An electrically controlled solid propellant coaxial small size charge combustion performance testing device

Abstract

The utility model discloses a kind of electric control solid propellant coaxial formula small size charge combustion performance testing device, comprising: window combustion chamber, coaxial electric control microthruster, light emitting diode, high-precision weighing sensor, voltage probe, current probe, oscilloscope, nitrogen cylinder, direct current voltage source, high-speed camera and computer. High-speed camera synchronously records the process of coaxial electric control microthruster from ignition to extinguishing, the process of light emitting diode light signal generation and disappearance, and the time difference of both is calculated to ignite / extinguish delay time;Oscilloscope and high-precision weighing sensor record the instantaneous mass change of propellant during combustion process to obtain instantaneous mass burning rate value;Oscilloscope and voltage probe, current probe synchronously record the voltage and the current size passing through applied on coaxial electric control microthruster. The device makes up the test deficiency of electric control solid propellant in small size charge combustion performance.

Description

Technical Field

[0001] This utility model relates to the field of solid propellant combustion performance testing, specifically to an electronically controlled coaxial small-sized combustion performance testing device for solid propellants. Background Technology

[0002] Compared to traditional solid propellants, electrically controlled solid propellants, due to their different composition and proportions, can actively control the combustion process under the influence of external voltage. By applying / removing voltage and changing the voltage value, operations such as controllable combustion and adjustable burning rate can be achieved. This feature highlights the advantages of electrically controlled solid propellants and distinguishes them from traditional solid propellants.

[0003] Currently, there are few testing methods for the combustion performance of this novel electrically controlled solid propellant. Ignition delay time, burning rate, and quenching delay time are important performance characterization parameters for electrically controlled solid propellants. Traditional solid propellant combustion performance testing methods, including the standard engine method, propellant strip method, ultrasonic method, target line method, and closed burner method, are no longer applicable to electrically controlled solid propellants. Patent CN 115389699 B discloses a magnetically driven electrically controlled solid propellant combustion performance testing system and method. CN 119178838 A discloses a high-pressure visual electrically controlled solid propellant combustion characteristic measurement device. In both of these devices, due to the large propellant grain size (diameter greater than 20mm), the propellant loading structure adopts an end-face "sandwich" structure, suitable for the combustion of large-size propellant loadings in attitude control engines and other applications. This structure requires external power to ensure real-time contact between the propellant and the electrodes. Changes in temperature and the length of the propellant grain itself affect the propellant's conductivity, resulting in significant differences in burning rate at the same voltage. Therefore, the obtained average burning rate cannot represent the entire combustion process.

[0004] Furthermore, as an electrically controlled micro-thruster for space micro- and nano-satellites, the coaxial propellant structure requires a small diameter (less than 5 mm) and a small amount (less than 1 g), resulting in a weak combustion flame. Photoelectric sensors cannot accurately capture the flame intensity at the moment of propellant ignition and extinguishing, making it impossible to accurately determine propellant ignition and extinguishing. Therefore, existing testing devices are not suitable for characterizing the combustion performance of coaxial small-sized electrically controlled solid propellants. Utility Model Content

[0005] In view of the above-mentioned shortcomings of the prior art, the technical problem to be solved by this utility model is to provide a device that can test the combustion performance of small-sized electronically controlled solid propellants, specifically, the device that can test the ignition / extinguishing delay time and instantaneous mass burning rate of coaxial small-sized electronically controlled solid propellants under different voltages and pressures.

[0006] The technical solution adopted by this utility model to solve its technical problem is:

[0007] A combustion performance testing device for coaxial small-sized electronically controlled solid propellants is disclosed. The device includes a windowed combustion chamber, a coaxial electronically controlled micro-thruster, a light-emitting diode, a high-precision weighing sensor, a voltage probe, a current probe, an oscilloscope, a nitrogen cylinder, a DC voltage source, a high-speed camera, and a computer.

[0008] The through-window combustion chamber includes high-pressure resistant glass, a flange, sample holders, a pressure gauge, and a solenoid valve. The flange secures the high-pressure resistant glass to the through-window combustion chamber, providing an observation window during propellant combustion.

[0009] Nitrogen cylinders are used to pressurize the windowed combustion chamber, and pressure gauges are used to monitor and adjust solenoid valves to simulate different pressure environments during propellant combustion.

[0010] A DC voltage source is used to provide the voltage required for propellant combustion, and the voltage is adjustable.

[0011] A coaxial electrically controlled micro-thruster and a light-emitting diode (LED) are placed on the sample holder. The LED is connected in series with the coaxial electrically controlled micro-thruster in the circuit. When energized, the LED generates a light signal, and the propellant burns to produce a flame.

[0012] High-speed cameras are used to record the ignition, combustion, and extinguishing processes of coaxial electronically controlled micro-thrusters and the time when light-emitting diodes generate signals. The time difference between the two is used as the ignition / extinguishing delay time.

[0013] The computer works in conjunction with the high-speed camera to save and analyze the data transmitted by the high-speed camera.

[0014] The oscilloscope is used in conjunction with voltage probes, current probes, and high-precision load cells to convert feedback voltage, current, and real-time mass changes into signal outputs.

[0015] Voltage and current probes are used to record the voltage applied to the coaxial electronically controlled micro-thrust and the current flowing through it, respectively. The product of the voltage and current values, integrated over the ignition delay time, yields the energy required for ignition. A high-precision weighing sensor records the real-time mass change of the propellant during combustion in the coaxial electronically controlled micro-thrust; this mass change is calculated as the instantaneous mass burning rate.

[0016] The advantages of this invention compared to the prior art are:

[0017] 1. This utility model utilizes a high-speed camera to synchronously record the process from ignition to extinguishing of a coaxial electronically controlled micro-thruster, as well as the generation and disappearance of the light signal from the light-emitting diode. The time difference between the two can be used to directly calculate the ignition / extinguishing delay time, thus solving the problem that traditional photoelectric sensors cannot accurately capture weak flame signals in the coaxial small-size charge mode.

[0018] 2. In view of the shortcomings of irregular end-face combustion surface shape and different instantaneous burning rates of electronically controlled solid propellants, this utility model proposes an instantaneous mass burning rate, which uses an oscilloscope and a high-precision weighing sensor to record the instantaneous mass change of the propellant during combustion to obtain the instantaneous mass burning rate value.

[0019] 3. The oscilloscope of this invention synchronously records the voltage and current applied to the coaxial electronically controlled micro-thruster with the voltage probe and current probe, and calculates the ignition energy required for propellant combustion by integrating the recorded voltage and current curves. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the electronically controlled solid propellant testing device of this utility model.

[0021] Figure 2 This is a diagram showing the arrangement of the coaxial micro-thruster and the light-emitting diode in this utility model.

[0022] Figure 3 The diagram shows the ignition, combustion, and extinguishing process of the coaxial micro-thruster of this utility model as measured in actual operation.

[0023] The attached figures are labeled as follows: 1 Oscilloscope; 2 High-precision weighing sensor; 3 Pressure gauge; 4 High-pressure resistant glass; 5 Transparent combustion chamber; 6 Solenoid valve; 7 Computer; 8 Nitrogen cylinder; 9 High-speed camera; 10 Light-emitting diode; 11 Sample clamp; 12 Coaxial electrically controlled micro-thruster; 13 Flange; 14 Current probe; 15 DC voltage source; 16 Voltage probe. Detailed Implementation

[0024] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments:

[0025] like Figures 1-3 As shown, a coaxial small-sized combustion performance testing device for electrically controlled solid propellants includes an oscilloscope 1, a high-precision weighing sensor 2, a pressure gauge 3, high-pressure resistant glass 4, a combustion chamber with a transparent window 5, a solenoid valve 6, a computer 7, a nitrogen cylinder 8, a high-speed camera 9, a light-emitting diode 10, a sample clamp 11, a coaxial electrically controlled micro-thruster 12, a flange 13, a current probe 14, a DC voltage source 15, and a voltage probe 16.

[0026] A pressure gauge 3 and a solenoid valve 6 are installed on the window combustion chamber 5; the high-pressure resistant glass 4 is fixedly installed on the window combustion chamber 5 via a flange 13;

[0027] Nitrogen cylinder 8 is connected to windowed combustion chamber 5, and the ambient pressure inside windowed combustion chamber 5 is dynamically adjusted by pressure gauge 3 and solenoid valve 6.

[0028] The coaxial electronically controlled micro thruster 12 and the light-emitting diode 10 are connected in series in the ignition circuit, placed on the sample holder 11, and placed in the window combustion chamber 5 through the sample holder 11.

[0029] The high-precision weighing sensor 2 is placed inside the sample clamp 11 and is placed inside the window combustion chamber 5 through the sample clamp 11 and connected to the coaxial electronically controlled micro thruster 12.

[0030] The coaxial electronically controlled micro-thruster 12 is connected to the current probe 14, voltage probe 16, and DC voltage source 15 outside the windowed combustion chamber 5, respectively.

[0031] The high-speed camera 9 is coaxially aligned with the high-pressure resistant glass 4 on the transparent combustion chamber 5, and captures the working status of the light-emitting diode 10 and the coaxial electronically controlled micro-thruster 12 through the high-pressure resistant glass 4.

[0032] Oscilloscope 1 is used to display the signals recorded by voltage probe 16, current probe 14 and high-precision weighing sensor 2.

[0033] This utility model provides a specific implementation method in which the positive electrode rod and the negative electrode shell in the coaxial electronically controlled micro thruster 12 are arranged coaxially, and the electronically controlled solid propellant is placed between them.

[0034] This utility model provides a specific implementation method in which a high-precision weighing sensor 2 is used to record the real-time mass change of the propellant in the coaxial electronically controlled micro-thruster 12 during combustion.

[0035] This utility model provides a specific implementation method in which one end of the high-precision weighing sensor 2, the current probe 14, and the voltage probe 16 are connected to the coaxial electronically controlled micro-thruster 12 and its lead wires, and the other end is connected to the oscilloscope 1.

[0036] This utility model provides a specific implementation method in which the current loop in the current probe 14 is passed through any lead wire of the positive electrode rod and the negative electrode shell in the coaxial electronically controlled micro thruster 12, and the current probe 14 monitors the current value passing through the coaxial electronically controlled micro thruster 12.

[0037] This utility model provides a specific implementation method in which the positive and negative clamps of the voltage probe 16 are respectively connected to the two leads of the positive rod and the negative tube shell of the coaxial electronically controlled micro thruster 12 to monitor the voltage value applied to the coaxial electronically controlled micro thruster 12.

[0038] This utility model provides a specific implementation method in which a nitrogen cylinder 8 is used to pressurize the window combustion chamber 5, a pressure gauge 3 monitors the pressure inside the window combustion chamber 5, and the pressure is dynamically adjusted by a solenoid valve 6.

[0039] This utility model provides a specific implementation method in which a DC voltage source 15 is used to apply voltage to a coaxial electrically controlled micro-thruster 12, a voltage probe 16 is used to record the magnitude of the voltage applied to the coaxial electrically controlled micro-thruster 12, and a current probe 14 is used to record the magnitude of the current passing through the coaxial electrically controlled micro-thruster 12.

[0040] This utility model provides a specific implementation method in which a high-speed camera 9 records the ignition, combustion, and extinguishing of a coaxial electrically controlled micro-thruster 12 through a high-pressure resistant glass 4 fixed by a flange 13.

[0041] This utility model provides a specific implementation method in which a computer 7 is used to record, store, and analyze images captured by a high-speed camera 9.

[0042] In this invention, nitrogen cylinder 8 pressurizes the windowed combustion chamber 5. The ambient pressure inside the windowed combustion chamber 5 can be dynamically adjusted by pressure gauge 3 and solenoid valve 6 to simulate the ambient pressure when the coaxial electronically controlled micro-thruster 12 is working. The pressure adjustment range is 0.1MPa to 10MPa.

[0043] In this invention, computer 7 is connected to high-speed camera 9. Computer 7 sets the relevant parameters for high-speed camera 9 when shooting, and then saves the results captured by high-speed camera 9.

[0044] In this invention, the DC voltage source 15 provides the voltage required for the operation of the coaxial electronically controlled micro-thruster 12, and the voltage is adjustable in the range of 0V to 300V.

[0045] In this invention, the coaxial electronically controlled micro-thruster 12 has a propellant diameter of 4mm, is connected in series with the light-emitting diode 10 in the ignition circuit, is placed on the sample holder 11, and is placed in the transparent combustion chamber 5 through the sample holder 11.

[0046] In this invention, a high-precision weighing sensor 2 is placed in the sample holder 11 to monitor the mass change of the propellant in the coaxial electronically controlled micro-thruster 12 in real time, with an accuracy of 0.01 mg.

[0047] In this invention, the oscilloscope 1 processes the signals transmitted by the high-precision weighing sensor 2, the current probe 14, and the voltage probe 16 and converts them into digital signals for output.

[0048] The testing process for the combustion performance of coaxial small-sized coaxial charges of electrically controlled solid propellants is as follows:

[0049] The coaxial electronically controlled micro-thruster 12 is connected in series with the light-emitting diode 10 and sent into the transparent combustion chamber 5 through the sample clamp 11.

[0050] One end of the high-precision weighing sensor 2, current probe 14, and voltage probe 16 is connected to the coaxial electronically controlled micro-thruster 12 and its lead wires, and the other end is connected to the oscilloscope 1. The oscilloscope 1 is adjusted to the required time interval and the numerical range of each channel, and the oscilloscope 1 is in the ready-to-trigger mode.

[0051] The computer 7 adjusts the exposure time and frame rate of the high-speed camera 9. The coaxial electronically controlled micro-thruster 12 and the light-emitting diode 10 appear within the shooting window of the high-speed camera 9 through the high-pressure resistant glass 4 on the flange 13.

[0052] The valve of nitrogen cylinder 8 is opened to pressurize the window combustion chamber 5 with nitrogen. Pressure gauge 3 monitors the pressurization value. After the predetermined pressure value is reached in the window combustion chamber 5, the solenoid valve 6 dynamically adjusts to ensure that the pressure is consistent with the preset value.

[0053] Adjust the output voltage of DC voltage source 15, then turn on the switch to power the ignition circuit, and simultaneously start the high-speed camera 9 to acquire images.

[0054] After the experiment was completed, the pressure in the through-window combustion chamber 5 was released through the solenoid valve 6.

[0055] The voltage curve, current curve, and propellant mass change curve transmitted to oscilloscope 1 are saved and exported. The entire ignition, combustion, and extinguishing process captured by high-speed camera 9 is also saved and exported.

[0056] Data processing of combustion performance test results for coaxial small-sized coaxial charges of electrically controlled solid propellants:

[0057] The high-speed camera 9 captures the time t1 when the LED 10 emits a light signal after being powered on, and the time difference t2 when the coaxial electronically controlled micro-thruster 12 begins to generate a flame. Therefore, the ignition delay time is the time difference between the two: t i = t2–t1.

[0058] Oscilloscope 1 acquires the voltage U curve and the current I curve. The energy required for ignition is obtained by integrating the product of voltage U and current I over the ignition delay time.

[0059] Oscilloscope 1 acquired the mass change curve of the propellant m in the coaxial electronically controlled micro-thruster 12, and the instantaneous mass burning rate was obtained by differentiating the mass with respect to time.

[0060] The high-speed camera 9 captured the time t3 after the power outage when the light-emitting diode 10 disappeared, and the time difference between the disappearance of the flame from the coaxial electronically controlled micro-thruster 12 and t4 was then recorded. Therefore, the flameout delay time is the time difference between the two: t e = t4–t3.

[0061] Finally, it should be noted that the above examples are merely specific embodiments of this utility model. Obviously, this utility model is not limited to the above embodiments and can have many variations. All variations that can be directly derived or conceived by those skilled in the art from the disclosure of this utility model should be considered within the protection scope of this utility model.

Claims

1. A coaxial small-sized combustion performance testing device for electrically controlled solid propellants, characterized in that: include Transparent combustion chamber (5); A pressure gauge (3) and a solenoid valve (6) are installed on the windowed combustion chamber (5); High-pressure resistant glass (4) is fixedly installed in the window combustion chamber (5) via flange (13); The nitrogen cylinder (8) is connected to the window combustion chamber (5), and the ambient pressure inside the window combustion chamber (5) is dynamically adjusted by the pressure gauge (3) and the solenoid valve (6); It is equipped with a coaxial electrically controlled micro-thruster (12); The coaxial electronically controlled micro thruster (12) and the light-emitting diode (10) are connected in series in the ignition circuit and placed on the sample holder (11). The sample holder (11) is placed in the transparent combustion chamber (5). The high-precision weighing sensor (2) is placed in the sample holder (11) and is placed in the window combustion chamber (5) through the sample holder (11) and connected to the coaxial electronically controlled micro thruster (12); The coaxial electronically controlled micro thruster (12) is connected to the current probe (14), voltage probe (16), and DC voltage source (15) outside the window combustion chamber (5); The high-speed camera (9) is coaxially aligned with the high-pressure resistant glass (4) on the transparent combustion chamber (5) and takes pictures of the working status of the light-emitting diode (10) and the coaxial electronically controlled micro thruster (12) through the high-pressure resistant glass (4); An oscilloscope (1) is provided to display the signals recorded by the voltage probe (16), the current probe (14) and the high-precision weighing sensor (2).

2. The combustion performance testing device for coaxial small-sized electronically controlled solid propellant according to claim 1, characterized in that: In the coaxial electronically controlled micro-thruster (12), the positive electrode rod and the negative electrode shell are arranged coaxially, and the electronically controlled solid propellant is placed between them.

3. The combustion performance testing device for coaxial small-sized electronically controlled solid propellant as described in claim 1, characterized in that: The high-precision weighing sensor (2) is used to record the real-time mass change of the propellant in the coaxial electronically controlled micro-thruster (12) during combustion.

4. A combustion performance testing device for coaxial small-sized electronically controlled solid propellant as described in claim 2 or 3, characterized in that: One end of the high-precision weighing sensor (2), current probe (14), and voltage probe (16) is connected to the coaxial electronically controlled micro-thruster (12) and its lead wires, and the other end is connected to the oscilloscope (1).

5. The combustion performance testing device for a coaxial small-sized charge of electrically controlled solid propellant according to claim 4, characterized in that: The current loop in the current probe (14) is passed through any lead wire of the positive electrode rod and negative electrode shell in the coaxial electric micro thruster (12), and the current probe (14) monitors the current value passing through the coaxial electric micro thruster (12).

6. The combustion performance testing device for coaxial small-sized electronically controlled solid propellant according to claim 4, characterized in that: The positive and negative clamps in the voltage probe (16) are connected to the two leads of the positive rod and negative tube shell in the coaxial electric micro thruster (12) to monitor the voltage applied to the coaxial electric micro thruster (12).

7. The combustion performance testing device for a coaxial small-sized charge of electrically controlled solid propellant according to claim 1, characterized in that: The nitrogen cylinder (8) is used to pressurize the window combustion chamber (5), and the pressure gauge (3) monitors the pressure inside the window combustion chamber (5). The pressure is dynamically adjusted by the solenoid valve (6).

8. The combustion performance testing device for a coaxial small-sized charge of electrically controlled solid propellant according to claim 1, characterized in that: The DC voltage source (15) is used to apply voltage to the coaxial electronically controlled micro thruster (12), the voltage probe (16) is used to record the magnitude of the voltage applied to the coaxial electronically controlled micro thruster (12), and the current probe (14) is used to record the magnitude of the current passing through the coaxial electronically controlled micro thruster (12).

9. The combustion performance testing device for a coaxial small-sized charge of electrically controlled solid propellant according to claim 1, characterized in that: The high-speed camera (9) is used to record the ignition, combustion and extinguishing of the coaxial electronically controlled micro-thruster (12) through the high-pressure resistant glass (4) fixed by the flange (13).

10. The combustion performance testing device for a coaxial small-sized charge of electrically controlled solid propellant according to claim 1, characterized in that: A computer (7) is provided to record, store and analyze images captured by the high-speed camera (9).

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