CN103345149A - Dynamically tuned gyroscope servo control loop - Google Patents
Dynamically tuned gyroscope servo control loop Download PDFInfo
- Publication number
- CN103345149A CN103345149A CN2013102513977A CN201310251397A CN103345149A CN 103345149 A CN103345149 A CN 103345149A CN 2013102513977 A CN2013102513977 A CN 2013102513977A CN 201310251397 A CN201310251397 A CN 201310251397A CN 103345149 A CN103345149 A CN 103345149A
- Authority
- CN
- China
- Prior art keywords
- controller
- low
- pass filter
- gyroscope
- torquer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Gyroscopes (AREA)
Abstract
The invention discloses a dynamically tuned gyroscope servo control loop which is composed of a gyroscope gauge outfit, a torquer and a controller. The controller is composed of a second-order integration element, a differentiation element, a low-pass filter and the like. For the transfer function of the controller, two integration elements are used by the dynamically tuned gyroscope servo control loop for the first time so that a system becomes a II-type system. By means of the second-order integration element, errors relevant to constant disturbance torque can be eliminated, so that the stability precision of a servo loop system is improved. The differentiation element is used for increasing the gain and phase margin of a low-frequency stage, unconditionally stabilizing the system and improving the robust stability of parameters. The low-pass filter is used for eliminating high-frequency noise.
Description
Technical field
The present invention relates to a kind of servo control loop of strap-down inertial measurement unit, relate in particular to a kind of dynamically tuned gyro, DTG servo control loop, be mainly used in the Aeronautics and Astronautics field of high precision angular velocity measurement.
Background technology
Dynamically tuned gyro, DTG is a kind of two degree-of-freedom gyro that the high speed rotor is constituted the supporting of universal joint formula with flexible member.Under tuning rotating speed, the dynamic force moment of gimbal has been offset the elastic restraint moment of flexible support, makes gyrorotor become free free rotor, therefore is called dynamically tuned gyro, DTG.Moving accent gyroscope and the carrier used in the strapdown system are connected, and the angular motion of carrier will directly be added on the gyroscope.Because the moving accent gyroscope of open-circuit condition is only limited in small angle range and works, the therefore gyroscope of using in strapdown system must be delivered to corresponding torquer by balanced loop again with its output, makes gyroscope work in closed circuit state.Under this condition, torquer applies moment to rotor, order about rotor and follow the tracks of the housing motion, gyrostatic error angle remains near zero, and the electric current by being transported to torquer (or voltage, pulsed frequency) is measured carrier around the angular velocity of gyro output axis.Domestic existing moving accent gyroscope servo control loop is type 0 system, and namely system does not contain integral element.Though this system is applied, along with the demand of high precision angular velocity measurement is more and more urgent, launch the controller design of transferring the gyroscope servo loop to moving again in different model.
The major defect of former type 0 system is that low-band gain is not high, the system stiffness deficiency, and the open-loop transfer function of establishing the gyroscope servo loop is G (s), then the relative error of systematic survey is
In the bandwidth range of system, the amplitude of open-loop transfer function is more big, and measuring accuracy is more high.For realizing the measurement high-precision requirement of gyroscope servo loop, the open loop enlargement factor of system should be greater than 150dB, for guaranteeing the robust stability of gyroscope servo-drive system, the bandwidth of gyroscope servo-drive system should be no more than 200rad/s, requiring the gyroscope servo-drive system simultaneously is a unconditional stability system, namely the phase place of open-loop transfer function in bandwidth with interior all more than-180 °.But present gyroscope servo loop can not satisfy accuracy requirement.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, a kind of dynamically tuned gyro, DTG servo control loop is provided, improved robust stability and the stable state accuracy of servo control loop.
Technical solution of the present invention: a kind of dynamically tuned gyro, DTG servo control loop,
The present invention's advantage compared with prior art is as follows:
(1) the present invention proposes to adopt 2 integral elements first, makes servo-control system become an II type system, adopts second order integral element can eliminate the error relevant with normal value rate of change of angular, thereby improves the stable state accuracy of servo loop system.
(2) the present invention redesigns the controller of servo control loop first, adopt second order integral element and differentiation element, system-gain is brought up to more than the 200dB, compare existing dynamically tuned gyro, DTG servo control loop low-band gain and have only problem about 100dB, the present invention can guarantee that servo-control system is a unconditional stability system, has improved the stability of system when closure.
(3) if adopt the method for pole-zero cancellation to need the parameter of accurate known each accelerometer gauge outfit, be unfavorable for batch requirement of producing, the controller of the present invention's design then can guarantee system to the robust stability of gauge outfit parameter, is conducive to batch product of instrument.
Description of drawings
Fig. 1 is existing 0 type servo control loop open loop frequency characteristic synoptic diagram;
Fig. 2 is realization schematic diagram of the present invention;
Fig. 3 is II type servo control loop open loop frequency characteristic synoptic diagram of the present invention.
Embodiment
Dynamically tuned gyro, DTG is made up of critical pieces such as CD-ROM drive motor, supporting system, angular transducer, gyroscopic couple device, gyrorotor, seal casinghousings.CD-ROM drive motor drives supporting system by driving shaft and gyrorotor rotates with constant angular velocity, guarantees tuning rotating speed and angular momentum that gyro has to be needed.When instrumentation, flexibly mounted positive moment of elasticity can be balanced the power bounce-back property moment of the vibratory movement generation of ring fully and offset, and makes gyrorotor become free free rotor.Angular transducer is used for converting the relative instrument housing of gyrorotor to corresponding voltage signal around the corner of two quadrature output shafts.Torquer is the device that gyrorotor is applied moment.Gyrorotor is the inertial mass that produces angular momentum H, be made up of the permanent-magnetic clamp of flywheel, torquer, movable plate electrode and the angle bridle of sensor, so gyrorotor is again the ingredient of torquer, sensor and angle bridle.
Moving accent gyroscope and the carrier used in the strapdown system are connected, and the angular motion of carrier will directly be added on the gyroscope.Because the moving accent gyroscope of open-circuit condition is only limited in small angle range and works, the therefore gyroscope of using in strapdown system must be delivered to corresponding torquer by balanced loop again with its output, makes gyroscope work in closed circuit state.Under this condition, torquer applies moment to rotor, order about rotor and follow the tracks of the housing motion, gyrostatic error angle remains near zero, and the electric current by being transported to torquer (or voltage, pulsed frequency) is measured carrier around the angular velocity of gyro output axis.
The gyrostatic gauge outfit transport function of moving accent comprises two parts: (1) gauge outfit output-transfer function
Described the frequency field mathematical relation between carrier angular velocity and the gyroscope angular transducer, wherein, H is the gyroscope angular momentum, and λ is the cross damping moment coefficient; (2) gauge outfit precession transport function
The frequency field mathematical relation that is applied between epitrochanterian moment and the angular velocity has been described.The controller can guarantee that system is a unconditional stability system at present, be that the phase place of low-frequency range is all more than-180 °, system bandwidth is 200rad/s, satisfy the requirement of robust stability, as shown in Figure 1, but because system has only about 100dB in the gain of low-frequency range, be difficult to satisfy strap-down inertial measurement unit to the requirement of angular velocity high-acruracy survey.Therefore, need controller of redesign to make servo loop to improve the gain of system.
Controller of the present invention is made up of second order integral element, differentiation element, low-pass filter etc., and 2 integral elements make system become an II type system, can eliminate the error relevant with normal value disturbance torque, thereby improves the stable state accuracy of servo loop system; Differentiation element is in order to realize improving low-band gain and phase margin, unconditional stability system and parameter robust stability, and low-pass filter is in order to eliminate high frequency noise.The servo loop of the present invention design as shown in Figure 2, K wherein
p, K
tBe respectively the amplification coefficient of angular transducer and torquer, C (s) is the transport function of servo loop controller.The present invention has redesigned the transport function of controller, make gyroscope servo loop system zero limit all at the robust stability of RHP with the raising parameter, and to make gyroscope servo loop system be thereby that the stability when closed has been guaranteed in unconditional stability, adopts second order integral element to improve stable state accuracy simultaneously.
Wherein, K is the enlargement factor of controller, T
1, T
2Be the time constant of controller Mid Frequency,
Be the transport function of low-pass filter in the controller, ξ is the ratio of damping of low-pass filter, T
3Be the time constant of low-pass filter, T
1With the time constant approximately equal of gyroscope gauge outfit, T
2S+1 is the transport function of differentiation element in the controller,
Be the transport function of second order integral element, T
3<T
2<T
1
Used gyroscope servo loop does not comprise integral element at present
Will there be an error relevant with normal value disturbance torque in system.The present invention proposes to adopt two integral elements first in controller, namely
Can eliminate the error term relevant with normal value disturbance torque, improve the stable state accuracy of system.
Because the imperfection of manufacturing process makes the numerical value of this limit not unique, for guaranteeing the robust stability of system when parameter changes, zero limit is all in RHP in the controller of the present invention's design.For guaranteeing that system is the unconditional stability system, namely in bandwidth with interior phase place all more than-180 °, adopt second order integral element to improve stable state accuracy.Adopt behind this controller gyroscope servo loop open-loop transfer function Bode diagram as shown in Figure 3.As can be seen, the open loop enlargement factor of system is greater than 200dB, and the bandwidth of system is approximate identical with former design, is no more than 200rad/s, and phase place in bandwidth with interior all more than-180 °, satisfy the design objective requirement.
The present invention not detailed description is technology as well known to those skilled in the art.
Claims (1)
1. dynamically tuned gyro, DTG servo control loop, by sensor, torquer and controller are formed, when carrier has the angular velocity input, thereby the relative gyrowheel of gyroscope housing departs from an angle produces deviation signal, sensor detects this deviation signal, controller converts the detected deviation signal of sensor to electric signal, electric signal after controller will be changed feeds back to torquer, producing trimming moment by torquer makes gyrowheel rotate to eliminate above-mentioned deviation signal again, the output of controller is as gyrostatic output the most at last, it is characterized in that: described controller is by second order integral element, differentiation element and low-pass filter are formed, and the transport function C of controller (s) is:
Wherein, K is the enlargement factor of controller, T
1, T
2Be the time constant of controller Mid Frequency,
Be the transport function of low-pass filter in the controller, ξ is the ratio of damping of low-pass filter, T
3Be the time constant of low-pass filter, T
2S+1 is the transport function of differentiation element,
Be the transport function of second order integral element, T
3<T
2<T
1
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2013102513977A CN103345149A (en) | 2013-06-24 | 2013-06-24 | Dynamically tuned gyroscope servo control loop |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2013102513977A CN103345149A (en) | 2013-06-24 | 2013-06-24 | Dynamically tuned gyroscope servo control loop |
Publications (1)
Publication Number | Publication Date |
---|---|
CN103345149A true CN103345149A (en) | 2013-10-09 |
Family
ID=49279953
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN2013102513977A Pending CN103345149A (en) | 2013-06-24 | 2013-06-24 | Dynamically tuned gyroscope servo control loop |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN103345149A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107255477A (en) * | 2017-05-10 | 2017-10-17 | 北京航天控制仪器研究所 | A kind of instrument redundancy Inertial Platform System |
CN108681239A (en) * | 2018-04-28 | 2018-10-19 | 北京航天控制仪器研究所 | A kind of two axis one gyroaccelerometers decoupling servo control loop system and method |
WO2019091419A1 (en) * | 2017-11-09 | 2019-05-16 | 酷黑科技(北京)有限公司 | Control method for augmenting drone stabilization, device and drone |
CN111189447A (en) * | 2018-11-15 | 2020-05-22 | 北京自动化控制设备研究所 | Low-pass filtering method of position measurement inertial navigation system |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5914781A (en) * | 1997-12-31 | 1999-06-22 | Aai Corporation | Method for stabilizing the phase modulator transfer function in closed loop interferometric fiber optic gyroscopes |
CN101750054A (en) * | 2008-11-28 | 2010-06-23 | 国营三四○五厂 | Flexible gyro digital rebalancing device based on DSP |
CN102359782A (en) * | 2011-07-14 | 2012-02-22 | 第二炮兵装备研究院中试与检测中心 | Digital conversion amplifying and rebalancing device of flexible gyroscope |
CN202304840U (en) * | 2011-11-10 | 2012-07-04 | 河北汉光重工有限责任公司 | Flexible gyroscope rebalancing loop board |
-
2013
- 2013-06-24 CN CN2013102513977A patent/CN103345149A/en active Pending
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5914781A (en) * | 1997-12-31 | 1999-06-22 | Aai Corporation | Method for stabilizing the phase modulator transfer function in closed loop interferometric fiber optic gyroscopes |
CN101750054A (en) * | 2008-11-28 | 2010-06-23 | 国营三四○五厂 | Flexible gyro digital rebalancing device based on DSP |
CN102359782A (en) * | 2011-07-14 | 2012-02-22 | 第二炮兵装备研究院中试与检测中心 | Digital conversion amplifying and rebalancing device of flexible gyroscope |
CN202304840U (en) * | 2011-11-10 | 2012-07-04 | 河北汉光重工有限责任公司 | Flexible gyroscope rebalancing loop board |
Non-Patent Citations (5)
Title |
---|
***等: "单力矩器大角速率动调陀螺仪力矩再平衡回路的分析与综合", 《中国惯性技术学报》, vol. 9, no. 3, 30 September 2001 (2001-09-30), pages 62 - 66 * |
张春艳: "捷联***中动力调谐陀螺仪脉冲再平衡回路的设计", 《中国优秀硕士学位论文全文数据库》, no. 6, 15 January 2006 (2006-01-15), pages 35 * |
秦永元: "《惯性导航》", 31 May 2006, 科学出版社, article "惯性导航", pages: 50-51 * |
肖琦: "动力调谐陀螺仪再平衡回路的数字控制器的设计与分析", 《中国优秀硕士学位论文全文数据库》, no. 6, 15 June 2010 (2010-06-15), pages 69 * |
黄颖: "动力调谐陀螺仪数字再平衡回路的设计与实现", 《中国优秀硕士学位论文全文数据库》, no. 4, 15 October 2007 (2007-10-15), pages 65 * |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107255477A (en) * | 2017-05-10 | 2017-10-17 | 北京航天控制仪器研究所 | A kind of instrument redundancy Inertial Platform System |
WO2019091419A1 (en) * | 2017-11-09 | 2019-05-16 | 酷黑科技(北京)有限公司 | Control method for augmenting drone stabilization, device and drone |
CN108681239A (en) * | 2018-04-28 | 2018-10-19 | 北京航天控制仪器研究所 | A kind of two axis one gyroaccelerometers decoupling servo control loop system and method |
CN111189447A (en) * | 2018-11-15 | 2020-05-22 | 北京自动化控制设备研究所 | Low-pass filtering method of position measurement inertial navigation system |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN202304840U (en) | Flexible gyroscope rebalancing loop board | |
CN102506860B (en) | Inertial stabilization device based on acceleration feedback and feedforward and control method thereof | |
CN102759365B (en) | Bias stability improving method and device for silicon micromechanical gyroscope | |
CN103323625B (en) | Error calibration compensation method of accelerometers in MEMS-IMU under dynamic environment | |
CN103344226B (en) | A kind of north-seeking system based on MEMS rotation technique and method | |
CN103345149A (en) | Dynamically tuned gyroscope servo control loop | |
CN105371868A (en) | Error calibration and compensation method for accelerometer unit of inertially stabilized platform system | |
CN108195404A (en) | A kind of calibration method of gyroscope null offset | |
CN108681239B (en) | Decoupling servo control loop system and method for two-axis integrated gyro accelerometer | |
CN102679979A (en) | Method for monitoring working mode of aerial remote sensing triaxial inertia stabilization platform | |
CN202420505U (en) | Combined gesture measuring device of stable platform for self-correction ship | |
CN103543636B (en) | A kind of Discoupling For Dynamic Tuned Gyroscope servo control loop | |
CN102636184B (en) | Specific force-sensitive term calibration method for flexible gyroscope based on centrifuge in environment without angular movement | |
CN112577514A (en) | Calibration method of MEMS (micro-electromechanical system) inertial device | |
Jianli et al. | Fuzzy modeling and compensation of scale factor for MEMS gyroscope | |
EP3043146B1 (en) | Approach for control redistribution of coriolis vibratory gyroscope ("cvg") for performance improvement | |
Kodgirwar et al. | Design of control system for quadcopter using Complementary Filter and PID controller | |
CN105674971B (en) | Two-dimentional spacecraft angular rate measurement method based on gyroscope flywheel system | |
KR20100088304A (en) | Mobile two-wheeled inverted pendulum system having multiple sensors | |
CN111006664A (en) | Triaxial inertial platform system based on atomic spin gyroscope | |
CN102692226A (en) | Stable platform stabilizing method based on fiber-optic gyroscope | |
CN103471593B (en) | A kind of inertial navigation system measuring error modification method based on GPS information | |
CN103115618B (en) | Isolation test method for orthoronal errors and parasitic coriolis force based on vibrating type micromechanical gyroscope | |
RU2382331C1 (en) | Monaxonic power gyrostabiliser | |
CN204535722U (en) | Liquid floated gyroscope system |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C12 | Rejection of a patent application after its publication | ||
RJ01 | Rejection of invention patent application after publication |
Application publication date: 20131009 |