CN111319792A - GEO satellite interference torque acquisition method based on-orbit telemetry data - Google Patents
GEO satellite interference torque acquisition method based on-orbit telemetry data Download PDFInfo
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- CN111319792A CN111319792A CN202010098886.3A CN202010098886A CN111319792A CN 111319792 A CN111319792 A CN 111319792A CN 202010098886 A CN202010098886 A CN 202010098886A CN 111319792 A CN111319792 A CN 111319792A
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- 238000005457 optimization Methods 0.000 claims abstract description 5
- 230000008859 change Effects 0.000 claims description 12
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- 238000004458 analytical method Methods 0.000 description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
- B64G1/245—Attitude control algorithms for spacecraft attitude control
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
- B64G1/283—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using reaction wheels
Abstract
The invention provides an on-orbit telemetry data-based GEO satellite interference torque acquisition method, which comprises the following specific processes: setting an initial time and a time step; acquiring the on-track remote measurement of the rotating speeds of the reaction wheels corresponding to two moments which are separated by the time step from the initial moment, judging whether the rotating speeds meet set conditions, and if so, calculating the interference moment M according to the on-track remote measurement of the rotating speeds of the reaction wheels corresponding to the two moments; and calculating all interference moments M meeting set conditions to obtain an annual GEO satellite actual interference moment array, and providing technical support for improvement and optimization of a satellite attitude control scheme and on-orbit accurate management of a satellite.
Description
Technical Field
The invention belongs to the technical field of aircraft design, and particularly relates to a GEO satellite interference torque acquisition method based on-orbit telemetry data.
Background
The satellite is interfered by various perturbation factors during the in-orbit operation. For the GEO satellite, the main factor influencing the attitude is sunlight pressure interference torque, and therefore the satellite platform is provided with the reaction wheel, and the control computer drives the rotation speed change of the reaction wheel to achieve the effect of closed-loop control of the satellite attitude. The technology calculates the actual interference moment of the GEO satellite based on engineering parameters such as satellite reaction accurate measurement results and the like and on-orbit remote measurement parameters of the rotating speed of the reaction wheel, and provides technical support for improvement and optimization of a satellite attitude control scheme and on-orbit accurate management of the satellite.
Disclosure of Invention
In view of the above, the invention aims to provide a GEO satellite interference torque acquisition method based on-orbit telemetry data, which utilizes satellite on-orbit telemetry parameters to acquire the rule that the interference torque borne by the GEO satellite changes along with seasons, and provides technical support for improvement and optimization of a satellite attitude control scheme and accurate on-orbit management of the satellite.
The technical solution of the invention is as follows:
a GEO satellite interference torque acquisition method based on-orbit telemetry data comprises the following specific processes:
setting an initial time and a time step;
acquiring the on-track remote measurement of the rotating speeds of the reaction wheels corresponding to two moments which are separated by the time step from the initial moment, judging whether the rotating speeds meet set conditions, and if so, calculating the interference moment M according to the on-track remote measurement of the rotating speeds of the reaction wheels corresponding to the two moments;
and calculating all interference moments M meeting set conditions to obtain an annual GEO satellite actual interference moment array, and providing technical support for improvement and optimization of a satellite attitude control scheme and on-orbit accurate management of a satellite.
Further, the invention satisfies the set conditions as follows:
two adjacent time points are arrangedThe corresponding on-track telemetry of the rotational speed of the reaction wheel is respectively marked as w10，w20，w30，w40And w11，w21，w31，w41And calculating the change of the rotating speed of the four wheels:
Δ1＝w11-w10
Δ2＝w21-w20
Δ3＝w31-w30
Δ4＝w41-w40
when delta1,Δ2,Δ3,Δ4At least one more than 5rpm or at least two more than 3rpm is present, the set condition is considered to be satisfied.
Further, the disturbance moment M of the present invention is:
wherein, α1、β1、γ1，…，α4、β4、γ4The three-axis included angle, I, between the installation normal of 4 reaction wheels of the GEO satellite and the star coordinate systemw1，…，Iw4For the moment of inertia of the 4 reaction wheels, T0 and T1 indicate two consecutive moments, T1 being T0+ Δ T, Δ T being a set time step.
Further, the Δ T of the present invention is 60 s.
Compared with the prior art, the invention has the beneficial effects that:
the analysis method can calculate and analyze the change of the interference moment borne by the GEO satellite in real time aiming at the change of the actual on-orbit telemetry parameters, and provides support for the satellite on-orbit fine management. Meanwhile, the on-orbit actual result is fed back to the satellite design, and the method can be used for optimizing the satellite design scheme.
Drawings
FIG. 1 is a flow chart of the present embodiment;
FIG. 2 is a curve of the GEO satellite 3-day arc length reaction speed variation;
FIG. 3 is a sequence of GEO satellite reaction wheel speed parameters.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention.
The derivation process of the GEO satellite disturbance moment comprises the following steps:
according to ground accurate measurement engineering parameters and on-orbit remote measurement data of the GEO satellite, the angular momentum of the whole satellite is analyzed, wherein the angular momentum comprises angular momentum generated by orbital motion and reaction wheel system angular momentum caused by external light pressure interference torque. The related parameters comprise the mounting position of the reaction wheel, the rotational inertia of the reaction wheel, the rotating speed of a flywheel, the rotational inertia of a satellite, the angular speed of a satellite orbit, the angular speed of a satellite body Z axis, the yaw attitude angle of the satellite and the like.
And (I) calculating the angular momentum Hw of the reaction wheel based on the ground accurate measurement result.
According to the satellite precision measurement result, the included angles of the mounting normal lines of the GEO satellite reaction wheels 1-4 and the three axes of the satellite coordinate system are α1、β1、γ1，…，α4、β4、γ4Then, the angular momentum of the wheel train composed of four reaction wheels is:
wherein, Iw1，…，Iw41-4 moment of inertia of the reaction wheel; w is a1，…，w4The rotational speed of the reaction wheels 1-4.
And (III) calculating the angular momentum of the satellite body.
The whole-star angular momentum is the sum of the resultant angular momentum of the reaction wheel system and the angular momentum of the star body:
H＝Hw+Hb(2)
wherein，Ix,Iy,IzAre respectively the three-axis moment of inertia of the star body, w0Is the satellite orbital angular velocity, # is the satellite yaw attitude angle, wzbIs the angular velocity of the satellite about the Z axis of the satellite.
For the Beidou GEO satellite adopting the zero yaw attitude control mode, the yaw angle psi is 0, and the angular speed w is around the Z axis of the satellite bodyzbIs 0. Thus, GEO satellite angular momentum is determined by the reaction wheel train, i.e.:
and (IV) according to the theorem of angular momentum, taking the whole satellite as an analysis object, wherein the interference torque of the satellite conforms to the following conditions:
in the formula (4), according to the accurate measurement result before the whole satellite is launched, the reaction wheel train installation matrix is a constant matrix, and the interference moment M is determined by the rotation speed change of the reaction wheel, so that the GEO satellite interference moment is obtained as follows:
based on the GEO satellite interference torque and on-orbit telemetering data, the process of calculating the GEO satellite interference torque is as follows:
the change rule of the disturbance moment of the GEO satellite is determined by the orbit characteristics of the GEO satellite to be consistent with the cycle of the sun around the ecliptic of one year, and the change curve of the rotating speed of the reaction wheel in 3 days of the GEO satellite in orbit in the graph of figure 2 and the rotating speed change of the reaction wheel in the graph of figure 3 are used for telemetering and counting results, so that the change of the reaction rotating speed is very stable. The calculation process is shown in fig. 1:
(1) first, an initial time T0 is selected and corresponding on-track reaction wheel rotational speed telemetry, denoted as w10，w20，w30，w40；
(2) On-track telemetry w reading T1 ═ T0+60s11，w21，w31，w41Judging the change of the rotating speed of the four wheels:
when delta1,Δ2,Δ3,Δ4If a value > 5rpm or at least 2 > 3rpm is present, the number of groups is counted and calculated
The disturbance torque at the moment is:
otherwise, reading the data of T2 ═ T1+60s, and making a validity judgment.
(3) All the effective moments obtained in the step (2) are collated and the disturbance torque (T) is determined corresponding to the effective momentsi,Mi) And forming an annual GEO satellite actual interference torque array set, and representing the change rule of the interference torque along with time and seasons by a curve.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. A GEO satellite interference torque acquisition method based on-orbit telemetry data is characterized by comprising the following specific processes:
setting an initial time and a time step;
acquiring the on-track remote measurement of the rotating speeds of the reaction wheels corresponding to two moments which are separated by the time step from the initial moment, judging whether the rotating speeds meet set conditions, and if so, calculating the interference moment M according to the on-track remote measurement of the rotating speeds of the reaction wheels corresponding to the two moments;
and calculating all interference moments M meeting set conditions to obtain an annual GEO satellite actual interference moment array, and providing technical support for improvement and optimization of a satellite attitude control scheme and on-orbit accurate management of a satellite.
2. The method for acquiring GEO satellite disturbance torque based on-orbit telemetry data as claimed in claim 1, wherein the meeting of the set conditions is:
the on-track telemetering of the rotating speed of the reaction wheel corresponding to two adjacent moments is recorded as w10，w20，w30，w40And w11，w21，w31，w41And calculating the change of the rotating speed of the four wheels:
Δ1＝w11-w10
Δ2＝w21-w20
Δ3＝w31-w30
Δ4＝w41-w40
when delta1,Δ2,Δ3,Δ4At least one more than 5rpm or at least two more than 3rpm is present, the set condition is considered to be satisfied.
3. The method for acquiring GEO satellite disturbance torque based on-orbit telemetry data as claimed in claim 2, wherein the disturbance torque M is:
wherein, α1、β1、γ1，…，α4、β4、γ4The three-axis included angle, I, between the installation normal of 4 reaction wheels of the GEO satellite and the star coordinate systemw1，…，Iw4For the moment of inertia of the 4 reaction wheels, T0 and T1 indicate two consecutive moments, T1 being T0+ Δ T, Δ T being a set time step.
4. The on-orbit telemetry data-based GEO satellite jamming torque acquisition method of claim 3, wherein the Δ T is 60 s.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6260805B1 (en) * | 1998-12-29 | 2001-07-17 | Hughes Electronics Corporation | Method of controlling attitude of a momentum biased spacecraft during long-duration thruster firings |
| US6263264B1 (en) * | 2000-06-08 | 2001-07-17 | The Aerospace Corporation | Pseudo gyro with unmodeled disturbance torque estimation |
| CN107618678A (en) * | 2017-08-25 | 2018-01-23 | 中国科学院长春光学精密机械与物理研究所 | Attitude control information consolidation method of estimation under attitude of satellite angular deviation |
| CN108327927A (en) * | 2018-01-17 | 2018-07-27 | 浙江大学 | The adaptive Torque distribution control method of reaction wheel group based on microsatellite |
| CN108983637A (en) * | 2018-09-04 | 2018-12-11 | 上海微小卫星工程中心 | A kind of satellite control system semi-physical simulation method using reaction wheel |
-
2020
- 2020-02-18 CN CN202010098886.3A patent/CN111319792A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6260805B1 (en) * | 1998-12-29 | 2001-07-17 | Hughes Electronics Corporation | Method of controlling attitude of a momentum biased spacecraft during long-duration thruster firings |
| US6263264B1 (en) * | 2000-06-08 | 2001-07-17 | The Aerospace Corporation | Pseudo gyro with unmodeled disturbance torque estimation |
| CN107618678A (en) * | 2017-08-25 | 2018-01-23 | 中国科学院长春光学精密机械与物理研究所 | Attitude control information consolidation method of estimation under attitude of satellite angular deviation |
| CN108327927A (en) * | 2018-01-17 | 2018-07-27 | 浙江大学 | The adaptive Torque distribution control method of reaction wheel group based on microsatellite |
| CN108983637A (en) * | 2018-09-04 | 2018-12-11 | 上海微小卫星工程中心 | A kind of satellite control system semi-physical simulation method using reaction wheel |
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