CN111060773A - Spacecraft docking potential control test method - Google Patents
Spacecraft docking potential control test method Download PDFInfo
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- CN111060773A CN111060773A CN201911420401.1A CN201911420401A CN111060773A CN 111060773 A CN111060773 A CN 111060773A CN 201911420401 A CN201911420401 A CN 201911420401A CN 111060773 A CN111060773 A CN 111060773A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
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Abstract
The invention relates to a spacecraft docking potential control test method, which comprises the following steps: a. constructing a potential control test system; b. simulating on-orbit charging of a spacecraft; c. simulating the on-orbit docking of the spacecraft; d. and testing the discharge current characteristic. According to the spacecraft docking potential control test method, the potential control of the spacecraft in the on-orbit docking process is tested and verified on the ground, and related research results are transformed by engineering and can be applied to the test verification of the spacecraft docking potential control in the future, so that the spacecraft docking potential control performance can meet the requirements.
Description
Technical Field
The invention relates to the field of space flight and electricity, in particular to a spacecraft butt joint potential control test method.
Background
Under the interaction of the spacecraft running in space and the surrounding plasmas, solar radiation, high-energy charged particles and other environmental factors, electric charges are accumulated on the surface of the spacecraft, so that relative potential difference is generated between the surface of the spacecraft and the space plasmas. The absolute potential of the low orbit spacecraft has little influence on the independently running spacecraft, but when two spacecrafts carrying unequal charges are butted in an LEO orbit, the charges accumulated on the surfaces of the two spacecrafts can be instantaneously transferred between two charged bodies to generate instantaneous discharge. The electric pulse generated by the instantaneous discharge can generate strong broadband electromagnetic radiation, so that the spacecraft is trapped in abnormal work.
Aiming at the situation, when two spacecrafts with different voltage levels are butted, instantaneous discharge during butting needs to be inhibited, instantaneous discharge current is reduced to the maximum extent, and the normal work of the spacecrafts during butting is ensured. When two spacecrafts are butted, the discharge energy is firstly restrained by a resistor, and most energy is consumed, so that the energy of the two spacecraft cabins is reduced, and the working safety of the two spacecrafts in the butt joint process is ensured.
Considering that the real spacecraft cabin and the vacuum environment cannot be adopted to verify the butt joint potential control method, a test method needs to be adopted on the ground, the charged capacity of the spacecraft and the spacecraft contact process are simulated according to the design of the spacecraft, the proper butt joint resistance value is selected, and the discharge current amplitude and the discharge duration during butt joint are verified, so that the selected resistance value is reasonable, the current amplitude and the discharge duration during discharge meet the requirements, and the two spacecraft can be ensured to normally work during butt joint.
Disclosure of Invention
The invention aims to solve the problem that the butt-joint potential control method cannot be tested by adopting a real spacecraft cabin and a vacuum environment, and provides a spacecraft butt-joint potential control test method.
In order to achieve the aim, the invention provides a spacecraft docking potential control test method, which comprises the following steps:
a. constructing a potential control test system;
b. simulating on-orbit charging of a spacecraft;
c. simulating the on-orbit docking of the spacecraft;
d. and testing the discharge current characteristic.
According to an aspect of the present invention, in the step a, the method includes:
building an in-orbit spacecraft subsystem for simulating the in-orbit charging condition of the in-orbit spacecraft;
building an on-orbit visiting spacecraft subsystem for simulating the on-orbit charging condition of a visiting spacecraft;
and building a docking subsystem for simulating the docking process of the spacecraft.
According to an aspect of the present invention, in the b step, the method includes: simulating on-orbit charging of an on-orbit spacecraft and simulating on-orbit charging of a visiting spacecraft;
when the on-orbit spacecraft is simulated to be charged on the orbit, the direct-current power supply voltage is set to be the same as the power supply voltage of the spacecraft, the resistance value is 1k omega, and the capacitance value is the same as the equivalent capacitance value of the on-orbit spacecraft;
when the simulation visiting spacecraft is charged in an on-orbit mode, the direct-current power supply voltage is set to be the same as the power supply voltage of the visiting spacecraft, the resistance value is 1k omega, and the capacitance value is the same as the equivalent capacitance value of the on-orbit spacecraft.
According to an aspect of the invention, in the step c, the spacecraft is in-orbit docked by arranging a docking head device, the docking head device is configured according to contact characteristics of the actual spacecraft in docking contact, the spacecraft is in contact with one surface in a point-to-surface manner, one end of the docking head device is a pointed metal body, and the other end of the docking head device is a columnar metal body.
According to one aspect of the invention, in the step d, a switch and a bleeder resistor are configured to control the butt discharge, the selected value of the bleeder resistor is the same as the actually used resistance value in the butt discharge system, and an oscilloscope is used between the bleeder resistor and the in-orbit spacecraft to test the current waveform at the discharge moment.
According to the spacecraft docking potential control test method, the potential control of the spacecraft in the on-orbit docking process is tested and verified on the ground, and related research results are transformed by engineering and can be applied to the test verification of the spacecraft docking potential control in the future, so that the spacecraft docking potential control performance can meet the requirements.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Figure 1 schematically shows a flow chart of a spacecraft docking potential control test method according to the invention;
fig. 2 schematically shows a block diagram of the principle of a docking potential control test according to an embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Fig. 1 schematically shows a flow chart of a spacecraft docking potential control test method according to the invention. As shown in fig. 1, the spacecraft docking potential control test method according to the present invention comprises the following steps:
a. constructing a potential control test system;
b. simulating on-orbit charging of a spacecraft;
c. simulating the on-orbit docking of the spacecraft;
d. and testing the discharge current characteristic.
According to an embodiment of the invention, in the step a, a potential control test system is constructed, and the potential control test system is mainly realized by constructing three subsystems. Namely, an on-orbit spacecraft subsystem is built to simulate the on-orbit charging condition of the on-orbit spacecraft; the system is built in a visiting spacecraft subsystem to simulate the on-orbit charging condition of the visiting spacecraft; and (4) building a docking subsystem to simulate the docking process of the spacecraft.
Fig. 2 schematically shows a block diagram of the principle of a docking potential control test according to an embodiment of the present invention. In the step b, the on-orbit charging of the simulated on-orbit spacecraft and the on-orbit charging of the simulated visiting spacecraft are included in combination with fig. 2. On-orbit charging simulation of an on-orbit spacecraft: the charging condition of the on-rail spacecraft is simulated by configuring a switch K3, a resistor R2, a capacitor C2 and a direct-current power supply V2. In the test, the voltage of a direct current power supply V2 is set to be the same as the power supply voltage of the spacecraft, the value of a resistor R2 is 1k omega, and the value of a capacitor C2 is set to be the same as the equivalent capacitance value of the on-orbit spacecraft.
In-orbit charging simulation of the visiting spacecraft: the charging condition of the visiting spacecraft is simulated by configuring a switch K1, a resistor R1, a capacitor C1 and a direct-current power supply V1. In the test, the voltage of a direct current power supply V1 is set to be the same as the power supply voltage of a visiting spacecraft, the value of a resistor R1 is 1k omega, and the value of a capacitor C1 is set to be the same as the equivalent capacitance value of an on-orbit spacecraft.
According to an embodiment of the invention, in the step c, the method for simulating the in-orbit docking of the spacecraft is mainly carried out by arranging a docking head device. The butt joint device needs to be configured according to the actual contact characteristic of the spacecraft in butt contact, and the spacecraft is in butt contact with one point to one surface, so that one end of the butt joint device adopts a pointed metal body, and the other end of the butt joint device adopts a columnar metal body.
According to an embodiment of the present invention, in the step d, the switch K5 and the bleed-off resistor are configured to control the contact discharge, and the selected value of the bleed-off resistor is the same as the designed value. And simultaneously, an oscilloscope is used between the discharge resistor and the in-orbit spacecraft to test the current waveform at the moment of discharge.
The test process comprises the following steps: setting the voltage of a power supply V2 to be consistent with the power supply voltage of a spacecraft, turning on a switch K3 to charge a capacitor C2, setting the voltage of a power supply V1 to be consistent with the power supply voltage of a visiting spacecraft, turning on a switch K1 to charge a capacitor C1, turning off switches K3 and K1, turning on a switch K5, moving a butt joint device to enable two ends to be in contact, and measuring the current waveform at the contact moment by using an oscilloscope.
If the measurement needs to be carried out again, the switches K4 and K2 are turned on to discharge the capacitors C2 and C1, and the test process is repeated after the discharge is finished.
Therefore, the invention simulates the in-orbit charging process of the in-orbit spacecraft and the visiting spacecraft and the docking process of the in-orbit spacecraft and the visiting spacecraft by building the docking potential control test system, and tests the discharge current characteristics under the conditions of different discharge resistance values. And then comparing the discharge current characteristic with a design required value, verifying that the waveform amplitude of the discharge current is lower than the required value, and the discharge time is lower than the required value so as to ensure that the discharge resistance has reasonable value selection and the discharge current characteristic meets the requirement.
According to the method, the spacecraft docking potential control test method provided by the invention has good practicability, can realize the verification of spacecraft docking potential control, and ensures the reasonable design of spacecraft docking potential control.
Although the principles and methods of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes may be made in the specific embodiments, such as changing the resistance of the bleed resistor, the test method of the discharge current, and the on/off timing of the switch, without departing from the principles and spirit of the invention, the scope of which is defined in the claims and their equivalents.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (5)
1. A spacecraft docking potential control test method comprises the following steps:
a. constructing a potential control test system;
b. simulating on-orbit charging of a spacecraft;
c. simulating the on-orbit docking of the spacecraft;
d. and testing the discharge current characteristic.
2. A spacecraft docking potential control test method according to claim 1, wherein in the step a, the method comprises:
building an in-orbit spacecraft subsystem for simulating the in-orbit charging condition of the in-orbit spacecraft;
building an on-orbit visiting spacecraft subsystem for simulating the on-orbit charging condition of a visiting spacecraft;
and building a docking subsystem for simulating the docking process of the spacecraft.
3. A spacecraft docking potential control test method according to claim 1, wherein in the step b, the method comprises: simulating on-orbit charging of an on-orbit spacecraft and simulating on-orbit charging of a visiting spacecraft;
when the on-orbit spacecraft is simulated to be charged on the orbit, the direct-current power supply voltage is set to be the same as the power supply voltage of the spacecraft, the resistance value is 1k omega, and the capacitance value is the same as the equivalent capacitance value of the on-orbit spacecraft;
when the simulation visiting spacecraft is charged in an on-orbit mode, the direct-current power supply voltage is set to be the same as the power supply voltage of the visiting spacecraft, the resistance value is 1k omega, and the capacitance value is the same as the equivalent capacitance value of the on-orbit spacecraft.
4. A spacecraft docking potential control test method according to claim 1, wherein in the step c, the spacecraft is docked in orbit by arranging a docking head device, the docking head device is configured according to contact characteristics of an actual spacecraft in docking contact, the spacecraft is in contact with one surface at one point, one end of the docking head device is a pointed metal body, and the other end of the docking head device is a columnar metal body.
5. A spacecraft docking potential control test method according to any one of claims 1 to 4, wherein in the step d, a switch and a bleeder resistor are configured to control docking discharge, the selected value of the bleeder resistor is the same as the actually used resistance value in the docking discharge system, and an oscilloscope is used between the bleeder resistor and the in-orbit spacecraft to test the current waveform at the moment of discharge.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111465163A (en) * | 2020-05-11 | 2020-07-28 | 北京卫星环境工程研究所 | Plasma contactor based on satellite-borne radio frequency discharge |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111465163A (en) * | 2020-05-11 | 2020-07-28 | 北京卫星环境工程研究所 | Plasma contactor based on satellite-borne radio frequency discharge |
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Application publication date: 20200424 |