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An Improved Predictive Guidance Method for Rlv Reentry Heat Flow Rate Tracking

A technology of predictive guidance and predictive correction guidance, applied in the field of flight guidance, can solve problems such as complex tasks, and achieve the effect of meeting mission requirements and ensuring landing accuracy.

Active Publication Date: 2021-06-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

[0005] However, future reentry vehicles will have more complex missions and more stringent load requirements. In order to meet the needs of future flight missions, it is necessary to design corresponding predictive correction guidance laws for the heat flow tracking of reentry vehicles.

Method used

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  • An Improved Predictive Guidance Method for Rlv Reentry Heat Flow Rate Tracking
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  • An Improved Predictive Guidance Method for Rlv Reentry Heat Flow Rate Tracking

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Embodiment Construction

[0066] In order to enable those skilled in the art to better understand the technical solutions of the present invention, the present invention will be further described in detail below in conjunction with specific embodiments.

[0067] An embodiment of the present invention provides an improved predictive guidance method for RLV reentry heat flow rate tracking, such as figure 1 As shown, the reusable carrier with a medium lift-to-drag ratio in this embodiment is Horus-2B. The maximum heat flow rate of this aircraft is usually 450 kilowatts per square meter, and the maximum overload is about 4g. The initial state of its reentry section And the end state is shown in Table 1.

[0068]

[0069] Table 1

[0070] In the table, the unit of aircraft altitude is km, the unit of speed is m / s, and the unit of other angles is degree. These six state quantities represent the flight altitude, the latitude and longitude of the sub-satellite point, the speed of the aircraft, the inclina...

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Abstract

The invention discloses an improved predictive guidance method for RLV (reusable launch vehicle, reusable vehicle) reentry heat flow rate tracking, and relates to the technical field of flight guidance. The present invention improves the longitudinal guidance law and the lateral guidance law in the predictive correction guidance, which mainly includes the following aspects: when designing the longitudinal guidance law, first determine the maximum value of the heat flow rate at the current moment, and then contribute to the design of the longitudinal guidance law Introduce heat flow rate tracking compensation item to correct the roll angle amplitude; in the design process of lateral guidance law, the lateral guidance logic designed by the improved artificial potential field method can effectively deal with geographical constraints, when the reusable vehicle flies through the no-fly zone The subsequent lateral guidance logic is determined by the track azimuth error corridor. The invention can not only ensure the landing point accuracy of the aircraft, but also satisfy the process constraints and geographical constraints during the flight.

Description

technical field [0001] The invention relates to the technical field of flight guidance, in particular to an improved predictive guidance method for RLV reentry heat flow rate tracking. Background technique [0002] A reusable launch vehicle (RLV, reusable launch vehicle) can not only be used as a civilian vehicle that travels freely between the world and the earth, but also has the ability to quickly strike globally. After the end of the space shuttle era, the success of "Falcon 9" and X-37 greatly encouraged people's research and development boom for reusable vehicles. Therefore, major countries in the world have carried out in-depth research on the structure, materials, guidance, control and other systems of reusable vehicles. [0003] However, due to the complex flight environment, diverse missions, and harsh constraints in the re-entry process of reusable vehicles, this poses new requirements and challenges for the design of guidance laws. At present, reentry guidance ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/12
CPCG05D1/12
Inventor 林海兵都延丽刘武唐明明
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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