Performance testing device of loop antenna satellite navigation system
A technology of satellite navigation system and loop antenna, applied in satellite radio beacon positioning system, measurement device, radio wave measurement system, etc., can solve the problem of inability to locate, rough performance of satellite navigation system, star search status and poor signal-to-noise ratio And other issues
Pending Publication Date: 2022-03-04
XIAN AEROSPACE PROPULSION TECH INST
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[0004] According to the existing published information or the method adopted, the loop antenna is tested statically. The engineers analyze the static pattern and satellite signal gain based on the existing experience to judge whether the designed loop antenna meets the dynamic use conditions. , or manually rotate the antenna and receiver, roughly check the performance of the satellite navigation system, and cannot accurately reproduce the use environment, resulting in differences between the antenna performance and the unit test during the actual flight , even if the location cannot be located, even if the location is normal, its satellite search status and signal-to-noise ratio are worse than the performance of the acceptance test
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[0039] The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0040] In order to fully verify the performance of the loop antenna satellite navigation system on the ground in a real environment, simulate the pitching and rolling attitude changes of the rocket during flight as much as possible, strictly control the quality of the product, and pass the design of the ground performance test The organization simulates the attitude information of missiles in actual flight, increases the rationality of the test performance of ring navigation antenna products, ensures that the delivered products meet the actual use environment, and ensures the success of the flight test.
[0041] Loop antenna testing mechanism of the present invention such as figure 1 As shown, it mainly includes: fixed support 1 (such as figure 2 shown), pitch leveling mechanism 2 (such as image 3 shown), roll test mechanism 3 (such as Figure 4 shown...
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The invention discloses a performance testing device for a loop antenna satellite navigation system, which can be used for simulating the influence of pitch attitude and rolling attitude changes on the performance of a loop antenna in the flight process of the satellite navigation system. According to the technical scheme, the performance testing device of the loop antenna satellite navigation system comprises a fixed support, a pitching leveling mechanism and a rolling testing mechanism. And the fixed support is fixed on the test platform. The pitching leveling mechanism is used for providing attitude angle changes in the pitching direction for the loop antenna and simulating pitching motion of the projectile in the flight process. The rolling test mechanism is used for providing rolling angle changes for an annular antenna of the satellite navigation system and simulating rolling motion of a projectile in the flight process. The test platform performs performance test on pitching motion and rolling motion.
Description
technical field [0001] The invention relates to the technical field of ring satellite navigation antenna testing, in particular to a performance test device for a ring antenna satellite navigation system. Background technique [0002] With the increase of the flight distance of missiles or rockets and the improvement of the requirements for position accuracy and attitude accuracy, inertial navigation alone cannot meet the flight requirements of missiles or rockets, or the cost of using pure inertial navigation devices is too high. The integrated navigation system using satellite navigation + inertial navigation becomes a necessary navigation method. However, due to the needs of use, a certain type of missile or rocket has a rolling motion around the X-axis during the entire flight process. Therefore, a single-antenna satellite The navigation system is not suitable for missiles and rockets that roll around the X-axis or launch vertically. In order to ensure the normal operati...
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IPC IPC(8): G01S19/23
CPCG01S19/23
Inventor 刘宝宁龚学兵陈华兵陈肖雨杨秀羽蒋炬龙婧杨若眉胡思翱尚妮妮胡颖蔺睿
Owner XIAN AEROSPACE PROPULSION TECH INST