CN105883008A - Satellite thruster layout method - Google Patents
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Abstract
The invention provides a satellite thruster layout method used for three-axis stabilization satellite thruster layout. A propellant is saved. The method comprises the steps that according to the quality characteristics and structural configuration parameters of a satellite and layout configuration parameters of a satellite thruster, initial layout parameters of the satellite thruster are determined; according to plume impact analysis results and sensor view field analysis results of the satellite thruster, the initial layout parameters of the satellite thruster are adjusted, and therefore optimal thruster layout parameters are obtained. Accordingly, thrust produced by attitude control in the orbital transferring period of a satellite transfer orbit and attitude control thrust produced by north-south position keeping and momentum wheel unloading in the in-orbit operation period can be effectively utilized for auxiliary orbit control, propellant consumption is reduced, the in-orbit operation life of the satellite is prolonged, many attitude and orbit control function backups are obtained, the requirement for the large satellite mass center change range is met, satellite antenna layout design is promoted, and thruster reduction can be carried out according to client requirements.
Description
Technical field
The invention belongs to spacecraft master-plan field, relate to Satellite Engine layout, particularly geostationary orbit three-axis stabilization
The thruster layout of satellite, is specifically related to a kind of Satellite Engine layout method, for the thruster layout of three axis stabilized satellite,
Realize the saving of propellant.
Background technology
After the transmitting of geostationary orbit three axis stabilized satellite is entered the orbit, typically need to separate through the satellite and the rocket, transfer orbit becomes rail, fixed point is caught
After obtaining, pre-orbit determination position could be entered.Period has needed position to keep in orbit, three-axis attitude controls, and possible rail position
The tasks such as adjustment, end of lifetime has also needed to satellite and has left the right or normal track task.Their entire life needs thruster to work, to provide control
Moment processed and thrust, complete the attitude of satellite and orbits controlling task.Satellite Engine layout directly determines satellite gravity anomaly power
Square, orbits controlling thrust and the performance of function backup, the quality of its layout designs directly affects Satellite Attitude Control and in-orbit
Life-span.Therefore, the work that Satellite Engine layout designs is important and crucial in being satellite master-plan.
At present, the thruster layout of domestic and international geostationary orbit three axis stabilized satellite, because of satellite configuration, thruster properties of product
And configuring condition, there is kinds of schemes.
Therefore, it is badly in need of a kind of three axis stabilized satellite thruster placement scheme, in conjunction with domestic eastern four enhanced platforms developments, can be effective
Save satellite booster agent consumption, thrust that during also can effectively utilizing satellite transfer orbit to become rail, gesture stability produces and
The gesture stability thrust that period north-south position keeps and momenttum wheel unloading produces in orbit, carries out the orbits controlling assisted, to subtract
Little propellant waste, increases the satellite life-span in orbit, and attitude and orbit control function to be possessed backup is many, adaptation
Centroid of satellite excursion is big, be beneficial to satellite antenna layout designs and can carry out subtracting the advantage joined according to customer requirement.
Summary of the invention
In order to solve problems of the prior art, the present invention proposes one and is applicable to geostationary orbit three axis stabilized satellite
Thruster placement scheme, it is possible to increase thruster established angle efficiency, and make full use of Satellite Orbit Maneuver, north-south position keep, with
And the thrust that in momenttum wheel uninstall process, gesture stability produces, for orbits controlling, thus save propellant, extend satellite
In the life-span in-orbit, geostationary orbit three axis stabilized satellite attitude and orbit control task in-orbit can be met.
The invention provides a kind of Satellite Engine layout method, for the thruster layout of three axis stabilized satellite, it is achieved propellant
Saving.The method comprises the following steps: step one, according to the mass property of satellite and node configuration parameter and satellite thrust
The layout structure parameters of device, determines the preliminary placement parameter of Satellite Engine；And step 2, according to the plume of Satellite Engine
Impact analysis result and sensor blinding analysis result, be adjusted the preliminary placement parameter of Satellite Engine, thus obtain excellent
The thruster layout parameter changed.
Step one performs: according to the mass property of satellite, it is thus achieved that the average centroid vector of satellite；And according to Satellite Engine
Mount point coordinate and direction vector, determine the installation parameter of Satellite Engine.
Specifically, the average centroid vector of satellite is the vector of the average heart of the mechanical coordinate system initial point sensing satellite of satellite, satellite
The vents face center that mount point coordinate is Satellite Engine of thruster obtains coordinate under the mechanical coordinate system of satellite, and
The direction vector of Satellite Engine is that the jet pipe of Satellite Engine is axially under the mounting coordinate system of Satellite Engine and between coordinate axes
Angle.
Preferably, the mechanical coordinate system of satellite and the mounting coordinate system of Satellite Engine are translation relation and all meet right-hand rule.
Extraly, also perform in step one: satellite-based mechanical coordinate system, configure multiple Satellite Engine and electromotor,
Thus obtain the layout structure parameters of Satellite Engine, wherein, multiple Satellite Engine be respectively used to satellite thing position protect control,
Control is protected in position, north and south, three-axis attitude controls and propellant sinks to the bottom.
In step one, the determination of the preliminary placement parameter of Satellite Engine includes: in multiple Satellite Engine, by therein
4 Satellite Engine are installed on 4 corner positions in satellite face privately, so that these 4 sink to the bottom for satellite booster agent and shift
The thrust side that during the thrust of thruster generation of gesture stability becomes rail with the transfer orbit of satellite during track change rail, electromotor produces
To unanimously；In multiple Satellite Engine, 8 Satellite Engine controlled are protected in the position, north and south being used for satellite and is arranged on satellite
Near 4 jiaos of face, north and south, so that these 8 Satellite Engine protect gesture stability and the momenttum wheel unloading of control period in position, satellite north and south
Time the thrust and the position, satellite north and south that produce protect that to control the thrust direction of generation consistent；And in multiple Satellite Engine, will be used for
The thing position of satellite is protected 8 Satellite Engine controlled and is arranged near 4 jiaos of the thing face of satellite, so that these 8 satellite thrusts
The making a concerted effort producing the biggest power in a predetermined direction of the thrust that device produces and overcoming in other directions may be little and many
The moment produced during individual Satellite Engine work in combination is the least.
In the present invention, choosing based on symmetry principle of the preliminary placement parameter of Satellite Engine, and guarantee producing control power
With reduce perturbed force and moment while moment the most as much as possible, thus meet the attitude and orbit control precision of satellite.
Step 2 performs: on the basis of the preliminary placement parameter of Satellite Engine, plume impact, the sensor on satellite
Visual field and attitude orbits controlling performance are analyzed；And based on analysis result, suitably adjust preliminary placement parameter, thus obtain
The thruster layout parameter that must optimize.
Therefore, use the placement scheme of the present invention, the thrust that during can effectively utilizing satellite transfer orbit to become rail, gesture stability produces,
And the gesture stability thrust that period north-south position keeps and momenttum wheel unloading produces in orbit, carry out the orbits controlling assisted,
To reduce propellant waste, increase the satellite life-span in orbit, make the backup of attitude and orbit control function many simultaneously, adapt to
Centroid of satellite excursion is big, beneficially satellite antenna layout designs, and can carry out subtracting joining according to customer requirement.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of thruster installation parameter under satellite machinery coordinate system；
Fig. 2 is the schematic diagram of thruster layout configuration；And
Fig. 3 is the flowchart of the thruster placement scheme of the geostationary orbit three axis stabilized satellite of the present invention.
Detailed description of the invention
It will be appreciated that Satellite Engine layout has considered each stage track and gesture stability functional requirement after satellite launch is entered the orbit,
For satellite transfer orbit gesture stability, and period north-south position keeps and momenttum wheel Unloading Control in orbit, is pushed away
Power device layout designs optimizes, it is achieved that the thrust effectively utilizing gesture stability to produce carries out the orbits controlling assisted, and decreases propelling
Agent consumption, increases the satellite life-span in orbit.
The Satellite Engine placement scheme of the present invention to implement step as follows:
1) according to satellite mass characteristic, node configuration and thruster layout configuration, Satellite Engine preliminary placement parameter is determined；With
And
2) according to Satellite Engine plume impact analysis and sensor blinding analysis result, thruster layout parameter is optimized and revised.
The present invention is described in detail for 1-3 and detailed description of the invention below in conjunction with the accompanying drawings.
Fig. 1 gives the schematic diagram of thruster installation parameter under satellite machinery coordinate system.As it is shown in figure 1, OscXscYscZscCoordinate
System is satellite machinery coordinate system, OiXiYiZiCoordinate system is thruster mounting coordinate system, is translation relation with satellite machinery coordinate system,
Translation vector is Ri。O0For the satellite average centroid position of period in orbit, satellite mass characteristic analysis obtain, average barycenter
Vector R0For mechanical coordinate system initial point OscPoint to satellite average barycenter O0Vector.Thruster installation parameter is by thruster mount point
Coordinate OiWith thruster direction vector TiDetermine.Wherein, thruster mount point coordinate OiFor in the vents face of Satellite Engine i
Heart position coordinate under satellite machinery coordinate system；Thruster direction vector TiAxially (can be similar in engineering for thruster jet pipe
Thrust opposite direction) under mounting coordinate system with angle α, β, γ of three coordinate axess.
First, satellite machinery coordinate system is defined as follows:
Coordinate origin Osc-it is positioned at satellite lower end frame and carrier rocket mechanical separation face, formed with pin in satellite interface
The center of circle of theoretical circle overlaps；
OscXscAxle-consistent with satellite east plate theory normal direction, positive direction is consistent with plate exterior normal direction, east；
OscYscAxle-consistent with satellite north plate theory normal direction, positive direction is consistent with plate exterior normal direction, south；
OscZscThe connection parting surface of axle-be perpendicular to satellite and carrier rocket, its positive direction is pointed to floor from initial point；And
OscXscYscZscCoordinate system meets right-hand rule.
It follows that thruster mounting coordinate system is defined as follows:
Coordinate origin Oi-it is positioned at the vents face center of Satellite Engine i, it is translation relation with satellite machinery coordinate system, flat
The amount of shifting to is Ri；
OiXiAxle-and satellite machinery coordinate system OscXscAxle is consistent, and direction is identical；
OiYiAxle-and satellite machinery coordinate system OscYscAxle is consistent, and direction is identical；
OiZiAxle-and satellite machinery coordinate system OscZscAxle is consistent, and direction is identical；And
Equally, OiXiYiZiCoordinate system meets right-hand rule.
Fig. 2 is the schematic diagram of thruster layout configuration.As in figure 2 it is shown, coordinate system OscXscYscZscFor satellite machinery coordinate system,
Satellite configures 20 thrusters and 1 electromotor altogether.Wherein, electromotor is arranged on satellite center, face (-Z privatelyscDirection).
As in figure 2 it is shown, give installation site and the direction of thruster 2A～11A and 2B～11B.Satellite East, West, South, North
Four face corner locations are respectively mounted 1 thruster, protect control, the guarantor's control of position, north and south and satellite three axle appearance for satellite thing position
State controls, and corner, face is respectively mounted 1 thruster and sinks to the bottom for satellite booster agent privately, and OscXscAxle and OscYscAxle appearance
State controls.
It will be appreciated that Satellite Engine installation site need to consider the design of satellite structure configuration and satellite barycenter situation of change in-orbit.
The most first according to the average centroid position of satellite at XscOscYsc plane inner projection, determine that 12 of satellite corner, face privately push away
Power device position, determines 8 thruster installation sites in 4 faces of East, West, South, North in +Z direction further according to height of center of mass.
Installation site according to each thruster determines the thruster work in combination situation in table 1 below and table 2.During thruster work
The thrust to satellite body produced is Fi, thrust vectoring direction and thruster axial vector TiIn opposite direction, the moment of generation is
(Ri-R0)×Fi.Table 1 gives each station keeping mode of satellite and sinks to the bottom thruster selection, and table 2 gives each appearance control pattern and pushes away
Power device selects.
Table 1
Table 2
It will be appreciated that for improving thruster work in combination efficiency, thruster layout designs parameter need to follow following principle when choosing.
1) for making full use of the thrust that during satellite transfer orbit becomes rail, gesture stability produces, satellite 4, face thruster privately is installed
In 4 corner positions, thruster direction vector sensing-ZscDirection.In Satellite Orbit Maneuver code, the thrust that orbit maneuver motor produces
Direction sensing+ZscDirection, the disturbance torque not produced on thrust vectoring because of barycenter is mainly at Xsc、YscOn axle, satellite controls
System utilizes 4, face thruster (10A, 11A, 10B, 11B) work privately to offset disturbance torque impact, with stabilized satellite
Attitude, now for 4 thrusters of gesture stability, the thrust direction that the thrust direction of generation produces with orbit maneuver motor is consistent,
Being beneficial to Satellite Orbit Maneuver task, 4 thrusters are additionally operable to satellite booster agent and sink to the bottom simultaneously, and can back up as orbit maneuver motor.Should
Layout not only saves satellite booster agent consumption, and improves satellite and complete to become the reliability of rail task.
2) for making full use of the thrust that satellite north-south position in-orbit keeps the gesture stability during unloading to produce with momenttum wheel, it is used for defending
During star north-south position keeps 8 the thruster layout designs controlled, the gesture stability during position, north and south is protected need to be considered
Moment and momenttum wheel unloading moment factor.
Satellite north-south position keeps thruster layout to be arranged near 4 jiaos of satellite north north, and generally satellite position to the south is protected
Holding employing 6A+7A+8A+9A cooperation, northwards position keeps using 6B+7B+8B+9B cooperation.Position, satellite north and south
During putting holding, the disturbance torque of generation is mainly at Xsc、ZscAxle, because of satellite body flexible characteristic, during actual control
Ysc axle also can produce certain disturbance torque.
When satellite north-south position keeps thruster layout parameter to choose, it is desirable to F6A+F7A+F8A+F9AAnd F6B+F7B+F8B+
F9BMake a concerted effort at YscDirection produces the biggest power, the least, requires thruster work in combination simultaneously
Time produce moment: (Ri-R0)×(F6A+F7A+F8A+F9A) and (Ri-R0)×(F6A+F7A+F8A+F9A) the most to the greatest extent may be used
Can be little.
The X produced during keeping controlling for north-south positionscAnd ZscAxle disturbance torque, can be combined by the thruster in face, north and south
Work is offset, and such as thruster 6A+8A work can offset-XscMoment on direction, its gesture stability thrust produced is protected with position
Thrust direction is consistent, improves position, north and south and protects overall efficiency.
The Y produced during keeping controlling for north-south positionscAxle disturbance torque, by optimizing north and south in the face of the installation of angle thruster
Parameter, makes to produce a suitable Y during diagonal angle thruster configuration work of coplanarscAxle control moment, in opposite direction.I.e. (Ri-R0)
×(F6A+F7A)=-(Ri-R0)×(F8A+F9A)=(Ri-R0)×(F6B+F7B)=-(Ri-R0)×(F8B+F9B), should
Control moment size is determined by satellite body flexible characteristic, and this control moment can be used for offsetting satellite north-south position and keeps control process
The Y of middle generationscAxle disturbance torque, and the thruster direction that gesture stability produces is consistent with guarantor direction, position.
Therefore, during position, north and south is protected, the thrust that three-axis attitude controls to produce is all consistent with position guarantor's thrust direction, effectively utilizes south
Gesture stability thrust during the guarantor of position, north.This layout is also with north and south in the face of angle thruster is at the ascending, descending intersection point of satellite orbit
Carry out momenttum wheel YscNorth-south position holding is carried out, to make full use of the attitude control during momentum discharge while the unloading of axle moment
Controlling push-force, effectively to save satellite on-board propulsion agent use.
3) the thruster layout that satellite thing position keeps is near the corner location in thing face, when its layout designs parameter is chosen,
Require F2A+F3A, F4B+F5B, F2B+F3B, F4A+F5AMake a concerted effort at XscDirection produces the biggest power, at other
On direction the least, the moment that produces when simultaneously requiring thruster work in combination: (Ri-R0)×(F2A+F3A)、(Ri-R0)
×(F4B+F5B)、(Ri-R0)×(F2B+F3B) and (Ri-R0)×(F4A+F5A) the least.
4) for producing perturbed force and disturbance torque during reducing thruster work in combination, thruster layout parameter is chosen process and is followed
Symmetry principle, i.e. ensures during thruster work in combination, while producing control power and moment, reduce as far as possible perturbed force and
Moment, to meet the attitude of satellite and orbit control accuracy requirement.
Can get Satellite Engine preliminary placement parameter based on above principle, carry out satellite plume impact analysis and appearance on this basis
State orbits controlling performance evaluation, and preliminary placement parameter is suitably adjusted according to analysis result, finally give the thruster layout of optimization
Result.
As a example by certain earth Synchronous-Orbiting Communication Satellite, satellite body is the cuboid of 2360mm × 2100mm × 4200mm,
Consider that satellite structure configuration, thruster layout configuration, satellite average center-of-mass coordinate in-orbit is (0,0,1975), and satellite sun
The wing, antenna structure configuration and thruster plume impact, the thruster layout parameter finally drawn is as shown in table 3 below, and satellite is every
Guarantor's pattern and sink to the bottom thruster select and power as shown in table 4 below with moment, each appearance control pattern thruster selection and power as follows with moment
Shown in table 5.
Table 3
Table 4
Table 5
Therefore, this placement scheme north-south position keeps thruster established angle efficiency to be 0.966, and thing position keeps thruster established angle
Degree efficiency is 0.958, is above active service geostationary orbit public satellite platform thruster efficiency, and can effectively utilize satellite to become
During rail and in orbit period north-south position keeps and attitude control thruster in momenttum wheel uninstall process, is effectively reduced satellite
On-board propulsion agent consumption about 30kg, increases about half a year in satellite life-span in orbit.
Visible, technical scheme has considered each stage track and gesture stability functional requirement after satellite launch is entered the orbit,
Emphasis is for satellite transfer orbit gesture stability, and period north-south position keeps and momenttum wheel Unloading Control in orbit, carries out
Thruster layout designs optimizes, and finally achieves the orbits controlling that the thrust effectively utilizing gesture stability to produce carries out assisting, subtracts
Lack propellant waste, increase the satellite life-span in orbit.Such as, domestic eastern four Platform Satellite, 5.5 tons of take-off weights, adopt
Launching with CZ-3B delivery, use this patent thruster layout, transfer orbit can reduce about 15kg, 15 year life-span of geo-stationary orbit
Propellant about 15kg can be reduced, propellant about 30kg can be saved altogether, about half a year in satellite life-span in-orbit can be extended.
Undeclared in the present invention partly belong to techniques known.
Claims (8)
1. a Satellite Engine layout method, for the thruster layout of three axis stabilized satellite, to realize the saving of propellant,
It is characterized in that, comprise the following steps:
Step one, according to mass property and the layout structure parameters of node configuration parameter and described Satellite Engine of satellite,
Determine the preliminary placement parameter of described Satellite Engine；And
Step 2, according to plume impact analysis result and the sensor blinding analysis result of described Satellite Engine, defends described
The preliminary placement parameter of star thruster is adjusted, thus obtains the thruster layout parameter of optimization.
Satellite Engine layout method the most according to claim 1, it is characterised in that perform in described step one:
Mass property according to described satellite, it is thus achieved that the average centroid vector of satellite；And
Mount point coordinate according to described Satellite Engine and direction vector, determine the installation parameter of described Satellite Engine.
Satellite Engine layout method the most according to claim 2, it is characterised in that
The average centroid vector of described satellite is the arrow of the average heart of the mechanical coordinate system initial point described satellite of sensing of described satellite
Amount,
The vents face center that mount point coordinate is described Satellite Engine of described Satellite Engine is at described satellite
Coordinate is obtained under mechanical coordinate system, and
The direction vector of described Satellite Engine is that the jet pipe of described Satellite Engine is axially in the installation of described Satellite Engine
Angle under coordinate system and between coordinate axes.
Satellite Engine layout method the most according to claim 2, it is characterised in that
The mechanical coordinate system of described satellite and the mounting coordinate system of described Satellite Engine are translation relation and all meet the right hand
Rule.
Satellite Engine layout method the most according to claim 2, it is characterised in that also perform in described step one:
Mechanical coordinate system based on described satellite, configures the plurality of Satellite Engine and electromotor, thus defends described in obtaining
The layout structure parameters of star thruster,
Wherein, the plurality of Satellite Engine is respectively used to thing position guarantor's control of described satellite, control, three axles are protected in position, north and south
Gesture stability and propellant sink to the bottom.
Satellite Engine layout method the most according to claim 5, it is characterised in that in described step one, described
The determination of the preliminary placement parameter of Satellite Engine includes:
In the plurality of Satellite Engine, 4 Satellite Engine therein are installed on 4 drift angle positions in satellite face privately
Put, so that these 4 sink to the bottom for described satellite booster agent and to become what the thruster of gesture stability during rail produced with transfer orbit
The thrust direction that thrust produces with electromotor during the transfer orbit of described satellite change rail is consistent；
In the plurality of Satellite Engine, 8 Satellite Engine controlled are protected in the position, north and south being used for described satellite and is arranged on
Near 4 jiaos of the face, north and south of described satellite, so that these 8 Satellite Engine protect control period in the position, north and south of described satellite
It is consistent that the thrust produced when gesture stability unloads with momenttum wheel protects, with the position, north and south of described satellite, the thrust direction controlling to produce；
And
In the plurality of Satellite Engine, 8 Satellite Engine controlled are protected in the thing position being used for described satellite and is arranged on
Near 4 jiaos of the thing face of described satellite so that the thrust that produces of these 8 Satellite Engine make a concerted effort produce in a predetermined direction
The biggest raw power and overcoming in other directions may be little, and produce during the plurality of Satellite Engine work in combination
Raw moment is the least.
Satellite Engine layout method the most according to claim 6, it is characterised in that described Satellite Engine preliminary
Choosing based on symmetry principle of layout parameter, and guarantee to reduce perturbed force the most as much as possible while producing control power and moment
And moment, thus meet the attitude and orbit control precision of described satellite.
Satellite Engine layout method the most according to claim 6, it is characterised in that perform in described step 2:
On the basis of the preliminary placement parameter of described Satellite Engine, on the plume impact of described satellite, sensor visual field,
It is analyzed with attitude orbits controlling performance；And
Based on analysis result, suitably adjust described preliminary placement parameter, thus obtain the thruster layout parameter of optimization.
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