CN102303708A - Device and method for controlling satellite attitudes through liquid circuit valve - Google Patents
Device and method for controlling satellite attitudes through liquid circuit valve Download PDFInfo
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- CN102303708A CN102303708A CN201110152482A CN201110152482A CN102303708A CN 102303708 A CN102303708 A CN 102303708A CN 201110152482 A CN201110152482 A CN 201110152482A CN 201110152482 A CN201110152482 A CN 201110152482A CN 102303708 A CN102303708 A CN 102303708A
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Abstract
The invention relates to a device and method for controlling satellite attitudes through a liquid circuit valve, relating to the device and method for controlling satellite attitudes, and solving the problem of bad effect of control of satellite attitudes caused by serious bearing abrasion and poor heat radiation and lubrication in the traditional device adopting flywheel-type momentum interchange to control the satellite attitudes. In the device provided by the invention, a group of satellite attitude control units are respectively installed in the directions of three axles of a satellite body. The method provided by the invention comprises a step of controlling the quantity of flow entering a forward circuit and a backward circuit through a circuit control valve or a forward/reverse control valve so as to realize the control of the satellite attitudes. The device and method provided by the invention are suitable for the control of the satellite attitudes.
Description
Technical field
The present invention relates to a kind of apparatus and method of controlling satellite attitude.
Background technology
At present, be used for satellite initiatively the actuating unit of attitude control can be divided into quality according to principle of work and discharge formula, momentum exchange formula and environment field formula etc.Wherein, The momentum exchange formula is to utilize momentum generating means and the moment of momentum between the satellite body of inside satellite to exchange to realize attitude control; Has no working medium consumption, pollution-free and the satellite center of mass motion do not produced advantages such as interference; With the flywheel is that the momentum exchange formula attitude control actuator that the typical case represents is used widely on microsatellite, but rotation of flywheel high speed and work life require very high to gyroscope support.Ball bearing of main shaft is modal a kind of support pattern, but owing to there is friction between ball and the bearing frame, particularly can't carry out good heat radiation and lubricated under the vacuum environment, makes that the work life of ball bearing of main shaft and even whole star is very influenced.
Summary of the invention
The present invention in the device that solves existing flywheel-type momentum exchange control satellite attitude because the problem of the weak effect that wear-out of a bearing is serious, heat radiation and poor lubrication cause controlling satellite attitude, thereby a kind of apparatus and method of fluid loop valve control satellite attitude are provided.
The device of fluid loop valve control satellite attitude; It comprises three groups of satellite attitude control unit; The axis of three groups of satellite attitude control unit respectively with three-dimensional cartesian coordinate system OXYZ in OX axle, OY axle parallel with the OZ axle, the initial point of said three-dimensional cartesian coordinate system OXYZ is the barycenter of satellite body; The structure of three groups of satellite attitude control unit is identical, and every group of satellite attitude control unit includes forward loop, return circuit, loop control valve, motor and fluid pump; Forward loop and return circuit are along the axis symmetric arrangement of its satellite attitude control unit, place; The output shaft of motor is connected with the input shaft of fluid pump, and said motor is used to drive fluid pump work; Fluid pump is arranged on the common inlet place of forward loop and return circuit, and the worker quality liquid stream that is used to drive in forward loop, the return circuit flows;
The liquid outlet that the inlet of the forward loop in every group of satellite attitude control unit and the inlet of return circuit pass through the reservoir on loop control valve and the satellite body simultaneously is communicated with; Said loop control valve is arranged on this liquid outlet place, is used to control the flow of the liquid working substance stream that gets into forward loop or return circuit; An inlet of the reservoir on the liquid outlet of the forward loop in every group of satellite attitude control unit and the liquid outlet while of return circuit and the satellite body is communicated with.
Based on the method for the fluid loop valve of said apparatus control satellite attitude, its method is:
Adopt the motor-driven fluid pump, make reservoir and every group of satellite attitude control unit on the satellite body form the worker quality liquid circuit;
The loop control valve control that employing is arranged in the satellite attitude control unit on the OX axle flows into the flow of the worker quality liquid stream of forward loop or return circuit, produces along the axial control torque of OX, realizes that satellite attitude is in the axial control of OX;
The loop control valve control that employing is arranged in the satellite attitude control unit on the OY axle flows into the flow of the worker quality liquid stream of forward loop or return circuit, produces along the axial control torque of OY, realizes that satellite attitude is in the axial control of OY;
The loop control valve control that employing is arranged in the satellite attitude control unit on the OZ axle flows into the flow of the worker quality liquid stream of forward loop or return circuit, produces along the axial control torque of OZ, realizes that satellite attitude is in the axial control of OZ;
Thereby realize three axle controls of satellite attitude.
The material of liquid working substance stream for having flowing power.
The device of fluid loop valve control satellite attitude; It comprises three groups of satellite attitude control unit; The axis of three groups of satellite attitude control unit respectively with three-dimensional cartesian coordinate system OXYZ in OX axle, OY axle parallel with the OZ axle, the initial point of said three-dimensional cartesian coordinate system OXYZ is the barycenter of satellite body; The structure of three groups of satellite attitude control unit is identical, and every group of satellite attitude control unit includes forward loop, return circuit, forward loop control cock, return circuit control cock, motor and fluid pump; Forward loop and return circuit are along the axis symmetric arrangement of its satellite attitude control unit, place; The forward control cock is arranged on the inlet place of forward loop, is used to control the flow of the liquid working substance stream that gets into forward loop; Cutback control valve is arranged on the inlet place of return circuit, is used to control the flow of the liquid working substance stream that gets into the return circuit; The output shaft of motor is connected with the input shaft of fluid pump, and said motor is used to drive fluid pump work; Fluid pump is arranged on the common inlet place of forward loop and return circuit, and the worker quality liquid stream that is used to drive in forward loop and the return circuit flows;
The inlet of the forward loop in every group of satellite attitude control unit and the inlet of return circuit respectively with satellite body on a liquid outlet of reservoir be communicated with; The liquid outlet of the forward loop in every group of satellite attitude control unit and the liquid outlet of return circuit respectively with satellite body on an inlet of reservoir be communicated with.
Based on the method for the fluid loop valve of said apparatus control satellite attitude, its method is:
Adopt the motor-driven fluid pump, make reservoir and every group of satellite attitude control unit on the satellite body form the worker quality liquid circuit;
Employing is arranged in the forward loop control cock and the perhaps combined action separately of return circuit control cock of the satellite attitude control unit on the OX axle; Control flows into the flow of the worker quality liquid stream in forward loop and the return circuit; Generation realizes that along the axial control torque of OX satellite attitude is in the axial control of OX;
Employing is arranged in the forward loop control cock and the perhaps combined action separately of return circuit control cock of the satellite attitude control unit on the OY axle; Control flows into the flow of the worker quality liquid stream in forward loop and the return circuit; Generation realizes that along the axial control torque of OY satellite attitude is in the axial control of OY;
Employing is arranged in the forward loop control cock and the perhaps combined action separately of return circuit control cock of the satellite attitude control unit on the OZ axle; The flow that control flows in the forward loop and the worker quality liquid in the return circuit flows; Generation realizes that along the axial control torque of OZ satellite attitude is in the axial control of OZ;
Thereby realize three axle controls of satellite attitude.
Beneficial effect: the pipeline of fluid loop valve control system of the present invention is installed along satellite is peripheral; Has bigger radius of rotation; The present invention utilizes the characteristics of the alerting ability of fluid own can rely on very little valve voltage to realize the distribution of forward and reverse loop fluid flow, all has advantage aspect power consumption, weight and volume efficient and the alerting ability.And because liquid working substance itself just has lubricated and thermolysis to turning unit (pump), can reduce wearing and tearing, and not influenced by irradiation space, satellite attitude control is effective.
Description of drawings
Fig. 1 is the structural representation of the specific embodiment of the invention one; Fig. 2 is the principle schematic of the inventive method; Fig. 3 is the structural representation of the specific embodiment of the invention six.
The specific embodiment
The specific embodiment one, combination Fig. 1 illustrate this specific embodiment; The device of fluid loop valve control satellite attitude; It comprises three groups of satellite attitude control unit; The axis of three groups of satellite attitude control unit respectively with three-dimensional cartesian coordinate system OXYZ in OX axle, OY axle parallel with the OZ axle, the initial point of said three-dimensional cartesian coordinate system OXYZ is the barycenter of satellite body; The structure of three groups of satellite attitude control unit is identical, and every group of satellite attitude control unit includes forward loop 1, return circuit 2, loop control valve 3, motor 5 and fluid pump 6; Forward loop 1 and the axis symmetric arrangement of return circuit 2 along its satellite attitude control unit, place; The output shaft of motor 5 is connected with the input shaft of fluid pump 6, and said motor 5 is used to drive fluid pump 6 work; Fluid pump 6 is arranged on the common inlet place of forward loop 1 and return circuit 2, and the worker quality liquid stream that is used to drive in forward loop 1, the return circuit 2 flows;
The liquid outlet that the inlet of the forward loop 1 in every group of satellite attitude control unit and the inlet of return circuit 2 pass through the reservoir on loop control valve 3 and the satellite body simultaneously is communicated with; Said loop control valve 3 is arranged on this liquid outlet place, is used to control the flow of the liquid working substance stream that gets into forward loop 1 or return circuit 2; An inlet of the reservoir on the liquid outlet of the forward loop 1 in every group of satellite attitude control unit and the liquid outlet while of return circuit 2 and the satellite body is communicated with.
Principle of work: drive total liquid working substance and flow in forward loop 1, the return circuit 2 and circulate; The moment of momentum of the axial line along the loop will be produced; Regulate the inlet aperture in forward and reverse loop through the motion of control loop control cock 3; Thereby the flow that gets into two loops is changed; Produce control corresponding moment, realize the attitude control of satellite.
Below through the emulation that produces moment principle of work of the present invention is described:
(1) calculate the correlated expression formula:
The moment of momentum of fluid loop can be expressed as:
H
L＝J
1Ω
1-J
2Ω
2
＝(V
1-V
2)J/r
＝[ηV-(1-η)V]J/r
＝(2η-1)VJ/r
＝(2x
V/D-1)VJ/r
J wherein
1, J
2Be respectively the liquid rotor inertia in forward and reverse loop, make J usually
1=J
2=J; Ω
1, Ω
2Be respectively the rotational angular velocity of liquid working substance wraparound road, forward and reverse loop axis; V
1, V
2Be respectively forward and reverse loop flow rate of liquid; R is the radius of turn in loop; η is a valve opening; V is the nominal flow rate of liquid working substance; x
VFor positive loop spool displacement, x is arranged
V=D η, and forward and reverse loop spool displacement sum is valve port length D.
Thereby can obtain the control torque that can produce
Because it is constant movement, the nominal flow velocity V as well as other structural parameters are constant, visible control torque T is the rate of change of the variable spool displacement
function.
(2) confirm correlation parameter
Liquid working substance is with reference to the density of water under the normal temperature and pressure, i.e. ρ=1000kg/m
3Get D=0.05m, r=0.5m, V=1m/s, moment of momentum is during the valve wide open of then positive loop:
H
L≈3.1N·m·s
Without loss of generality, take the spool displacement rate of change
you can get control of torque
T≈-1.2N
Can the compare moment value of wheel control, simultaneously since the valve core movement energy consumption low, be convenient to fine setting, be suitable for the High Accuracy Control of satellite attitude.
(3) valve transfer function
According to the physical model of force feedback two-stage electrohydraulic servo valve, be that input is with the valve core of servo valve displacement x with the current i
VFor output ground closed loop transfer function, can be expressed as
K in the formula
tBe the torque motor moment coefficient; K
fBe feedback rod rigidity; R for the burner bore axial line to armature component centre of gration distance; B arrives burner bore axial line distance for the feedback rod center of pellet; K
VfValue characterizes servovalve frequency range size; ω
MfAnd ξ
MfBe respectively the characteristic frequency and the damping coefficient of system.
Through rationally choosing servovalve and each physical parameter, motion change that can automatically controlled realization spool displacement, and then obtain actual control torque by rate of change.For electrohydraulic servo valve, the spool displacement rate of change can access bigger control torque much larger than the example value usually.
The difference of the device of the specific embodiment two, this specific embodiment and the specific embodiment one described fluid loop valve control satellite attitude is that fluid pump 6 is a mechanical pump.
The difference of the device of the specific embodiment three, this specific embodiment and the specific embodiment one described fluid loop valve control satellite attitude is; It also comprises the radiation fin, and said radiation fin is fixed on the lateral surface of every group of forward loop 1 in the satellite attitude control unit and the lateral surface of return circuit 2.
Radiation fin in this embodiment, waste heat radiation is in space environment in the star that is used for the process of circulating is absorbed.
The specific embodiment four, based on the method for the fluid loop valve of the specific embodiment one control satellite attitude, its method is:
Adopt motor 5 driven fluid pump 6, make reservoir and every group of satellite attitude control unit on the satellite body form the worker quality liquid circuit;
Thereby realize three axle controls of satellite attitude.
The difference of the method for the specific embodiment five, this specific embodiment and the specific embodiment four described fluid loop valve control satellite attitude is the material of liquid working substance stream for having flowing power.
The specific embodiment six, combination Fig. 3 illustrate this specific embodiment; It comprises three groups of satellite attitude control unit; The axis of three groups of satellite attitude control unit respectively with three-dimensional cartesian coordinate system OXYZ in OX axle, OY axle parallel with the OZ axle, the initial point of said three-dimensional cartesian coordinate system OXYZ is the barycenter of satellite body; The structure of three groups of satellite attitude control unit is identical, and every group of satellite attitude control unit includes forward loop 1, return circuit 2, forward loop control cock 31, return circuit control cock 32, motor 5 and fluid pump 6; Forward loop 1 and the axis symmetric arrangement of return circuit 2 along its satellite attitude control unit, place; Forward control cock 31 is arranged on the inlet place of forward loop 1, is used to control the flow of the liquid working substance stream that gets into forward loop 1; Cutback control valve 32 is arranged on the inlet place of return circuit 2, is used to control the flow of the liquid working substance stream that gets into return circuit 2; The output shaft of motor 5 is connected with the input shaft of fluid pump 6, and said motor 5 is used to drive fluid pump 6 work; Fluid pump 6 is arranged on the common inlet place of forward loop 1 and return circuit 2, and it is mobile with the worker quality liquid stream in the return circuit 2 to be used to drive forward loop 1;
The inlet of the forward loop 1 in every group of satellite attitude control unit and the inlet of return circuit 2 respectively with satellite body on a liquid outlet of reservoir be communicated with; The liquid outlet of the forward loop 1 in every group of satellite attitude control unit and the liquid outlet of return circuit 2 respectively with satellite body on an inlet of reservoir be communicated with.
Principle of work: drive total liquid working substance flow to forward loop 1, return circuit 2, in circulate; The moment of momentum of the axial line along the loop will be produced; The inlet aperture of regulating forward and reverse loop through the motion of control forward control cock 31 and forward control cock 32; Thereby the flow that gets into two loops is changed; Produce control corresponding moment, realize the attitude control of satellite.
In this embodiment, in the satellite body a plurality of reservoirs can be set, make it corresponding one by one with each forward and reverse loop.In this embodiment, the exit of the reservoir in can also satellite body is provided with safety valve 7.
The difference of the device of the specific embodiment seven, this specific embodiment and the specific embodiment six described fluid loop valve control satellite attitude is that fluid pump 6 is a mechanical pump.
The difference of the device of the specific embodiment eight, this specific embodiment and the specific embodiment six described fluid loop valve control satellite attitude is; It also comprises a plurality of radiation fins, and the lateral surface of the forward loop 1 in every group of satellite attitude control unit and the lateral surface of return circuit 2 all are fixed with said radiation fin.
Radiation fin in this embodiment, waste heat radiation is in space environment in the star that is used for the process of circulating is absorbed.
The specific embodiment nine, based on the method for the fluid loop valve of the specific embodiment six control satellite attitude, its method is:
Adopt motor 5 driven fluid pump 6, make reservoir and every group of satellite attitude control unit on the satellite body form the worker quality liquid circuit;
Employing is arranged in the forward loop control cock 31 and return circuit control cock 32 perhaps combined action separately of the satellite attitude control unit on the OX axle; Control flows into the flow of the worker quality liquid stream in forward loop 1 and the return circuit 2; Generation realizes that along the axial control torque of OX satellite attitude is in the axial control of OX;
Employing is arranged in the forward loop control cock 31 and return circuit control cock 32 perhaps combined action separately of the satellite attitude control unit on the OY axle; Control flows into the flow of the worker quality liquid stream in forward loop 1 and the return circuit 2; Generation realizes that along the axial control torque of OY satellite attitude is in the axial control of OY;
Employing is arranged in the forward loop control cock 31 and return circuit control cock 32 perhaps combined action separately of the satellite attitude control unit on the OZ axle; The flow that control flows in the forward loop 1 and the worker quality liquid in the return circuit 2 flows; Generation realizes that along the axial control torque of OZ satellite attitude is in the axial control of OZ;
Thereby realize three axle controls of satellite attitude.
The difference of the method for the specific embodiment ten, this specific embodiment and the specific embodiment nine described fluid loop valve control satellite attitude is the material of liquid working substance stream for having flowing power.
The difference of the method for the specific embodiment 11, this specific embodiment and the specific embodiment nine described fluid loop valve control satellite attitude is that a loop control valve 31 and No. two loop control valves 32 are the high precision electrohydraulic servo valve.
Claims (10)
1. the fluid loop valve is controlled the device of satellite attitude; It is characterized in that: it comprises three groups of satellite attitude control unit; The axis of three groups of satellite attitude control unit respectively with three-dimensional cartesian coordinate system OXYZ in OX axle, OY axle parallel with the OZ axle, the initial point of said three-dimensional cartesian coordinate system OXYZ is the barycenter of satellite body; The structure of three groups of satellite attitude control unit is identical, and every group of satellite attitude control unit includes forward loop (1), return circuit (2), loop control valve (3), motor (5) and fluid pump (6); Forward loop (1) and return circuit (2) are along the axis symmetric arrangement of its satellite attitude control unit, place; The output shaft of motor (5) is connected with the input shaft of fluid pump (6), and said motor (5) is used to drive fluid pump (6) work; Fluid pump (6) is arranged on the common inlet place of forward loop (1) and return circuit (2), and the worker quality liquid stream that is used to drive in forward loop (1), return circuit (2) flows;
The liquid outlet that the inlet of the forward loop (1) in every group of satellite attitude control unit and the inlet of return circuit (2) pass through the reservoir on loop control valve (3) and the satellite body simultaneously is communicated with; Said loop control valve (3) is arranged on this liquid outlet place, is used for the flow that control gets into the liquid working substance stream of forward loop (1) or return circuit (2); An inlet of the reservoir on the liquid outlet of the forward loop (1) in every group of satellite attitude control unit and the liquid outlet while of return circuit (2) and the satellite body is communicated with.
2. the device of fluid loop valve control satellite attitude according to claim 1 is characterized in that fluid pump (6) is a mechanical pump.
3. the device of fluid loop valve control satellite attitude according to claim 1; It is characterized in that; It also comprises a plurality of radiation fins, and the lateral surface of the forward loop (1) in every group of satellite attitude control unit and the lateral surface of return circuit (2) all are fixed with said radiation fin.
4. control the method for satellite attitude based on the fluid loop valve of claim 1, it is characterized in that: its method is:
Adopt motor (5) driven fluid pump (6), make reservoir and every group of satellite attitude control unit on the satellite body form the worker quality liquid circuit;
Loop control valve (3) control that employing is arranged in the satellite attitude control unit on the OX axle flows into the flow of the worker quality liquid stream of forward loop (1) or return circuit (2), produces along the axial control torque of OX, realizes that satellite attitude is in the axial control of OX;
Loop control valve (3) control that employing is arranged in the satellite attitude control unit on the OY axle flows into the flow of the worker quality liquid stream of forward loop (1) or return circuit (2), produces along the axial control torque of OY, realizes that satellite attitude is in the axial control of OY;
Loop control valve (3) control that employing is arranged in the satellite attitude control unit on the OZ axle flows into the flow of the worker quality liquid stream of forward loop (1) or return circuit (2), produces along the axial control torque of OZ, realizes that satellite attitude is in the axial control of OZ;
Thereby realize three axle controls of satellite attitude.
5. the method for fluid loop valve control satellite attitude according to claim 4 is characterized in that the material of liquid working substance stream for having flowing power.
6. the fluid loop valve is controlled the device of satellite attitude; It is characterized in that: it comprises three groups of satellite attitude control unit; The axis of three groups of satellite attitude control unit respectively with three-dimensional cartesian coordinate system OXYZ in OX axle, OY axle parallel with the OZ axle, the initial point of said three-dimensional cartesian coordinate system OXYZ is the barycenter of satellite body; The structure of three groups of satellite attitude control unit is identical, and every group of satellite attitude control unit includes forward loop (1), return circuit (2), forward loop control cock (31), return circuit control cock (32), motor (5) and fluid pump (6); Forward loop (1) and return circuit (2) are along the axis symmetric arrangement of its satellite attitude control unit, place; Forward control cock (31) is arranged on the inlet place of forward loop (1), is used for the flow that control gets into the liquid working substance stream of forward loop (1); Cutback control valve (32) is arranged on the inlet place of return circuit (2), is used for the flow that control gets into the liquid working substance stream of return circuit (2); The output shaft of motor (5) is connected with the input shaft of fluid pump (6), and said motor (5) is used to drive fluid pump (6) work; Fluid pump (6) is arranged on the common inlet place of forward loop (1) and return circuit (2), and the worker quality liquid stream that is used to drive in forward loop (1) and return circuit (2) flows;
The inlet of the forward loop (1) in every group of satellite attitude control unit and the inlet of return circuit (2) respectively with satellite body on a liquid outlet of reservoir be communicated with; The liquid outlet of the forward loop (1) in every group of satellite attitude control unit and the liquid outlet of return circuit (2) respectively with satellite body on an inlet of reservoir be communicated with.
7. the device of fluid loop valve control satellite attitude according to claim 6 is characterized in that fluid pump (6) is a mechanical pump.
8. the device of fluid loop valve control satellite attitude according to claim 6; It is characterized in that; It also comprises the radiation fin, and said radiation fin is fixed on the lateral surface of every group of forward loop (1) in the satellite attitude control unit and the lateral surface of return circuit (2).
9. control the method for satellite attitude based on the fluid loop valve of claim 6, it is characterized in that: its method is:
Adopt motor (5) driven fluid pump (6), make reservoir and every group of satellite attitude control unit on the satellite body form the worker quality liquid circuit;
Employing is arranged in the forward loop control cock (31) and return circuit control cock (32) the perhaps combined action separately of the satellite attitude control unit on the OX axle; Control flows into the flow of the worker quality liquid stream in forward loop (1) and return circuit (2); Generation realizes that along the axial control torque of OX satellite attitude is in the axial control of OX;
Employing is arranged in the forward loop control cock (31) and return circuit control cock (32) the perhaps combined action separately of the satellite attitude control unit on the OY axle; Control flows into the flow of the worker quality liquid stream in forward loop (1) and return circuit (2); Generation realizes that along the axial control torque of OY satellite attitude is in the axial control of OY;
Employing is arranged in the forward loop control cock (31) and return circuit control cock (32) the perhaps combined action separately of the satellite attitude control unit on the OZ axle; The flow that control flows in the forward loop (1) and the worker quality liquid in return circuit (2) flows; Generation realizes that along the axial control torque of OZ satellite attitude is in the axial control of OZ;
Thereby realize three axle controls of satellite attitude.
10. the method for fluid loop valve control satellite attitude according to claim 9 is characterized in that the material of liquid working substance stream for having flowing power.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101524829A CN102303708B (en) | 2011-06-08 | 2011-06-08 | Device and method for controlling satellite attitudes through liquid circuit valve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101524829A CN102303708B (en) | 2011-06-08 | 2011-06-08 | Device and method for controlling satellite attitudes through liquid circuit valve |
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| Publication Number | Publication Date |
|---|---|
| CN102303708A true CN102303708A (en) | 2012-01-04 |
| CN102303708B CN102303708B (en) | 2013-11-13 |
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ID=45377658
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|---|---|---|---|
| CN2011101524829A Expired - Fee Related CN102303708B (en) | 2011-06-08 | 2011-06-08 | Device and method for controlling satellite attitudes through liquid circuit valve |
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| Country | Link |
|---|---|
| CN (1) | CN102303708B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109515757A (en) * | 2018-10-18 | 2019-03-26 | 贵州航天林泉电机有限公司 | A kind of jet aircraft attitude-control device |
| CN110173375A (en) * | 2019-04-26 | 2019-08-27 | 陕西蓝箭航天技术有限公司 | A kind of liquid-propellant rocket engine thrust regulating system and carrier rocket |
| WO2021179022A3 (en) * | 2020-03-06 | 2021-10-14 | Newspace Systems (Pty) Ltd | A unit for causing angular momentum about an axis |
| CN113761664A (en) * | 2021-09-15 | 2021-12-07 | 长光卫星技术有限公司 | Flywheel rotating speed optimization method during remote sensing satellite imaging period |
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|---|---|---|---|---|
| GB2051246A (en) * | 1979-04-25 | 1981-01-14 | British Aerospace | Propellant Feed System |
| JPS6380051U (en) * | 1986-11-12 | 1988-05-26 | ||
| US5880356A (en) * | 1995-02-20 | 1999-03-09 | Centre National D'etudes Spatiales | Device for pressurizing a unified two-liquid propulsion subsystem geostationary satellites |
| US6285927B1 (en) * | 1999-05-26 | 2001-09-04 | Hughes Electronics Corporation | Spacecraft attitude determination system and method |
| EP1616790A1 (en) * | 2004-07-13 | 2006-01-18 | Korea Advanced Institute of Science and Technology | Method for attitude control of satellites in elliptic orbits using solar radiation pressure |
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2011
- 2011-06-08 CN CN2011101524829A patent/CN102303708B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2051246A (en) * | 1979-04-25 | 1981-01-14 | British Aerospace | Propellant Feed System |
| JPS6380051U (en) * | 1986-11-12 | 1988-05-26 | ||
| US5880356A (en) * | 1995-02-20 | 1999-03-09 | Centre National D'etudes Spatiales | Device for pressurizing a unified two-liquid propulsion subsystem geostationary satellites |
| US6285927B1 (en) * | 1999-05-26 | 2001-09-04 | Hughes Electronics Corporation | Spacecraft attitude determination system and method |
| EP1616790A1 (en) * | 2004-07-13 | 2006-01-18 | Korea Advanced Institute of Science and Technology | Method for attitude control of satellites in elliptic orbits using solar radiation pressure |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109515757A (en) * | 2018-10-18 | 2019-03-26 | 贵州航天林泉电机有限公司 | A kind of jet aircraft attitude-control device |
| CN110173375A (en) * | 2019-04-26 | 2019-08-27 | 陕西蓝箭航天技术有限公司 | A kind of liquid-propellant rocket engine thrust regulating system and carrier rocket |
| WO2021179022A3 (en) * | 2020-03-06 | 2021-10-14 | Newspace Systems (Pty) Ltd | A unit for causing angular momentum about an axis |
| EP4114740A4 (en) * | 2020-03-06 | 2024-02-28 | Newspace Systems (Pty) Ltd | A unit for causing angular momentum about an axis |
| CN113761664A (en) * | 2021-09-15 | 2021-12-07 | 长光卫星技术有限公司 | Flywheel rotating speed optimization method during remote sensing satellite imaging period |
| CN113761664B (en) * | 2021-09-15 | 2024-01-30 | 长光卫星技术股份有限公司 | Flywheel rotation speed optimization method during remote sensing satellite imaging |
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| Publication number | Publication date |
|---|---|
| CN102303708B (en) | 2013-11-13 |
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