CN111666672B - Capability assessment method for thrust decline fault of low-thrust engine - Google Patents
Capability assessment method for thrust decline fault of low-thrust engine Download PDFInfo
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- CN111666672B CN111666672B CN202010483267.6A CN202010483267A CN111666672B CN 111666672 B CN111666672 B CN 111666672B CN 202010483267 A CN202010483267 A CN 202010483267A CN 111666672 B CN111666672 B CN 111666672B
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Abstract
A capability assessment method for a thrust decline fault of a low-thrust engine comprises the following steps: (1) calculating the residual degree D of the axial thrust of the engine; (2) Performing fault severity grading judgment on the residual degree D of the axial thrust of the engine; (3) Remaining time of flight t s Predictive calculation; (4) Theoretical remaining time of flight t sl Calculating; (5) Remaining time of flight t s From the theoretical remaining time of flight t sl A comparison is made. The invention carries out capability assessment by utilizing the shutdown quantity information within a certain period of time aiming at the low thrust engine, eliminates the influence of interference such as quantization error, inertial measurement unit tool error and the like on the capability assessment, and improves the accuracy of the assessment.
Description
Technical Field
The invention belongs to the field of guidance control systems, and particularly relates to a capability assessment method for a thrust decline fault of a low-thrust engine.
Background
The low thrust engine is generally used in a final speed correction section of the rocket and is used for accurately controlling the track-entering speed of the rocket so as to realize accurate entry of the rocket into a preset track. If the performance of the catalyst of the engine fails and the like in the rocket flight process, a thrust drop fault is caused, so that the orbit entering precision of the rocket is affected, therefore, the capability evaluation of the thrust drop fault on the influence of the flight time is required for solving the problem, and a foundation is provided for the follow-up change of a control strategy and the realization of accurate orbit entering.
There is currently no capability assessment for the low thrust engine thrust decline failure mode. The method utilizes the information of the control system, does not need to use external system information, can be realized by only modifying flight software, avoids the reconstruction of hardware equipment, and saves the development cost.
Disclosure of Invention
The invention provides a capability assessment method for solving the influence on flight time after a small thrust engine has a thrust descending fault in the flight process.
Working principle: the rocket is configured with a low-thrust engine to perform orbit control, when the engine has a thrust descending fault, the residual degree of the rocket axial thrust is calculated, capability evaluation aiming at the flight time is performed, whether the residual flight time is predicted is selected according to the residual degree of the axial thrust, the residual flight time is calculated under the condition that the prediction is required, and whether the subsequent control strategy is required to be changed is evaluated according to the residual flight time and the theoretical residual flight time.
A capability assessment method for a thrust decline fault of a low-thrust engine comprises the following steps:
(1) Calculating the residual degree D of the axial thrust of the engine;
(2) Performing fault severity grading judgment on the residual degree D of the axial thrust of the engine;
(3) Remaining time of flight t s Predictive calculation;
(4) Theoretical remaining time of flight t sl Calculating;
(5) Remaining time of flight t s From the theoretical remaining time of flight t sl A comparison is made.
Further, the residual degree of the axial thrust of the engine in the step (1)Wherein n is x1 For actual flight overload, n x1 ＝ΔW x1 /Δt，ΔW x1 For the axial apparent velocity increment measured by the strapdown inertial measurement unit in delta t time, delta t is the navigation calculation period, and the strapdown inertial measurement unit is in the form of a delta t>Is a theoretical flight overload standard value.
Further, the step (2) further includes the following steps:
(1) When the value range of the residual degree D of the axial thrust of the engine is 100 percent to more than or equal to 80 percent, capability assessment is not needed;
(2) When 80% > D is more than or equal to 10%, carrying out capability assessment, and predicting the residual flight time;
(3) When 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, the remaining time of flight of step (3)Wherein->Kw is the actual shutdown amount calculated in the current control period for the theoretical shutdown amount; calculation error of Kw in time t=5s, 5s versus T s Less than 5%; ΔKw 1 And (5) rolling accumulation is adopted for increasing the shutdown amount in the time T.
Further, the theoretical remaining time of flight t in step (4) sl ＝[t xd -(t-TK)]*K1，t xd For the relative timing shutdown time, t is the current flight time taking take off as a zero point, TK is the computer shutdown time of the previous flight segment, K1 is an evaluation coefficient, and 90% of the current residual flight time is used for capability evaluation, and the value is 0.9.
Further, the remaining time of flight t of the step (5) s From the theoretical remaining time of flight t sl Comparing, when t s ＞t sl When the track control strategy is needed to be changed subsequently, otherwise, the current track control strategy is kept.
The invention has the beneficial effects that:
(1) The invention utilizes the relation between the required remaining flight time and the theoretical remaining flight time to realize the capability assessment for the flight time;
(2) The invention utilizes the information of the control system, does not need to use external system information, can be realized by only modifying flight software, avoids the reconstruction of hardware equipment and saves the development cost;
(3) The invention carries out capability assessment by utilizing the shutdown quantity information within a certain period of time aiming at the low thrust engine, eliminates the influence of interference such as quantization error, inertial measurement unit tool error and the like on the capability assessment, and greatly improves the accuracy of the assessment.
Drawings
FIG. 1 is a flow chart of a method of capability assessment for a low thrust engine thrust decline fault.
Detailed Description
The invention is capable of other embodiments and of being practiced or of being carried out in various ways in addition to those described below. It is to be understood, therefore, that this invention is not limited to the details of construction of the components set forth in the following description or illustrated in the drawings. When only one embodiment is described herein, the claims are not limited to that embodiment.
The capability assessment method for the thrust decline fault of the low-thrust engine comprises the following steps of:
(1) Calculating the remaining degree D of the axial thrust of the engine:
wherein n is x1 For actual flight overload, n x1 ＝ΔW x1 /Δt，ΔW x1 For the axial apparent velocity increment measured by the strapdown inertial measurement unit in delta t time, delta t is the navigation calculation period, and the strapdown inertial measurement unit is in the form of a delta t>As a theoretical flight overload standard value, turning to the step (2);
(2) And (5) performing fault severity grading judgment:
when the value range of the residual degree D of the axial thrust of the engine is 100 percent to D more than or equal to 80 percent, the residual thrust is more, the fault degree is very light, the normal track entering can still be ensured by the existing capability, and capability assessment is not needed; when 80% > D is more than or equal to 10%, the residual thrust is considered to be smaller, the secondary fault with a heavier degree is considered to be included, and the step (3) is carried out to predict the required residual flight time; when D is less than 10%, the rocket has no thrust, belongs to a serious first-stage fault, does not need capability assessment, and can complete corresponding actions according to a preset time sequence of the rocket;
(3) Remaining time of flight t s And (3) prediction calculation:
wherein->Kw is the actual shutdown amount calculated in the current control period for the theoretical shutdown amount; t=5s (calculated error of Kw over 5s time vs T s Less than 5%); ΔKw 1 The shutdown quantity increment in the time T is adopted for rolling accumulation;
(4) Theoretical remaining time of flight t sl And (3) calculating:
t sl ＝[t xd -(t-TK)]*K1，t xd for the relative timing shutdown time, t is the current flight time taking take-off as a zero point, TK is the computer shutdown time of the previous flight segment, K1 is an evaluation coefficient, and the value is 0.9 (90% of the current residual flight time is used for capability evaluation after the influence of calculation errors is considered);
(5) Remaining time of flight t s From the theoretical remaining time of flight t sl Comparison is performed: t is t s ＞t sl The track control strategy needs to be changed subsequently, otherwise, the current track control strategy is maintained.
Various modifications may be made to the method set forth above without departing from the spirit of the invention, and the scope of the invention should therefore be determined from the appended claims.
Claims (4)
1. A capability assessment method for a thrust decline failure of a low thrust engine, comprising the steps of:
(1) Calculating the residual degree D of the axial thrust of the engine;
(2) Performing fault severity grading judgment on the residual degree D of the axial thrust of the engine;
(3) Remaining time of flight t s Predictive calculation; said remaining time of flightWherein->Kw is the actual shutdown amount calculated in the current control period for the theoretical shutdown amount; calculation error of Kw in time t=5s, 5s versus T s Less than 5%; ΔKw 1 The shutdown quantity increment in the time T is adopted for rolling accumulation;
(4) Theoretical remaining time of flight t sl Calculating; said theoretical remaining time of flight t sl ＝[t xd -(t-TK)]*K1，t xd For the relative timing shutdown time, t is the current flight time taking take-off as a zero point, TK is the computer shutdown time of the previous flight segment, K1 is an evaluation coefficient, and 90% of the current residual flight time is used for capability evaluation, and the value is 0.9;
(5) Remaining time of flight t s From the theoretical remaining time of flight t sl A comparison is made.
2. The capacity assessment method according to claim 1, wherein said degree of remaining engine axial thrust of step (1)Wherein n is x1 For actual flight overload, n x1 ＝ΔW x1 /Δt，ΔW x1 For the axial apparent velocity increment measured by the strapdown inertial measurement unit in delta t time, delta t is the navigation calculation period, and the strapdown inertial measurement unit is in the form of a delta t>Is a theoretical flight overload standard value.
3. The capability 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 100 percent to more than or equal to 80 percent, capability assessment is not needed;
(2) When 80% > D is more than or equal to 10%, carrying out capability assessment, and predicting the residual flight time;
(3) When 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 of claim 1, wherein said step (5) is a remaining time of flight t s From the theoretical remaining time of flight t sl Comparing, when t s ＞t sl When the track control strategy is needed to be changed subsequently, otherwise, the current track control strategy is kept.
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| 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 |
| 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 |
| CN112208800B (en) * | 2020-12-01 | 2021-04-16 | 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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| 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 |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
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