CN112937912B - Rotary formation body lateral force control experimental device based on array type plasma - Google Patents
Rotary formation body lateral force control experimental device based on array type plasma Download PDFInfo
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- CN112937912B CN112937912B CN202110082062.1A CN202110082062A CN112937912B CN 112937912 B CN112937912 B CN 112937912B CN 202110082062 A CN202110082062 A CN 202110082062A CN 112937912 B CN112937912 B CN 112937912B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention discloses a spin-forming body lateral force control experimental device based on array type plasmas, which comprises a shell, wherein the shell comprises a front end and a rear end, the front end is of a cone structure, a groove is arranged at the bottom of the front end, a high-voltage direct-current power supply is arranged in the groove, the front end is clamped with a plasma exciter, one end of the rear end is connected with the front end, side wings are arranged on two sides of the other end, the rear end is of a hollow cylinder, and a control system connected with the plasma exciter is further arranged in the shell. The experimental device can effectively reduce the problems encountered in the real flight process through the preliminary simulation test, and has the advantages of high frequency response speed, low energy consumption, high reliability, low cost, relatively simple maintenance and long service life.
Description
Technical Field
The invention belongs to the technical fields of aerodynamics, plasma physics and flow control, and relates to a spin-forming body lateral force control experimental device based on array type plasmas.
Background
Most of the existing flying weapons are winged flying weapons, and the flying weapons mainly rely on generated aerodynamic force for maneuvering flight. The winged flying weapon generally requires good aerodynamic profile, and common winged flying weapon adopts slender spinning body structure, which can effectively reduce air resistance in the flying process.
The flow control method is mainly divided into active flow control and passive flow control, and the plasma flow control method is an active flow control method for improving the pneumatic performance of a spinning body model by adopting a plasma exciter. The aerodynamic characteristics of the spinning model can be improved by the methods of reducing drag, increasing lift, improving stall attack angle and maneuverability, reducing noise, reducing vibration, improving the flow field quality of an air inlet/exhaust system, forming new flight control force and the like. At present, a large number of synthetic jet flows are studied in plasma flow control, and a synthetic jet flow technology is a brand new active flow control technology, and a core component of the technology is a synthetic jet flow exciter. When the vibration membrane is started to work, no actuating component exists except the vibration of the vibration membrane, and the adjustment and the control can be carried out according to the requirement only by changing the frequency, the amplitude and the phase of the electric signal of the exciter. Meanwhile, the synthetic jet actuator does not need a jet supply and injection system, so that the structure is very simple, the weight of the structure is greatly reduced, and the synthetic jet actuator has an adjusting function. Studies have shown that: the impulse generated by a single jet pulse is 14[ mu N, s ] at 100mJ, and if the pulse discharge energy is further increased to 500mJ, the impulse generated by the single jet pulse is about 130[ mu N, s ], but the resultant vortex formed by the single jet pulse and the incoming flow is insufficient to generate a sufficient control moment.
Disclosure of Invention
The invention aims to provide a spin-forming body lateral force control experimental device based on array type plasmas, which has the characteristic of reducing problems encountered by an aircraft in real flight through a pre-simulation test.
The technical scheme adopted by the invention is that the spin-forming body lateral force control experimental device based on array type plasmas is characterized by comprising a shell, wherein the shell comprises a front end and a rear end, the front end is of a cone structure, a groove is formed in the bottom of the front end, a high-voltage direct-current power supply is arranged in the groove, the front end is clamped with a plasma exciter, one end of the rear end is connected with the front end, side wings are arranged on two sides of the other end, the rear end is of a hollow cylinder, and a control system connected with the plasma exciter is further arranged in the shell.
The invention is also characterized in that:
the number of the plasma exciters is 2-6, and the plasma exciters are arranged at the front end in an array mode.
The plasma exciters are equally spaced and located on the same bus bar of the housing.
An electrode unit is arranged in the plasma exciter, the electrode unit comprises an exciting positive electrode and an exciting negative electrode, and the exciting positive electrode and the exciting negative electrode are connected with a control system.
The electrode materials of the exciting positive electrode and the exciting negative electrode are tungsten bars or copper bars.
The exposed length of the exciting positive electrode and the exciting negative electrode in the plasma exciter is 2mm-4mm, and the interval distance between the exciting positive electrode and the exciting negative electrode is 6mm-8mm.
The control system comprises a collection module and a processing module, wherein the collection module comprises a sensor arranged at the front end, the sensor is connected with a signal collection card arranged at the rear end, and the signal collection card is connected with the processing module.
The high-voltage direct-current power supply is connected with a capacitor for storing energy.
The other end of the rear end is connected with a long handle shaft.
The shell is made of epoxy resin.
The beneficial effects of the invention are as follows:
1. the array-based plasma-based spinning body lateral force control experimental device fills the gap of the current spinning body model control experimental device, can more completely simulate the dynamic change condition of a spinning body model in the actual flight process, and has important reference significance for controlling the lateral force around the actual spinning body prototype through data and conclusions obtained by simulating the flight environment in the experimental device;
2. according to the array type plasma exciter arrangement mode of the spin-forming body lateral force control experimental device based on the array type plasma, under the condition that the minimum resistance is ensured, the switches of different plasma exciters are controlled to spray air flow, so that the strength of the plasma spray air flow is increased, and the lateral force around the spin-forming body model is well controlled;
3. according to the rotating body side force control experimental device based on array type plasmas, the embedded closed-loop control system is connected to perform feedback control on the current state of the rotating body model, different strategies can be adopted to control the switch of the plasma exciter to spray air flow under different attack angle states, and the optimal control effect is achieved;
4. according to the array-based plasma-based spin-forming body lateral force control experimental device, the tail long stem is connected with the inner conduction of the plasma exciter, so that the control of the spin-forming body model lateral force at any angle can be realized, the limitation of the control direction is broken through, and the control efficiency is greatly improved.
Drawings
FIG. 1 is a schematic diagram of a spin-on body lateral force control experimental apparatus based on array type plasmas;
FIG. 2 is a schematic diagram of the structure of a plasma exciter in an array-based plasma-based spin-body lateral force control experimental apparatus;
FIG. 3 is a block diagram of the operation of the control module in the spin-on body lateral force control experimental apparatus based on array type plasma of the present invention;
fig. 4 is a state diagram of the jet flow of the plasma actuator in the array-based plasma-based spin-body lateral force control experimental apparatus according to the present invention.
In the figure, 1, a high-voltage direct current power supply, 2, a plasma exciter, 3, a control system, 4, a shell, 5, a long handle shaft, 6, an excitation positive electrode and 7, an excitation negative electrode.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
The invention relates to a spin-forming body lateral force control experimental device based on array type plasmas, which is shown in fig. 1, and comprises a shell 4, wherein the shell 4 comprises a front end and a rear end, the front end is of a cone structure, a groove is arranged at the bottom of the front end, a high-voltage direct current power supply 1 is arranged in the groove, the front end is clamped with a plasma exciter 2, one end of the rear end is connected with the front end, side wings are arranged on two sides of the other end, the rear end is of a hollow cylinder, a control system 3 connected with the plasma exciter 2 is also arranged in the shell 4, and the control system 3 is an embedded closed-loop control system;
the number of the plasma exciters 2 is 2-6, the plasma exciters 2 are arranged at the front end in an array manner, the control force of the plasma exciters 2 on the lateral force at the position closer to the front end of the shell 4 is stronger, and the control force of the plasma exciters 2 is sequentially weakened along with the continuous increase of the distance;
the distance between the plasma exciters 2 is equal and the plasma exciters are positioned on the same bus of the shell 4;
as shown in fig. 2, an electrode unit is arranged in the plasma exciter 2, the electrode unit comprises an exciting positive electrode 6 and an exciting negative electrode 7, and the exciting positive electrode 6 and the exciting negative electrode 7 are connected with the control system 3; the electrode materials of the excitation positive electrode 6 and the excitation negative electrode 7 are tungsten bars or copper bars; the exposed length of the exciting positive electrode 6 and the exciting negative electrode 7 in the plasma exciter 2 is 2mm-4mm, and the interval distance between the exciting positive electrode 6 and the exciting negative electrode 7 is 6mm-8mm; the plasma exciter 2 is connected with the exciting positive electrode and the exciting negative electrode correspondingly from the inside of the shell 4 through wires, and finally the exciting positive electrode 6 and the exciting negative electrode 7 are respectively connected with the embedded closed-loop control system 3 through binding posts;
the embedded closed-loop control system 3 is connected with the positive electrode and the negative electrode of the plasma exciter 2 through binding posts to control the switch of the exciter, the embedded closed-loop control system 3 comprises an acquisition module and a processing module, the acquisition module comprises a sensor arranged at the front end, the sensor is connected with an ART2153 signal acquisition card arranged at the rear end, the signal acquisition card is connected with the processing module, and the processing module is PCM-3365; the positive electrode of the output of the sensor is connected to the positive electrode of a channel on the ART3153 signal acquisition card, the negative electrode of the output line and the grounding end of the ART3153 signal acquisition card are mainly used for measuring the flight state parameters of the slender body model, and the acquired digital signals are directly transmitted and stored in the ART3153 signal acquisition card; the ART3153 signal acquisition card transmits the stored flight state parameters to the PCM-3365 system in real time for analysis and processing, and the PCM-3365 system is connected with the ART3153 signal acquisition card through a USB line to read data stored in the acquisition card, and simultaneously sets the initially optimized parameter values and performs closed-loop feedback control according to the initial values;
the high-voltage direct-current power supply 1 is also connected with a capacitor for energy storage, the capacitance of the capacitor is 0.05-0.5, and the withstand voltage is not less than 5000V
The other end of the rear end is connected with a long handle shaft 5;
the shell 4 is made of epoxy resin;
as shown in fig. 3, which is a working block diagram of the embedded closed-loop control system, when the rotary model flies at a constant speed in a straight line, the embedded closed-loop control system 3 does not work when the plasma exciter 2 is in a closed state, and the rotary model does not need to be adjusted in real time according to the current state; when the rotary model is inclined in angle, detecting the change condition of the pitch angle and the roll angle of the rotary model in the flying process through the MEMS sensor 3, and transmitting data to the embedded closed-loop control system 3;
as shown in fig. 4, the state of the airflow around the front end of the back-rotation model of the experimental device is shown, because the embedded closed-loop control system 3 is preset to be in a small attack angle range of 0-15 degrees and in a large attack angle range of more than 15 degrees, when the MEMS sensor 3 measures that the current rotation model is in the small attack angle range, the embedded closed-loop control system 3 controls the front two plasma actuators 2 close to the front end of the shell to open to spray airflow so as to change the lateral force around the rotation model; when the MEMS sensor 3 measures that the current state of the spinning body model is in a large attack angle range, the embedded closed-loop control system 3 starts all plasma exciters 2 to spray air flow so as to change the lateral force around the spinning body model; the control of the moving direction of the rotary model can be realized through a long handle shaft 5 connected with the tail part, the long handle shaft 5 is connected with the tail part of the shell 4 through a bearing, and the bearing is connected with the front end of the shell and is reinforced through a screw, so that the function of rotating angle is realized.
The experimental device of the invention has the following advantages: firstly, the gap of the current rotary adult model experimental device is filled, and the problems encountered in the real flight process can be effectively reduced through the pre-simulation test of the experimental device; secondly, a novel array-type arrangement plasma exciter is provided, and the switch of the plasma exciter is controlled to jet air flow through an embedded closed-loop control system, so that the air flow jet force of the plasma exciter is enhanced; thirdly, the long stem connected with the tail of the rotary model can measure experimental parameters at any angle, and the limitation of measuring angles is broken through; fourthly, the experimental device has simple structure, flexibility and convenience, and the arrangement of one row can be suitable for most of flight weapons in consideration of smaller diameters of real flight weapons, so that the applicability is strong; fifthly, no mechanical element exists, the electric power is triggered, the frequency response speed is high, the energy consumption is low, and the reliability is high. And sixth, the cost is low, maintenance is relatively simple, the service life is long, compared with other solutions, the weight of the system is greatly reduced, and the reliability is improved.
Claims (3)
1. The spin-forming body lateral force control experimental device based on array type plasmas is characterized by comprising a shell (4), wherein the shell (4) comprises a front end and a rear end, the front end is of a cone structure, a groove is formed in the bottom of the front end, a high-voltage direct-current power supply (1) is arranged in the groove, a plasma exciter (2) is clamped at the front end, the rear end is a hollow cylinder, one end of the rear end is connected with the front end, side wings are arranged on two sides of the other end, the end of the other end of the rear end is connected with a long handle shaft (5), and a control system (3) connected with the plasma exciter (2) is further arranged in the shell (4);
the control system (3) comprises an acquisition module and a processing module, wherein the acquisition module comprises a sensor arranged at the front end, the sensor is connected with a signal acquisition card arranged at the rear end, and the signal acquisition card is connected with the processing module;
the plasma exciters (2) are 2-6 and are arranged at the front end in an array, the distances between the plasma exciters (2) are equal, and the plasma exciters are positioned on the same bus of the shell (4);
an electrode unit is arranged in the plasma exciter (2), the electrode unit comprises an excitation positive electrode (6) and an excitation negative electrode (7), the exposed lengths of the excitation positive electrode (6) and the excitation negative electrode (7) in the plasma exciter (2) are 2mm-4mm, and the interval distance between the excitation positive electrode (6) and the excitation negative electrode (7) is 6mm-8mm; the electrode materials of the exciting positive electrode (6) and the exciting negative electrode (7) are tungsten rods or copper rods; the excitation positive electrode (6) and the excitation negative electrode (7) are connected with the control system (3).
2. An array plasma-based spin-body lateral force control experimental device according to claim 1, wherein the high-voltage direct current power supply (1) is connected with a capacitor for storing energy.
3. The array plasma-based spin-body lateral force control experimental device according to claim 1, wherein the shell (4) is made of epoxy resin.
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