A test device and design method for a descent radar system based on a delay component

Abstract

The present application relates to a test device and design method for a low-altitude radar system based on a delay component. The delay component is connected to the inside of the radar system during ground testing and experiments, and the delay of the delay component is used to replace the propagation delay of the radar electromagnetic wave in the altitude direction. Without changing the timing parameters of the radar system, the radar system can be fully and wirelessly tested under close-range and small-site testing conditions, thereby reducing the restrictions on site conditions such as altitude and distance required for radar testing, thereby reducing the difficulty and cost of the test.

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 design method. Background Art

[0002] Asteroid exploration is a landmark mission included in China's "Major Planetary Exploration Project." China has finalized its asteroid exploration mission for its deep space exploration program, designated Tianwen-2. This mission, through a single launch, will enable close-range exploration of near-Earth asteroids, sample return, and flyby exploration of main-belt comets. This will provide scientific data and authentic samples for cutting-edge research on the origins and evolution of small celestial bodies, bringing my country's asteroid exploration capabilities to internationally advanced levels.

[0003] The Tianwen-2 probe, carrying a scientific payload, will conduct a flyby of the near-Earth asteroid 2016 HO3. It will then select an appropriate time to land on the asteroid's surface and collect samples. After returning to Earth, it will release its return capsule, returning the samples to Earth. This process will be completed in approximately three years. Following this, the Tianwen-2 probe, leveraging Earth and Mars for approximately seven years, will reach the asteroid belt and conduct a flyby of the main-belt comet 311P / (2013P5) PANSTARRS (hereinafter referred to as 311P).

[0004] The sounding radar is one of the scientific exploration payloads carried by the Tianwen-2 probe. Its primary purpose is to obtain radar echo data from the asteroid's surface and subsurface, and to explore the asteroid's subsurface structure. The sounding altitude range for the near-Earth asteroid 2016 HO3 is set at 600-1000 meters, and for the main-belt comet 311P, it is set at 5-20 kilometers.

[0005] Detection radar systems are designed based on the on-orbit altitude, allowing for margins within the required altitude range. For example, for detecting the near-Earth asteroid 2016 HO3, the closest detection range is 450 meters, meeting the 600-1000-meter detection range requirement. However, at altitudes below 450 meters, hardware and timing constraints prevent proper operation. Testing the radar system at an altitude of 650 meters requires flying the radar on an aircraft to perform a power-on test. This presents significant challenges and costs. Summary of the Invention

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

[0007] In a first aspect, a delay component-based descent radar system test device is provided, comprising: providing a delay component and an attenuator in a receiving link or a transmitting link of the radar system, wherein 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 range attenuation caused by the radar system lowering its altitude is determined using the following formula:

[0015]

[0016] Where ΔA is the range 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 to which the radar system needs to be lowered.

[0017] In a second aspect, a method for designing a test device for a descent radar system based on a delay component 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] Setting the delay component 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 range attenuation caused by the radar system lowering its altitude is determined using the following formula:

[0027]

[0028] Where ΔA is the range 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 to which the radar system needs to be lowered.

[0029] Compared with the existing technology, the present application has the following beneficial effects: the present application adopts a delay component, which is connected to 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 comprehensive and wireless testing of the radar system is completed under close-range and small-site testing conditions, 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 in conjunction with the accompanying drawings, which together with the following detailed description are incorporated into and form a part of this specification. In the drawings:

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

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

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

[0034] It is also necessary to explain here that, in order to avoid obscuring the present application due to unnecessary details, the accompanying drawings only show the device structure closely related to the solution according to the present application, 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 embodiments due to the following description with reference to the accompanying drawings. In this document, where feasible, the embodiments may be combined with each other, features between different embodiments may be replaced or borrowed, and one or more features may be omitted in one embodiment.

[0036] This application uses a delay component, which is connected to the radar system during ground testing and experiments. The delay of the delay component replaces the propagation delay of the radar electromagnetic wave in the height direction. Without changing the timing parameters of the radar system, the radar system can be 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] The specific radar system, detection range, and altitude that needs to be lowered need to be determined based on the actual product and application environment. Taking the detection of small celestial bodies by a detection radar as an example, an embodiment of the present application provides a test device for a radar system with a reduced altitude based on a delay component, including: providing a delay component and an attenuator in a receiving link or a transmitting link of the radar system, wherein 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 then 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 figure degradation. If the transmitting link has an interface that can be connected to the delay component, it is recommended to connect the delay component to the transmitting link if possible. If the transmitting link has a transmission power requirement, or the receiving link can accept a certain noise figure degradation, the delay component can also be connected to the receiving link.

[0041] The connected delay component module will bring a certain amount of power attenuation. Similarly, the propagation of electromagnetic waves in space will also bring corresponding spatial attenuation. Generally, the attenuation caused by the delay component will be smaller than the spatial attenuation. An attenuator needs to be configured 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 horn, and the attenuator may be disposed between the receiving channel and the receiving component or between the delay component and the receiving horn.

[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 range attenuation caused by the radar system lowering its altitude is determined using the following formula:

[0049]

[0050] Where ΔA is the range 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 to which 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 figure shows the test block diagram after the delay component is connected.

[0052] To verify the detection performance of a target at a 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 operating 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 lowered to 50m. Then, various methods such as suspension and drone can be used for testing, greatly reducing the difficulty and cost of the test. This application can quickly and accurately test the system performance under the radar's actual operating parameters, reduce the restrictions on site conditions such as altitude and distance required for radar operation, and thus reduce the difficulty and cost of the test.

[0054] The present application also provides a method for designing a test device for a descent radar system based on a delay component, including:

[0055] Step S1, determining the delay of the delay component according to the altitude to which 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, and connecting the attenuator 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 range attenuation caused by the radar system lowering its altitude is determined using the following formula:

[0064]

[0065] Where ΔA is the range 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 to which 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 that the system after the access delay is assembled is equivalent to the original system in terms of system delay and attenuation.

[0067] The introduction of delay components changes the original waveguide and cable connections. In addition, 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 descriptions are merely examples of various embodiments of the present application, but the scope of protection of the present application is not limited thereto. Any modifications or substitutions that can be readily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included within the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection 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 provided 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 as the attenuation of the attenuator; 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; The delay of the delay component is determined by 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 to, and c is the speed of light; The range attenuation caused by the radar system lowering its altitude is determined using the following formula: Where ΔA is the range 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 to which the radar system needs to be lowered.

2. 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; 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; The delay of the delay component is determined by 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 to, and c is the speed of light; The range attenuation caused by the radar system lowering its altitude is determined using the following formula: Where ΔA is the range 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 to which the radar system needs to be lowered.

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