CN106909166B - Method and device for correcting ascension parameter of ascending intersection point - Google Patents
Method and device for correcting ascension parameter of ascending intersection point Download PDFInfo
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- CN106909166B CN106909166B CN201710115354.4A CN201710115354A CN106909166B CN 106909166 B CN106909166 B CN 106909166B CN 201710115354 A CN201710115354 A CN 201710115354A CN 106909166 B CN106909166 B CN 106909166B
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- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
Abstract
The invention discloses a method and a device for correcting ascension parameters of a rising intersection point. The method comprises the following steps: acquiring actual takeoff time of a carrier and a rising point right ascension parameter corresponding to the actual takeoff time; calculating the time deviation between the actual takeoff time and the preset takeoff time; carrying out amplitude limiting processing on the time deviation to obtain the time deviation after amplitude limiting; calculating the deviation value of the right ascension parameter of the ascending intersection point according to the time deviation after amplitude limiting; and correcting the ascension point parameter corresponding to the actual takeoff time according to the ascension point ascension parameter deviation amount. The invention solves the problem that the right ascension parameter of the ascending intersection point changes and the carrier can not accurately enter the preset track when the carrier is delayed to launch, and realizes the effect of improving the flight control reliability of the carrier.
Description
Technical Field
The invention relates to a flight orbit parameter correction technology, in particular to a correction method and a correction device for a ascension parameter of a rising intersection point.
Background
The ascent point right ascension parameter is an inertia space orbit parameter, namely the ascent point right ascension parameter is a target orbit parameter related to the takeoff time of the carrier. When the takeoff time of the carrier is changed, the ascension parameter of the ascending point is changed. The flight control computer of the carrier can control the carrier to accurately enter the rail according to the target rail parameters such as the ascension point right ascension parameter and the like.
During the actual launch of the vehicle, a situation may occur in which the launch of the vehicle is delayed. If the vehicle fails to take off at the predetermined take-off time, the ascent point right ascension parameter will change. If the ascension point right ascension parameter at the moment is not corrected to the ascension point right ascension parameter corresponding to the preset take-off time, the carrier cannot accurately enter the preset track, and the whole flight mission is further affected catastrophically.
Disclosure of Invention
The invention provides a method and a device for correcting a ascension parameter of a rising intersection point, which are used for achieving the effect of improving the flight control reliability of a carrier.
In a first aspect, the present invention provides a method for correcting a ascension parameter at a crossover point, comprising:
acquiring actual takeoff time of a carrier and a rising point right ascension parameter corresponding to the actual takeoff time;
calculating the time deviation between the actual takeoff time and the preset takeoff time;
carrying out amplitude limiting processing on the time deviation to obtain the time deviation after amplitude limiting;
calculating the deviation value of the right ascension parameter of the ascending intersection point according to the time deviation after amplitude limiting;
and correcting the ascension point parameter corresponding to the actual takeoff time according to the ascension point ascension parameter deviation amount.
Further, the calculation formula of the time deviation is as follows:
ΔT＝T-T*(1)
in the formula (1), Δ T is a time deviation between the actual takeoff time and a predetermined takeoff time, T is an actual takeoff time, and T is*Is the predetermined takeoff time.
Further, the clipping formula of the time offset is as follows:
in the formula (2), Δ T*And delta T is the time deviation after amplitude limiting, and is the time deviation between the actual takeoff time and the preset takeoff time.
Further, the calculation formula of the deviation amount of the ascension parameter at the ascending intersection is as follows:
ΔΩ＝ωie·ΔT*(3)
in the formula (3), Δ Ω is the deviation of the right ascension parameter at the elevation intersection, ωieIs the angular velocity of rotation, Δ T, of the earth*Is the time offset after clipping.
Further, according to the deviation of the ascent point right ascent parameter, correcting the ascent point right ascent parameter corresponding to the actual takeoff time, including:
and subtracting the deviation value of the ascension point ascension parameter from the ascension point ascension parameter corresponding to the actual takeoff time so as to correct the ascension point ascension parameter corresponding to the actual takeoff time.
In a second aspect, the present invention also provides a device for correcting the ascension parameter of the intersection point, the device comprising:
the system comprises an acquisition module, a control module and a display module, wherein the acquisition module is used for acquiring the actual takeoff time of a carrier and the ascension point right ascension parameter corresponding to the actual takeoff time;
the first calculation module is used for calculating the time deviation between the actual takeoff time and the preset takeoff time;
the amplitude limiting module is used for carrying out amplitude limiting processing on the time deviation so as to obtain the time deviation after amplitude limiting;
the second calculation module is used for calculating the deviation amount of the right ascension parameter of the ascending intersection point according to the time deviation after amplitude limiting;
and the correction module is used for correcting the ascent point right ascent channel parameter corresponding to the actual takeoff time according to the ascent point right ascent channel parameter deviation value.
Further, the calculation formula of the time deviation is as follows:
ΔT＝T-T*(1)
in the formula (1), Δ T is the time between the actual takeoff time and the predetermined takeoff timeInter-deviation, T being actual takeoff time, T*Is the predetermined takeoff time.
Further, the clipping formula of the time offset is as follows:
in the formula (2), Δ T*And delta T is the time deviation after amplitude limiting, and is the time deviation between the actual takeoff time and the preset takeoff time.
Further, the calculation formula of the deviation amount of the ascension parameter at the ascending intersection is as follows:
ΔΩ＝ωie·ΔT*(3)
in the formula (3), Δ Ω is the deviation of the right ascension parameter at the elevation intersection, ωieIs the angular velocity of rotation, Δ T, of the earth*Is the time offset after clipping.
Further, the correction module comprises:
and the calculating unit is used for subtracting the deviation amount of the ascension parameter of the ascension corresponding to the actual takeoff time so as to correct the ascension parameter of the ascension corresponding to the actual takeoff time.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the invention, the time deviation between the actual takeoff time and the preset takeoff time of the carrier is calculated, the amplitude limiting processing is carried out on the time deviation, the deviation quantity of the right ascension parameter of the ascending intersection point is calculated according to the time deviation after amplitude limiting, and the right ascension parameter of the ascending intersection point corresponding to the actual takeoff time is corrected according to the deviation quantity of the right ascension parameter of the ascending intersection point, so that the problem that the carrier cannot accurately enter a preset track due to the change of the right ascension parameter of the ascending intersection point when the carrier is delayed to launch is solved.
(2) The invention realizes the effect of improving the flight control reliability of the carrier, so that the carrier can still accurately enter the preset track when delayed launching occurs.
Drawings
FIG. 1 is a flowchart illustrating a method for correcting a ascension parameter of an intersection point according to a first embodiment of the present invention;
fig. 2 is a structural diagram of a device for correcting the ascension parameter at the intersection point in the second embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
Example one
Fig. 1 is a flowchart of a method for correcting a ascension parameter of an ascending intersection according to a first embodiment of the present invention, where the method is applicable to a situation that the ascension parameter of the ascending intersection needs to be corrected, and the method can be executed by a device for correcting the ascension parameter of the ascending intersection, where the device can be implemented by software and/or hardware, and the device can be integrated into an aircraft control computer of a vehicle. Referring to fig. 1, the method for correcting the ascension parameter at the ascending intersection provided in this embodiment may specifically include the following steps:
s110, acquiring the actual takeoff time of the carrier and the ascension point right ascension parameter corresponding to the actual takeoff time.
Specifically, the ascension point parameter is an inertia space orbit parameter, that is, the ascension point ascension parameter is a target orbit parameter related to the takeoff time of the carrier. And the take-off time of different carriers corresponds to different ascent point right ascent parameter. In this embodiment, the actual takeoff time of the carrier and the ascent point right ascension parameter corresponding to the actual takeoff time are obtained.
And S120, calculating the time deviation between the actual takeoff time and the preset takeoff time.
Specifically, when the carrier is launched in a delayed manner, the actual takeoff time of the carrier is delayed from the predetermined takeoff time, and obviously, a time deviation exists between the actual takeoff time and the predetermined takeoff time.
Optionally, the calculation formula of the time offset is as follows:
ΔT＝T-T*(1)
in the formula (1), Δ T is a time deviation between the actual takeoff time and a predetermined takeoff time, T is an actual takeoff time, and T is*Is the predetermined takeoff time.
And S130, carrying out amplitude limiting processing on the time deviation to obtain the time deviation after amplitude limiting.
Optionally, the clipping formula of the time offset is as follows:
in the formula (2), Δ T*And delta T is the time deviation after amplitude limiting, and is the time deviation between the actual takeoff time and the preset takeoff time.
Specifically, when the delta T is less than or equal to-43200, the delta T*43200 or less; when-43200<ΔT<43200,43200<ΔT*<43200; when Δ T ≧ 43200, Δ T*More than or equal to-43200. It can be seen that the time deviation Δ T after clipping*Has a value range of [ -43200,43200]。
And S140, calculating the deviation amount of the right ascension parameter at the ascending intersection according to the time deviation after amplitude limiting.
Optionally, the calculation formula of the deviation of the ascension parameter at the ascending intersection is as follows:
ΔΩ＝ωie·ΔT*(3)
in the formula (3), Δ Ω is the deviation of the right ascension parameter at the elevation intersection, ωieIs the angular velocity of rotation, Δ T, of the earth*Is the time offset after clipping.
S150, correcting the ascension point right ascension parameter corresponding to the actual takeoff time according to the ascension point right ascension parameter deviation amount.
Optionally, the correcting the ascension point parameter corresponding to the actual takeoff time according to the deviation of the ascension point parameter includes:
and subtracting the deviation value of the ascension point ascension parameter from the ascension point ascension parameter corresponding to the actual takeoff time so as to correct the ascension point ascension parameter corresponding to the actual takeoff time.
Specifically, the ascension parameter corresponding to the actual takeoff time is subtracted from the ascension parameter corresponding to the actual takeoff time to obtain the ascension parameter corresponding to the actual takeoff time, and the ascension parameter corresponding to the actual takeoff time is corrected to the ascension parameter corresponding to the predetermined takeoff time, so that the carrier can accurately enter the predetermined track corresponding to the predetermined takeoff time.
According to the technical scheme, the time deviation between the actual takeoff time and the preset takeoff time of the carrier is calculated, the time deviation is subjected to amplitude limiting processing, the deviation quantity of the ascension point parameter of the ascension point is calculated according to the time deviation after amplitude limiting, the ascension point parameter corresponding to the actual takeoff time is corrected according to the deviation quantity of the ascension point parameter of the ascension point, the problem that the ascension point parameter of the ascension point changes when the carrier is delayed to launch, and the carrier cannot accurately enter the preset track is solved, so that the carrier can still accurately enter the preset track when the delayed launching occurs, and the effect of improving the flight control reliability of the carrier is achieved.
Example two
Fig. 2 is a structural diagram of a device for correcting an ascension parameter at an intersection according to a second embodiment of the present invention, and this embodiment is applicable to a case where the ascension parameter at an intersection needs to be corrected. Referring to fig. 2, the device for correcting the ascension parameter at the ascending intersection provided in this embodiment may specifically be as follows:
an obtaining module 210, configured to obtain an actual takeoff time of a carrier and a right ascension parameter of a lift intersection corresponding to the actual takeoff time;
a first calculating module 220, configured to calculate a time deviation between the actual takeoff time and a predetermined takeoff time;
the amplitude limiting module 230 is configured to perform amplitude limiting processing on the time offset to obtain an amplitude-limited time offset;
a second calculating module 240, configured to calculate a deviation amount of the ascension parameter at the ascending intersection according to the limited time deviation;
and a correcting module 250, configured to correct the ascent point right ascent parameter corresponding to the actual takeoff time according to the deviation amount of the ascent point right ascent parameter.
Optionally, the calculation formula of the time offset is as follows:
ΔT＝T-T*(1)
in the formula (1), Δ T is a time deviation between the actual takeoff time and a predetermined takeoff time, T is an actual takeoff time, and T is*Is the predetermined takeoff time.
Optionally, the clipping formula of the time offset is as follows:
in the formula (2), Δ T*And delta T is the time deviation after amplitude limiting, and is the time deviation between the actual takeoff time and the preset takeoff time.
Optionally, the calculation formula of the deviation of the ascension parameter at the ascending intersection is as follows:
ΔΩ＝ωie·ΔT*(3)
in the formula (3), Δ Ω is the deviation of the right ascension parameter at the elevation intersection, ωieIs the angular velocity of rotation, Δ T, of the earth*Is the time offset after clipping.
Optionally, the modification module includes:
and the calculating unit is used for subtracting the deviation amount of the ascension parameter of the ascension corresponding to the actual takeoff time so as to correct the ascension parameter of the ascension corresponding to the actual takeoff time.
The device for correcting the ascension parameter of the ascending intersection point provided by the embodiment of the present invention and the method for correcting the ascension parameter of the ascending intersection point provided by any embodiment of the present invention belong to the same inventive concept, and the device for correcting the ascension parameter of the ascending intersection point provided by any embodiment of the present invention can be implemented. For details of the technique not described in detail in this embodiment, reference may be made to the method for correcting the ascension parameter at the intersection point provided in any embodiment of the present invention.
It is to be noted that the foregoing is only illustrative of the preferred embodiments of the present invention and the technical principles employed. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims (4)
1. A method for correcting a parameter of a right ascension crossing point, comprising:
acquiring actual takeoff time of a carrier and a rising point right ascension parameter corresponding to the actual takeoff time;
calculating the time deviation between the actual takeoff time and the preset takeoff time;
and carrying out amplitude limiting processing on the time deviation to obtain the time deviation after amplitude limiting, wherein:
the clipping formula of the time deviation is as follows:
in the formula (2), △ T*△ T is the time deviation after amplitude limiting, and is the time deviation between the actual takeoff time and the preset takeoff time;
calculating the deviation amount of the right ascension parameter of the ascending intersection according to the time deviation after the amplitude limiting, wherein:
the calculation formula of the deviation value of the ascension parameter at the ascending intersection is as follows:
△Ω＝ωie·△T*(3)
in the formula (3), △ Ω is the deviation of the ascension parameter at the ascending intersection, ωieIs rotational angular velocity of the earth, △ T*Is the time deviation after amplitude limiting;
correcting the ascension point parameter corresponding to the actual takeoff time according to the ascension point ascension parameter deviation amount, and the method comprises the following steps:
and subtracting the deviation value of the ascension point ascension parameter from the ascension point ascension parameter corresponding to the actual takeoff time so as to correct the ascension point ascension parameter corresponding to the actual takeoff time.
2. The method of claim 1, wherein the time offset is calculated by:
△T＝T-T*(1)
in the formula (1), △ T is the time deviation between the actual takeoff time and the preset takeoff time, T is the actual takeoff time, and T is*Is the predetermined takeoff time.
3. A device for modifying a parameter of a right ascension crossing, comprising:
the system comprises an acquisition module, a control module and a display module, wherein the acquisition module is used for acquiring the actual takeoff time of a carrier and the ascension point right ascension parameter corresponding to the actual takeoff time;
the first calculation module is used for calculating the time deviation between the actual takeoff time and the preset takeoff time;
the amplitude limiting module is used for carrying out amplitude limiting processing on the time deviation so as to obtain the time deviation after amplitude limiting, wherein:
the clipping formula of the time deviation is as follows:
in the formula (2), △ T*△ T is the time deviation after amplitude limiting, and is the time deviation between the actual takeoff time and the preset takeoff time;
the second calculation module is used for calculating the deviation amount of the right ascension parameter of the ascending intersection point according to the time deviation after amplitude limiting;
the calculation formula of the deviation value of the ascension parameter at the ascending intersection is as follows:
△Ω＝ωie·△T*(3)
in the formula (3), △ Ω is the deviation of the ascension parameter at the ascending intersection, ωieIs rotational angular velocity of the earth, △ T*Is the time deviation after amplitude limiting;
the correction module is used for correcting the ascension point right ascension parameter corresponding to the actual takeoff time according to the ascension point right ascension parameter deviation amount, and comprises:
and subtracting the deviation value of the ascension point ascension parameter from the ascension point ascension parameter corresponding to the actual takeoff time so as to correct the ascension point ascension parameter corresponding to the actual takeoff time.
4. The apparatus of claim 3, wherein the time offset is calculated by:
△T＝T-T*(1)
in the formula (1), △ T is the time deviation between the actual takeoff time and the preset takeoff time, T is the actual takeoff time, and T is*Is the predetermined takeoff time.
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| CN111881514B (en) * | 2020-07-16 | 2024-04-05 | 北京航天自动控制研究所 | Guidance reconstruction method under engine fault state |
| CN112416019B (en) * | 2020-11-30 | 2022-09-27 | 北京航天自动控制研究所 | Takeoff time deviation compensation method |
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| WO2008118140A2 (en) * | 2007-10-18 | 2008-10-02 | The Boeing Company | Methods and apparatus for node-synchronous eccentricity control |
| CN103198187A (en) * | 2013-04-02 | 2013-07-10 | 哈尔滨工业大学 | Track design method of deep space probe and based on differential modification |
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