CN118145028A - Satellite rocket separation autonomous power-up circuit for satellite - Google Patents

Satellite rocket separation autonomous power-up circuit for satellite Download PDF

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Publication number
CN118145028A
CN118145028A CN202410215544.3A CN202410215544A CN118145028A CN 118145028 A CN118145028 A CN 118145028A CN 202410215544 A CN202410215544 A CN 202410215544A CN 118145028 A CN118145028 A CN 118145028A
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CN
China
Prior art keywords
resistor
satellite
switch
rocket
capacitor
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CN202410215544.3A
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Chinese (zh)
Inventor
乔明
陈昕
王跃
刘艳丽
张晓晨
刘亚利
田塬润
肖梦菡
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China Academy of Space Technology CAST
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China Academy of Space Technology CAST
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Priority to CN202410215544.3A priority Critical patent/CN118145028A/en
Publication of CN118145028A publication Critical patent/CN118145028A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/645—Separators
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/002—Launch systems
    • B64G1/005—Air launch
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Power Engineering (AREA)
  • Photovoltaic Devices (AREA)

Abstract

The invention discloses a satellite and rocket separated autonomous power-up circuit for satellites, which comprises: the device comprises a platform storage battery, a driving circuit a, a driving circuit b, a satellite and arrow separation switch a, a satellite and arrow separation switch b, a discharge switch a and a discharge switch b; the cathode of the platform storage battery is respectively connected with the first end of the driving circuit a, one end of the satellite-rocket separating switch a, the first end of the driving circuit b and one end of the satellite-rocket separating switch b; the anode of the platform storage battery is respectively connected with the second end of the driving circuit a, the first end of the discharging switch a, the second end of the driving circuit b and the first end of the discharging switch b; the third end of the driving circuit a is connected with the other end of the satellite and rocket disconnecting switch a; the fourth terminal of the driving circuit a is connected with the second terminal of the discharge switch a. The invention has the advantages of simple circuit structure, small volume, light weight, clear control logic and high reliability.

Description

Satellite rocket separation autonomous power-up circuit for satellite
Technical Field
The invention belongs to the technical field of earth remote sensing satellites, and particularly relates to a satellite-rocket separation autonomous power-on circuit for satellites.
Background
The satellite-rocket separation technology is one of key technologies in the aerospace field, and whether a satellite rocket can accurately realize separation directly relates to whether the rocket can successfully launch or not, and whether the satellite can normally enter orbit has important influence on the overall performance of the satellite and the completion degree of task implementation. The design of the satellite-rocket separation system not only ensures that the satellite can be reliably connected and separated from the rocket, but also meets the requirements of the satellite-rocket separation speed, separation gesture, impact response and the like.
After the satellites and the satellites are separated, energy is required to be obtained from the solar wings and the storage battery to realize normal on-orbit operation and task demand execution, however, the solar wings are in a compressed state at the moment, a certain time is required in the unfolding process, the power demand of the satellites cannot be met timely, and the energy is supplied by the storage battery at the moment, so that the storage battery is not connected with a bus in the system before the satellites and the satellites are separated, and a corresponding autonomous power-on system is required to be designed, so that the storage battery is automatically connected with the bus after the satellites and the satellites are separated, and the power-on of the whole system is completed. The design research on the autonomous power-up system for separating the satellites from the satellites at home and abroad is less, most of the designs realize the power-up of the system by manually plugging and unplugging the plug in a period of time before the satellite is launched, and the design causes the electric energy of the storage battery consumed by the equipment on the satellite before the satellite is launched to be wasted, and the manual plugging and unplugging can bring inconvenience and potential safety hazard.
Disclosure of Invention
The invention solves the technical problems that: the satellite and rocket separation autonomous power-on circuit overcomes the defects of the prior art, and has the advantages of simple circuit structure, small volume, light weight, clear control logic and high reliability.
The invention aims at realizing the following technical scheme: a satellite-rocket separation autonomous power-up circuit for a satellite, comprising: the device comprises a platform storage battery, a driving circuit a, a driving circuit b, a satellite and arrow separation switch a, a satellite and arrow separation switch b, a discharge switch a and a discharge switch b; the cathode of the platform storage battery is respectively connected with the first end of the driving circuit a, one end of the satellite and rocket separating switch a, the first end of the driving circuit b and one end of the satellite and rocket separating switch b; the positive electrode of the platform storage battery is respectively connected with the second end of the driving circuit a, the first end of the discharging switch a, the second end of the driving circuit b and the first end of the discharging switch b; the third end of the driving circuit a is connected with the other end of the satellite and rocket separating switch a; the fourth end of the driving circuit a is connected with the second end of the discharge switch a; the third end of the driving circuit b is connected with the other end of the satellite-rocket disconnecting switch b; the fourth end of the driving circuit b is connected with the second end of the discharge switch b; the third end of the discharging switch a is connected with an external middle bus, and the third end of the discharging switch b is connected with an external middle bus.
In the satellite rocket separation autonomous power-on circuit, the driving circuit a comprises a resistor R a3, a resistor R a4, a resistor R a5, a resistor R a6, a resistor R a7, a resistor R a8, a MOS tube Q a2, a MOS tube Q a3, a diode D a, a capacitor C a1, a capacitor C a2 and a capacitor C a3; the emitter of the MOS tube Q a2, one end of the resistor R a5, one end of the capacitor C a2, the emitter of the MOS tube Q a3, one end of the resistor R a6 and one end of the capacitor C a3 are respectively connected with the negative electrode of the platform storage battery; the base electrode of the MOS tube Q a2 is respectively connected with the other end of the resistor R a5, the other end of the capacitor C a2 and one end of the resistor R a7; the other end of the resistor R a7 is connected with a signal PA1 and a signal SA1; the collector of the MOS tube Q a2 is respectively connected with the anode of the diode D a, one end of the resistor R a4 and the collector of the MOS tube Q a3; the cathode of the diode D a is connected with the other end of the satellite and rocket disconnecting switch a; the base electrode of the MOS tube Q a3 is respectively connected with the other end of the resistor R a6, the other end of the capacitor C a3 and one end of the resistor R a8; the other end of the resistor R a8 is connected with a signal PA2 and a signal SA2; the other end of the resistor R a4 is respectively connected with one end of the resistor R a3, one end of the capacitor C a1 and the second end of the discharge switch a; the other end of the resistor R a3 and the other end of the capacitor C a1 are connected with the anode of the platform storage battery.
In the satellite-rocket separation autonomous power-on circuit, the satellite-rocket separation switch a comprises an a 1 pin, an a 2 pin and an a 3 pin; wherein the cathode of the diode D a is connected with the a 1 pin; before the satellite and arrow are separated, the a 1 pin is connected with the a 2 pin; after the satellite and arrow are separated, the a 1 pin is connected with the a 3 pin.
In the satellite rocket separation autonomous power-on circuit, the discharge switch a comprises a resistor R a1, a resistor R a2 and a switching tube Q a1; one end of the resistor R a1 is respectively connected with the other end of the resistor R a4, one end of the resistor R a3 and one end of the capacitor C a1; the other end of the resistor R a1 is respectively connected with the G pole of the switch tube Q a1 and one end of the resistor R a2; the other end of the resistor R a2 is connected with the anode of the platform storage battery; the D pole of the switch tube Q a1 is connected with an external middle bus, and the S pole of the switch tube Q a1 is connected with the positive pole of the platform storage battery.
In the satellite rocket separation autonomous power-on circuit, the driving circuit b comprises a resistor R b3, a resistor R b4, a resistor R b5, a resistor R b6, a resistor R b7, a resistor R b8, a MOS tube Q b2, a MOS tube Q b3, a diode D b, a capacitor C b1, a capacitor C b2 and a capacitor C b3; the emitter of the MOS tube Q b2, one end of the resistor R b5, one end of the capacitor C b2, the emitter of the MOS tube Q b3, one end of the resistor R b6 and one end of the capacitor C b3 are respectively connected with the negative electrode of the platform storage battery; the base electrode of the MOS tube Q b2 is respectively connected with the other end of the resistor R b5, the other end of the capacitor C b2 and one end of the resistor R b7; the other end of the resistor R b7 is connected with a signal PB1 and a signal SB1; the collector of the MOS tube Q b2 is respectively connected with the anode of the diode D b, one end of the resistor R b4 and the collector of the MOS tube Q b3; the cathode of the diode D b is connected with the other end of the satellite and rocket disconnecting switch b; the base electrode of the MOS tube Q b3 is respectively connected with the other end of the resistor R b6, the other end of the capacitor C b3 and one end of the resistor R b8; the other end of the resistor R b8 is connected with a signal PB2 and a signal SB2; the other end of the resistor R b4 is respectively connected with one end of the resistor R b3, one end of the capacitor C b1 and the second end of the discharge switch b; the other end of the resistor R b3 and the other end of the capacitor C b1 are connected with the anode of the platform storage battery.
In the satellite-rocket separation autonomous power-on circuit, the satellite-rocket separation switch b comprises a pin b 1, a pin b 2 and a pin b 3; wherein the cathode of the diode D b is connected with the b 1 pin; before the satellite and arrow are separated, the b 1 pin is connected with the b 2 pin; after the satellite and arrow are separated, the b 1 pin is connected with the b 3 pin.
In the satellite rocket separation autonomous power-on circuit, the discharge switch b comprises a resistor R b1, a resistor R b2 and a switching tube Q b1; one end of the resistor R b1 is respectively connected with the other end of the resistor R b4, one end of the resistor R b3 and one end of the capacitor C b1; the other end of the resistor R b1 is respectively connected with the G pole of the switch tube Q b1 and one end of the resistor R b2; the other end of the resistor R b2 is connected with the anode of the platform storage battery; the D pole of the switch tube Q b1 is connected with an external middle bus, and the S pole of the switch tube Q b1 is connected with the positive pole of the platform storage battery.
In the satellite rocket separation autonomous power-on circuit, the driving circuit a is used for driving the discharge switch a, and the driving circuit b is used for driving the discharge switch b; after the satellite is separated from the rocket, the satellite-rocket separating switch a acts, so that the driving signal level of the driving circuit a changes, and the discharging switch a is turned on; the satellite separating switch b acts to change the level of a driving signal of the driving circuit b, so that the discharging switch b is turned on.
In the satellite-used satellite-arrow separation autonomous power-on circuit, after a satellite arrow is separated, a satellite arrow separation switch a is closed, an a 1 pin of the satellite arrow separation switch a is connected with an a 3 pin, a diode D a is conducted, current flows through a resistor R a3 and a capacitor C a1 parallel branch from the positive electrode of a platform storage battery and then sequentially flows through a resistor R a4 and a diode D a, and finally flows back to the negative electrode of the platform storage battery through the satellite arrow separation switch a, so that a switch tube Q a1 is conducted, and a discharge switch a is switched on.
In the satellite-used satellite-arrow separation autonomous power-on circuit, after a satellite arrow is separated, a satellite arrow separation switch b is closed, a pin b 1 of the satellite arrow separation switch b is connected with a pin b 3, a diode D b is conducted, current flows through a resistor R b3 and a capacitor C b1 parallel branch from the positive electrode of a platform storage battery and then sequentially flows through a resistor R b4 and a diode D b, and finally flows back to the negative electrode of the platform storage battery through the satellite arrow separation switch b, so that a switching tube Q b1 is conducted, and a discharging switch b is switched on.
Compared with the prior art, the invention has the following beneficial effects:
the invention has the advantages of simple circuit structure, small volume, light weight, clear control logic and high reliability.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to designate like parts throughout the figures. In the drawings:
FIG. 1 is a schematic diagram of an autonomous power-up circuit for satellite rocket separation provided by an embodiment of the invention;
fig. 2 is an interface diagram and a control logic diagram of a battery discharging switch system according to an embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
Fig. 1 is a schematic diagram of a satellite rocket separation autonomous power-up circuit provided by an embodiment of the invention. As shown in fig. 1, the satellite rocket separation autonomous power-up circuit comprises: the device comprises a platform storage battery, a driving circuit a, a driving circuit b, a satellite and rocket disconnecting switch a, a satellite and rocket disconnecting switch b, a discharging switch a and a discharging switch b. Wherein,
The cathode of the platform storage battery is respectively connected with the first end of the driving circuit a, one end of the satellite and rocket separating switch a, the first end of the driving circuit b and one end of the satellite and rocket separating switch b; the anode of the platform storage battery is respectively connected with the second end of the driving circuit a, the first end of the discharging switch a, the second end of the driving circuit b and the first end of the discharging switch b; the third end of the driving circuit a is connected with the other end of the satellite and rocket disconnecting switch a; the fourth end of the driving circuit a is connected with the second end of the discharge switch a; the third end of the driving circuit b is connected with the other end of the satellite and rocket disconnecting switch b; the fourth end of the driving circuit b is connected with the second end of the discharge switch b; the third end of the discharging switch a is connected with an external middle bus, and the third end of the discharging switch b is connected with an external middle bus.
The driving circuit a is used for driving the discharge switch a, and the driving circuit b is used for driving the discharge switch b; after the satellite is separated from the rocket, the satellite-rocket separating switch a acts, so that the driving signal level of the driving circuit a changes, and the discharging switch a is turned on; the satellite separating switch b acts to change the level of a driving signal of the driving circuit b, so that the discharging switch b is turned on.
The driving circuit a comprises a resistor R a3, a resistor R a4, a resistor R a5, a resistor R a6, a resistor R a7, a resistor R a8, a MOS transistor Q a2, a MOS transistor Q a3, a diode D a, a capacitor C a1, a capacitor C a2 and a capacitor C a3; the emitter of the MOS tube Q a2, one end of the resistor R a5, one end of the capacitor C a2, the emitter of the MOS tube Q a3, one end of the resistor R a6 and one end of the capacitor C a3 are respectively connected with the negative electrode of the platform storage battery; the base electrode of the MOS tube Q a2 is respectively connected with the other end of the resistor R a5, the other end of the capacitor C a2 and one end of the resistor R a7; the other end of the resistor R a7 is connected with the signal PA1 and the signal SA1; the collector of the MOS tube Q a2 is respectively connected with the anode of the diode D a, one end of the resistor R a4 and the collector of the MOS tube Q a3; the cathode of the diode D a is connected with the other end of the satellite and rocket disconnecting switch a; the base electrode of the MOS tube Q a3 is respectively connected with the other end of the resistor R a6, the other end of the capacitor C a3 and one end of the resistor R a8; the other end of the resistor R a8 is connected with the signal PA2 and the signal SA2; the other end of the resistor R a4 is respectively connected with one end of the resistor R a3, one end of the capacitor C a1 and the second end of the discharge switch a; the other end of the resistor R a3 and the other end of the capacitor C a1 are connected with the anode of the platform storage battery.
The satellite-rocket disconnecting switch a comprises a 1 pin, a 2 pin and a 3 pin; wherein the cathode of the diode D a is connected with the a 1 pin; before the satellite and arrow are separated, the pin a 1 is connected with the pin a 2; after the satellite and arrow are separated, the pin a 1 is connected with the pin a 3.
The discharging switch a comprises a resistor R a1, a resistor R a2 and a switching tube Q a1; one end of the resistor R a1 is respectively connected with the other end of the resistor R a4, one end of the resistor R a3 and one end of the capacitor C a1; the other end of the resistor R a1 is respectively connected with the G pole of the switch tube Q a1 and one end of the resistor R a2; the other end of the resistor R a2 is connected with the anode of the platform storage battery; the D pole of the switch tube Q a1 is connected with an external middle bus, and the S pole of the switch tube Q a1 is connected with the positive pole of the platform storage battery.
After a satellite and a rocket are separated, a satellite and rocket separating switch a is closed, a 1 pin of the satellite and rocket separating switch a is connected with a 3 pin, a diode D a is conducted, current flows through a resistor R a3 and a capacitor C a1 parallel branch from the positive electrode of the platform storage battery and then sequentially flows through a resistor R a4 and a diode D a, and finally flows back to the negative electrode of the platform storage battery through the satellite and rocket separating switch a, so that a switch tube Q a1 is conducted, and a discharge switch a is switched on.
The driving circuit b comprises a resistor R b3, a resistor R b4, a resistor R b5, a resistor R b6, a resistor R b7, a resistor R b8, a MOS transistor Q b2, a MOS transistor Q b3, a diode D b, a capacitor C b1, a capacitor C b2 and a capacitor C b3; the emitter of the MOS tube Q b2, one end of the resistor R b5, one end of the capacitor C b2, the emitter of the MOS tube Q b3, one end of the resistor R b6 and one end of the capacitor C b3 are respectively connected with the negative electrode of the platform storage battery; the base electrode of the MOS tube Q b2 is respectively connected with the other end of the resistor R b5, the other end of the capacitor C b2 and one end of the resistor R b7; the other end of the resistor R b7 is connected with the signal PB1 and the signal SB1; the collector of the MOS tube Q b2 is respectively connected with the anode of the diode D b, one end of the resistor R b4 and the collector of the MOS tube Q b3; the cathode of the diode D b is connected with the other end of the satellite and rocket disconnecting switch b; the base electrode of the MOS tube Q b3 is respectively connected with the other end of the resistor R b6, the other end of the capacitor C b3 and one end of the resistor R b8; the other end of the resistor R b8 is connected with the signal PB2 and the signal SB2; the other end of the resistor R b4 is respectively connected with one end of the resistor R b3, one end of the capacitor C b1 and the second end of the discharge switch b; the other end of the resistor R b3 and the other end of the capacitor C b1 are connected with the anode of the platform storage battery.
The satellite-rocket disconnecting switch b comprises a pin b 1, a pin b 2 and a pin b 3; wherein the cathode of the diode D b is connected with the pin b 1; before the satellite and arrow are separated, the pin b 1 is connected with the pin b 2; after the satellite and arrow are separated, the pin b 1 is connected with the pin b 3.
The discharging switch b comprises a resistor R b1, a resistor R b2 and a switching tube Q b1; one end of the resistor R b1 is respectively connected with the other end of the resistor R b4, one end of the resistor R b3 and one end of the capacitor C b1; the other end of the resistor R b1 is respectively connected with the G pole of the switch tube Q b1 and one end of the resistor R b2; the other end of the resistor R b2 is connected with the anode of the platform storage battery; the D pole of the switch tube Q b1 is connected with an external middle bus, and the S pole of the switch tube Q b1 is connected with the positive pole of the platform storage battery.
After a satellite and a rocket are separated, a satellite and rocket separating switch b is closed, a pin b 1 of the satellite and rocket separating switch b is connected with a pin b 3, a diode D b is conducted, current flows through a resistor R b3 and a capacitor C b1 parallel branch from the positive electrode of the platform storage battery and then sequentially flows through a resistor R b4 and a diode D b, and finally flows back to the negative electrode of the platform storage battery through the satellite and rocket separating switch b, so that a switching tube Q b1 is conducted, and a discharging switch b is switched on.
As shown in fig. 1, the battery discharging switches a and b are respectively composed of two parallel P-tubes, Q a1 and Q b1, and four gate driving resistors R a1,Ra2 and R b1,Rb2. The driving circuits a and b are respectively used for driving the switching tubes Q a1 and Q b1 in the discharging switching circuit, and R a3,Ra4,Ca1 and R b3,Rb4,Cb1 in the two groups of driving circuits are used for dividing voltage and adjusting the magnitude of driving voltage by adjusting the values of the driving circuits; diodes D a and D b are used to control the unidirectional flow of current; when the MOS transistors Q a2,Qa3 and Q b2,Qb3 are used for satellite remote control, the driving circuit is controlled, wherein R a5,Ra7,Ca2 is used for driving the MOS transistor Q a2,Ra6,Ra8,Ca3 and the MOS transistor Q a3,Rb5,Rb7,Cb2, and the MOS transistor Q b2,Rb6,Rb8,Cb3 and the MOS transistor Q b3. The satellite and rocket separating switches a and b can be specifically selected as JMW-270MA/027-2 type relays and are used for controlling and changing connection of circuits before and after satellite and rocket separation, 2 paths of separating signals are formed in the circuits and are respectively FL_SA and FL_SB, and the 2 relays are used as self-heating backup.
As shown in fig. 1, three sets of signals can perform switch control ON a discharging switch BCRB of the storage battery of the platform, namely, a satellite and rocket separation autonomous power-up signal gs_on; secondly, a platform storage battery discharging switch on/off command (on-board command), namely SA1, SA2, SB1 and SB2; and thirdly, the over-discharge protection signals of the storage battery of the platform are PA1, PA2, PB1 and PB2. In fig. 2, the control logic relationships and control principles of the three signals will be described in detail. In fig. 1, the whole system is formed by connecting two identical groups of circuits in parallel, namely a driving circuit a, a discharging switch a, a satellite separating switch a, a driving circuit b, a discharging switch b and a satellite separating switch b. The two groups of circuit structures and component parameters are identical, the on-orbit mutual hot backup relation is adopted, in order to reduce redundant description, the working principle of the circuit is described by taking the group a circuit as an example, the working principle of the group b circuit is identical to the group a, and the two groups are in parallel connection relation, namely, in theory, the corresponding circuit and the component are identical in working state at the same moment. In addition, in the a-group circuit, the corresponding BCRB driving a 1, the signals PA1, SA1 and BCRB driving a 2, the signals PA2 and SA2 are identical, so in fig. 2, only the principle of BCRB driving a 1, the signals PA1 and SA1 single-set circuit is described.
Fig. 2 shows the interface relation between the autonomous power-up system and the solar array, the secondary power module, etc. and the control priority, at this time, three signals can switch and control the discharging switch BCRB of the platform storage battery, and a certain logic relation and priority exist between the signals, and the three signals are the satellite and rocket separation autonomous power-up signal gs_on, the ON/off command (ON-board command) SA1 of the discharging switch of the platform storage battery, and the over-discharging protection signal PA1 of the platform storage battery. The satellite and rocket separating switch controls the discharging switch of the storage battery of the platform to be automatically switched on after the satellite and rocket are separated; the on-board command controls the discharge switch through the ground on-board remote control command; the over-discharge protection of the platform storage battery is realized by detecting the voltage of the storage battery by the comprehensive electrons of the whole star, comparing the voltage with a reference voltage, and switching the magnetic latching relay by sending a command when the over-discharge protection is judged to be realized, so that the discharge switch is disconnected. The satellite and rocket separation autonomous power-on signal has the highest priority, and the priority of the satellite command is the same as that of the over-discharge protection signal of the storage battery of the platform.
First, the priority principle of these three signals will be described: as can be seen in fig. 2, the gs_on signal has the highest priority of control ON, which directly controls the discharge switch. At this time, the on of the battery discharge switch can be achieved regardless of whether SA1 and PA1 are high or low, that is, regardless of whether the switching device of the driving circuit is on or off. Secondly, SA1 or PA1 signals have the same priority, and the control BCRB drives the a 1 circuit to further control the ON-off of the discharge switch, under the premise that GS_ON is low level, when SA1 and PA1 are both low level, the driving circuit is turned off, and when SA1 and PA1 are high level, the driving circuit is turned ON, and the discharge switch is turned ON. The relationship between the consolidated control signal and BCRB states is shown in table 1.
TABLE 1
Satellite and rocket separation signal On-board instruction Over-discharge protection signal for storage battery BCRB
Enabling × × Conduction
Inhibit ON Unprotected Conduction
Inhibit OFF × Shut off
Inhibit × Protection of Shut off
The satellite and rocket separated autonomous power-up signal has the highest priority of the on operation of the platform storage battery discharging switch BCRB, and as long as the satellite and rocket separated autonomous power-up function is enabled and the separating switch is in a release state, BCRB can be kept on under the action of the autonomous power-up signal regardless of the states of other two signals. In fig. 1, the ENA point is a contact point of a satellite separating switch, the satellite separating switch relay a is determined to be in a state that a 1 is connected with a 2 pin after the ground test is finished before satellite launching, the fl_sa point is a separating signal input and is connected with the satellite separating switch through an external connector, when the satellite is separated, the satellite separating switch is closed, the a 1 of the satellite separating switch is connected with a 3 pin, the fl_sa point is low level, namely the ENA point is low level, a diode D a is conducted, current flows through a parallel branch of R a3 and C a1 from the positive electrode of a storage battery to R a4, the diode D a finally flows back to the negative electrode of the storage battery through the satellite separating switch a, driving voltages exist at two ends of a gs_on point and a BAT point in the circuit, and Q a1 is conducted, and the storage battery of the platform is discharged after the satellite is separated, so that the storage battery of the platform is connected.
The design of the circuit branch is to prevent the satellite from being powered up caused by the fact that the satellite separation switch signal fails to normally drive the platform storage battery discharging switch BCRB, and to verify whether the autonomous power-on system operates normally by sending the satellite separation instruction when testing is performed before satellite emission. Before sending the instruction, a 1 of the satellite and rocket disconnecting switch a is connected with a pin a 2, an ENA point in the circuit shown in fig. 1 is at a high level, and a diode D a is cut off. Before satellite transmission, SA1 and SA2 are low level, and switching devices Q a2 and Q a3 of a driving circuit are not conducted, so that no current flows through a R a3,Ra4 serial path, voltages at two ends of GS_ON and BAT are 0, a discharging switch Q a1 is turned off, and a platform storage battery and a bus are in an off state; after a satellite and rocket separation remote control instruction is issued, the SA1 and SA2 points are high level, the switching devices Q a2 and Q a3 of the driving circuit are conducted, current flows from the anode of the storage battery to the R a4 through a parallel branch of R a3 and C a1, flows continuously through a parallel branch of the switching tubes Q a2 and Q a3 and finally flows back to the cathode of the storage battery, driving voltages exist at two ends of the GS_ON point and the BAT point in the circuit, the discharging switch Q a1 is conducted, the storage battery is connected with a bus, the satellite and rocket separation system realizes power-up.
The platform storage battery overdischarge protection circuit is used for protecting a spacecraft power supply system when overdischarge occurs, and the platform storage battery overdischarge protection circuit is used for protecting the platform storage battery by detecting the comparison between the intermediate bus voltage and the reference voltage and disconnecting a discharge switch when overdischarge protection is judged. In addition, the battery discharging switch can be automatically awakened when the electric energy is sufficient in the illumination period, and BCRB is automatically connected to the bus again, and the specific principle is described as follows. As shown in fig. 2, the over-discharge protection circuit is composed of components such as an operational amplifier, a comparator, a relay and the like, after the over-discharge abnormal condition occurs in the platform storage battery, the voltage of the whole star intermediate bus (namely the voltage of the platform storage battery) is continuously reduced, after the voltage of the intermediate bus is reduced to the over-discharge protection threshold value (V1), the comparator outputs a low level, namely PA1 is at the low level at this time, BCRB drives the a 1 circuit to be turned off, the discharge switch is turned off, and the working principle is identical to the SA1 signal action principle and is not repeated. The power supply controller disconnects the platform storage battery from the middle bus in a mode of disconnecting the platform discharge switch, so that the protection effect on the platform storage battery is achieved, and at the moment, the satellite enters a power-down state. After the satellite enters the illumination period, solar array energy is regulated by MPPT power and is output to an intermediate bus, a platform storage battery is charged by a platform discharge switch, the intermediate bus voltage is clamped by the storage battery, the intermediate bus voltage gradually rises along with the charging of the storage battery, after the voltage reaches a recovery threshold V2 (V2 > V1), a comparator outputs a high level, PA1 is pulled up, and a power supply controller is independently connected with the platform discharge switch to wake up the satellite.
The driving circuit a and the driving circuit b of the present embodiment are used to drive the discharge switch a and the discharge switch b, respectively. After the satellite is separated from the rocket, the satellite-rocket separating switch a and the satellite-rocket separating switch b act, so that the level of a driving signal of the driving circuit changes, and then the discharging switch of the storage battery is turned on, namely, the two P tubes Q a1 and Q b1 in the figure 1 are turned on, the storage battery is connected with a bus, and the bus is powered up, so that the autonomous power-up function of the platform storage battery after the satellite-rocket separation is realized. The embodiment has the advantages of simple circuit structure, small volume, light weight, clear control logic and high reliability.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.

Claims (10)

1. The satellite rocket separation autonomous power-up circuit for the satellite is characterized by comprising: the device comprises a platform storage battery, a driving circuit a, a driving circuit b, a satellite and arrow separation switch a, a satellite and arrow separation switch b, a discharge switch a and a discharge switch b; wherein,
The negative electrode of the platform storage battery is respectively connected with the first end of the driving circuit a, one end of the satellite and rocket separating switch a, the first end of the driving circuit b and one end of the satellite and rocket separating switch b;
the positive electrode of the platform storage battery is respectively connected with the second end of the driving circuit a, the first end of the discharging switch a, the second end of the driving circuit b and the first end of the discharging switch b;
The third end of the driving circuit a is connected with the other end of the satellite and rocket separating switch a; the fourth end of the driving circuit a is connected with the second end of the discharge switch a;
The third end of the driving circuit b is connected with the other end of the satellite-rocket disconnecting switch b; the fourth end of the driving circuit b is connected with the second end of the discharge switch b;
The third end of the discharging switch a is connected with an external middle bus, and the third end of the discharging switch b is connected with an external middle bus.
2. The satellite-based satellite-rocket separation autonomous power-up circuit according to claim 1, wherein: the driving circuit a comprises a resistor R a3, a resistor R a4, a resistor R a5, a resistor R a6, a resistor R a7, a resistor R a8, a MOS tube Q a2, a MOS tube Q a3, a diode D a, a capacitor C a1, a capacitor C a2 and a capacitor C a3; wherein,
The emitter of the MOS tube Q a2, one end of the resistor R a5, one end of the capacitor C a2, the emitter of the MOS tube Q a3, one end of the resistor R a6 and one end of the capacitor C a3 are respectively connected with the negative electrode of the platform storage battery;
The base electrode of the MOS tube Q a2 is respectively connected with the other end of the resistor R a5, the other end of the capacitor C a2 and one end of the resistor R a7; the other end of the resistor R a7 is connected with a signal PA1 and a signal SA1;
The collector of the MOS tube Q a2 is respectively connected with the anode of the diode D a, one end of the resistor R a4 and the collector of the MOS tube Q a3; the cathode of the diode D a is connected with the other end of the satellite and rocket disconnecting switch a;
The base electrode of the MOS tube Q a3 is respectively connected with the other end of the resistor R a6, the other end of the capacitor C a3 and one end of the resistor R a8; the other end of the resistor R a8 is connected with a signal PA2 and a signal SA2;
The other end of the resistor R a4 is respectively connected with one end of the resistor R a3, one end of the capacitor C a1 and the second end of the discharge switch a;
The other end of the resistor R a3 and the other end of the capacitor C a1 are connected with the anode of the platform storage battery.
3. The satellite-based satellite-rocket separation autonomous power-up circuit according to claim 2, wherein: the satellite and rocket disconnecting switch a comprises an a 1 pin, an a 2 pin and an a 3 pin; wherein,
The negative electrode of the diode D a is connected with the a 1 pin;
Before the satellite and arrow are separated, the a 1 pin is connected with the a 2 pin; after the satellite and arrow are separated, the a 1 pin is connected with the a 3 pin.
4. The satellite-based satellite-rocket separation autonomous power-up circuit according to claim 2, wherein: the discharge switch a comprises a resistor R a1, a resistor R a2 and a switching tube Q a1; wherein,
One end of the resistor R a1 is respectively connected with the other end of the resistor R a4, one end of the resistor R a3 and one end of the capacitor C a1;
The other end of the resistor R a1 is respectively connected with the G pole of the switch tube Q a1 and one end of the resistor R a2;
The other end of the resistor R a2 is connected with the anode of the platform storage battery;
The D pole of the switch tube Q a1 is connected with an external middle bus, and the S pole of the switch tube Q a1 is connected with the positive pole of the platform storage battery.
5. The satellite-based satellite-rocket separation autonomous power-up circuit according to claim 1, wherein: the driving circuit b comprises a resistor R b3, a resistor R b4, a resistor R b5, a resistor R b6, a resistor R b7, a resistor R b8, a MOS tube Q b2, a MOS tube Q b3, a diode D b, a capacitor C b1, a capacitor C b2 and a capacitor C b3; wherein,
The emitter of the MOS tube Q b2, one end of the resistor R b5, one end of the capacitor C b2, the emitter of the MOS tube Q b3, one end of the resistor R b6 and one end of the capacitor C b3 are respectively connected with the negative electrode of the platform storage battery;
The base electrode of the MOS tube Q b2 is respectively connected with the other end of the resistor R b5, the other end of the capacitor C b2 and one end of the resistor R b7;
The collector of the MOS tube Q b2 is respectively connected with the anode of the diode D b, one end of the resistor R b4 and the collector of the MOS tube Q b3; the cathode of the diode D b is connected with the other end of the satellite and rocket disconnecting switch b;
The base electrode of the MOS tube Q b3 is respectively connected with the other end of the resistor R b6, the other end of the capacitor C b3 and one end of the resistor R b8;
the other end of the resistor R b4 is respectively connected with one end of the resistor R b3, one end of the capacitor C b1 and the second end of the discharge switch b;
The other end of the resistor R b3 and the other end of the capacitor C b1 are connected with the anode of the platform storage battery.
6. The satellite-based satellite-rocket separation autonomous-power-up circuit according to claim 5, wherein: the satellite-rocket disconnecting switch b comprises a pin b 1, a pin b 2 and a pin b 3; wherein,
The cathode of the diode D b is connected with the b 1 pin;
Before the satellite and arrow are separated, the b 1 pin is connected with the b 2 pin; after the satellite and arrow are separated, the b 1 pin is connected with the b 3 pin.
7. The satellite-based satellite-rocket separation autonomous-power-up circuit according to claim 5, wherein: the discharging switch b comprises a resistor R b1, a resistor R b2 and a switching tube Q b1; wherein,
One end of the resistor R b1 is respectively connected with the other end of the resistor R b4, one end of the resistor R b3 and one end of the capacitor C b1;
The other end of the resistor R b1 is respectively connected with the G pole of the switch tube Q b1 and one end of the resistor R b2;
The other end of the resistor R b2 is connected with the anode of the platform storage battery;
The D pole of the switch tube Q b1 is connected with an external middle bus, and the S pole of the switch tube Q b1 is connected with the positive pole of the platform storage battery.
8. The satellite-based satellite-rocket separation autonomous power-up circuit according to claim 1, wherein: the driving circuit a is used for driving the discharge switch a, and the driving circuit b is used for driving the discharge switch b;
after the satellite is separated from the rocket, the satellite-rocket separating switch a acts, so that the driving signal level of the driving circuit a changes, and the discharging switch a is turned on; the satellite separating switch b acts to change the level of a driving signal of the driving circuit b, so that the discharging switch b is turned on.
9. The satellite-based satellite-rocket separation autonomous power-up circuit according to claim 4, wherein: after a satellite and a rocket are separated, a satellite and rocket separating switch a is closed, a 1 pin of the satellite and rocket separating switch a is connected with a 3 pin, a diode D a is conducted, current flows through a resistor R a3 and a capacitor C a1 parallel branch from the positive electrode of the platform storage battery and then sequentially flows through a resistor R a4 and a diode D a, and finally flows back to the negative electrode of the platform storage battery through the satellite and rocket separating switch a, so that a switch tube Q a1 is conducted, and a discharge switch a is switched on.
10. The satellite-based satellite-rocket separation autonomous power-up circuit according to claim 7, wherein: after a satellite and a rocket are separated, a satellite and rocket separating switch b is closed, a pin b 1 of the satellite and rocket separating switch b is connected with a pin b 3, a diode D b is conducted, current flows through a resistor R b3 and a capacitor C b1 parallel branch from the positive electrode of the platform storage battery and then sequentially flows through a resistor R b4 and a diode D b, and finally flows back to the negative electrode of the platform storage battery through the satellite and rocket separating switch b, so that a switching tube Q b1 is conducted, and a discharging switch b is switched on.
CN202410215544.3A 2024-02-27 2024-02-27 Satellite rocket separation autonomous power-up circuit for satellite Pending CN118145028A (en)

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CN202410215544.3A CN118145028A (en) 2024-02-27 2024-02-27 Satellite rocket separation autonomous power-up circuit for satellite

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202410215544.3A CN118145028A (en) 2024-02-27 2024-02-27 Satellite rocket separation autonomous power-up circuit for satellite

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CN118145028A true CN118145028A (en) 2024-06-07

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CN202410215544.3A Pending CN118145028A (en) 2024-02-27 2024-02-27 Satellite rocket separation autonomous power-up circuit for satellite

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