CN111666672A - Capability evaluation method for thrust descent fault of low-thrust engine - Google Patents

Capability evaluation method for thrust descent fault of low-thrust engine Download PDF

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CN111666672A
CN111666672A CN202010483267.6A CN202010483267A CN111666672A CN 111666672 A CN111666672 A CN 111666672A CN 202010483267 A CN202010483267 A CN 202010483267A CN 111666672 A CN111666672 A CN 111666672A
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CN111666672B (en
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叶松
陈曦
袁艳艳
罗婷
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Beijing Aerospace Automatic Control Research Institute
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Abstract

A capability evaluation method for a thrust dip fault of a low thrust engine comprises the following steps: (1) calculating the residual degree D of the axial thrust of the engine; (2) carrying out fault severity grading judgment on the residual degree D of the axial thrust of the engine; (3) time of flight t remainingsPerforming prediction calculation; (4) theoretical residual time of flight tslCalculating; (5) time of flight t remainingsAnd the theoretical residual flight time tslA comparison is made. According to the method, for the low-thrust engine, the capability evaluation is carried out by using the shutdown quantity information in a certain time period, so that the influence of interference such as quantization errors and inertial measurement unit tool errors on the capability evaluation is eliminated, and the accuracy of the evaluation is improved.

Description

Capability evaluation method for thrust descent fault of low-thrust engine
Technical Field
The invention belongs to the field of guidance control systems, and particularly relates to a capability evaluation method for a thrust descent fault of a low-thrust engine.
Background
The small-thrust engine is generally used in the final speed correction section of the rocket and used for accurately controlling the entry speed of the rocket and realizing the accurate entry of the rocket into a preset orbit. If the catalyst performance of the engine fails in the rocket flying process, the thrust descent fault can be generated, so that the rocket entering precision is influenced.
There is currently no capability assessment for low thrust engine thrust droop failure modes. The method utilizes the self information of the control system, does not need to use the information of an external system, and can be realized only by modifying flight software, thereby avoiding the transformation of hardware equipment and saving the development cost.
Disclosure of Invention
The invention provides a capability evaluation method for solving the influence on flight time after a small thrust engine has a thrust descent fault in the flight process.
The working principle is as follows: the method comprises the steps that a rocket is provided with a small-thrust engine to perform orbit control, when the engine has a thrust descent fault, the axial thrust residual degree of the rocket is calculated, the capacity evaluation aiming at the flight time is performed, whether the residual flight time is predicted or not is selected according to the axial thrust residual degree, the residual flight time is calculated under the condition that the prediction is needed, and whether the subsequent control strategy needs to be changed or not is evaluated according to the residual flight time and the theoretical residual flight time.
A capability evaluation method for a thrust dip fault of a low thrust engine comprises the following steps:
(1) calculating the residual degree D of the axial thrust of the engine;
(2) carrying out fault severity grading judgment on the residual degree D of the axial thrust of the engine;
(3) time of flight t remainingsPerforming prediction calculation;
(4) theoretical residual time of flight tslCalculating;
(5) time of flight t remainingsAnd the theoretical residual flight time tslA comparison is made.
Further, the engine axial thrust residual degree in the step (1)
Figure BDA0002517879580000021
Wherein n isx1For actual flight overload, nx1＝ΔWx1/Δt，ΔWx1The axial apparent velocity increment measured by the strapdown inertial measurement unit in the time delta t is obtained, the delta t is a navigation calculation period,
Figure BDA0002517879580000022
is a theoretical flight overload standard value.
Further, the step (2) further comprises the following steps:
(1) when the value range of the residual degree D of the axial thrust of the engine is more than 100% and D is more than or equal to 80%, capacity evaluation is not needed;
(2) when D is more than 80% and is more than or equal to 10%, capacity evaluation is carried out, and residual flight time is predicted;
(3) and when the D is less than 10%, the rocket has no thrust, capability evaluation is not needed, and corresponding actions are completed according to a preset time sequence of the rocket.
Further, said step (3) remaining time of flight
Figure BDA0002517879580000023
Wherein
Figure BDA0002517879580000024
Kw is the actual shutdown quantity calculated in the current control period; t is 5s, and the calculation error of Kw in 5s is TsLess than 5%; Δ Kw1And rolling accumulation is adopted for the increment of the shutdown quantity in the T time.
Further, the theoretical remaining flight time t in the step (4)sl＝[txd-(t-TK)]*K1，txdAnd (3) relative timing shutdown time, t is the current flight time taking take-off as a zero point, TK is the shutdown time of a computer in the previous flight section, K1 is an evaluation coefficient, and 90% of the current residual flight time is used for capacity evaluation and is valued at 0.9.
Further, said step (5) of remaining time of flight tsAnd the theoretical residual flight time tslMaking a comparison when ts＞tslWhen, the track control strategy needs to be changed subsequentlyOtherwise, the current track control strategy is maintained.
The invention has the beneficial effects that:
(1) the invention realizes the capability evaluation aiming at the flight time by utilizing the relation between the required residual flight time and the theoretical residual flight time;
(2) the invention utilizes the self information of the control system, does not need to use the information of an external system, and can be realized only by modifying flight software, thereby avoiding the transformation of hardware equipment and saving the development cost;
(3) aiming at the low-thrust engine, the capability evaluation is carried out by using the shutdown quantity information in a certain time period, so that the influence of interference such as quantization error, inertial measurement unit tool error and the like on the capability evaluation is eliminated, and the evaluation accuracy is greatly improved.
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FIG. 1 is a flow chart of a method for capability assessment for a thrust cutback fault of a low thrust engine.
Detailed Description
In addition to the embodiments described below, the invention is capable of other embodiments or of being practiced or carried out in various ways. It is to be understood, therefore, that the invention is not limited in its application to the details of construction and the arrangements of the components set forth in the following description or illustrated in the drawings. While only one embodiment has been described herein, the claims are not to be limited to that embodiment.
When the thrust drop fault occurs to the engine, the method for evaluating the capacity of the flight time specifically comprises the following steps:
(1) calculating the residual degree D of the axial thrust of the engine:
Figure BDA0002517879580000031
wherein n isx1For actual flight overload, nx1＝ΔWx1/Δt，ΔWx1The axial apparent velocity increment measured by the strapdown inertial measurement unit in the time delta t is obtained, the delta t is a navigation calculation period,
Figure BDA0002517879580000032
turning to the step (2) for the theoretical flight overload standard value;
(2) and (3) carrying out fault severity grading evaluation:
when the value range of the residual degree D of the axial thrust of the engine is more than 100% and D is more than or equal to 80%, the residual thrust is more, the fault degree is very light, the normal rail entering can still be guaranteed by the existing capacity, and the capacity evaluation is not needed; when D is larger than 80% and is larger than or equal to 10%, the residual thrust is considered to be small, and the fault belongs to a secondary fault with a heavy degree, and the step (3) is carried out to predict the needed residual flight time; when D is less than 10%, the rocket has no thrust, belongs to a first-level fault with serious degree, does not need to carry out capability evaluation, and finishes corresponding actions according to a preset time sequence of the rocket;
(3) time of flight t remainingsAnd (3) prediction calculation:
Figure BDA0002517879580000033
wherein
Figure BDA0002517879580000034
Kw is the actual shutdown quantity calculated in the current control period; t-5 s (calculation error of Kw over time 5s for TsLess than 5%); Δ Kw1Rolling accumulation is adopted for the increment of the shutdown quantity in the T time;
(4) theoretical residual time of flight tslAnd (3) calculating:
tsl＝[txd-(t-TK)]*K1，txdrelative timing shutdown time, t is current flight time taking takeoff as a zero point, TK is shutdown time of a previous flight segment computer, and K1 is an evaluation coefficient and takes a value of 0.9 (90% of current remaining flight time is used for capacity evaluation after considering the influence of calculation errors);
(5) time of flight t remainingsAnd the theoretical residual flight time tslAnd (3) comparison: t is ts＞tslThe track control strategy needs to be subsequently changed, otherwise, the current track control strategy is maintained.
Various modifications may be made to the method of the invention described above without departing from the scope of the invention, and the scope of protection should therefore be determined from the content of the appended claims.

Claims (6)

1. A capability evaluation method for a thrust dip fault of a low thrust engine is characterized by comprising the following steps:
(1) calculating the residual degree D of the axial thrust of the engine;
(2) carrying out fault severity grading judgment on the residual degree D of the axial thrust of the engine;
(3) time of flight t remainingsPerforming prediction calculation;
(4) theoretical residual time of flight tslCalculating;
(5) time of flight t remainingsAnd the theoretical residual flight time tslA comparison is made.
2. The capability assessment method according to claim 1, wherein said engine axial thrust residual degree of step (1)
Figure RE-FDA0002591023260000011
Wherein n isx1For actual flight overload, nx1＝ΔWx1/Δt，ΔWx1The axial apparent velocity increment measured by the strapdown inertial measurement unit in the time delta t is obtained, the delta t is a navigation calculation period,
Figure RE-FDA0002591023260000012
is a theoretical flight overload standard value.
3. The ability assessment method according to claim 1, wherein said step (2) further comprises the steps of:
(1) when the value range of the residual degree D of the axial thrust of the engine is more than 100% and D is more than or equal to 80%, capacity evaluation is not needed;
(2) when D is more than 80% and is more than or equal to 10%, capacity evaluation is carried out, and residual flight time is predicted;
(3) and when the D is less than 10%, the rocket has no thrust, capability evaluation is not needed, and corresponding actions are completed according to a preset time sequence of the rocket.
4. The capability assessment method according to claim 1, wherein said step (3) of remaining time of flight
Figure RE-FDA0002591023260000013
Wherein
Figure RE-FDA0002591023260000014
Kw is the actual shutdown quantity calculated in the current control period; t is 5s, and the calculation error of Kw in 5s is TsLess than 5%; Δ Kw1And rolling accumulation is adopted for the increment of the shutdown quantity in the T time.
5. The ability assessment method according to claim 1, wherein the theoretical remaining flight time t in step (4)sl＝[txd-(t-TK)]*K1，txdAnd (3) relative timing shutdown time, t is the current flight time taking take-off as a zero point, TK is the shutdown time of a computer in the previous flight section, K1 is an evaluation coefficient, and 90% of the current residual flight time is used for capacity evaluation and is valued at 0.9.
6. The capability assessment method according to claim 1, characterized in that said step (5) of residual time of flight tsAnd the theoretical residual flight time tslMaking a comparison when ts＞tslAnd when the track control strategy needs to be changed subsequently, otherwise, the current track control strategy is kept.
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112208800A (en) * 2020-12-01 2021-01-12 蓝箭航天空间科技股份有限公司 Configuration and control method and device for upper-stage attitude and orbit control engine of spacecraft
CN112327916A (en) * 2020-11-12 2021-02-05 北京航天自动控制研究所 Guidance reconstruction method and device and storage medium
CN112462795A (en) * 2020-11-12 2021-03-09 北京航天自动控制研究所 Low-thrust engine fault positioning method and device and storage medium

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CN106892136A (en) * 2017-02-16 2017-06-27 北京航天自动控制研究所 A kind of aerospace craft metro planning method based on world communication
CN109573103A (en) * 2018-11-19 2019-04-05 北京航天自动控制研究所 A kind of remaining carrying capacity appraisal procedure declined under fault condition suitable for thrust
CN111176263A (en) * 2020-01-23 2020-05-19 北京航天自动控制研究所 Online aircraft thrust fault identification method based on BP neural network

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Publication number Priority date Publication date Assignee Title
CN105717937A (en) * 2014-12-23 2016-06-29 通用电气航空系统有限责任公司 A METHOD OF AUTOMATICALLY CONTROLLING THE DESCENT PHASE OF AN AIRCRAFT USING AIRCRAFT avionic device
CN106892136A (en) * 2017-02-16 2017-06-27 北京航天自动控制研究所 A kind of aerospace craft metro planning method based on world communication
CN109573103A (en) * 2018-11-19 2019-04-05 北京航天自动控制研究所 A kind of remaining carrying capacity appraisal procedure declined under fault condition suitable for thrust
CN111176263A (en) * 2020-01-23 2020-05-19 北京航天自动控制研究所 Online aircraft thrust fault identification method based on BP neural network

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112327916A (en) * 2020-11-12 2021-02-05 北京航天自动控制研究所 Guidance reconstruction method and device and storage medium
CN112462795A (en) * 2020-11-12 2021-03-09 北京航天自动控制研究所 Low-thrust engine fault positioning method and device and storage medium
CN112462795B (en) * 2020-11-12 2022-10-21 北京航天自动控制研究所 Low-thrust engine fault positioning method and device and storage medium
CN112208800A (en) * 2020-12-01 2021-01-12 蓝箭航天空间科技股份有限公司 Configuration and control method and device for upper-stage attitude and orbit control engine of spacecraft

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