Method for building ka-band electromagnetic pulse test platform in space environment

Abstract

The invention discloses a method for building a ka-band electromagnetic pulse test platform in a space environment. The method comprises the following steps: 1) building a megawatt-level miniaturized Ka-band electromagnetic pulse source; 2) removing an original observation window of the vacuum tank and replacing the observation window with a transmitting antenna input port; 3) replacing a lateral flange of the vacuum tank with an N interface flange with a sealing function; (4) closing the modified vacuum tank, vacuumizing, recording the minimum value which can be reached by the vacuum tank, and comparing with the original capacity of the vacuum tank to ensure that the minimum vacuum degree in the tank is less than or equal to 6.65 * 10 <-3 > Pa; (5) putting the receiving antenna into the vacuum tank, enabling the center of the receiving antenna to face the center of the transmitting antenna, transmitting electromagnetic waves to the receiving antenna through the transmitting antenna by using a pulse source, reading on an oscilloscope, and calculating transmitting energy and insertion loss according to gains of the transmitting antenna and the receiving antenna; and 6) vacuumizing the equipment, and carrying out electromagnetic pulse test on the protection component at high temperature. The problems that the space electromagnetic pulse effect mechanism is not clear and no space test platform exists are solved.

Description

Technical Field

[0001] The invention relates to a method for building a ka-band electromagnetic pulse test platform in a space environment, and belongs to the technical field of electromagnetic pulse test. Background Art

[0002] As the space offensive and defensive situation intensifies, strong electromagnetic attacks have become the main anti-satellite means, posing a serious threat to the safety of spacecraft in orbit. The use of miniaturized high-power microwave weapons carried by spacecraft for in-orbit attacks is the future attack method for spacecraft. Compared with other anti-satellite weapons, this attack method has the characteristics of concealment, high efficiency, wide attack range, and no influence from the external environment. It is an effective attack method in a non-total war situation and poses a serious threat to the safety of spacecraft in orbit.

[0003] However, there is little research on the evaluation of spacecraft's protection effectiveness against strong artificial electromagnetic pulse attacks. The electromagnetic pulse emission and protection effectiveness under thermal vacuum conditions are different from those at normal temperature. There is no data mechanism for the electromagnetic pulse attack and protection effectiveness changes under the influence of the space environment. Summary of the invention

[0004] The technical problem to be solved by the present invention is: to overcome the shortcomings of the existing technology, propose a method for building a Ka-band electromagnetic pulse test platform in a space environment, and solve the problem that the mechanism of space electromagnetic pulse effect is unclear and there is no space test platform.

[0005] The technical solution adopted by the present invention is:

[0006] A method for building a Ka-band electromagnetic pulse test platform in a space environment comprises the following steps:

[0007] (1) Build a 100-megawatt-class miniaturized Ka-band electromagnetic pulse source;

[0008] (2) Remove the original forward observation window of the vacuum tank, replace it with a transmitting antenna with the same size as the interface of the forward observation window, and seal the interface of the transmitting antenna. One end of the transmitting antenna is outside the vacuum tank, and the other end is inside the vacuum tank;

[0009] (3) Replace the side flange of the vacuum tank with an N-interface flange, seal it with a sealing ring, and use an N-interface wire to lead out from the plug on the N-interface flange and connect it to the oscilloscope outside the vacuum tank;

[0010] (4) Close the modified vacuum tank, evacuate the tank and record the lowest vacuum value that the tank can reach to ensure that the lowest vacuum value in the tank is the same as the original capacity of the vacuum tank;

[0011] (5) Install the receiving antenna on the product to be tested and place it in a vacuum tank, with the center of the receiving antenna facing the center of the transmitting antenna. The receiving antenna is also connected to the N interface flange through a wire.

[0012] Use an electromagnetic pulse source to transmit electromagnetic waves from the transmitting antenna to the receiving antenna, read the readings on the oscilloscope, and calculate the transmission energy and insertion loss based on the gains of the transmitting antenna and the receiving antenna;

[0013] (6) Evacuate the vacuum tank and perform an electromagnetic pulse test on the product to be tested at a preset high temperature.

[0014] Furthermore, the 100-megawatt miniaturized Ka-band electromagnetic pulse source includes a Tesla power supply and a gyromagnetic tube. The electromagnetic pulse source generates electromagnetic pulses with a fast rising edge, a rising edge time of ≤1.5ns, and a repetition frequency of ≥100 times.

[0015] Furthermore, a thermal vacuum tank is selected, and the vacuum degree of the vacuum tank is ≤6.65×10 -3 , the high temperature is higher than 70℃, the low temperature is lower than -35℃, and the inner cavity depth of the vacuum tank is greater than 2m.

[0016] Furthermore, an electromagnetic pulse test is performed on the product to be tested to verify that the target power at the position of the product to be tested in the vacuum tank is ≥1000W / m2, the number of repetitions is ≥100 times, and the rise time is ≤1.5ns.

[0017] Second,

[0018] The present invention provides a Ka-band electromagnetic pulse test platform in a vacuum environment, comprising a vacuum tank, a Ka-band electromagnetic pulse source, an oscilloscope, a transmitting antenna, a receiving antenna, an N-interface flange and an N-interface wire;

[0019] The transmitting antenna is installed at the original observation window position of the vacuum tank. The observation window is replaced by the transmitting antenna, and the interface is sealed. One end of the transmitting antenna is outside the vacuum tank, and the other end is inside the vacuum tank.

[0020] The N interface flange is installed at the side flange position of the vacuum tank, the side flange is replaced with the N interface flange, sealed with a sealing ring, and the N interface wire is led out from the plug on the N interface flange and connected to the oscilloscope outside the vacuum tank;

[0021] The receiving antenna is installed on the product to be tested and placed in a vacuum tank. The center of the receiving antenna faces the center of the transmitting antenna. The receiving antenna is also connected to the N interface flange through a wire.

[0022] Use a Ka-band electromagnetic pulse source to transmit electromagnetic waves to the receiving antenna through the transmitting antenna, read the readings on the oscilloscope, and calculate the transmission energy and insertion loss based on the gains of the transmitting antenna and the receiving antenna.

[0023] Furthermore, the Ka-band electromagnetic pulse source is a 100-megawatt miniaturized Ka-band electromagnetic pulse source, including a Tesla power supply and a gyromagnetic tube. The electromagnetic pulse source generates electromagnetic pulses with a fast rising edge, a rising edge time of ≤1.5ns, and a repetition frequency of ≥100 times.

[0024] Furthermore, the vacuum tank is a thermal vacuum tank, and the vacuum degree of the vacuum tank is ≤6.65×10 -3 , the high temperature is higher than 70℃, the low temperature is lower than -35℃, and the inner cavity depth of the vacuum tank is greater than 2m.

[0025] Furthermore, the vacuum tank is evacuated, and the lowest vacuum value that the vacuum tank can reach is recorded to ensure that the lowest vacuum degree in the tank is the same as the original capacity of the vacuum tank; an electromagnetic pulse test is performed on the product to be tested at a preset high temperature.

[0026] Furthermore, an electromagnetic pulse test is performed on the product to be tested to verify that the target power at the position of the product to be tested in the vacuum tank is ≥1000W / m2, the number of repetitions is ≥100 times, and the rise time is ≤1.5ns.

[0027] The advantages of the present invention compared with the prior art are:

[0028] (1) Currently, there is no test platform that integrates the coupled space environment and the electromagnetic pulse source. The present invention comprehensively considers the volume, emission capability, vacuum tank volume and thermal vacuum capability of the electromagnetic pulse source to establish an electromagnetic pulse test platform with a target power of 100 megawatts, a rise time of ≤1.5ns, and a target power density of 1000W / m2.

[0029] (2) The present invention adopts a miniaturized electromagnetic pulse source to reduce the volume of the system and realizes rapid docking and rapid testing with the vacuum tank. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 Schematic diagram of gyromagnetic microwave source;

[0031] Figure 2 Schematic diagram of the receiving antenna output signal waveform;

[0032] Figure 3 Flow chart of the method of the present invention. DETAILED DESCRIPTION

[0033] The present invention aims to address the problem that the existing electromagnetic pulse platform is based on a ground environment and conducts electromagnetic pulse testing under an atmospheric pressure, but is not coupled to an electromagnetic pulse testing platform under a typical space environment. By integrating a miniaturized electromagnetic pulse source and a thermal vacuum test tank, the space attack situation is simulated under a thermal vacuum and a low-temperature vacuum environment, and an electromagnetic pulse testing platform that simulates a vacuum electromagnetic pulse environment is established.

[0034] The present invention provides a Ka-band electromagnetic pulse test platform in a vacuum environment, comprising a vacuum tank, a Ka-band electromagnetic pulse source, an oscilloscope, a transmitting antenna, a receiving antenna, an N-interface flange and an N-interface wire;

[0035] The transmitting antenna is installed at the original observation window position of the vacuum tank. The observation window is replaced by the transmitting antenna, and the interface is sealed. One end of the transmitting antenna is outside the vacuum tank, and the other end is inside the vacuum tank.

[0036] The N interface flange is installed at the side flange position of the vacuum tank, the side flange is replaced with the N interface flange, sealed with a sealing ring, and the N interface wire is led out from the plug on the N interface flange and connected to the oscilloscope outside the vacuum tank;

[0037] The receiving antenna is installed on the product to be tested and placed in a vacuum tank. The center of the receiving antenna faces the center of the transmitting antenna. The receiving antenna is also connected to the N interface flange through a wire.

[0038] Use a Ka-band electromagnetic pulse source to transmit electromagnetic waves to the receiving antenna through the transmitting antenna, read the readings on the oscilloscope, and calculate the transmission energy and insertion loss based on the gains of the transmitting antenna and the receiving antenna.

[0039] like Figure 3 As shown, the present invention also proposes a method for building a Ka-band electromagnetic pulse test platform in a space environment, comprising the following steps:

[0040] (1) Build a 100-megawatt-class miniaturized Ka-band electromagnetic pulse source;

[0041] The present invention adopts the technical solution of Tesla pulse source and gyromagnetic tube to establish a miniaturized fast rising edge electromagnetic pulse test platform. The 100-megawatt miniaturized Ka-band electromagnetic pulse source includes Tesla power supply and gyromagnetic tube, such as Figure 1 As shown, the electromagnetic pulse source generates electromagnetic pulses with fast rising edges, with rising edge time ≤1.5ns and repetition frequency ≥100 times.

[0042] (2) Remove the original forward observation window of the vacuum tank, replace it with a transmitting antenna with the same size as the interface of the forward observation window, and seal the interface of the transmitting antenna. One end of the transmitting antenna is outside the vacuum tank, and the other end is inside the vacuum tank;

[0043] Choose a thermal vacuum tank with a vacuum degree of ≤6.65×10 -3 , the high temperature is higher than 70℃, the low temperature is lower than -35℃, and the inner cavity depth of the vacuum tank is greater than 2m.

[0044] The present invention realizes the integration of the thermal vacuum system and the electromagnetic pulse system by designing a transmitting antenna that penetrates the tank.

[0045] (3) Replace the side flange of the vacuum tank with an N-interface flange, seal it with a sealing ring, and use an N-interface wire to lead out from the plug on the N-interface flange and connect it to the oscilloscope outside the vacuum tank;

[0046] (4) Close the modified vacuum tank, evacuate the tank and record the lowest vacuum value that the tank can reach to ensure that the lowest vacuum value in the tank is the same as the original capacity of the vacuum tank;

[0047] (5) Install the receiving antenna on the product to be tested and place it in a vacuum tank, with the center of the receiving antenna facing the center of the transmitting antenna. The receiving antenna is also connected to the N interface flange through a wire.

[0048] Use an electromagnetic pulse source to transmit electromagnetic waves to the receiving antenna through the transmitting antenna, and read the readings on the oscilloscope. The waveform obtained is as shown in the attached figure. Figure 2 As shown, the transmission energy and insertion loss are calculated based on the gains of the transmitting antenna and the receiving antenna;

[0049] (6) Evacuate the vacuum tank and perform an electromagnetic pulse test on the product to be tested at a preset high temperature.

[0050] Conduct electromagnetic pulse test on the product to be tested to verify that the target power at the position of the product to be tested in the vacuum tank is ≥1000W / m2, the repetition frequency is ≥100 times, and the rise time is ≤1.5ns.

[0051] The present invention comprehensively considers the volume of the electromagnetic pulse source, the emission capability, the volume of the vacuum tank and the thermal vacuum capability, and establishes an electromagnetic pulse test platform with a target power of 100 megawatts, a rise time of ≤1.5ns, and a target power density of 1000W / m2, thereby realizing rapid docking and rapid testing with the vacuum tank.

[0052] Parts of the present invention that are not described in detail belong to common knowledge among those skilled in the art.

Claims

1. A method for constructing a ka-band electromagnetic pulse test platform in a space environment, characterized in that: include: Build a 100-megawatt-class miniaturized Ka-band electromagnetic pulse source; Remove the original forward observation window of the vacuum tank, replace it with a transmitting antenna with the same size as the interface of the forward observation window, and seal the interface of the transmitting antenna. One end of the transmitting antenna is outside the vacuum tank, and the other end is inside the vacuum tank; Replace the side flange of the vacuum tank with an N-interface flange, seal it with a sealing ring, and use an N-interface wire to lead out from the plug on the N-interface flange and connect it to the oscilloscope outside the vacuum tank; Close the modified vacuum tank, evacuate the tank and record the lowest vacuum value that the tank can reach to ensure that the lowest vacuum degree in the tank is equivalent to the original capacity of the vacuum tank; Install the receiving antenna on the product to be tested and put it into the vacuum tank. The center of the receiving antenna is facing the center of the transmitting antenna. The receiving antenna is also connected to the N interface flange through a wire. Use an electromagnetic pulse source to transmit electromagnetic waves from the transmitting antenna to the receiving antenna, read the readings on the oscilloscope, and calculate the transmission energy and insertion loss based on the gains of the transmitting antenna and the receiving antenna; The vacuum tank is evacuated and the product to be tested is subjected to an electromagnetic pulse test at a preset high temperature.

2. The method for constructing a Ka-band electromagnetic pulse test platform in a space environment according to claim 1, characterized in that: The 100-megawatt miniaturized Ka-band electromagnetic pulse source includes a Tesla power supply and a gyromagnetic tube. The electromagnetic pulse source generates electromagnetic pulses with a fast rising edge, a rising edge time of ≤1.5ns, and a repetition frequency of ≥100 times.

3. The method for constructing a Ka-band electromagnetic pulse test platform in a space environment according to claim 1, characterized in that: Choose a thermal vacuum tank with a vacuum degree of ≤6.65×10 -3 , the high temperature is higher than 70℃, the low temperature is lower than -35℃, and the inner cavity depth of the vacuum tank is greater than 2m.

4. The method for constructing a Ka-band electromagnetic pulse test platform in a space environment according to claim 1, characterized in that: Conduct electromagnetic pulse test on the product to be tested to verify that the target power at the position of the product to be tested in the vacuum tank is ≥1000W / m2, the repetition frequency is ≥100 times, and the rise time is ≤1.5ns.

5. A Ka-band electromagnetic pulse test platform in a vacuum environment, characterized by: Includes vacuum tank, Ka-band electromagnetic pulse source, oscilloscope, transmitting antenna, receiving antenna, N-interface flange and N-interface wire; The transmitting antenna is installed at the original observation window position of the vacuum tank. The observation window is replaced by the transmitting antenna, and the interface is sealed. One end of the transmitting antenna is outside the vacuum tank, and the other end is inside the vacuum tank. The N interface flange is installed at the side flange position of the vacuum tank, the side flange is replaced with the N interface flange, sealed with a sealing ring, and the N interface wire is led out from the plug on the N interface flange and connected to the oscilloscope outside the vacuum tank; The receiving antenna is installed on the product to be tested and placed in a vacuum tank. The center of the receiving antenna faces the center of the transmitting antenna. The receiving antenna is also connected to the N interface flange through a wire. Use a Ka-band electromagnetic pulse source to transmit electromagnetic waves to the receiving antenna through the transmitting antenna, read the readings on the oscilloscope, and calculate the transmission energy and insertion loss based on the gains of the transmitting antenna and the receiving antenna.

6. The Ka-band electromagnetic pulse test platform in a vacuum environment according to claim 5, characterized in that: The Ka-band electromagnetic pulse source is a 100-megawatt miniaturized Ka-band electromagnetic pulse source, including a Tesla power supply and a gyromagnetic tube. The electromagnetic pulse source generates electromagnetic pulses with a fast rising edge, with a rising edge time of ≤1.5ns and a repetition frequency of ≥100 times.

7. The method for constructing a Ka-band electromagnetic pulse test platform in a space environment according to claim 5, characterized in that: The vacuum tank should be a thermal vacuum tank with a vacuum degree of ≤6.65×10 -3 , the high temperature is higher than 70℃, the low temperature is lower than -35℃, and the inner cavity depth of the vacuum tank is greater than 2m.

8. The method for constructing a Ka-band electromagnetic pulse test platform in a space environment according to claim 5, characterized in that: Evacuate the vacuum tank and record the lowest vacuum value that the vacuum tank can reach to ensure that the lowest vacuum degree in the tank is the same as the original capacity of the vacuum tank; perform electromagnetic pulse test on the product to be tested at a preset high temperature.

9. The method for constructing a Ka-band electromagnetic pulse test platform in a space environment according to claim 8, characterized in that: Conduct electromagnetic pulse test on the product to be tested to verify that the target power at the position of the product to be tested in the vacuum tank is ≥1000W / m2, the repetition frequency is ≥100 times, and the rise time is ≤1.5ns.

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