Capability evaluation method for thrust descending fault of low-thrust engine

An engine and low-thrust technology, which is applied in motor vehicles, space navigation equipment, and space navigation vehicles, etc., can solve thrust drop failures, failure mode capability evaluation of thrust drop failures without small thrust engines, and affect rocket orbital accuracy, etc. problems, to achieve the effect of improving accuracy, avoiding hardware equipment modification, and saving development costs

Pending Publication Date: 2020-09-15
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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Problems solved by technology

During the flight of the rocket, if the catalyst performance of the engine fails, etc., it will lead to a thrust drop failure, which will affect the accuracy of the rocket’s orbit. Provide a basis for subsequent change control strategies and achieve accurate orbiting
[0003] there are no capability assessments for low thrust engine thrust drop failure modes

Method used

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  • Capability evaluation method for thrust descending fault of low-thrust engine

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Embodiment Construction

[0025] In addition to the embodiments described below, the invention can be embodied in other embodiments or carried out in different ways. It is, therefore, to be understood that the invention is not limited to the details of construction of the components described in the following description or shown in the drawings. While only one embodiment is described here, the claims are not limited to that embodiment.

[0026] A method for evaluating the capability of a small-thrust engine with a thrust drop failure. When the engine has a thrust drop failure, the capability assessment method for flight time is as follows:

[0027] (1) Calculation of engine axial thrust residual degree D:

[0028] where n x1 is the actual flight overload, n x1 =ΔW x1 / Δt,ΔW x1 is the axial apparent velocity increment measured by the strapdown inertial group within Δt time, Δt is the navigation calculation cycle, Is the theoretical flight overload standard value, turn to step (2);

[0029] (2...

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Abstract

The invention discloses a capability evaluation method for a thrust descending fault of a low-thrust engine. The capability evaluation method comprises the following steps: (1) calculating the residual degree D of the axial thrust of an engine; (2) performing fault severity grading judgment on the residual degree D of the axial thrust of the engine; (3) predicting and calculating the remaining flight time ts; (4) calculating theoretical residual flight time tsl; and (5) comparing the remaining flight time ts with the theoretical remaining flight time tsl. According to the capability evaluationmethod, for the small-thrust engine, the shutdown amount information within a certain time period is used for carrying out capacity evaluation, and the influence of quantization errors, inertial measurement unit tool errors and other interference on capacity evaluation is eliminated, and the evaluation accuracy is improved.

Description

technical field [0001] The invention belongs to the field of guidance and control systems, and in particular relates to a capability evaluation method for thrust drop faults of small thrust engines. Background technique [0002] The small-thrust engine is generally used in the terminal speed correction section of the rocket to precisely control the orbital speed of the rocket and realize the precise entry of the rocket into the predetermined orbit. During the flight of the rocket, if the catalyst performance of the engine fails, etc., it will lead to a thrust drop failure, which will affect the accuracy of the rocket’s orbit. It provides a basis for subsequent change control strategies and accurate orbitalization. [0003] There is currently no capability assessment for the thrust drop failure mode of small thrust engines. The method utilizes the control system's own information, does not need to use external system information, and can be realized only by modifying the fl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F30/15B64G1/24G06F119/14
CPCG06F30/20G06F30/15B64G1/242G06F2119/14
Inventor 叶松陈曦袁艳艳罗婷
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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