Method for lateral prediction correction guidance in stage of entering mars atmosphere

A technology of prediction, correction, guidance and prediction and correction, applied in the field of deep space exploration, can solve problems such as lack of flexibility, and achieve the effect of flexible planning

Inactive Publication Date: 2015-12-02
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

For these requirements, the traditional method of constraining lateral moti

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  • Method for lateral prediction correction guidance in stage of entering mars atmosphere
  • Method for lateral prediction correction guidance in stage of entering mars atmosphere
  • Method for lateral prediction correction guidance in stage of entering mars atmosphere

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Embodiment 1

[0064] This embodiment discloses a lateral prediction and correction guidance method for the Mars atmosphere entry section, which is used to perform a lateral maneuver in the Mars atmosphere entry section. The lateral maneuver is the roll angle reversal maneuver, so as to save fuel Purpose. Including the following steps:

[0065] Use the dynamic model of the detector to perform numerical integration until the parachute opening condition is met (and the parachute dynamic pressure interval [q min ,q max ] and the parachute Mach number interval [Ma min , Ma max ]), calculate the parachute accuracy deviation s between the parachute opening time and the target position f , the specific implementation method is:

[0066] Step 1. Determine the longitudinal motion guidance instruction |σ|.

[0067] A Probe Considering the Effect of Mars' Rotation on Dimensionless Time The three-degree-of-freedom dimensionless entry dynamics model is

[0068] ...

Embodiment 2

[0108] This embodiment discloses a lateral prediction and correction guidance method for the Mars atmosphere entry section. For the radio navigation scheme of the Mars atmosphere entry section in the future, the aircraft flying over the corresponding considerable area will significantly improve the observability of the navigation system, thereby improving the navigation accuracy. Therefore, it is desirable that the trajectory of the aircraft over a considerable area be as long as possible. For the sake of simplicity, it is assumed here that the aircraft flies over the centroid of the observable area (in this embodiment, the coordinates of the centroid of the observable area are selected as (θ 1 ,φ 1 )=(-45.14°,-43.67°)), the trajectory of its flying over the observable area is the longest.

[0109] This embodiment includes the following steps:

[0110] Use the dynamic model of the detector to perform numerical integration until the parachute opening condition is met (and the...

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Abstract

The invention discloses a method for lateral prediction correction guidance in the stage of entering mars atmosphere, relates to a lateral prediction correction guidance method and belongs to the technical field of deep-space exploration. On the basis of a conventional longitudinal prediction correction guidance method, the prediction correction method is introduced into design of a detector lateral motion guidance law. Firstly, lateral motion constraint conditions required by a landing detection task are determined, so as to determine heeling angle inversion frequency required by a detector at the entering stage; then, lateral motion constraint conditions are solved to determine energy of the detector at the heeling angle inversion moment, and when the energy of the detector exceeds energy at the heeling angle inversion moment, heeling angle inversion is carried out. After the constraint conditions are met, next heeling angle inversion energy is determined; finally, a current guidance cycle is determined by combing energy at the heeling angle inversion moment and the longitudinal guidance law and output is guided finally. By adopting the method provided by the invention, while parachute-opening point position accuracy is ensured, lateral motion of the detector entering an orbit can be flexibly planned according to task needs and fuel is saved.

Description

technical field [0001] The invention relates to a lateral prediction and correction guidance method, in particular to a lateral prediction and correction guidance method for the Martian atmosphere entry section, and belongs to the technical field of deep space exploration. Background technique [0002] In the future, Mars landing exploration missions will put forward higher requirements for the landing accuracy on the surface of Mars. The entry into the Martian atmosphere is the longest and harshest stage in the entire Mars entry, descent, and landing process. Ensuring the successful implementation of the entry stage mission plays a vital role in ensuring the accuracy of the final landing. [0003] So far, a total of seven Mars rovers have successfully landed on the surface of Mars. In the latest landing mission "Mars Science Laboratory / Curiosity", the guidance law was adopted for the first time in the entry phase, and the parachute was safely opened in the predetermined pa...

Claims

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Application Information

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IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 崔平远龙嘉腾高艾朱圣英徐瑞
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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