CN105738690B - A kind of counteraction flyback dynamic power consumption appraisal procedure of complexity maneuvering satellite - Google Patents
A kind of counteraction flyback dynamic power consumption appraisal procedure of complexity maneuvering satellite Download PDFInfo
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- CN105738690B CN105738690B CN201610081921.4A CN201610081921A CN105738690B CN 105738690 B CN105738690 B CN 105738690B CN 201610081921 A CN201610081921 A CN 201610081921A CN 105738690 B CN105738690 B CN 105738690B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R21/00—Arrangements for measuring electric power or power factor
- G01R21/06—Arrangements for measuring electric power or power factor by measuring current and voltage
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K17/00—Measuring quantity of heat
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
A kind of counteraction flyback dynamic power consumption appraisal procedure of complexity maneuvering satellite, includes the following steps：Test platform on one star is provided；Power consumption measured value is obtained using above-mentioned platform；Based on above-mentioned measured value, the exact value of power consumption calculation formula parameter is obtained；The exact value of heat consumption is obtained on the basis of power consumption, and is used as the input quantity of dynamic power consumption assessment by the torque of dynamics simulation acquisition flywheel and wheel speed.The advantage of the invention is that, the it is proposed of current control counteraction flyback power consumption, calculation of heat rate method, for using current control counteraction flyback component as the satellite of executing agency, power consumption under the in-orbit period difference operation conditions of flywheel assembly, heat consumption can be accurately estimated out, important input foundation is provided for Power Management Design, the thermal control design of whole star.
Description
Technical field
The present invention relates to space technology fields more particularly to a kind of counteraction flyback dynamic power consumption of complicated maneuvering satellite to comment
Estimate method.
Background technology
Flywheel is the inertia execution unit in satellite attitude control system.In Satellite Attitude Control System, flywheel is according to attitude control
System command provides suitable control moment, corrects the attitude misalignment of satellite or completes predetermined pose adjustment.Flywheel is generally divided into
Counteraction flyback and biasing flywheel, wherein counteraction flyback be applied in combination be the long-life, three axis of high-precision zero momentum control defend
The most widely used main execution unit of star.
The most common two kinds of control modes of counteraction flyback are current control and speed control.Current control is with fly-wheel motor
Armature supply as feedback quantity, do not consider the flywheel power department of the Chinese Academy of Sciences point；Speed control is using flywheel wheel speed as feedback quantity, backfeed loop
In contain the flywheel power department of the Chinese Academy of Sciences point.
Complicated maneuvering satellite refers to causing the attitude of satellite is in-orbit to need frequent machine since the complexity of load task increases
It is dynamic.Using reaction wheel as the complicated maneuvering satellite of main executing agency, a combination thereof takes four angle mounts or three positive one tiltedly installations more
Mode, with the increase of satellite task complexity, the power consumption of counteraction flyback, heat consumption increase with variation range caused by attitudes vibration
Greatly, peak value is higher.So during satellite global design, the power consumption of four or even the combination of greater number of counteraction flyback,
Heat consumption demand influences whole star thermal control design, Power Management Design and windsurfing Selection and Design very big.This just needs dynamic analysis anti-
The in-orbit service condition of flywheel is acted on, and combines its power consumption and heat consumption characteristic under different operating modes to counteraction flyback group
It closes in-orbit power consumption and makes accurate evaluation.
Parameter value in counteraction flyback power consumption and heat consumption theoretical calculation formula that flywheel manufacturer provides has certain franchise
A kind of range, so for specific a certain model current control counteraction flyback, it is desirable to provide the calculating of new method to flywheel
Formula carries out parameter adjustment.
Invention content
The technical problem to be solved by the invention is to provide a kind of accurate counteraction flybacks for complicated maneuvering satellite
Dynamic power consumption appraisal procedure carries out parameter adjustment for the calculation formula to flywheel.
To solve the above-mentioned problems, the present invention provides a kind of counteraction flyback dynamic power consumption assessments of complicated maneuvering satellite
Method includes the following steps：Test platform on one star is provided, the test platform includes power supply, flywheel and house keeping computer,
Power supply is responsible for power supply, and house keeping computer is communicated with power supply, sends switching on and shutting down and instructs and adopt the voltage and load current of power supply, Star Service
Computer is communicated with flywheel, is sent flywheel moment control instruction and is acquired flywheel working condition amount, and house keeping computer receiving comes from
Instruction in ground, and collected data are sent to ground；Power consumption when energization static using above-mentioned platform test；Using upper
It states platform and different torque commands is sent to house keeping computer by ground, collect the rotating speed and current of electric of flywheel, calculate not
Power consumption under same torque, rotating speed, while supply voltage and load current are acquired, obtain power consumption measured value；Made with above-mentioned measured value
Based on, obtain the exact value of power consumption calculation formula parameter；The exact value of heat consumption is obtained on the basis of power consumption, and passes through power
Learn the input quantity that emulation obtains the torque of flywheel and wheel speed is assessed as dynamic power consumption.
Optionally, the power supply includes accumulator group and power-supply controller of electric.
Optionally, the flywheel working condition parameter includes one kind or more of Speed of Reaction Wheels, current of electric, bearing temperature
Kind.
Optionally, the instruction for coming from ground shows machine hair by the front end prison for satellite of a setting on the ground
Go out.
Optionally, the dynamics simulation includes the following steps：The torque command that house keeping computer is sent out is converted to
The posture and speed of satellite motion；The posture of inertial system in satellite and angular speed are converted to the object exported under sensor this system
Reason amount；Determine appearance using sensor output, and the theory for needing to be applied on celestial body is calculated for different motor-driven task directions
Torque；In conjunction with actuator characteristics, calculated ideal torque is converted into actual flywheel moment and wheel speed.
It is an advantage of the current invention that the proposition of current control counteraction flyback power consumption, calculation of heat rate method, for using electricity
Satellite of the flow control counteraction flyback component as executing agency can accurately estimate out the in-orbit period difference operation of flywheel assembly
Power consumption, heat consumption under situation provide important input foundation for Power Management Design, the thermal control design of whole star.
Description of the drawings
It is the implementation steps schematic diagram of the specific embodiment of the invention shown in attached drawing 1.
It is the structural schematic diagram of test platform on star that the specific embodiment of the invention is provided shown in attached drawing 2.
It is the schematic diagram of calculation result of one embodiment of the invention shown in attached drawing 3A to 3D.
Specific implementation mode
Below in conjunction with the accompanying drawings to the counteraction flyback dynamic power consumption appraisal procedure of complicated maneuvering satellite provided by the invention
Specific implementation mode elaborates.
It is the implementation steps schematic diagram of present embodiment shown in attached drawing 1, including：Step S10 is provided and is tested on a star
Platform；Step S11, power consumption when energization static using above-mentioned platform test；Step S12, using above-mentioned platform by ground to
House keeping computer sends different torque commands, collects the rotating speed and current of electric of flywheel, calculates the electricity under different torques, rotating speed
Consumption, while supply voltage and load current are acquired, obtain power consumption measured value；Step S13 is obtained based on above-mentioned measured value
Obtain the exact value of power consumption calculation formula parameter；Step S14, obtains the exact value of heat consumption on the basis of power consumption, and passes through power
Learn the input quantity that emulation obtains the torque of flywheel and wheel speed is assessed as dynamic power consumption.
Step S10 provides test platform on a star.Shown in refer to the attached drawing 2, the test platform includes power supply 21, flywheel
22 and house keeping computer 23.Power supply 21 is responsible for power supply, and the power supply 21 includes accumulator group 211 and power-supply controller of electric 212.Star
Business computer 23 is communicated with power supply 21, is sent switching on and shutting down and is instructed and adopt the voltage and load current of power supply 21.House keeping computer 23
It is communicated with flywheel 22, send flywheel moment control instruction and acquires the working condition amount of flywheel 22, the flywheel working condition ginseng
Amount include Speed of Reaction Wheels, current of electric, bearing temperature it is one or more.House keeping computer 23 receives the finger for coming from ground
It enables, and sends collected data to ground.The instruction for coming from ground by a setting on the ground for satellite
Front end prison shows machine 24 and sends out.
Step S11, power consumption when energization static using above-mentioned platform test.It is described it is static refer to that flywheel is in and at the uniform velocity rotates
Stable state.
Step S12 sends different torque commands to house keeping computer by ground using above-mentioned platform, collects flywheel
Rotating speed and current of electric calculate the power consumption under different torques, rotating speed, while acquiring supply voltage and load current, obtain power consumption
Measured value.Described instruction is supervised the machine of showing 24 by front end and is sent out.
Step S13 obtains the exact value of power consumption calculation formula parameter based on above-mentioned measured value.
Power consumption calculation formula can be derived according to the actual conditions of flywheel and satellite system.Present embodiment
A kind of typical calculation formula is provided, point acceleration, stable state, three kinds of operating modes of slowing down propose flywheel power consumption, calculation of heat rate method：
(1) accelerate power consumption PB=PQ+1/ η [IM (UD+sf* ω)+IM2(RA+RON)]
Accelerate heat consumption PD=PB- (TM-TL) * ω
(2) stable state power consumption PB=PQ+1/ η [TL (UD/sf+ ω)+(TL/sf)2(RA+RON)]
Stable state heat consumption PD=PB
(3) deceleration power consumption PB=PQ
Deceleration heat consumption PD=PB+ (TM+TL) * ω
Wherein PQ be quiescent dissipation, i.e., flywheel be powered not output torque when static power consumption；η is fly-wheel motor conversion effect
Rate, sf are the motor proportional factor, and RA is armature resistance, is all that the parameter of electric machine is provided by flywheel manufacturer；IM is motor electricity
Stream, it is in a linear relationship with input instruction torque size, as working state monitoring amount；UD is flywheel control circuit diode pressure
Drop；ω is Speed of Reaction Wheels size (rad/s), and in a linear relationship, flywheel working state monitoring amount is integrated with output torque；RON is
The conducting resistance of field transistor switch in rectification brake apparatus, by flywheel, manufacturer provides；TL be moment of friction size, with turn
Speed is corresponding, passes through the moment of friction under test calibration flywheel different rotating speeds；TM is input instruction torque size.
Step S14 obtains the exact value of heat consumption on the basis of power consumption, and the torque of flywheel is obtained by dynamics simulation
The input quantity assessed as dynamic power consumption with wheel speed.Above-mentioned formula can not only calculate power consumption, can be with design heat loss.But it calculates
Heat consumption needs the wheel speed ω of flywheel, the parameter that can be obtained by dynamics simulation.Dynamics simulation can according to flywheel and
The actual conditions of satellite system are modeled.It includes following step that present embodiment, which provides a kind of typical dynamics simulation,
Suddenly：The torque command that house keeping computer is sent out is converted to the posture and speed of satellite motion；By the appearance of inertial system in satellite
State and angular speed are converted to the physical quantity exported under sensor this system；Determine appearance using sensor output, and is directed to different machines
Dynamic task direction calculates the ideal torque for needing to be applied on celestial body；In conjunction with actuator characteristics, by calculated ideal torque
Be converted to actual flywheel moment and wheel speed.Aforementioned four step can be respectively adopted dynamics module, sensor module, determine appearance
Implemented with control module and execution module.
Since input condition and primary condition are different, can obtainable reaction wheel power consumption it is different, it is therefore desirable to change more
Group parameter, obtains multigroup reaction wheel dynamic power consumption.For multigroup reaction wheel dynamic power consumption, using average power consumption as foundation, choosing
Take the maximum one group of parameter of average power consumption as complicated maneuvering satellite reaction wheel dynamic power consumption calculation basis.
One embodiment and result of calculation of the above method is given below.
1 a certain current control counteraction flyback parameter value of table
Use four angle mount flywheel assemblies as executing agency based on the above counteraction flyback, X satellites complete maneuver autopilot mistake
The torque of flywheel, rotating speed, electrical power consumed and heat power consumption variation correspond to four angle mount flywheels respectively as shown in attached drawing 3A~attached drawing 3D in journey
Four flywheels are in Torque Control instruction and rotation speed change power consumption at present and heat consumption situation of change in component.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
Member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications also should be regarded as
Protection scope of the present invention.
Claims (5)
1. a kind of counteraction flyback dynamic power consumption appraisal procedure of complexity maneuvering satellite, which is characterized in that include the following steps：
Test platform on a star is provided, the test platform includes power supply, flywheel and house keeping computer, and power supply is responsible for power supply, star
Business computer is communicated with power supply, is sent switching on and shutting down and is instructed and adopt the voltage and load current of power supply, house keeping computer leads to flywheel
News send flywheel moment control instruction and acquire flywheel working condition amount, and house keeping computer receives the instruction for coming from ground, and
Collected data are sent to ground,
Power consumption when energization static using above-mentioned platform test；It is described it is static refer to that flywheel is in the stable state at the uniform velocity rotated；
Different torque commands are sent to house keeping computer by ground using above-mentioned platform, collect the rotating speed and motor electricity of flywheel
Stream, calculates the power consumption under different torques, rotating speed, while acquiring supply voltage and load current, obtains power consumption measured value；
Based on above-mentioned measured value, the exact value of power consumption calculation formula parameter is obtained；
The exact value of heat consumption is obtained on the basis of power consumption, and is used as by the torque of dynamics simulation acquisition flywheel and wheel speed and is moved
The input quantity of state power consumption assessment.
2. dynamic power consumption appraisal procedure according to claim 1, which is characterized in that the power supply includes accumulator group and electricity
Source controller.
3. dynamic power consumption appraisal procedure according to claim 1, which is characterized in that the flywheel working condition parameter includes
Speed of Reaction Wheels, current of electric, bearing temperature it is one or more.
4. dynamic power consumption appraisal procedure according to claim 1, which is characterized in that the instruction for coming from ground is by one
The aobvious machine of front end prison for satellite being arranged on the ground is sent out.
5. dynamic power consumption appraisal procedure according to claim 1, which is characterized in that the dynamics simulation includes following step
Suddenly：
The torque command that house keeping computer is sent out is converted to the posture and speed of satellite motion；
The posture of inertial system in satellite and angular speed are converted to the physical quantity exported under sensor this system；
Determine appearance using sensor output, and the theoretical power needed to be applied on celestial body is calculated for different motor-driven task directions
Square；
In conjunction with actuator characteristics, calculated ideal torque is converted into actual flywheel moment and wheel speed.
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| KR101906011B1 (en) * | 2016-12-13 | 2018-10-10 | 현대자동차주식회사 | Method for estimating power consumption of motor in fuel cell system |
| CN109974996A (en) * | 2019-04-22 | 2019-07-05 | 湖南揽月机电科技有限公司 | A kind of counteraction flyback service life examination vacuum experiment system and working method |
| CN114279467B (en) * | 2021-12-24 | 2023-06-06 | 深圳航天科技创新研究院 | Intelligent evaluation system and method for reactive flywheel performance parameters |
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