Delay component-based height reduction radar system testing device and design method

Abstract

The invention relates to a height reduction radar system test device based on a delay component and a design method, the delay component is connected into a radar system in ground test and test, the propagation time delay of radar electromagnetic waves in the height direction is replaced by the time delay of the delay component, and the radar system can be tested without changing the time sequence parameters of the radar system. Comprehensive and wireless testing of a radar system is completed under the short-distance and small-site testing conditions, limitation of site conditions such as height and distance required by radar testing work is reduced, and then the testing difficulty and cost are reduced.

Description

Technical Field

[0001] The present application relates to the field of radar system testing, and in particular, to a delay component-based altitude reduction radar system testing device and a design method. Background Art

[0002] Asteroid exploration is a landmark mission listed in the country's "major planetary exploration project". The asteroid exploration mission in China's deep space exploration plan has been determined and named Tianwen-2. The asteroid exploration mission will achieve close-range exploration of near-Earth asteroids, sample return and flyby exploration of main-belt comets through a single launch, providing scientific exploration data and real samples for cutting-edge scientific research on the origin and evolution of small celestial bodies, enabling my country to reach the international advanced level in the field of asteroid exploration.

[0003] The Tianwen-2 probe carries a scientific payload and will fly around the near-Earth asteroid 2016HO3. It will then attach to the asteroid surface and collect samples, then return to Earth to release the return capsule and send the samples back to Earth. This process will be completed in about three years. After the above process is completed, the Tianwen-2 probe will fly to the asteroid belt with the help of Earth and Mars in about seven years, and will fly around the main-belt comet 311P / (2013P5)PANSTARRS (hereinafter referred to as 311P).

[0004] The detection radar is one of the scientific detection payloads carried by the Tianwen-2 probe. Its main purpose is to obtain radar echo data of the asteroid surface and subsurface, and to conduct subsurface structure detection of the asteroid. The detection altitude range for the near-Earth asteroid 2016HO3 is set at 600m-1000m, and the detection altitude range for the main-belt comet 311P is set at 5km-20km.

[0005] The detection radar is designed according to the height of the orbit, leaving a certain margin while meeting the altitude range. Taking the detection of the near-Earth asteroid 2016HO3 as an example, the closest detection range can reach 450m, meeting the detection range requirement of 600m-1000m, but when the altitude is less than 450m, it cannot work properly due to hardware design and timing design constraints. When testing the radar system, taking the detection radar working at an altitude of 650m as an example, it is necessary to use an aircraft to fly the radar to an altitude of 650m for power-on testing, which is difficult and costly. Summary of the invention

[0006] In order to overcome at least one deficiency in the prior art, the present application provides a delay component-based descending radar system testing device and a design method.

[0007] In a first aspect, a delay component-based descent radar system test device is provided, comprising: a delay component and an attenuator are arranged in a receiving link or a transmitting link of the radar system, and the attenuator is connected to the delay component;

[0008] The delay of the delay component is determined according to the altitude to which the radar system needs to be lowered;

[0009] The attenuation of the attenuator is determined by calculating the distance attenuation caused by the radar system lowering its altitude, and calculating the difference between the distance attenuation and the attenuation of the delay component, which is the attenuation of the attenuator.

[0010] In one embodiment, the delay component is disposed between the transmitting channel and the transmitting horn, and the attenuator is disposed between the transmitting channel and the delay component or between the delay component and the transmitting horn.

[0011] In one embodiment, the delay of the delay component is determined using the following formula:

[0012] τ=2H / c

[0013] Where τ is the delay of the delay component, H is the altitude that the radar system needs to be lowered, and c is the speed of light.

[0014] In one embodiment, the distance attenuation caused by the radar system lowering its altitude is determined using the following formula:

[0015]

[0016] Among them, ΔA is the distance attenuation caused by the radar system lowering its altitude, R is the distance between the radar system and the target, and H is the altitude that the radar system needs to be lowered.

[0017] In a second aspect, a design method for a delay component-based descent radar system test device is provided, comprising:

[0018] Determining the delay of the delay component according to the altitude to which the radar system needs to be lowered;

[0019] The delay component is arranged in a receiving chain or a transmitting chain of the radar system;

[0020] An attenuator is provided in the radar system, and the attenuator is connected to the delay component;

[0021] Determining the attenuation of the attenuator includes: calculating the distance attenuation caused by the radar system lowering its altitude, and calculating the difference between the distance attenuation and the attenuation of the delay component as the attenuation of the attenuator.

[0022] In one embodiment, the delay component is disposed between the transmitting channel and the transmitting horn, and the attenuator is disposed between the transmitting channel and the delay component or between the delay component and the transmitting horn.

[0023] In one embodiment, the delay of the delay component is determined using the following formula:

[0024] τ=2H / c

[0025] Where τ is the delay of the delay component, H is the altitude that the radar system needs to be lowered, and c is the speed of light.

[0026] In one embodiment, the distance attenuation caused by the radar system lowering its altitude is determined using the following formula:

[0027]

[0028] Among them, ΔA is the distance attenuation caused by the radar system lowering its altitude, R is the distance between the radar system and the target, and H is the altitude that the radar system needs to be lowered.

[0029] Compared with the prior art, the present application has the following beneficial effects: the present application adopts a delay component, which is connected to the inside of the radar system during ground testing and experiments, and replaces the propagation delay of the radar electromagnetic wave in the height direction with the delay of the delay component. Without changing the timing parameters of the radar system, the radar system is fully and wirelessly tested under close-range and small-site testing conditions, thereby reducing the restrictions on site conditions such as height and distance required for radar testing, thereby reducing the difficulty and cost of the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The present application may be better understood by referring to the following description given in conjunction with the accompanying drawings, which together with the following detailed description are included in this specification and form a part of this specification. In the drawings:

[0031] Figure 1 shows a test block diagram before the delay component is connected;

[0032] Figure 2 The test block diagram after the delay component is connected is shown. DETAILED DESCRIPTION

[0033] The exemplary embodiments of the present application will be described below in conjunction with the accompanying drawings. For the sake of clarity and conciseness, not all features of the actual embodiments are described in the specification. However, it should be understood that many implementation-specific decisions can be made in the process of developing any such actual embodiments in order to achieve the specific goals of the developer, and these decisions may vary from embodiment to embodiment.

[0034] It is also necessary to explain here that, in order to avoid obscuring the present application due to unnecessary details, only the device structure closely related to the scheme according to the present application is shown in the drawings, while other details that are not closely related to the present application are omitted.

[0035] It should be understood that the present application is not limited to the described implementation forms due to the following description with reference to the accompanying drawings. In this article, where feasible, the embodiments can be combined with each other, features between different embodiments can be replaced or borrowed, and one or more features can be omitted in one embodiment.

[0036] This application uses a delay component, which is connected to the inside of the radar system during ground testing and experiments, and replaces the propagation delay of the radar electromagnetic wave in the height direction with the delay of the delay component. Without changing the timing parameters of the radar system, the radar system is fully and wirelessly tested under close-range and small-site testing conditions, thereby reducing the restrictions on site conditions such as height and distance required for radar testing, thereby reducing the difficulty and cost of the test.

[0037] For a specific radar system, detection range, and height to be lowered, it is necessary to determine according to the actual product and application environment. Taking the detection of small celestial body targets by detection radar as an example, an embodiment of the present application provides a test device for a radar system for lowering altitude based on a delay component, including: a delay component and an attenuator are arranged in a receiving link or a transmitting link of the radar system, and the attenuator is connected to the delay component;

[0038] The delay of the delay component is determined according to the altitude to which the radar system needs to be lowered;

[0039] The attenuation of the attenuator is determined by calculating the distance attenuation ΔA caused by the radar system lowering its altitude, and calculating the difference between the distance attenuation ΔA and the attenuation L of the delay component, which is the attenuation of the attenuator.

[0040] Because the delay component will cause attenuation, if it is connected to the receiving link, it will introduce noise coefficient degradation. If the transmitting link has an interface that can be connected to the delay component, it is best to connect the delay component to the transmitting link. If the transmitting link has a transmission power requirement, or the receiving link can accept a certain noise coefficient degradation, the delay component can also be connected to the receiving link.

[0041] The connected delay component module will bring a certain power attenuation. Similarly, the propagation of electromagnetic waves in space will also bring corresponding spatial attenuation. Generally, the attenuation brought by the delay component will be smaller than the spatial attenuation. It is necessary to configure an attenuator separately to make the attenuation after the delay component is connected consistent with the change in spatial attenuation. Therefore, an attenuator is set in the radar system.

[0042] In one embodiment, the delay component may be disposed between the receiving channel and the receiving speaker, and the attenuator may be disposed between the receiving channel and the receiving component or between the delay component and the receiving speaker.

[0043] Preferably, the delay component is arranged between the transmitting channel and the transmitting horn, and the attenuator is arranged between the transmitting channel and the delay component or between the delay component and the transmitting horn.

[0044] In one embodiment, the delay of the delay component is determined using the following formula:

[0045] τ=2H / c

[0046] Where τ is the delay of the delay component, H is the altitude that the radar system needs to be lowered, and c is the speed of light.

[0047] Here, the delay component is used to replace the propagation delay of the radar electromagnetic wave in the height direction.

[0048] Specifically, the distance attenuation caused by the radar system lowering its altitude is determined using the following formula:

[0049]

[0050] Among them, ΔA is the distance attenuation caused by the radar system lowering its altitude, R is the distance between the radar system and the target, and H is the altitude that the radar system needs to be lowered.

[0051] Figure 1 The test block diagram before the delay component is connected is shown. Figure 2 The test block diagram after the delay component is connected is shown.

[0052] To verify the detection performance of the target at the radar test distance R, the target needs to be placed at a distance R from the radar system. Assuming the time delay of the delay component is τ, the radar working distance can be effectively reduced by H by inserting the delay component. c is the speed of light.

[0053] Taking the detection radar working at an altitude of 650m as an example, it is necessary to use an aircraft to fly the radar to an altitude of 650m for power-on testing. If a 4us delay component is connected, the radar altitude can be reduced to 50m, and then it can be carried out in various ways such as suspension and drones, which greatly reduces the difficulty and cost of the test. This application can quickly and accurately test the system performance under the actual working parameters of the radar, reduce the restrictions on the site conditions such as the height and distance required for the radar to work, and thus reduce the difficulty and cost of the test.

[0054] The embodiment of the present application also provides a design method for a test device for a descending altitude radar system based on a delay component, including:

[0055] Step S1, determining the delay of the delay component according to the height that the radar system needs to be lowered;

[0056] Step S2, setting a delay component in a receiving link or a transmitting link of the radar system;

[0057] Step S3, setting an attenuator in the radar system, wherein the attenuator is connected to the delay component;

[0058] Step S4, determining the attenuation of the attenuator, includes: calculating the distance attenuation caused by the radar system lowering its altitude, and calculating the difference between the distance attenuation and the attenuation of the delay component as the attenuation of the attenuator.

[0059] Specifically, the delay component is arranged between the transmitting channel and the transmitting horn, and the attenuator is arranged between the transmitting channel and the delay component or between the delay component and the transmitting horn.

[0060] Specifically, the delay of the delay component is determined using the following formula:

[0061] τ=2H / c

[0062] Where τ is the delay of the delay component, H is the altitude that the radar system needs to be lowered, and c is the speed of light.

[0063] Specifically, the distance attenuation caused by the radar system lowering its altitude is determined using the following formula:

[0064]

[0065] Among them, ΔA is the distance attenuation caused by the radar system lowering its altitude, R is the distance between the radar system and the target, and H is the altitude that the radar system needs to be lowered.

[0066] Furthermore, the design method of the delay component-based altitude reduction radar system test device also includes: ensuring the equivalence of the system delay and attenuation between the system after the access delay assembly and the original system.

[0067] The introduction of delay components changes the original waveguide and cable connections. The introduction of delay components also introduces additional connectors. Therefore, it is necessary to further confirm the changes in delay and attenuation caused by changes in system details.

[0068] The above are only various implementations of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art who is familiar with the present technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A test device for a descent radar system based on a delay component, characterized in that: include: A delay component and an attenuator are arranged in a receiving link or a transmitting link of a radar system, wherein the attenuator is connected to the delay component; The delay of the delay component is determined according to the altitude to which the radar system needs to be lowered; The attenuation of the attenuator is determined by calculating the distance attenuation caused by the radar system lowering its altitude, and calculating the difference between the distance attenuation and the attenuation of the delay component, which is the attenuation of the attenuator.

2. The device according to claim 1, characterized in that The delay component is arranged between the transmitting channel and the transmitting horn, and the attenuator is arranged between the transmitting channel and the delay component or between the delay component and the transmitting horn.

3. The device according to claim 1, characterized in that The delay of the delay component is determined using the following formula: τ=2H / c Where τ is the delay of the delay component, H is the altitude that the radar system needs to be lowered, and c is the speed of light.

4. The device according to claim 1, characterized in that The distance attenuation caused by the radar system lowering its altitude is determined by the following formula: Among them, ΔA is the distance attenuation caused by the radar system lowering its altitude, R is the distance between the radar system and the target, and H is the altitude that the radar system needs to be lowered.

5. A design method for a test device for a descent radar system based on a delay component, characterized in that: include: Determining the delay of the delay component according to the altitude to which the radar system needs to be lowered; The delay component is arranged in a receiving link or a transmitting link of a radar system; An attenuator is provided in the radar system, wherein the attenuator is connected to the delay component; Determining the attenuation of the attenuator includes: calculating the distance attenuation caused by the radar system lowering its altitude, and calculating the difference between the distance attenuation and the attenuation of the delay component as the attenuation of the attenuator.

6. The method according to claim 5, characterized in that The delay component is arranged between the transmitting channel and the transmitting horn, and the attenuator is arranged between the transmitting channel and the delay component or between the delay component and the transmitting horn.

7. The method according to claim 5, characterized in that The delay of the delay component is determined using the following formula: τ=2H / c Where τ is the delay of the delay component, H is the altitude that the radar system needs to be lowered, and c is the speed of light.

8. The method according to claim 1, characterized in that The distance attenuation caused by the radar system lowering its altitude is determined by the following formula: Among them, ΔA is the distance attenuation caused by lowering the altitude of the radar system, R is the distance between the radar system and the target, and H is the altitude that the radar system needs to be lowered.

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