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Method for measuring microwave radar beam central transverse velocity

A technology of beam center and microwave radar, which is applied in the direction of radio wave measurement system, measurement device, radio wave reflection/re-radiation, etc., can solve the problems of inability to complete the calculation of fuzzy times, inability to find integers, etc., and achieve simple algorithm and measurement High precision, simple engineering effect

Active Publication Date: 2011-01-12
XIAN INSTITUE OF SPACE RADIO TECH
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Problems solved by technology

However, considering the high rate of change of the landing system's motion speed, its Doppler frequency is always changing, so it is impossible to find an integer that satisfies the three frequencies at the same time by using the traditional remainder theorem (fuzzy number)
Therefore, it is impossible to solve the fuzzy number simply by using the remainder theorem

Method used

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  • Method for measuring microwave radar beam central transverse velocity
  • Method for measuring microwave radar beam central transverse velocity
  • Method for measuring microwave radar beam central transverse velocity

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Embodiment Construction

[0050] Such as figure 1 As shown, the satellite platform moves from point A to point B, A and B are on the surface yox, and A and B are any two points during the landing process of the lander. xoz is the surface of the planet, the angle between AB and the x-axis (horizontal line) is β, the azimuth angle of the beam is θ, and the pitch angle is The angle between the beam and the surface of the planet remains constant. There is a point E on the surface of the planet. During the movement of the platform from A to B, point E can always be irradiated by the beam. Then, when the platform is at point B, point E Distance to radar R(t m ) can be expressed as:

[0051]

[0052] Among them, t m is the slow time, that is, the azimuth dimension time, and v is the moving speed of the lander.

[0053] The complete processing flow of the present invention is as figure 2 As shown, the steps are as follows:

[0054] (1) The microwave radar on the lander first transmits at least n set...

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Abstract

The invention discloses a method for measuring microwave radar beam central transverse velocity, which comprises the following steps of: selecting relatively prime pulse repetition frequency (repetition frequency for short) according to the distance unambiguity principle, and selecting the pulse accumulation number of each repetition frequency according to the requirements on the operating distance and the detected signal to noise ratio; transmitting a pulse signal, receiving a planet surface echo, detecting the distance gate number of the maximum power point, performing Doppler-related processing on the echo data of the distance gate, and solving an ambiguous beam central transverse velocity; and processing all pulses with repetition frequencies in turn, solving velocity ambiguity times according to the principle of the modified remainder theorem, and solving a real beam central transverse velocity by combining the ambiguous velocity result. The method for measuring the microwave radar beam central transverse velocity is only applied to a pulse radar system, can simultaneously measure the projection of horizontal and vertical two-dimensional velocity components in the beam direction, provides the distance measurement function, and has the characteristics of high measuring accuracy and simpler engineering implementation.

Description

technical field [0001] The invention relates to a method for measuring the center-to-center velocity of a microwave radar beam, in particular to a method for measuring the center-to-center velocity of a microwave radar by a planetary lander. Background technique [0002] The planetary lander is generally installed on the orbiter, and flies around the planet at a relatively high speed with the orbiter before starting to land. The landing process of the lander is as follows: first, the lander is separated from the orbiter, and the lander still has a relatively high speed at this time. The motion speed of the lander is measured by the microwave landing radar, which is provided to the GNC system to control the deceleration of the lander. For planetary landings, the landing point is generally selected in advance. Therefore, the GNC system needs to control the flight speed and altitude of the lander so that when it reaches the predetermined landing point, the horizontal and verti...

Claims

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Application Information

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IPC IPC(8): G01S13/60
Inventor 宋大伟尚社孙文锋
Owner XIAN INSTITUE OF SPACE RADIO TECH
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