and the lower connector 4-2 are plate-like structures. During installation, gaps exist between the support wing 3, the upper connector 4-1, and the lower connector 4-2 and the cover plate 5, preventing direct contact and ensuring accurate resistance transmission during the experiment. A groove 4-3 is provided on the opposite side of both the upper connector 4-1 and the lower connector 4-2. Several screws connecting the force sensor 2 and the upper connector 4-1 are located within the groove 4-3, preventing interference between the screws and the lower connector 4-2.

[0065] The sealing cover includes a side baffle 6-1 and a top plate 6-2. The side baffle 6-1 has a rectangular structure, and the top plate 6-2 is fixed to the top of the side baffle 6-1 by several bolts. The side baffle 6-1 and the cover plate 5 are sealed and fixed together. This design makes the structure between the top plate 6-2 and the side baffle 6-1 detachable, facilitating the installation and removal of the force sensor 2.

[0066] A rubber gasket 6-3 is installed between the top plate 6-2 and the side baffle 6-1. This design serves to seal and waterproof the surface.

[0067] Specific implementation method three: Combining Figures 1-3This embodiment describes an experimental system using the aforementioned combined ventilated aircraft experimental model, comprising the combined ventilated aircraft experimental model, an air pump 8, a high-pressure air tank 9, a ventilation pipe 10, a gas flow meter 11, a gas regulating valve 12, a data acquisition instrument 13, and a data terminal 14. The air pump 8 and the high-pressure air tank 9 are connected via a pipeline. One end of the ventilation pipe 10 is connected to the high-pressure air tank 9, and the other end is sequentially installed within a sealing cover, a connecting assembly, and a support wing 3, and connected to the model body 1. The gas regulating valve 12 and the gas flow meter 11 are mounted on the ventilation pipe 10. A force sensor 2 is connected to the data terminal 14 via wires and the data acquisition instrument 13. The data terminal 14 is a computer. Air is compressed into the high-pressure air tank 9 by the air pump 8, the flow rate of the air exiting the high-pressure air tank 9 is adjusted by the gas regulating valve 12, and the ventilation flow rate is read in real time by the gas flow meter 11. Ventilation is achieved at the head 1-1 of the aircraft through the ventilation pipe 10. By adjusting the ventilation flow rate and the fluid velocity within the test section, cavitation bubbles are formed to envelop the vehicle, thereby achieving the purpose of supercavitation drag reduction.

[0068] Specific implementation method four: Combination Figures 1-3 This embodiment describes a method for using the above-described experimental system, comprising the following steps:

[0069] Step 1: Assemble the experimental system and then fix the assembled experimental system in the test section of the circulating water tunnel;

[0070] Step 2: The experiment begins by adjusting the flow rate of the gas from the high-pressure gas tank 9 through the gas regulating valve 12, reading the flow rate in real time through the gas flow meter 11, and measuring and collecting the resistance of the ship through the data acquisition instrument 13 and the data terminal 14.

[0071] Step 3: After the experiment, save and process the drag data of the main body 1 of the navigable vehicle model. Then, turn off the data acquisition device 13 and the computer in sequence, and remove the entire combined ventilated navigable vehicle experimental model from the test section. This is to prevent the force sensor 2 from being damaged by water ingress due to prolonged immersion in water.

[0072] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A combined ventilated airborne vehicle experimental model, characterized in that: The model includes a main body (1), a force sensor (2), a support wing (3), a connecting component, a cover plate (5), and a sealing cover. The support wing (3) is fixedly mounted on the top of the main body (1), and the force sensor (2) is fixedly mounted on the top of the support wing (3) through the connecting component. The cover plate (5) has a sensor mounting hole. The force sensor (2) and the connecting component are both located inside the sensor mounting hole, and the upper part of the force sensor (2) is fixedly connected to the cover plate (5) through a support piece. The lower surface of the connecting component is on the same horizontal plane as the lower surface of the cover plate (5). The sealing cover is located above the sensor mounting hole and is fixedly connected to the cover plate (5). The cover plate (5) is the top of the test section of the circulating water tunnel. The top of the sealing cover, the interior of the connecting component, and the interior of the support wing (3) are all provided with guide holes from top to bottom. The sealing cover is also provided with wire holes. The main body (1) of the model includes a head (1-1), a middle section pipe (1-2), a tail (1-3), a venting connector (1-4), and a fairing (1-5). The head (1-1) is located at one end of the middle section pipe (1-2) and there is a gap between the head (1-1) and the middle section pipe (1-2). The tail (1-3) is threadedly installed at the other end of the middle section pipe (1-2). One end of the venting connector (1-4) is threaded into one end of the head (1-1), and the other end of the venting connector (1-4) is threaded into one end of the middle section pipe (1-2). The outer wall of the middle part of the venting connector (1-4) is connected to the middle section pipe (1-2). An annular cavity is formed between the inner walls of one end of the fairing and the inner wall of the fairing (1-4). The fairing (1-5) has a first vent hole (1-41) arranged along its axial direction and several second vent holes (1-42) arranged along its radial direction and communicating with the first vent hole (1-41). One end of the fairing (1-5) is fixedly fitted onto the head (1-1) and there is a gap between the inner wall of the other end and the outer wall of the middle section pipe (1-2). The first vent hole (1-41), the second vent hole (1-42), the annular cavity, the gap between the head (1-1) and the middle section pipe (1-2) and the gap between the fairing (1-5) and the middle section pipe (1-2) are sequentially connected.

2. A combined ventilated airborne vehicle experimental model, characterized in that: The model includes a main body (1), a force sensor (2), a support wing (3), a connecting component, a cover plate (5), and a sealing cover. The support wing (3) is fixedly mounted on the top of the main body (1), and the force sensor (2) is fixedly mounted on the top of the support wing (3) through the connecting component. The cover plate (5) has a sensor mounting hole. The force sensor (2) and the connecting component are both located inside the sensor mounting hole, and the upper part of the force sensor (2) is fixedly connected to the cover plate (5) through a support piece. The lower surface of the connecting component and the lower surface of the cover plate (5) are on the same horizontal plane. The sealing cover is located above the sensor mounting hole and is fixedly connected to the cover plate (5). The cover plate (5) is fixedly mounted on the inner wall of the top of the test section. The sealing cover is sealed and installed on the top of the test section. The top of the sealing cover, the inside of the connecting component, and the inside of the support wing (3) are all provided with guide holes from top to bottom. The sealing cover is also provided with wire holes. The main body (1) of the model includes a head (1-1), a middle section pipe (1-2), a tail (1-3), a venting connector (1-4), and a fairing (1-5). The head (1-1) is located at one end of the middle section pipe (1-2) and there is a gap between the head (1-1) and the middle section pipe (1-2). The tail (1-3) is threadedly installed at the other end of the middle section pipe (1-2). One end of the venting connector (1-4) is threaded into one end of the head (1-1), and the other end of the venting connector (1-4) is threaded into one end of the middle section pipe (1-2). The outer wall of the middle part of the venting connector (1-4) is connected to the middle section pipe (1-2). An annular cavity is formed between the inner walls of one end of the fairing and the inner wall of the fairing (1-4). The fairing (1-5) has a first vent hole (1-41) arranged along its axial direction and several second vent holes (1-42) arranged along its radial direction and communicating with the first vent hole (1-41). One end of the fairing (1-5) is fixedly fitted onto the head (1-1) and there is a gap between the inner wall of the other end and the outer wall of the middle section pipe (1-2). The first vent hole (1-41), the second vent hole (1-42), the annular cavity, the gap between the head (1-1) and the middle section pipe (1-2) and the gap between the fairing (1-5) and the middle section pipe (1-2) are sequentially connected.

3. The experimental model of a combined ventilated aircraft according to claim 1, characterized in that: The number of second vents (1-42) is eight, and they are evenly distributed around the circumference.

4. The experimental model of a combined ventilated aircraft body according to claim 1, characterized in that: One end of the ventilator (10) is fixed in the first ventilator (1-41) through a quick-connect ventilator plug.

5. A combined ventilated airborne experimental model according to claim 1 or 2, characterized in that: The connecting assembly includes an upper connector (4-1) and a lower connector (4-2) that are fixed together by bolts. The lower connector (4-2) is fixed to the support wing (3), and the force sensor (2) is fixed to the upper connector (4-1). There is a gap between the upper connector (4-1) and the lower connector (4-2) and the sensor mounting hole.

6. A combined ventilated airborne vehicle experimental model according to claim 1 or 2, characterized in that: The sealing cover includes a side baffle (6-1) and a top plate (6-2), wherein the side baffle (6-1) has a rectangular structure, and the top plate (6-2) is fixed to the top of the side baffle (6-1) by several bolts, and the side baffle (6-1) and the cover plate (5) are sealed and fixed together.

7. The experimental model of a combined ventilated aircraft body according to claim 6, characterized in that: A rubber pad (6-3) is provided between the top plate (6-2) and the side baffle (6-1).

8. An experimental system using the combined ventilated airborne vehicle experimental model described in any one of claims 1 to 7, comprising the combined ventilated airborne vehicle experimental model, an air pump (8), a high-pressure gas tank (9), an air pipe (10), a gas flow meter (11), a gas regulating valve (12), a data acquisition instrument (13), and a data terminal (14), wherein the air pump (8) and the high-pressure gas tank (9) are connected by a pipeline, one end of the air pipe (10) is connected to the high-pressure gas tank (9), and the other end is sequentially installed in a sealing cover, a connecting component, and a support wing (3) and connected to the model body (1), the gas regulating valve (12) and the gas flow meter (11) are installed on the air pipe (10), and the force sensor (2) is connected to the data terminal (14) through a wire and the data acquisition instrument (13).

9. A method of using the experimental system according to claim 8, comprising the following steps: Step 1: Assemble the experimental system and then fix the assembled experimental system in the test section of the circulating water tunnel; Step 2: The experiment begins by adjusting the flow rate of the high-pressure gas tank (9) through the gas regulating valve (12), reading the flow rate of the gas in real time through the gas flow meter (11), and measuring and collecting the resistance of the ship through the data acquisition instrument (13) and the data terminal (14). Step 3: After the experiment is completed, save and process the drag data of the main body (1) of the airborne vehicle model, turn off the data acquisition instrument (13) and the data terminal (14) in sequence, and take the entire combined ventilated airborne vehicle experimental model out of the test section.

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