CN110674567A - Rocket power situation judgment method based on external acceleration - Google Patents
Rocket power situation judgment method based on external acceleration Download PDFInfo
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Abstract
The invention discloses an rocket power condition judgment method based on external acceleration, which comprises the following steps: (1) carrying out initial assignment on each relevant parameter in the rocket launching process; (2) calculating a prior dynamic judgment safety region according to the correlation model of the external acceleration and the dynamic parameter; (3) and (3) comparing the position relation of the measured result of the external acceleration and the prior power safety region in real time according to the prior power safety region obtained by calculation in the step (2), judging that the power is abnormal when the external acceleration exceeds the prior power safety region, and judging that the power is normal if the external acceleration exceeds the prior power safety region. The rocket power condition judgment method based on the external acceleration establishes a fusion association model of the power parameters and the external acceleration, calculates a corresponding prior judgment safe region through the model, judges the power condition through the safe region in real time, and meets the judgment requirement of the power condition of a ground safety control system without remote measurement parameters.
Description
Technical Field
The invention relates to the field of aerospace ground safety control, in particular to an arrow power condition judgment method based on external acceleration.
Background
The ground safety control system is an indispensable important component in space launching, is an effective means for protecting the safety of lives and properties of people to the maximum extent, takes ground safety control judgment as a main basis for safety control implementation, and requires that a telemetering information source is referred to for confirmation when an external information source is used for judgment, wherein the power system parameters on the arrow are the main telemetering information source.
The existing judging method of the power condition on the rocket by the ground safety control system is to compare the real-time downloaded engine power remote measurement parameter with the size of a power safety zone calculated in advance, judge the parameter to be abnormal when the real-time parameter size exceeds the safety zone in advance, and judge the parameter to be normal when the real-time parameter does not exceed the safety zone in advance. Some rocket targets often need no telemetering transmitting equipment or telemetering power parameters to the ground due to equipment development, so that judgment of rocket power conditions cannot be carried out.
Disclosure of Invention
The invention aims to solve the problems and provides an arrow power condition judgment method based on external acceleration.
In order to achieve the purpose, the invention adopts the following technical scheme:
an rocket power condition judgment method based on external acceleration comprises the following steps:
(1) theoretical pitch angle phi, theoretical yaw angle psi, theoretical ballistic inclination angle theta, theoretical ballistic deflection angle sigma, theoretical attack angle alpha, theoretical sideslip angle beta and aerodynamic characteristic coefficient C in rocket launching processxAnd
flying speed V, target instantaneous mass m, target maximum cross-sectional area SmSectional area S of engine nozzleaEngine thrust characteristic parameter a0And b0Allowable variation range delta P of engine pressure parameterrCarrying out initial assignment;
(2) and the correlation model of the external acceleration and the dynamic parameter (engine pressure) is as follows:
wherein P isrAs theoretical power parameter (engine pressure), gi、
The components of the gravitational acceleration, the Coriolis acceleration and the bulk acceleration in the direction i (x, y and z), q is the velocity head, and p isaThe gas pressure of the nozzle opening of the engine is shown, and p is the atmospheric pressure (which changes along with the change of the height);
(3) suppose a0If the measured acceleration is more than 0, calculating a safe area for advance power judgment by the correlation model of the measured acceleration and the power parameter in the step (2) and having the following relation:
the prior dynamic safety area is as follows:
(4) and (3) comparing the position relation of the measured result of the external acceleration and the prior power safety region in real time by using the prior power safety region obtained by calculation in the step (3), judging that the power is abnormal when the external acceleration exceeds the prior power safety region, and judging that the power is normal when the external acceleration does not exceed the prior power safety region.
Further, the air density ρ and the atmospheric pressure p in the step (2) are calculated by using a 1976 united states standard atmospheric model.
Go toStep (2), the calculation formula of the speed head q in the step (2) is
Further, the theoretical power parameter PrIs 6 MPa, and the allowable variation range delta P of the engine pressure parameterrIs [ -3, 3 [)]Megapascals.
Further, the gravitational acceleration is obtained by solving through a spherical harmonic expansion method, and the Coriolis acceleration and the involved acceleration are obtained by solving through a theoretical mechanics basic theory.
The invention has the beneficial effects that: the rocket power condition judgment method based on the external acceleration establishes a fusion association model of the power parameters and the external acceleration, calculates a corresponding prior judgment safe region through the model, judges the power condition through the safe region in real time, and meets the judgment requirement of the power condition of a ground safety control system without remote measurement parameters.
Drawings
Fig. 1 is a schematic view of a prior dynamic safety area in aerospace launch according to the invention.
Fig. 2 is a schematic diagram of "normal decision" of a prior dynamic safety area in aerospace launch.
Fig. 3 is a schematic diagram of "abnormal decision" of a prior dynamic safety area in aerospace launch.
Fig. 4 is a schematic diagram of pitch model error in accordance with the present invention.
FIG. 5 is a schematic view of the yaw angle model error of the present invention.
FIG. 6 is a schematic view of a safety region calculated in advance for the attitude angle on the arrow in the aerospace emission according to the present invention.
Detailed Description
The following examples are presented to enable those skilled in the art to more fully understand the present invention and are not intended to limit the invention in any way.
An rocket power condition judgment method based on external acceleration comprises the following steps:
(1) to rocketTheoretical pitch angle phi, theoretical yaw angle psi, theoretical ballistic inclination angle theta, theoretical ballistic deflection angle sigma, theoretical attack angle alpha, theoretical sideslip angle beta and aerodynamic characteristic coefficient C in the launching processxAnd
flying speed V, target instantaneous mass m, target maximum cross-sectional area SmSectional area S of engine nozzleaEngine thrust characteristic parameter a0And b0Allowable variation range delta P of engine pressure parameterrCarrying out initial assignment;
(2) and the correlation model of the external acceleration and the dynamic parameter (engine pressure) is as follows:
wherein P isrAs theoretical power parameter (engine pressure), gi、
The components of the gravitational acceleration, the Coriolis acceleration and the bulk acceleration in the direction i (x, y and z), q is the velocity head, and p isaThe gas pressure of the nozzle opening of the engine is shown, and p is the atmospheric pressure (which changes along with the change of the height);
(3) suppose a0If the measured acceleration is more than 0, calculating a safe area for advance power judgment by the correlation model of the measured acceleration and the power parameter in the step (2) and having the following relation:
the prior dynamic safety area is as follows:
(4) and (3) comparing the position relation of the measured result of the external acceleration and the prior power safety region in real time by using the prior power safety region obtained by calculation in the step (3), judging that the power is abnormal when the external acceleration exceeds the prior power safety region, and judging that the power is normal when the external acceleration does not exceed the prior power safety region.
In the preferred embodiment, the air density ρ and the atmospheric pressure p in step (2) are calculated by using a 1976 united states standard atmospheric model.
In the preferred embodiment, the calculation formula of the speed head q in the step (2) is
In the preferred embodiment, the theoretical power parameter PrIs 6 MPa, and the allowable variation range delta P of the engine pressure parameterrIs [ -3, 3 [)]Megapascals.
In the preferred embodiment, the gravitational acceleration is obtained by solving through a spherical harmonic expansion method, and the coriolis acceleration and the involved acceleration are obtained by solving through a theoretical mechanics basic theory.
Those skilled in the art will appreciate that the above embodiments are merely exemplary embodiments and that various changes, substitutions, and alterations can be made without departing from the spirit and scope of the invention.
Claims (5)
1. A rocket power condition judgment method based on external acceleration is characterized by comprising the following steps:
(1) theoretical pitch angle phi, theoretical yaw angle psi, theoretical ballistic inclination angle theta, theoretical ballistic deflection angle sigma, theoretical attack angle alpha, theoretical sideslip angle beta and aerodynamic characteristic coefficient C in rocket launching processxAnd
flying speed V, target instantaneous mass m, target maximum cross-sectional area SmEngine jetCross sectional area of mouth SaEngine thrust characteristic parameter a0And b0Allowable variation range delta P of engine pressure parameterrCarrying out initial assignment;
(2) and the correlation model of the external acceleration and the dynamic parameter (engine pressure) is as follows:
wherein P isrAs theoretical power parameter (engine pressure), gi、
The components of the gravitational acceleration, the Coriolis acceleration and the bulk acceleration in the direction i (x, y and z), q is the velocity head, and p isaThe gas pressure of the nozzle opening of the engine is shown, and p is the atmospheric pressure (which changes along with the change of the height);
(3) suppose a0If the measured acceleration is more than 0, calculating a safe area for advance power judgment by the correlation model of the measured acceleration and the power parameter in the step (2) and having the following relation:
the prior dynamic safety area is as follows:
(4) and (3) comparing the position relation of the measured result of the external acceleration and the prior power safety region in real time by using the prior power safety region obtained by calculation in the step (3), judging that the power is abnormal when the external acceleration exceeds the prior power safety region, and judging that the power is normal when the external acceleration does not exceed the prior power safety region.
2. The rocket power situation judging method based on the external acceleration according to claim 1, wherein the air density p and the atmospheric pressure p in the step (2) are calculated by adopting a 1976 American standard atmospheric model.
3. The rocket power situation judging method based on the external acceleration according to claim 1, wherein the calculation formula of the speed head q in the step (2) is
4. The rocket power situation judging method based on the external acceleration according to claim 1, characterized in that the theoretical power parameter PrIs 6 MPa, and the allowable variation range delta P of the engine pressure parameterrIs [ -3, 3 [)]Megapascals.
5. The rocket power situation judging method based on the external acceleration as claimed in claim 1, wherein the gravitational acceleration is obtained by solving through a spherical harmonic expansion method, and the Coriolis acceleration and the involved acceleration are obtained by solving through a theoretical mechanics basic theory.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112118022A (en) * | 2020-09-13 | 2020-12-22 | 中国运载火箭技术研究院 | Integrated radio frequency system on arrow |
| CN113448346A (en) * | 2020-03-27 | 2021-09-28 | 中国人民解放军63729部队 | Trajectory optimization method based on telemetering information |
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| US6647352B1 (en) * | 1998-06-05 | 2003-11-11 | Crossbow Technology | Dynamic attitude measurement method and apparatus |
| WO2005088317A1 (en) * | 2004-03-16 | 2005-09-22 | Continental Teves Ag & Co.Ohg | Sensor arrangement |
| CN102460319A (en) * | 2009-04-15 | 2012-05-16 | 空中客车运营有限公司 | System and method for determining local accelerations, dynamic load distributions and aerodynamic data in an aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113448346A (en) * | 2020-03-27 | 2021-09-28 | 中国人民解放军63729部队 | Trajectory optimization method based on telemetering information |
| CN112118022A (en) * | 2020-09-13 | 2020-12-22 | 中国运载火箭技术研究院 | Integrated radio frequency system on arrow |
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