阅读说明：本技术 一种高温高速模型发射装置及方法 (High-temperature high-speed model launching device and method ) 是由 于哲峰 杨鹰 胥建宇 罗庆 黄雪刚 孙良奎 李松 于 2021-07-06 设计创作，主要内容包括：本发明提供了一种高温高速模型发射装置及方法,该装置包括：发射模块、感应加热模块、测量模块和控制模块；发射模块包括弹道,用于发射模型；感应加热模块包括感应线圈,感应线圈套设于弹道的起始端,用于产生交变磁场,以加热弹道内的模型；测量模块包括测温器和测速器；测温器用于测量弹道内的模型的温度,测速器用于测量模型在弹道中运动的速度；控制模块与发射模块、感应加热模块和测量模块电连接,用于设置感应加热模块和发射模块的工作参数,以及获取模型的温度和速度。本发明能够使发射的模型同时具有高温和高速的特点,更加真实地复现高超声速飞行器在大气层中飞行时的实际情况。(The invention provides a high-temperature high-speed model launching device and a method, wherein the device comprises: the device comprises an emission module, an induction heating module, a measurement module and a control module; the launching module comprises a trajectory for launching the model; the induction heating module comprises an induction coil, and the induction coil is sleeved at the starting end of the trajectory and used for generating an alternating magnetic field so as to heat the model in the trajectory; the measuring module comprises a temperature detector and a speed detector; the temperature measurer is used for measuring the temperature of the model in the trajectory, and the speed measurer is used for measuring the moving speed of the model in the trajectory; the control module is electrically connected with the emission module, the induction heating module and the measurement module and is used for setting working parameters of the induction heating module and the emission module and acquiring the temperature and the speed of the model. The method can ensure that the transmitted model has the characteristics of high temperature and high speed at the same time, and more truly reproduces the actual situation of the hypersonic aircraft when flying in the atmosphere.)

1. A high temperature high speed model launching device, comprising:

a launching module comprising a trajectory for launching the model;

the induction heating module comprises an induction coil, the induction coil is sleeved at the starting end of the trajectory and used for generating an alternating magnetic field so as to heat the model in the trajectory;

the measuring module comprises a temperature detector and a speed detector; the temperature measurer is used for measuring the temperature of the model in the trajectory, and the speed measurer is used for measuring the speed of the model moving in the trajectory;

and the control module is electrically connected with the emission module, the induction heating module and the measurement module and is used for setting working parameters of the induction heating module and the emission module and acquiring the temperature and the speed of the model.

2. A high-temperature high-speed model launching device according to claim 1,

the model is a ferromagnetic model, or the model is arranged in the trajectory through a ferromagnetic bullet holder.

3. A high-temperature high-speed model launching device according to claim 1,

the device is arranged in a vacuum target chamber;

the control module is also used for setting the vacuum degree of the vacuum target chamber.

4. A high-temperature high-speed model launching device according to claim 1,

the circuitry of the induction heating module comprises: first to seventh capacitors C1 to C7, first to fourth diodes D1 to D4, seventh to twelfth diodes D7 to D10, second to fifth enhancement mode NMOS transistors Q2 to Q5, and a booster T1;

the anode of the first diode D1 is connected with the cathode of the third diode D3, the anode of the second diode D2 is connected with the cathode of the fourth diode D4, the cathode of the first diode D1 is connected with the cathode of the second diode D2, and the anode of the third diode D3 is connected with the anode of the fourth diode D4; one end of the alternating current power supply is connected with the anode of the first diode D1, and the other end of the alternating current power supply is connected with the anode of the second diode D2;

the first capacitor C1 is an electrolytic capacitor and is connected in parallel with the second capacitor C2, the positive end of the first capacitor C1 is connected with the cathode of the second diode D2, and the negative end of the first capacitor C1 is connected with the anode of the fourth diode D4;

the grid electrode of the second enhancement type NMOS transistor Q2, the negative electrode of the seventh diode D7 and one end of a third capacitor C3 are connected with the positive end of the first capacitor C1, and the source electrode of the second enhancement type NMOS transistor Q2, the positive electrode of the seventh diode D7 and the other end of the third capacitor C3 are connected with the grid electrode of the fourth enhancement type NMOS transistor Q4; the grid electrode of the fourth enhancement type NMOS transistor Q4, the negative electrode of the ninth diode D9 and one end of a fifth capacitor C5 are connected, and the source electrode of the fourth enhancement type NMOS transistor Q4, the positive electrode of the ninth diode D9 and the other end of the fifth capacitor C5 are connected with the negative end of the first capacitor C1; the grid electrode of the third enhancement NMOS transistor Q3, the negative electrode of the eighth diode D8 and one end of the fourth capacitor C4 are connected with the positive end of the first capacitor C1, and the source electrode of the third enhancement NMOS transistor Q3, the positive electrode of the eighth diode D8 and the other end of the fourth capacitor C4 are connected with the grid electrode of the fifth enhancement NMOS transistor Q5; the grid electrode of the fifth enhanced NMOS tube Q5, the negative electrode of the twelfth diode D10 and one end of a sixth capacitor C6 are connected, and the source electrode of the fifth enhanced NMOS tube Q5, the positive electrode of the twelfth diode D10 and the other end of the sixth capacitor C6 are connected with the negative end of the first capacitor C1;

the input side of the booster T1 has one end connected to the gate of the fourth enhancement NMOS transistor Q4 and the other end connected to the gate of the fifth enhancement NMOS transistor Q5, and an induction coil and a compensation capacitor C7 are connected in series between the two output sides of the booster T1.

5. A high-temperature high-speed model launching device according to claim 4,

the circuitry of the induction heating module further comprises: the circuit comprises a first resistor R1-a sixth resistor R6, a fifth diode D5, a voltage regulator D6, a relay and a first PNP type triode Q1;

the first resistor R1 is connected between the cathode of the second diode D2 and the positive end of the first capacitor C1, the relay comprises a switch S1 and a coil RI, and two ends of the switch S1 are connected to two ends of the first resistor R1;

the direct current side input is connected with a reference end REF of a voltage regulator D6 through a third resistor R3 and a fourth resistor R4 which are connected in series, an anode A of the voltage regulator D6 is connected with the reference end REF through a fifth resistor R5 and is connected with a signal ground GND, a cathode C of the voltage regulator D6 is connected with a grid electrode of a first PNP type triode Q1, and a drain electrode of the first PNP type triode Q1 is connected with the signal ground GND;

the source of the first PNP transistor Q1 is connected to the anode of the fifth diode D5, the gate of the first PNP transistor Q1 is connected to the cathode of the fifth diode D5 through the second resistor R2, the cathode of the fifth diode D5 is connected to-15V, and the fifth diode D5 is connected in parallel with the coil R1.

6. A high-temperature high-speed model launching device according to claim 1,

the transmitting module is a coil gun, a secondary light gas gun or a rail gun.

7. A high-temperature high-speed model launching device according to claim 6,

and if the transmitting module is a coil cannon, the control module is also used for generating a charging control instruction to charge the coil cannon.

8. A high-temperature high-speed model launching method, which is implemented by the high-temperature high-speed model launching device according to any one of claims 1 to 7, and comprises the following steps:

working parameters of the induction heating module and the emission module are set through the control module;

the control module generates a heating control instruction and sends the heating control instruction to the induction heating module;

heating the model by using the induction heating module, and measuring the temperature of the model by using a temperature detector;

the control module acquires the temperature of the model, generates a transmitting control instruction after confirming that the temperature of the model is increased to a preset temperature, and transmits the transmitting control instruction to the transmitting module;

launching the model by using the launching module, and measuring the moving speed of the model in a trajectory by using a velometer;

the control module obtains a velocity of the model.

9. A high-speed model flight flow field simulation system comprising a target chamber and the high-temperature high-speed model launching device of any one of claims 1 to 7.

10. A high-speed model flight flow field simulation method implemented by the high-speed model flight flow field simulation system according to claim 9, comprising:

setting working parameters of an induction heating module and a transmitting module in a target chamber and a high-temperature high-speed model transmitting device through a control module;

the control module generates a heating control instruction and sends the heating control instruction to the induction heating module;

heating the model by using the induction heating module, and measuring the temperature of the model by using a temperature detector;

the control module acquires the temperature of the model, generates a transmitting control instruction after confirming that the temperature of the model is increased to a preset temperature, and transmits the transmitting control instruction to the transmitting module;

launching the model by using the launching module, and measuring the moving speed of the model in a trajectory by using a velometer;

the control module acquires the speed of the model;

and enabling the launched model to penetrate into the target chamber, and realizing the flight flow field simulation of the high-speed model.

Technical Field

The invention relates to the technical field of space environment ground simulation, in particular to a high-temperature high-speed model launching device and method and a high-speed model flight flow field simulation system and method.

Background

When the hypersonic aircraft flies in the atmosphere for a long time, the hypersonic aircraft can be heated to a higher temperature due to pneumatic heating and ablation, and the higher temperature has obvious influence on part of characteristics of the hypersonic aircraft, such as flow field characteristics, light radiation characteristics, electromagnetic scattering characteristics and the like of the hypersonic aircraft.

At present, the existing equipment, such as a ballistic target and the like, can only be used for launching a high-speed model, and can not realize the simultaneous simulation of the high temperature on the surface of the hypersonic aircraft on the ground, so that the measurement result of the aircraft model is different from the actual situation of the aircraft during flying during ground simulation measurement, and the flying characteristic of the hypersonic aircraft can not be accurately reflected.

Disclosure of Invention

The embodiment of the invention provides a high-temperature high-speed model transmitting device and method, which can be used for transmitting a high-temperature high-speed model so as to more truly reproduce the actual situation of a hypersonic aircraft flying in the atmosphere.

In a first aspect, an embodiment of the present invention provides a high-temperature and high-speed model launching device, including:

a launching module comprising a trajectory for launching the model;

the induction heating module comprises an induction coil, the induction coil is sleeved at the starting end of the trajectory and used for generating an alternating magnetic field so as to heat the model in the trajectory;

the measuring module comprises a temperature detector and a speed detector; the temperature measurer is used for measuring the temperature of the model in the trajectory, and the speed measurer is used for measuring the speed of the model moving in the trajectory;

and the control module is electrically connected with the emission module, the induction heating module and the measurement module and is used for setting working parameters of the induction heating module and the emission module and acquiring the temperature and the speed of the model.

In one possible embodiment, the former is a ferromagnetic former, or the former is disposed within the trajectory by a ferromagnetic sabot.

In one possible embodiment, the apparatus is disposed within a vacuum target chamber;

the control module is also used for setting the vacuum degree of the vacuum target chamber.

In one possible embodiment, the circuitry of the induction heating module comprises: first to seventh capacitors C1 to C7, first to fourth diodes D1 to D4, seventh to twelfth diodes D7 to D10, second to fifth enhancement mode NMOS transistors Q2 to Q5, and a booster T1;

the anode of the first diode D1 is connected with the cathode of the third diode D3, the anode of the second diode D2 is connected with the cathode of the fourth diode D4, the cathode of the first diode D1 is connected with the cathode of the second diode D2, and the anode of the third diode D3 is connected with the anode of the fourth diode D4; one end of the alternating current power supply is connected with the anode of the first diode D1, and the other end of the alternating current power supply is connected with the anode of the second diode D2;

the first capacitor C1 is an electrolytic capacitor and is connected in parallel with the second capacitor C2, the positive end of the first capacitor C1 is connected with the cathode of the second diode D2, and the negative end of the first capacitor C1 is connected with the anode of the fourth diode D4;

the grid electrode of the second enhancement type NMOS transistor Q2, the negative electrode of the seventh diode D7 and one end of a third capacitor C3 are connected with the positive end of the first capacitor C1, and the source electrode of the second enhancement type NMOS transistor Q2, the positive electrode of the seventh diode D7 and the other end of the third capacitor C3 are connected with the grid electrode of the fourth enhancement type NMOS transistor Q4; the grid electrode of the fourth enhancement type NMOS transistor Q4, the negative electrode of the ninth diode D9 and one end of a fifth capacitor C5 are connected, and the source electrode of the fourth enhancement type NMOS transistor Q4, the positive electrode of the ninth diode D9 and the other end of the fifth capacitor C5 are connected with the negative end of the first capacitor C1; the grid electrode of the third enhancement NMOS transistor Q3, the negative electrode of the eighth diode D8 and one end of the fourth capacitor C4 are connected with the positive end of the first capacitor C1, and the source electrode of the third enhancement NMOS transistor Q3, the positive electrode of the eighth diode D8 and the other end of the fourth capacitor C4 are connected with the grid electrode of the fifth enhancement NMOS transistor Q5; the grid electrode of the fifth enhanced NMOS tube Q5, the negative electrode of the twelfth diode D10 and one end of a sixth capacitor C6 are connected, and the source electrode of the fifth enhanced NMOS tube Q5, the positive electrode of the twelfth diode D10 and the other end of the sixth capacitor C6 are connected with the negative end of the first capacitor C1;

the input side of the booster T1 has one end connected to the gate of the fourth enhancement NMOS transistor Q4 and the other end connected to the gate of the fifth enhancement NMOS transistor Q5, and an induction coil and a compensation capacitor C7 are connected in series between the two output sides of the booster T1.

In one possible embodiment, the circuitry of the induction heating module further comprises: the circuit comprises a first resistor R1-a sixth resistor R6, a fifth diode D5, a voltage regulator D6, a relay and a first PNP type triode Q1;

the first resistor R1 is connected between the cathode of the second diode D2 and the positive end of the first capacitor C1, the relay comprises a switch S1 and a coil RI, and two ends of the switch S1 are connected to two ends of the first resistor R1;

the direct current side input is connected with a reference end REF of a voltage regulator D6 through a third resistor R3 and a fourth resistor R4 which are connected in series, an anode A of the voltage regulator D6 is connected with the reference end REF through a fifth resistor R5 and is connected with a signal ground GND, a cathode C of the voltage regulator D6 is connected with a grid electrode of a first PNP type triode Q1, and a drain electrode of the first PNP type triode Q1 is connected with the signal ground GND;

the source of the first PNP transistor Q1 is connected to the anode of the fifth diode D5, the gate of the first PNP transistor Q1 is connected to the cathode of the fifth diode D5 through the second resistor R2, the cathode of the fifth diode D5 is connected to-15V, and the fifth diode D5 is connected in parallel with the coil R1.

In one possible embodiment, the transmitting module is a coil gun, a secondary light gas gun or an orbital gun.

In a possible embodiment, if the transmitting module is a coil gun, the control module is further configured to generate a charging control command to charge the coil gun.

In a second aspect, an embodiment of the present invention further provides a high-temperature and high-speed model launching method, which is implemented by using the high-temperature and high-speed model launching apparatus described in any one of the above embodiments, and includes:

working parameters of the induction heating module and the emission module are set through the control module;

the control module generates a heating control instruction and sends the heating control instruction to the induction heating module;

heating the model by using the induction heating module, and measuring the temperature of the model by using a temperature detector;

the control module acquires the temperature of the model, generates a transmitting control instruction after confirming that the temperature of the model is increased to a preset temperature, and transmits the transmitting control instruction to the transmitting module;

launching the model by using the launching module, and measuring the moving speed of the model in a trajectory by using a velometer;

the control module obtains a velocity of the model.

In a third aspect, an embodiment of the present invention further provides a high-speed model flight flow field simulation system, including a target chamber and the high-temperature high-speed model launching device as described in any one of the above.

In a fourth aspect, an embodiment of the present invention further provides a method for simulating a flight flow field of a high-speed model, which is implemented by using the system for simulating a flight flow field of a high-speed model described above, and includes:

setting working parameters of an induction heating module and a transmitting module in a target chamber and a high-temperature high-speed model transmitting device through a control module;

the control module generates a heating control instruction and sends the heating control instruction to the induction heating module;

heating the model by using the induction heating module, and measuring the temperature of the model by using a temperature detector;

the control module acquires the temperature of the model, generates a transmitting control instruction after confirming that the temperature of the model is increased to a preset temperature, and transmits the transmitting control instruction to the transmitting module;

launching the model by using the launching module, and measuring the moving speed of the model in a trajectory by using a velometer;

the control module acquires the speed of the model;

and enabling the launched model to penetrate into the target chamber, and realizing the flight flow field simulation of the high-speed model.

The embodiment of the invention provides a high-temperature high-speed model launching device and a high-temperature high-speed model launching method, wherein a model to be launched is heated in an induction heating mode, and is launched at a preset speed after reaching a preset temperature, so that the model flies at a high speed, the surface temperature of the model is ensured to reach a high-temperature state, and the actual flying situation of a hypersonic aircraft in the atmosphere can be more truly reproduced.

The embodiment of the invention also provides a high-speed model flight flow field simulation system and a high-speed model flight flow field simulation method, wherein the model to be launched is heated in an induction heating mode, after the preset temperature is reached, the model is launched at the preset speed, the model is made to fly into the target chamber, and the actual situation of the hypersonic aircraft flying in the atmosphere is simulated by using the target chamber and the high-temperature high-speed flying model, so that the flow field characteristic, the light radiation characteristic, the electromagnetic scattering characteristic and the like of the hypersonic aircraft can be researched, and the measurement data with high accuracy and high reliability can be further obtained.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a high-temperature high-speed model launching device according to an embodiment of the present invention;

FIG. 2 is an equivalent circuit diagram of an induction heating module according to an embodiment of the present invention;

fig. 3 is a schematic step diagram of a high-temperature high-speed model launching method according to an embodiment of the present invention.

In the figure: 1: a trajectory; 2: an induction coil; 3: a control module; 4: a temperature detector; 5: a velometer; 6: a transmitting module; 7: and (4) modeling.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer and more complete, the technical solutions in the embodiments of the present invention will be described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention, and based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the scope of the present invention.

As mentioned above, when the hypersonic aircraft flies in the atmosphere for a long time, due to pneumatic heating and ablation, the air around the hypersonic aircraft is dissociated and ionized, a high-temperature plasma sheath is formed at the head and body of the hypersonic aircraft, a plasma trail is formed at the tail of the hypersonic aircraft along with the downstream development of the flow, and the hypersonic aircraft can be heated to a higher temperature. Therefore, the model to be launched is heated, the surface of the model is launched at a high speed after reaching a high-temperature state, and the actual situation of the hypersonic aircraft flying in the atmosphere is more truly reproduced.

Specific implementations of the above concepts are described below.

Referring to fig. 1, an embodiment of the present invention provides a high-temperature high-speed model launching device, including: the device comprises a transmitting module 6, an induction heating module, a measuring module and a control module 3; in particular, among others, the use of,

the launching module 6 comprises a trajectory 1, the launching module 6 being used for launching the model.

Before firing, the model 7 to be fired is loaded into the starting end of the trajectory 1, accelerated in the trajectory 1 and ejected from the terminating end of the trajectory 1. The model 7 is made of magnetic conductive material, and the shape is matched with the trajectory 1.

The induction heating module comprises an induction coil 2, and the induction coil 2 is sleeved at the starting end of the trajectory 1 and used for generating an alternating magnetic field so as to heat a model 7 to be launched in the trajectory 1.

Adopt induction heating's mode, can make the model of awaiting the transmission in the trajectory 1 intensifies fast, and utilize the induction coil 2 of the initiating terminal that the cover was located the trajectory 1 to heat, can reduce the interference to emission module, avoid influencing emission model 7.

The measuring module comprises a temperature detector 4 and a speed detector 5; the temperature detector 4 is used to measure the temperature of the model within the trajectory 1 and the velocity detector 5 is used to measure the velocity at which the model moves in the trajectory 1.

The number, specific type, specific setting position and the like of the temperature detectors 4 and the speed detectors 5 can be selected according to actual needs. For example, the temperature detector 4, preferably an infrared thermal imager, may be provided on the starting end side of the trajectory 1 in order to monitor the temperature of the model to be shot. The velocimeter 5 is preferably provided in plurality and may be provided on the side close to the end of the trajectory 1 in order to obtain the speed at or near the exit of the model, ensuring that the model can be launched at a preset speed.

The control module 3 is electrically connected with the emission module 6, the induction heating module and the measurement module, and the control module 3 is used for setting working parameters of the induction heating module and the emission module 6 and acquiring the temperature and the speed of the model.

When the induction heating type heating device is used, the control module 3 is used for responding to a user input instruction, generating a corresponding control instruction, correspondingly sending the control instruction to the transmitting module 6, the induction heating module and the measuring module, and receiving feedback information of the transmitting module, the induction heating module and the measuring module.

In the embodiment of the invention, the working parameters of the induction heating module and the emission module, including the preset heating temperature, the preset emission speed and the like, are set through the control module 3, the induction coil 2 generates an alternating magnetic field, the surface of the model arranged in the induction coil 2 cuts alternating magnetic lines to generate alternating eddy current, and the eddy current enables carriers and atoms in the model to collide and rub with each other to generate heat energy, so that the effect of heating the model is achieved; when the model is heated to the preset temperature, the temperature of the model can be determined through the control module 3, the launching module is controlled to launch the model, and the moving speed of the model in the trajectory 1 is obtained. The technical scheme can emit a high-temperature and high-speed model so as to more truly reproduce the actual situation of the hypersonic aircraft flying in the atmosphere.

In some embodiments, the former is a ferromagnetic former, or the former is disposed within trajectory 1 by a ferromagnetic sabot. When a ferromagnetic model or a bullet support is adopted, the ferromagnetic material has good magnetic conductivity and electric conductivity, so that the heating rate can be further improved, the model is rapidly heated, and the heating time is shortened.

In some embodiments, the high-temperature high-speed model launching device is arranged in a vacuum target chamber, and a vacuum environment is provided by the vacuum target chamber, so that the interference of the environment on the model can be reduced. Further, the control module 3 is also used for setting the vacuum degree of the vacuum target chamber, and a user can adjust the environment for measurement according to actual needs through the control module 3.

In some embodiments, the circuitry of the induction heating module comprises: first to seventh capacitors C1 to C7, first to fourth diodes D1 to D4, seventh to twelfth diodes D7 to D10, second to fifth enhancement mode NMOS transistors Q2 to Q5, and a booster T1; wherein:

the anode of the first diode D1 is connected with the cathode of the third diode D3, the anode of the second diode D2 is connected with the cathode of the fourth diode D4, the cathode of the first diode D1 is connected with the cathode of the second diode D2, the anode of the third diode D3 is connected with the anode of the fourth diode D4, the first diode D1 to the fourth diode D4 form a rectifying circuit, one end of a 220V alternating current power supply is connected with the anode of the first diode D1, and the other end of the 220V alternating current power supply is connected with the anode of the second diode D2.

The first capacitor C1 is an electrolytic capacitor and is connected in parallel with the second capacitor C2 to form a filter circuit, after the first capacitor C1 is connected in parallel, the positive end of the first capacitor C1 is connected with the negative electrode of the second diode D2, and the negative end of the first capacitor C1 is connected with the positive electrode of the fourth diode D4.

The grid electrode of the second enhancement type NMOS transistor Q2, the negative electrode of the seventh diode D7 and one end of a third capacitor C3 are connected with the positive end of the first capacitor C1, and the source electrode of the second enhancement type NMOS transistor Q2, the positive electrode of the seventh diode D7 and the other end of the third capacitor C3 are connected with the grid electrode of the fourth enhancement type NMOS transistor Q4; the grid electrode of the fourth enhancement type NMOS transistor Q4, the negative electrode of the ninth diode D9 and one end of a fifth capacitor C5 are connected, and the source electrode of the fourth enhancement type NMOS transistor Q4, the positive electrode of the ninth diode D9 and the other end of the fifth capacitor C5 are connected with the negative end of the first capacitor C1; the grid electrode of the third enhancement NMOS transistor Q3, the negative electrode of the eighth diode D8 and one end of the fourth capacitor C4 are connected with the positive end of the first capacitor C1, and the source electrode of the third enhancement NMOS transistor Q3, the positive electrode of the eighth diode D8 and the other end of the fourth capacitor C4 are connected with the grid electrode of the fifth enhancement NMOS transistor Q5; the gate of the fifth enhancement NMOS transistor Q5, the negative electrode of the twelfth diode D10 and one end of the sixth capacitor C6 are connected, and the source of the fifth enhancement NMOS transistor Q5, the positive electrode of the twelfth diode D10 and the other end of the sixth capacitor C6 are connected with the negative end of the first capacitor C1, so that an inverter circuit is formed.

The input side of the booster T1 has one end connected to the gate of the fourth enhancement NMOS transistor Q4 and the other end connected to the gate of the fifth enhancement NMOS transistor Q5, and the inductor 2 and the compensation capacitor C7 are connected in series between the two output side ends of the booster T1. The induction coil 2 is sleeved outside the model. Fig. 2 shows an equivalent circuit diagram of the induction heating module, the induction coil 2 and the model constitute a load, and may be equivalent to an equivalent inductor L1 and an equivalent resistor R7 connected in series with a compensation capacitor C7 across the output side of the booster T1.

In this embodiment, ac power is input to a rectifying circuit, and a pulsating dc voltage is obtained after rectification is completed. The pulsating direct current voltage is filtered by a filter circuit to form smooth direct current voltage. The filtered direct current voltage is input to an inverter circuit, when a second enhancement type NMOS transistor Q2 and a fifth enhancement type NMOS transistor Q5 are conducted, and a third enhancement type NMOS transistor Q3 and a fourth enhancement type NMOS transistor Q4 are disconnected, a closed loop is formed, the voltage between two ends of the output side of a booster T1 is positive, when the second enhancement type NMOS transistor Q2 and the fifth enhancement type NMOS transistor Q5 are disconnected, and the third enhancement type NMOS transistor Q3 and the fourth enhancement type NMOS transistor Q4 are conducted, the closed loop is formed, and the voltage between two ends of the output side of the booster T1 is negative. Two closed loops in the inverter circuit are switched on and off, so that alternating voltage can be generated between two ends of the output side of the booster T1, namely, high-frequency alternating voltage is output to the induction coil 2 and the model, the model generates induced electromotive force, eddy current is formed on the surface of the model, heating heat is generated, and the model is rapidly heated to the required temperature.

Further, in some embodiments, the circuitry of the induction heating module further comprises: the buffer circuit comprises a first resistor R1-a sixth resistor R6, a fifth diode D5, a voltage regulator D6, a relay and a first PNP type triode Q1;

the first resistor R1 is connected between the negative electrode of the second diode D2 and the positive end of the first capacitor C1, the relay comprises a switch S1 and a coil RI, two ends of the switch S1 are connected to two ends of the first resistor R1, and the first resistor R1 is in short circuit when the switch S1 is closed;

the direct current side input is connected with a reference end REF of a voltage regulator D6 through a third resistor R3 and a fourth resistor R4 which are connected in series, an anode A of the voltage regulator D6 is connected with the reference end REF through a fifth resistor R5, the anode A is connected with a signal ground GND, a cathode C of the voltage regulator D6 is connected with a grid electrode of a first PNP type triode Q1, and a drain electrode of the first PNP type triode Q1 is connected with the signal ground GND;

the source of the first PNP transistor Q1 is connected to the anode of the fifth diode D5, the gate of the first PNP transistor Q1 is connected to the cathode of the fifth diode D5 through the second resistor R2, the cathode of the fifth diode D5 is connected to-15V, and the fifth diode D5 is connected in parallel with the coil R1. The resistances of the third resistor R3, the fourth resistor R4 and the fifth resistor R5 can be respectively selected to be 100K, 3K and 1K ohm. The voltage regulator D6 may be TL431 controllable precision voltage regulator.

In this embodiment, in order to prevent the inverter circuit from being adversely affected by an excessive voltage generated at the moment of starting the induction heating module, a buffer circuit is connected between the rectifier circuit and the filter circuit. The switch S1 and the coil RI form a relay, the part of the circuit plays a role in starting, and the first resistor R1 carries out current limiting in the starting process, so that the input voltage of the inverter circuit cannot be overhigh instantaneously. When the rated voltage is reached, the relay closes the switch S1, and the switch is switched to a normal working state, so that the starting buffer is completed.

In some embodiments, the transmitting module may be selected from a coil gun, a secondary light gas gun, or an orbital gun. These transmitting modules can meet the requirement of transmitting high-speed targets, and are convenient for arranging the induction coil 2 of the induction heating module.

Further, if the transmitting module is a coil gun, the control module 3 is further configured to generate a charging control instruction to charge the coil gun. And when the specified voltage is reached, the coil cannon stops charging. After being rectified by the rectifying circuit, the input alternating current is converted into direct current, and the direct current can charge a capacitor bank in the coil cannon. After the model is heated to the preset temperature, the control module 3 generates and sends a corresponding control instruction, the silicon controlled switch triggers a capacitor bank in the coil cannon to generate electricity, induction current is generated in the model, the model is driven to accelerate, and the model is launched out. The launching speed of the model can be adjusted by adjusting the voltage of a capacitor bank in the coil cannon and the stage number of the coil cannon.

As shown in fig. 3, an embodiment of the present invention further provides a high-temperature and high-speed model launching method, which is implemented by using the high-temperature and high-speed model launching apparatus according to any of the embodiments described above, and includes:

301, setting working parameters of an induction heating module and an emission module through a control module;

step 302, the control module generates a heating control instruction and sends the heating control instruction to the induction heating module;

303, heating the model by using the induction heating module, and measuring the temperature of the model by using a temperature detector;

step 304, the control module obtains the temperature of the model, generates a transmitting control instruction and sends the transmitting control instruction to the transmitting module after confirming that the temperature of the model is increased to a preset temperature;

305, launching the model by using a launching module, and measuring the moving speed of the model in a trajectory by using a velometer;

step 306, the control module obtains the speed of the model.

By adopting the technical scheme, the model to be launched is heated to the preset temperature and then is launched at the preset speed, so that the actual situation of the hypersonic aircraft flying in the atmosphere can be more truly reproduced. The control module obtains the speed of the model, preferably the speed of the emergent trajectory of the model, so as to compare with the preset speed or record.

The embodiment of the invention also provides a high-speed model flight flow field simulation system which comprises a target chamber and the high-temperature high-speed model launching device in any one of the embodiments.

In the embodiment, the model is heated and then launched into the target chamber through the high-temperature high-speed model launching device, so that the high temperature on the surface of the hypersonic aircraft and the flow characteristics of the flow field around the hypersonic aircraft can be simulated at the same time.

The embodiment of the invention also provides a high-speed model flight flow field simulation system, which is realized by adopting the high-speed model flight flow field simulation system and comprises the following steps:

setting working parameters of an induction heating module and a transmitting module in a target chamber and a high-temperature high-speed model transmitting device through a control module;

the control module generates a heating control instruction and sends the heating control instruction to the induction heating module;

heating the model by using an induction heating module, and measuring the temperature of the model by using a temperature detector;

the control module acquires the temperature of the model, generates a transmitting control instruction and sends the transmitting control instruction to the transmitting module after confirming that the temperature of the model is increased to a preset temperature;

launching the model by using a launching module, and measuring the moving speed of the model in a trajectory by using a velometer;

the control module acquires the speed of the model;

and enabling the launched model to penetrate into the target chamber, and realizing the flight flow field simulation of the high-speed model.

In the embodiment, the model is heated and then is emitted into the target chamber, and the working parameters of the target chamber are set, so that the actual situation of the high-temperature and high-speed aircraft flying in the flow field can be reproduced, the simulation measurement can be conveniently carried out, the flow field characteristic, the light radiation characteristic, the electromagnetic scattering characteristic and the like of the aircraft can be researched when the hypersonic aircraft flies in the atmosphere for a long time, and the technical support is provided for the characteristic analysis of the aircraft, the design and the manufacture of the aircraft and the like.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an …" does not exclude the presence of other similar elements in a process, method, article, or apparatus that comprises the element.

Those of ordinary skill in the art will understand that: all or part of the steps for realizing the method embodiments can be completed by hardware related to program instructions, the program can be stored in a computer readable storage medium, and the program executes the steps comprising the method embodiments when executed; and the aforementioned storage medium includes: various media that can store program codes, such as ROM, RAM, magnetic or optical disks.

Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.