Matrix type ventilation wall in wind tunnel of low-altitude aircraft and control system of matrix type ventilation wall

Abstract

The invention discloses a matrix type ventilation wall in a low-altitude aircraft wind tunnel and a control system thereof, and relates to the field of low-altitude aircraft experiments, and the matrix type ventilation wall comprises a wind tunnel flight model which is arranged in the wind tunnel and is divided into a fixed attitude and a flight attitude; a fine adjustment mechanism; the fine adjustment mechanism is used for supporting the wind tunnel flight model with the fixed attitude and injecting weight increasing glue; the number of the bearing mechanisms is at least four, and the four bearing mechanisms are arranged around the wind tunnel flight model; the rapid curing epoxy resin is injected into the wind tunnel flight model through the fine adjustment mechanism, the purpose of increasing the weight of the wind tunnel flight model is achieved, the weight of components is replaced, the requirement for rapid experiment comparison is met, the metering valve can monitor the output amount of the resin, and the injection amount of the weight increasing glue is accurately controlled. Fine adjustment or large-scale adjustment of the weight of the wind tunnel flight model can be achieved, and the high-precision experiment requirement is met.

Description

Technical Field

[0001] The present invention relates to the field of low-altitude aircraft experiments, and in particular to a matrix wind wall in a low-altitude aircraft wind tunnel and a control system thereof. Background Art

[0002] For specialized wind tunnel tests of aircraft (such as aircraft and missiles), such as free flight and spin experiments, strict requirements are placed on the model's mass characteristics (including weight, center of gravity, and moment of inertia). Due to inevitable precision losses in materials, manufacturing, and assembly, the mass characteristics of the completed model may exhibit certain errors. When this error exceeds the design requirements, subtle adjustments to the model's mass characteristics are necessary.

[0003] The existing technology is that after the preliminary experiment is completed, components will be added to the aircraft according to the experimental requirements. However, subsequent experiments with additional components require the re-production of new models or on-site installation of components before the experiments can be carried out, which takes a long time and affects the experimental efficiency.

[0004] Therefore, it is necessary to propose a matrix wind wall and its control system in a low-altitude aircraft wind tunnel to solve the above problems. Summary of the Invention

[0005] The purpose of the present invention is to provide a matrix wind wall and its control system in a low-altitude aircraft wind tunnel, so as to solve the problem in the prior art that after the preliminary experiment is completed, components will be added to the aircraft according to the experimental requirements, but subsequent experiments with additional components will require the re-production of new models or on-site installation of components before the experiments can be carried out, which takes a long time to operate and affects the experimental efficiency.

[0006] To achieve the above-mentioned object, the present invention provides the following technical solution: a low-altitude aircraft, comprising:

[0007] A wind tunnel flight model is provided in a wind tunnel and has two positions: a fixed attitude and a flying attitude.

[0008] Fine-tuning mechanism; the fine-tuning mechanism is used to support and inject weight-increasing glue into the wind tunnel flight model with a fixed attitude;

[0009] A receiving mechanism, wherein at least four receiving mechanisms are provided, and the four receiving mechanisms are arranged around the wind tunnel flight model;

[0010] A lightweight connecting rope is connected between the wind tunnel flight model and the corresponding receiving mechanism;

[0011] The lightweight connecting rope comprises a rope body, an air bag is wrapped on the outer side of the rope body, and a magnetic sheet is arranged on the outer side of the lightweight connecting rope.

[0012] The receiving mechanism is used to release or reel in the lightweight connecting rope.

[0013] Preferably, the bottom end of the wind tunnel flight model is connected to two supporting legs, and a cavity is formed inside the supporting legs;

[0014] Both sides of the support legs are provided with connection holes for corresponding lightweight connection ropes to pass through and connect.

[0015] Preferably, the fine-tuning mechanism includes a chassis, a support column is fixed to the top of the chassis, and a fixed plate is fixedly connected to the top of the support column;

[0016] Two magnetic plug-in blocks are fixed on the top of the fixed plate, and slots for inserting the corresponding magnetic plug-in blocks are provided at the bottom ends of the two supporting legs, and the slots are communicated with the corresponding cavities.

[0017] Preferably, a storage box and a material pump are fixedly connected to the bottom end of the fixed plate, the storage box and the material pump are connected, the material pump is connected to the cavity through a pipeline, and a metering valve is provided on the pipeline;

[0018] Among them, a discharge port is provided at the top end of the magnetic insertion block, and a feed port is provided at the bottom end of the magnetic insertion block. The feed port and the discharge port are communicated, and the feed port is connected to the material pump.

[0019] Preferably, an annular chute is provided at the top of the chassis, and the bottom ends of the four receiving mechanisms are slidably fitted in the annular chute;

[0020] Among them, the receiving mechanism includes a moving seat, the top of the moving seat is connected to an electric push rod, the top of the electric push rod is connected to a shell, the inside of the shell is rotatably connected to a winding shaft, and the lightweight connecting rope is wound around the outside of the winding shaft.

[0021] Preferably, a winding motor is fixed inside the housing, and the driving shaft of the winding motor is connected to the winding shaft;

[0022] The outer shell is provided with an opening for a lightweight connecting rope to enter, the entrance end of the opening is connected to a conical sleeve, a support leg is fixed inside the outer shell, a support sleeve is fixed to the top of the support leg, a cleaning sponge sleeve is fixed inside the support sleeve, and the lightweight connecting rope passes through the inner side of the cleaning sponge sleeve.

[0023] Preferably, an annular air groove is provided at the top of the chassis, and the annular air groove is arranged outside the annular sliding groove.

[0024] The present invention also discloses a matrix wind wall in a low-altitude aircraft wind tunnel, comprising a wind tunnel consisting of an inlet section, a contraction section, a test section, a diffusion section, a power section, and a transition section;

[0025] The inlet section, contraction section, experimental section, diffusion section, power section and transition section are interconnected to form a wind channel;

[0026] Among them, multiple power frames are arranged inside the power section, and a fan is fixedly arranged inside the power frame. A plurality of cells are fixedly arranged inside the transition section, and the multiple cells are arranged in a matrix. Circular grooves are formed inside the multiple cells, and the circular grooves are communicated with the fan for guiding the airflow of the fan.

[0027] A detachable skylight is arranged at the top of the experimental section, observation windows are arranged on both sides of the experimental section, and a sealing door is arranged on one side of the observation window.

[0028] Preferably, fixed legs are fixedly connected to the bottoms of the inlet section, the contraction section, the experimental section, the diffusion section, the power section and the transition section.

[0029] The present invention discloses a matrix-type wind wall control system in a wind tunnel for a low-altitude aircraft, including:

[0030] A data acquisition module for acquiring relevant parameters in the wind tunnel;

[0031] A host computer;

[0032] A plurality of slave computers, the slave computers are industrial programmable logic controllers (PLCs), and the slave computers perform data transmission with the host computer through the TCP / IP standard communication protocol;

[0033] A communication module for communicating the data collected by the data acquisition module and respectively transmitting the collected data to a plurality of different slave computers;

[0034] An inverter for driving the fan and adjusting the wind field in the fan by changing the power frequency and voltage;

[0035] An I / O module is respectively connected to the host computer and the slave computers for realizing data input and output, as well as transmission and processing of control signals.

[0036] The technical effects and advantages of the present invention:

[0037] 1. In the actual operation of the present invention, when the wind tunnel flight model is in a fixed posture for an airflow simulation experiment in the wind tunnel, when the personnel operate the wind tunnel flight model to descend onto the fixed disk, the slot of the wind tunnel flight model will be docked with the magnetic adsorption plug, and the wind tunnel flight model can be fixed through the magnetic adsorption connection, so that the wind tunnel flight model performs the experiment in a fixed posture, improving the efficiency of the experiment.

[0038] 2. By injecting fast-curing epoxy resin into the wind tunnel flight model through the fine adjustment mechanism, the purpose of increasing the weight of the wind tunnel flight model is achieved, thereby replacing the increase in the weight of components, so as to meet the need for rapid experimental comparison. The metering valve can monitor the output of the resin, and by precisely controlling the injection amount of the weight-increasing glue, the weight of the wind tunnel flight model can be finely adjusted or largely adjusted to meet the requirements of high-precision experiments.

[0039] 3. The four corners at the bottom of the wind tunnel flight model are connected to the corresponding receiving mechanisms through lightweight connecting ropes. When the wind tunnel flight model is in a flying attitude, the lightweight connecting ropes are connected to the receiving mechanisms in a relaxed state, so that the wind tunnel flight model will not be affected by the lightweight connecting ropes when flying within a certain range. If the wind tunnel flight model fails and drops during the airflow experiment, the four lightweight connecting ropes can pull the wind tunnel flight model to avoid direct impact with the ground and play a protective role. [[ID=^]]

[0040] 4. In addition, when the wind tunnel flight model is in a fixed attitude, the lightweight connecting ropes are connected to the receiving mechanisms in a tightened state, which can improve the connection strength of the wind tunnel flight model in the fixed attitude, avoid the influence of airflow, and prevent the wind tunnel flight model from tipping over and moving.

[0041] 5. The four receiving mechanisms can slide in the annular chute to drive the receiving mechanisms to move. The four receiving mechanisms can be distributed on the outside of the wind tunnel flight model at different angles according to needs to achieve different experimental purposes.

[0042] 6. The airflow is discharged from the annular wind groove and blown upward to form an annular protective wind wall, which cancels out the airflow in the wind tunnel, so that a no-airflow environment can be formed inside the protective wind wall. The wind tunnel flight model can rise and fall inside the protective wind wall, which is convenient for personnel to inject glue or fix the wind tunnel flight model, and avoids the energy loss caused by repeatedly turning on and off the fan in the wind tunnel.

[0043] 7. By setting airbags on the outside of the rope body, when the lightweight connecting rope floats with the generated airflow, the set airbags can improve the overall lightness of the lightweight connecting rope, make it easier to float under the influence of airflow, reduce the experimental influence of its own weight on the wind tunnel flight model. At the same time, by adding airbags, the outside of the rope body can be protected, reducing the corrosion and influence of airflow, and can improve the protection of the wind tunnel flight model, avoiding direct collision and friction between the rope body and the wind tunnel flight model, affecting the experimental data of the wind tunnel flight model, or reducing damage to the wind tunnel flight model.

[0044] 8. The magnetic pieces on two adjacent lightweight connecting ropes are arranged to repel each other, which can prevent the airflow from making the lightweight connecting ropes approach each other and causing the phenomenon of mutual entanglement of the lightweight connecting ropes, improving the safety of using the wind tunnel flight model. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a schematic structural diagram of the low-altitude aircraft of the present invention.

[0046] Figure 2 For the present invention Figure 1 An enlarged schematic view of part A in.

[0047] Figure 3 This is a schematic structural diagram of the electric push rod of the present invention.

[0048] Figure 4 This is a schematic structural diagram of the discharge port of the present invention.

[0049] Figure 5 This is a schematic diagram of the internal structure of the housing of the present invention.

[0050] Figure 6 This is a schematic structural diagram of the wind tunnel of the present invention.

[0051] Figure 7 This is a schematic structural diagram of the airbag of the present invention.

[0052] Figure 8 This is a schematic structural diagram of the connecting sleeve of the present invention.

[0053] In the figure: 1, chassis; 2, annular air groove; 3, annular sliding groove; 4, moving seat; 5, receiving mechanism; 6, light connecting rope; 7, wind tunnel flight model; 8, support column; 9, material pump; 10, storage box; 11, fixed disk; 12, magnetic plug; 13, support leg; 14, electric push rod; 15, discharge port; 16, winding motor; 17, conical sleeve; 18, winding shaft; 19, housing; 20, leg; 21, support sleeve; 22, cleaning sponge; 23, skylight; 24, inlet section; 25, contraction section; 26, experimental section; 27, diffusion section; 28, power section; 29, transition section; 30, cell; 31, rope body; 32, airbag; 33, connecting sleeve; 34, magnetic sheet. Detailed implementation manners

[0054] The present invention provides a low-altitude aircraft as Figures 1 to 8 shown, including: a wind tunnel flight model 7, two support legs 13 are connected to the bottom end of the wind tunnel flight model 7, and a cavity is provided inside the support legs 13.

[0055] As Figure 1 shown, the wind tunnel flight model 7 is arranged in the wind tunnel, and the wind tunnel flight model 7 is divided into a fixed attitude and a flight attitude;

[0056] As Figure 6 shown, the present invention discloses a matrix-type wind wall in a wind tunnel of a low-altitude aircraft, including a wind tunnel, the wind tunnel is composed of an inlet section 24, a contraction section 25, an experimental section 26, a diffusion section 27, a power section 28 and a transition section 29, fixed legs are fixedly connected to the bottom ends of the inlet section 24, the contraction section 25, the experimental section 26, the diffusion section 27, the power section 28 and the transition section 29, and the inlet section 24, the contraction section 25, the experimental section 26, the diffusion section 27, the power section 28 and the transition section 29 communicate with each other to form a wind passage.

[0057] Wind tunnel installation site requirements: The total length of the wind tunnel main body and supporting facilities is limited to no more than 60m, the width is limited to no more than 24m, and the height is limited to no more than 16m. The ground bearing capacity requirement is no more than 2 tons / m². According to the requirements of the ground of the installation site, different support methods are adopted for different components of the wind tunnel. Especially for the section with a large weight distribution in the power section 28, a layout of multiple fixed legs and an overall ground steel plate is used to disperse the weight of the tunnel body.

[0058] The inlet section 24, as the starting part of the wind tunnel, mainly serves to introduce the external air flow into the wind tunnel system. The shape of the inlet section 24 is usually a flared shape, which can enable the air flow to enter the wind tunnel smoothly, reduce the turbulence and eddy current of the air flow, and thus improve the air flow quality of the wind tunnel.

[0059] An air intake lip is provided at the front end of the inlet section 24. It adopts an arc structure with a radius of 1.2m. The inlet size is 14.4m * 12.4m, the outlet is 11.5m * 10m, and the length is 1.2m.

[0060] The cross-section of the inlet section 24 is a rectangular structure, and the plates are spliced and welded with 6mm thick dry plates.

[0061] Three circles of strong steel structures with the size of I-beams are set outside, and reinforcing plates are welded at the joints. The auxiliary steel structure is made of structural flat steel with a size of 100mm * 6mm, and the spacing is about 600mm longitudinally and 1000mm transversely.

[0062] The contraction section 25 is located behind the inlet section 24, and its main function is to accelerate the air flow and make it more stable. The cross-sectional area of the contraction section 25 gradually decreases. According to Bernoulli's equation, the velocity of the air flow will increase and the pressure will decrease when the air flow passes through the contraction section 25.

[0063] The wind tunnel flight model 7 is mainly concentrated in the test section 26 for flight experiments. On both sides of the test section 26, the cavity walls are diffused to make up for the problem of horizontal buoyancy caused by the thickening of the boundary layer. The unilateral diffusion angle is 0.25 degrees. The cross-sectional size of the test section 26 is 4.5m * 3.5m, which is laid with 10mm thick steel plates. Main structural steel bars are provided on the outer surface, and the auxiliary structural components are composed of 100mm * 8mm flat steel.

[0064] The inlet of the diffusion section 27 is 4.68m * 3.5m, the outlet is 8m * 6m, and the total length is 17m. It adopts a main beam structure and an auxiliary strengthening rib structure.

[0065] Among them, multiple power frames are arranged inside the power section 28, and fans are fixedly arranged inside the power frames. Multiple cells 30 are fixedly arranged inside the transition section 29. The multiple cells 30 are arranged in a matrix. Circular grooves are opened inside the multiple cells 30, and the circular grooves are communicated with the fans for guiding the air flow of the fans;

[0066] At the top of the test section 26, a detachable skylight 23 is provided. Observation windows are provided on both sides of the test section 26, and a sealed door is provided on one side of the observation window. The test section 26 is the core part of the wind tunnel and is also the main place for the flight experiment of the low-altitude aircraft wind tunnel flight model 7. The cross-sectional area of the test section 26 is relatively small and remains constant to ensure the relative stability of the air flow velocity and direction in this section.

[0067] As Figures 1 - 4 shown, a fine-tuning mechanism is provided; the fine-tuning mechanism is used to support the wind tunnel flight model 7 in a fixed posture and inject weight-increasing glue, facilitating the fine-tuning of the weight of the wind tunnel flight model 7 directly in the test section 26 and improving the efficiency of the experiment.

[0068] Specifically, the fine-tuning mechanism includes a chassis 1. A support column 8 is fixed at the top of the chassis 1, and a fixed disk 11 is fixedly connected to the top of the support column 8. The size of the chassis 1 is 1.2 meters × 1.2 meters, made of high-strength aluminum alloy material with a thickness of 10 millimeters, and can withstand a maximum load of 1000 kilograms, ensuring the stability and reliability of the entire fine-tuning mechanism.

[0069] Two magnetic adsorption inserts 12 are fixed at the top of the fixed disk 11. Slots for the corresponding magnetic adsorption inserts 12 to be inserted are opened at the bottom ends of the two support legs 13, and the slots communicate with the corresponding cavities.

[0070] A storage box 10 and a material pump 9 are fixedly connected to the bottom end of the fixed disk 11. The storage box 10 is connected to the material pump 9, the material pump 9 is connected to the cavity through a pipeline, and a metering valve is provided on the pipeline. Among them, a discharge port 15 is opened at the top of the magnetic adsorption insert 12, and a feed port is opened at the bottom end of the magnetic adsorption insert 12. The feed port communicates with the discharge port 15, and the feed port is connected to the material pump 9.

[0071] In the actual operation of the present invention, when the wind tunnel flight model 7 is in a fixed posture for the air flow simulation experiment in the wind tunnel, when the operator lowers the wind tunnel flight model 7 onto the fixed disk 11, the slot of the wind tunnel flight model 7 will be docked with the magnetic adsorption insert 12, and the wind tunnel flight model 7 can be fixed through the magnetic adsorption connection, enabling the wind tunnel flight model 7 to perform the experiment in a fixed posture and improving the efficiency of the experiment.

[0072] Furthermore, if additional components need to be added to the wind tunnel flight model 7 in subsequent experiments after the initial experiment of the wind tunnel flight model 7, fast-curing epoxy resin can be directly injected into the wind tunnel flight model 7 through the fine-tuning mechanism to increase the weight of the wind tunnel flight model 7, thereby replacing the weight of the added components to meet the need for rapid experimental comparison. The metering valve can monitor the output of the resin. By precisely controlling the injection amount of the weight-increasing glue, fine-tuning or large-scale adjustment of the weight of the wind tunnel flight model 7 can be achieved, meeting the requirements of high-precision experiments.

[0073] The fast-curing epoxy resin uses Huibo AM-8931A / B fast-curing and molding epoxy resin.

[0074] Specifically, the fast-curing epoxy resin can be input into the interior of the cavity through suction by the material pump 9 from the discharge port 15.

[0075] As Figure 1 shown, a receiving mechanism 5 is provided. There are at least four receiving mechanisms 5, and the four receiving mechanisms 5 are arranged around the wind tunnel flight model 7. A lightweight connecting rope 6 is connected between the wind tunnel flight model 7 and the receiving mechanism 5. Among them, the receiving mechanism 5 is used to release or wind up the lightweight connecting rope 6.

[0076] The specific connection method between the wind tunnel flight model 7 and the receiving mechanism 5:

[0077] As Figure 2 shown, a connection hole is pre-opened on the wind tunnel flight model 7, and one end of the lightweight connecting rope 6 passes through the connection hole and is knotted at the passing-through position.

[0078] As Figure 8 shown, one end of the lightweight connecting rope 6 is connected with a connecting sleeve 33. The connecting sleeve 33 is sleeved on the support leg 13, and the connecting sleeve 33 is formed by the relative connection of two semi-circular sleeves. The two semi-circular sleeves can be fixed by clamping or bolts.

[0079] The four corners at the bottom end of the wind tunnel flight model 7 will be connected to the corresponding receiving mechanism 5 through the lightweight connecting rope 6. And when the wind tunnel flight model 7 is in the flight attitude, the lightweight connecting rope 6 and the receiving mechanism 5 are connected in a relaxed state, so that the wind tunnel flight model 7 will not be affected by the lightweight connecting rope 6 when flying within a certain range. If the wind tunnel flight model 7 fails and drops during the airflow experiment, the four lightweight connecting ropes 6 can pull the wind tunnel flight model 7 to avoid direct impact with the ground and play a protective role.

[0080] Moreover, due to the start of the fan in the wind tunnel, the generated airflow will make the lightweight connecting rope 6 float, and a certain amount of weight will be lost when the wind tunnel flight model 7 is opened. The floating effect of the airflow and the lost weight can offset the weight of the wind tunnel flight model 7 borne by the lightweight connecting rope 6 and avoid affecting the experimental data.

[0081] In addition, when the wind tunnel flight model 7 is in the fixed attitude, the lightweight connecting rope 6 and the receiving mechanism 5 are connected in a tightened state, which can improve the connection strength of the wind tunnel flight model 7 in the fixed attitude, avoid the influence of the airflow, and prevent the wind tunnel flight model 7 from tipping over and moving.

[0082] The lightweight connecting rope 6 includes a rope body 31, and an airbag 31 is wrapped around the outside of the rope body 31. In the actual operation of the present invention, by arranging the airbag 31 on the outside of the rope body 31, when the lightweight connecting rope 6 floats with the generated airflow, the arranged airbag 31 can increase the overall lightness of the lightweight connecting rope 6, making it easier to float under the influence of the airflow, reducing the experimental influence of its own weight on the wind tunnel flight model 7. At the same time, by adding the airbag 31, the outside of the rope body 31 can be protected, reducing the corrosion and influence of the airflow, and improving the protection of the wind tunnel flight model 7, avoiding the rope body 31 directly colliding and rubbing with the wind tunnel flight model 7, affecting the data of the wind tunnel flight model 7, or reducing damage to the wind tunnel flight model 7.

[0083] A magnetic sheet 34 is provided on the outside of the lightweight connecting rope 6. There are multiple magnetic sheets 34, and the multiple magnetic sheets 34 are distributed at equal distances along the length direction of the lightweight connecting rope 6. The magnetic sheets 34 on two adjacent lightweight connecting ropes 6 are arranged to repel each other, which can prevent the airflow from bringing the lightweight connecting ropes 6 close to each other, causing the lightweight connecting ropes 6 to be entangled with each other, thereby improving the safety of use.

[0084] A winding motor 16 is fixed inside the outer shell 19, and the driving shaft of the winding motor 16 is connected to the winding shaft 18. By starting the winding motor 16, the lightweight connecting rope 6 can be released and reeled in, thereby forming a relaxed and tightened state between the lightweight connecting rope 6 and the wind tunnel flight model 7. According to needs, a longer lightweight connecting rope 6 can be released to avoid affecting the wind tunnel flight model 7 flying in a higher space.

[0085] At the same time, it should be noted that the height of the receiving mechanism 5 is lower than the flying height of the wind tunnel flight model 7 to prevent the receiving mechanism 5 from blocking the airflow in front of the wind tunnel flight model 7.

[0086] Both sides of the supporting legs 13 are provided with connection holes for the corresponding lightweight connecting ropes 6 to pass through. An annular slide groove 3 is provided at the top of the chassis 1, and the bottom ends of the four receiving mechanisms 5 slide and fit in the annular slide groove 3; wherein, the receiving mechanism 5 includes a moving seat 4, the top of the moving seat 4 is connected to the electric push rod 14, the top of the electric push rod 14 is connected to the outer shell 19, and the inner part of the outer shell 19 is rotatably connected to the winding shaft 18, and the lightweight connecting rope 6 is wound around the outside of the winding shaft 18.

[0087] In the actual operation of the present invention, the four receiving mechanisms 5 can slide in the annular slide groove 3, automatically driving the receiving mechanisms 5 to move. The four receiving mechanisms 5 can be distributed at different angles on the outside of the wind tunnel flight model 7 as needed, and the height can be automatically adjusted. The intervals between the four receiving mechanisms 5 can also be adjusted, or the four receiving mechanisms 5 can be concentrated together to connect the wind tunnel flight model 7 (for example, kite-type connection) to achieve different experimental purposes.

[0088] The lightweight connecting rope 6 can be made of ultra-high molecular weight polyethylene fiber material.

[0089] The housing 19 is provided with a through-hole for the lightweight connecting rope 6 to enter. A tapered sleeve 17 is connected to the entering end of the through-hole. Legs 20 are fixed inside the housing 19, a support sleeve 21 is fixed to the top ends of the legs 20, a cleaning sponge sleeve 22 is fixed inside the support sleeve 21, and the lightweight connecting rope 6 passes through the inside of the cleaning sponge sleeve 22.

[0090] In the actual operation of the present invention, after the lightweight connecting rope 6 is wound into the housing 19 by the winding shaft 18, the lightweight connecting rope 6 will first pass through the tapered sleeve 17. The tapered sleeve 17 will scrape off the impurities on the outside of the lightweight connecting rope 6. And as the lightweight connecting rope 6 is wound, the support sleeve 21 can support the lightweight connecting rope 6 wound into the housing 19. Also, since the winding movement of the lightweight connecting rope 6 will rub against the inside of the cleaning sponge sleeve 22, it can play a role in cleaning the lightweight connecting rope 6.

[0091] An annular air groove 2 is formed at the top end of the chassis 1, and the annular air groove 2 is arranged outside the annular sliding groove 3.

[0092] An air pump or a blower that blows air upward is provided at the bottom end of the chassis 1. By starting the blower or the air pump, air flow is discharged from the annular air groove 2 and blown upward to form an annular protective air wall. An airless environment can be formed inside the protective air wall, so as to offset the air flow in the wind tunnel, enabling the wind tunnel flight model 7 to rise and fall inside the protective air wall, which is convenient for personnel to inject glue or fix the wind tunnel flight model 7.

[0093] Repeatedly closing and opening the fan in the wind tunnel will increase the mechanical loss of the equipment, reduce the service life of the equipment, and also increase the maintenance cost. Although continuously turning on the fan will also consume a certain amount of energy, the operation of the equipment is relatively stable, and the service life and maintenance cost are relatively low.

[0094] The present invention discloses a matrix air wall control system in a low-altitude aircraft wind tunnel, including:

[0095] A data acquisition module for acquiring relevant parameters in the wind tunnel;

[0096] The data acquisition module includes a wind direction sensor, a wind speed sensor, a temperature sensor, a humidity sensor, and a barometric pressure sensor to acquire data inside the wind tunnel.

[0097] An upper computer analyzes and processes the data acquired by the data acquisition module to generate a real-time wind field model. According to experimental requirements, different experimental tasks are edited and set, including the setting of parameters such as wind speed, wind direction, temperature, and humidity, and the experimental data is analyzed to generate an experimental report, providing a reference for the design and optimization of low-altitude aircraft.

[0098] A number of slave machines, which are industrial programmable logic controllers (PLCs). The slave machines perform data transmission with the master machine through the TCP / IP standard communication protocol. According to the instructions of the master machine, they control the start and stop of the fan, the speed regulation, and the operation of the environmental regulation system, transmit the collected data to the master machine in real time, and at the same time receive the control instructions of the master machine, monitor the operation status of the equipment in real time, detect and handle faults in a timely manner, and ensure the stable operation of the system.

[0099] A communication module, which is used to communicate the data collected by the data acquisition module, transmit the collected data to a number of different slave machines respectively, transmit the data collected by the data acquisition module to the slave machines in real time, and at the same time transmit the data of the slave machines to the master machine and transmit the control instructions of the master machine to the slave machines to ensure the real-time control of the system. The transmission rate of the communication module is usually above 100 Mbps to ensure the real-time and reliable data transmission.

[0100] An inverter, which is used to drive the fan and adjust the wind field in the fan by changing the power frequency and voltage.

[0101] An I / O module, which is respectively connected to the master machine and the slave machines, is used to realize the input and output of data, as well as the transmission and processing of control signals, receive analog and digital signals from sensors, convert them into data formats suitable for processing by the master machine, convert the control instructions of the master machine into signals suitable for execution by the slave machines, realize the precise control of the equipment, and process the input and output signals, such as filtering and amplification, to ensure the stability and reliability of the signals.

Claims

1. A low-altitude aircraft, characterized in that: Comprising: A wind tunnel flight model (7), the wind tunnel flight model (7) is arranged in the wind tunnel, and the wind tunnel flight model (7) is divided into a fixed attitude and a flight attitude; A fine-tuning mechanism; The fine-tuning mechanism is used to support the wind tunnel flight model (7) in a fixed attitude and inject weight-increasing glue; A receiving mechanism (5), at least four receiving mechanisms (5) are provided, and the four receiving mechanisms (5) are arranged around the wind tunnel flight model (7); A lightweight connecting rope (6) is connected between the wind tunnel flight model (7) and the corresponding receiving mechanism (5); The lightweight connecting rope (6) includes a rope body (31), an airbag (32) is wrapped outside the rope body (31), and a magnetic sheet (34) is arranged outside the lightweight connecting rope (6); Wherein, the receiving mechanism (5) is used to release or wind up the lightweight connecting rope (6).

2. The low-altitude aircraft according to claim 1, characterized in that: Two support legs (13) are connected to the bottom end of the wind tunnel flight model (7), and a cavity is formed inside the support legs (13); Connection holes for the corresponding lightweight connecting ropes (6) to pass through and connect are formed on both sides of the support legs (13).

3. A low-altitude aircraft according to claim 1, characterized in that: The fine-tuning mechanism includes a chassis (1), a support column (8) is fixed to the top end of the chassis (1), and a fixed disk (11) is fixedly connected to the top end of the support column (8); Two magnetic adsorption plugs (12) are fixed to the top end of the fixed disk (11), slots for the corresponding magnetic adsorption plugs (12) to insert are formed at the bottom ends of the two support legs (13), and the slots are communicated with the corresponding cavities.

4. The low-altitude aircraft according to claim 3, wherein: A storage box (10) and a material pump (9) are fixedly connected to the bottom end of the fixed disk (11), the storage box (10) is connected to the material pump (9), the material pump (9) is connected to the cavity through a pipeline, and a metering valve is arranged on the pipeline; Wherein, a discharge port (15) is formed at the top end of the magnetic adsorption plug (12), a feed port is formed at the bottom end of the magnetic adsorption plug (12), the feed port is communicated with the discharge port (15), and the feed port is connected to the material pump (9).

5. The low-altitude aircraft according to claim 3, wherein: An annular sliding groove (3) is formed at the top end of the chassis (1), and the bottom ends of the four receiving mechanisms (5) are slidably matched in the annular sliding groove (3); Wherein, the receiving mechanism (5) includes a moving seat (4), an electric push rod (14) is connected to the top end of the moving seat (4), a housing (19) is connected to the top end of the electric push rod (14), a winding shaft (18) is rotatably connected inside the housing (19), and the lightweight connecting rope (6) is wound outside the winding shaft (18).

6. An unmanned aerial vehicle according to claim 5, characterized in that: A winding motor (16) is fixed inside the housing (19), and the drive shaft of the winding motor (16) is connected to the winding shaft (18); A through port for the lightweight connecting rope (6) to enter is formed on the housing (19), a conical sleeve (17) is connected to the entering end of the through port, a support leg (20) is fixed inside the housing (19), a support sleeve (21) is fixed to the top end of the support leg (20), a cleaning sponge sleeve (22) is fixed inside the support sleeve (21), and the lightweight connecting rope (6) passes through the inside of the cleaning sponge sleeve (22).

7. An ultra-low altitude aircraft according to claim 5, characterized in that: An annular wind groove (2) is formed at the top end of the chassis (1), and the annular wind groove (2) is arranged outside the annular sliding groove (3).

8. A matrix-type wind wall in a wind tunnel for a low-altitude aircraft, characterized in that: It includes a low-altitude aircraft as described in any one of claims 1-6, and further includes a wind tunnel, which is composed of an inlet section (24), a contraction section (25), a test section (26), a diffuser section (27), a power section (28) and a transition section (29); And the inlet section (24), the contraction section (25), the test section (26), the diffuser section (27), the power section (28) and the transition section (29) communicate with each other to form a wind passage; Among them, a plurality of power frames are arranged inside the power section (28), and a fan is fixedly arranged inside the power frame. A plurality of cells (30) are fixedly arranged inside the transition section (29). The plurality of cells (30) are arranged in a matrix. Circular grooves are formed inside the plurality of cells (30), and the circular grooves are communicated with the fan for guiding the air flow of the fan; A detachable skylight (23) is arranged at the top of the test section (26), observation windows are arranged on both sides of the test section (26), and a sealing door is arranged on one side of the observation window.

9. The matrix-type air wall in a wind tunnel of a low-altitude aircraft according to claim 7, characterized in that: Fixed legs are fixedly connected to the bottoms of the inlet section (24), the contraction section (25), the test section (26), the diffuser section (27), the power section (28) and the transition section (29).

10. A matrix-type wind wall control system for a low-altitude aircraft in a wind tunnel, characterized in that: Applied to the matrix wind wall in the wind tunnel of the low-altitude aircraft described in claim 6, it further includes: A data acquisition module for acquiring relevant parameters inside the wind tunnel; A host computer; A number of slave computers, the slave computers are industrial programmable logic controllers plc, and the slave computers perform data transmission with the host computer through the tcp / ip standard communication protocol; A communication module for communicating the data acquired by the data acquisition module and respectively transmitting the acquired data to a number of different slave computers; A frequency converter for driving the fan and adjusting the wind field in the fan by changing the power frequency and voltage; An i / o module, which is respectively connected to the host computer and the slave computers, and is used to realize the input and output of data, as well as the transmission and processing of control signals.

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