CN110789742A - Accurate time delay separation circuit for satellite - Google Patents
Accurate time delay separation circuit for satellite Download PDFInfo
- Publication number
- CN110789742A CN110789742A CN201910901440.7A CN201910901440A CN110789742A CN 110789742 A CN110789742 A CN 110789742A CN 201910901440 A CN201910901440 A CN 201910901440A CN 110789742 A CN110789742 A CN 110789742A
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- resistor
- circuit
- delay
- separation
- power supply
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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
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H9/00—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
- H02H9/02—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess current
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- 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
Abstract
The invention discloses a circuit for accurate time delay separation for a satellite, which comprises a storage battery pack, an autonomous power supply circuit, a time delay circuit, a driving circuit, an initiating explosive device power supply circuit, a detonation separation switch and an initiating explosive device bridge wire. Before the star and the rocket are separated, the detonation separation switch is in a disconnected state, and after a main star separation signal or a signal provided by the rocket is received, the detonation separation switch is switched on. And after the detonation separation switch is switched on, the storage battery pack supplies power to the autonomous power supply circuit. And after the autonomous power supply circuit is powered on, the power is supplied to the delay circuit. After the delay circuit carries out accurate delay, the drive circuit is triggered. After the driving circuit is triggered, a trigger signal is provided for the initiating explosive device power supply circuit. The initiating explosive device power supply circuit provides detonation energy for the initiating explosive device bridge wire under the control of the trigger signal of the drive circuit, and the satellite separation mechanism is unlocked. The invention can accurately control the separation time of the star and the arrow and is simple and reliable to realize.
Description
Technical Field
The invention belongs to the field of electricity, and relates to an accurate time delay separation circuit for a satellite.
Background
With the rapid development of microsatellite technology and satellite commercialization, the demand of one rocket or satellite-borne launching tasks is increasing, and the requirements on the orbit control, the separation time and the separation procedure of the satellite are becoming more and more strict. Currently, the separation of the satellite and the rocket is realized by controlling initiating explosive devices or ejecting satellites through a mechanical switch on the rocket, so that the separation time control of the satellite and the rocket is not accurate, or the precision of the satellite in the orbit is not accurate enough, and meanwhile, the accurate timing separation of a plurality of satellites is not realized.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, and the circuit for accurately delaying and separating the satellite is provided.
The technical scheme of the invention is as follows:
a circuit for accurate time delay separation for a satellite comprises a storage battery pack, an autonomous power supply circuit, a time delay circuit, a driving circuit, an initiating explosive device power supply circuit, a detonation separation switch and initiating explosive device bridge wires;
before the star and the rocket are separated, the detonation separation switch is in a disconnected state, and is switched on after a main star separation signal or a separation signal provided by the rocket is received;
after the detonation separation switch is switched on, the storage battery pack supplies power to the autonomous power supply circuit;
after the autonomous power supply circuit is powered on, the power is supplied to the delay circuit;
after the delay circuit carries out accurate delay, the drive circuit is triggered;
after the driving circuit is triggered, a trigger signal is provided for the initiating explosive device power supply circuit;
the initiating explosive device power supply circuit provides detonation energy for the initiating explosive device bridge wire under the control of the trigger signal of the drive circuit, and the initiating explosive device bridge wire unlocks the satellite separating mechanism.
The autonomous power supply circuit comprises a resistor RY1, a resistor RY2, a resistor RY3, a resistor RY4, a PMOS field-effect tube QY1 and a PMOS field-effect tube QY2, one end of the resistor RY2 is connected with the positive end of a storage battery, the other end of the resistor RY2 is connected with a grid G of the PMOS field-effect tube QY1, one end of the resistor RY4 is connected with the positive end of the storage battery, the other end of the resistor RY4 is connected with the grid G of the PMOS field-effect tube QY2, one end of the resistor RY1 is connected with the grid G of the PMOS field-effect tube QY1, one end of the resistor RY3 is connected with the grid G of the PMOS field-effect tube QY2, the resistor RY1 is connected with the other end of the resistor RY3 to serve as the input end of the autonomous power supply circuit and connected with the detonation separation switch K1, the source S of the PMOS field-effect tube QY1 and the source S of the PMOS field-effect tube.
One end of the detonation separation switch is connected with the input end of the autonomous power supply circuit, and the other end of the detonation separation switch is connected with the negative end of the storage battery pack.
The delay circuit comprises a diode D1-1, delay resistors R1, R2 and R3, a delay capacitor C1, a comparator U1, input resistors R4 and R6, a feedback resistor R7 and a pull-up resistor R8, wherein the A pole of the diode D1-1 is connected with the output end of the autonomous power supply circuit, the K pole of a diode D1-1 is connected with one end of the delay resistor R1, the other end of the delay resistor R1 is connected with the A pole of a diode D1-1, one end of the delay resistor R2 is connected with the A pole of the diode D2-1, the other end of the delay resistor R2 is simultaneously connected with one end of the delay resistor R2 and one end of the input resistor R2, the other end of the delay resistor R2 is connected with the negative pole of the storage battery pack, one end of the delay capacitor C2 is connected with the K pole of the diode D2-1, the other end of the delay capacitor C2 is connected with the negative pole of the input resistor R2, one end of the input resistor R2 is connected with the K pole of, the other end of the input resistor R6 is connected with a pin 2 of the comparator U1, the feedback resistor R7 is connected between a pin 1 and a pin 3 of the comparator U1, one end of the pull-up resistor R8 is connected with an A pole of the diode D1-1, and the other end of the pull-up resistor R8 is connected with a pin 1 of the comparator U1; pin 4 of the comparator U1 is connected with the negative terminal of the storage battery pack, and pin 1 of the comparator U1 is the output end of the delay circuit.
The satellite precise time delay separation circuit further comprises a current-limiting protection circuit, and the current-limiting protection circuit realizes current-limiting protection on the time delay circuit.
The current-limiting protection circuit comprises a resistor RU1, a capacitor CU1 and a capacitor CU 2; one end of the resistor RU1 is connected with the A pole of the diode D1-1, and the other end of the resistor RU1 is connected with the pin 8 of the comparator U1; one end of the capacitor CU2 is connected with the negative end of the storage battery pack, the other end of the capacitor CU2 is connected with one end of the capacitor CU1, and the other end of the capacitor CU1 is connected with a pin 8 of the comparator U1.
The driving circuit comprises an input resistor R9, a signal control transistor QS1 and a pull-down resistor R10, one end of the input resistor R9 is connected with the output end of the delay circuit, the other end of the input resistor R9 is connected with the B pole of the signal control transistor QS1, the E pole of the signal control transistor QS1 is connected with one end of the pull-down resistor R10, the other end of the pull-down resistor R10 is connected with the negative end of a storage battery pack, and the C pole of the signal control transistor QS1 serving as the output end of the driving circuit is connected with.
The initiating explosive device power supply circuit comprises drive control resistors RK1 and RK2, a PMOS field effect tube QD1, a current-limiting resistor RP1 and an electrostatic discharge resistor RK3, one end of the drive control resistor RK1 is connected with the output end of the drive circuit, the other end of the drive control resistor RK1 is simultaneously connected with a grid G of the PMOS field effect tube QD1 and one end of the drive control resistor RK2, the other end of the drive control resistor RK2 is connected with a source S of the PMOS field effect tube QD1, the source S of the PMOS field effect tube QD1 is connected with the positive end of a storage battery pack, a drain D of the PMOS field effect tube QD1 is connected with one end of a current-limiting resistor RP1, the other end of the current-limiting resistor RP1 is connected with one end of an electrostatic discharge resistor RK3 to serve.
One end of the initiating explosive device bridge wire is connected with the output end of the initiating explosive device power supply circuit, and the other end of the initiating explosive device bridge wire is connected with the negative end of the storage battery pack.
Compared with the prior art, the invention has the beneficial effects that:
(1) the delay circuit, the initiating explosive device power supply circuit and the initiating explosive device detonation energy are all provided by the internal storage battery, and a rocket is not required to independently provide energy for the separating mechanism.
(2) The satellite and arrow separation delay time is controlled by a delay capacitor C1, delay resistors R1, R2, R3 and D1-1 in a delay circuit, the time control is accurate, and the change of the voltage of a storage battery pack is avoided. The autonomous time-delay separation can be realized only by providing a separation signal by the rocket.
(3) The invention can carry out circuit expansion, is applied to the precise time delay separation of a plurality of satellites and rockets, reduces the probability of collision between the satellites and the rockets and improves the accuracy of the satellites entering the predetermined orbit.
(4) The invention is composed of transistor, comparator, resistor, capacitor, accumulator battery and diode, and the key circuit has redundancy backup reliability measure, simple and reliable.
Drawings
FIG. 1 is a circuit diagram of the present invention.
Detailed Description
The invention is further elucidated with reference to the drawing.
The invention provides a circuit for accurate time delay separation for a satellite, which comprises a storage battery pack, an autonomous power supply circuit, a time delay circuit, a driving circuit, an initiating explosive device power supply circuit, a detonation separation switch K1 and an initiating explosive device bridge wire, wherein the autonomous power supply circuit, the time delay circuit, the driving circuit, the initiating explosive device power supply circuit, the detonation separation switch K1 and the initiating explosive device bridge wire are shown in figure 1.
Before the star and the rocket are separated, the detonation separation switch is in a disconnected state, and after a main star separation signal or a signal provided by the rocket is received, the detonation separation switch is switched on. And after the detonation separation switch is switched on, the storage battery pack supplies power to the autonomous power supply circuit. And after the autonomous power supply circuit is powered on, the power is supplied to the delay circuit. After the delay circuit carries out accurate delay, the drive circuit is triggered. After the driving circuit is triggered, a trigger signal is provided for the initiating explosive device power supply circuit. The initiating explosive device power supply circuit provides detonation energy for the initiating explosive device bridge wire under the control of the trigger signal of the drive circuit, and the initiating explosive device bridge wire unlocks the satellite separating mechanism.
The autonomous power supply circuit comprises a resistor RY1, a resistor RY2, a resistor RY3, a resistor RY4, a PMOS field-effect tube QY1 and a PMOS field-effect tube QY2, one end of the resistor RY2 is connected with the positive end of the storage battery, the other end of the resistor RY2 is connected with the grid G of the PMOS field-effect tube QY1, one end of the resistor RY4 is connected with the positive end of the storage battery, the other end of the resistor RY4 is connected with the grid G of the PMOS field-effect tube QY2, one end of the resistor RY1 is connected with the grid G of the PMOS field-effect tube QY1, one end of the resistor RY3 is connected with the grid G of the PMOS field-effect tube QY2, the resistor RY1 is connected with the other end of the resistor RY3 to serve as the input end of the autonomous power supply circuit and is connected with the detonation separation switch K1, the source S of the PMOS field-effect tube QY1 and the source S of the PMOS field-.
One end of the detonation separation switch K1 is connected with the input end of the autonomous power supply circuit, and the other end of the detonation separation switch K1 is connected with the negative end of the storage battery pack.
The delay circuit comprises a diode D1-1, a delay resistor R1, a R2, a R3, a delay capacitor C1, a comparator U1, an input resistor R4, a R6, a feedback resistor R7 and a pull-up resistor R8, wherein the A pole of the diode D1-1 is connected with the output end of the autonomous power supply circuit (the drain D of a PMOS field effect transistor QY 1), the K pole of the diode D1-1 is connected with one end of a delay resistor R1, the other end of the delay resistor R1 is connected with the A pole of the diode D1-1, one end of a delay resistor R2 is connected with the A pole of the diode D1-1, the other end of the delay resistor R2 is simultaneously connected with one end of the delay resistor R2 and one end of the input resistor R2, the other end of the delay resistor R2 is connected with the negative end of the storage battery pack, one end of the delay capacitor C2 is connected with the K pole of the diode D2-1, the other end of the input resistor R4 is connected with a pin 3 of a comparator U1, the other end of the input resistor R6 is connected with a pin 2 of a comparator U1, the feedback resistor R7 is connected between the pin 1 and the pin 3 of the comparator U1, one end of a pull-up resistor R8 is connected with an A pole of a diode D1-1, and the other end of the pull-up resistor R8 is connected with a pin 1 of a comparator U1; pin 4 of comparator U1 is connected to the pack negative terminal.
The circuit for accurately delaying and separating the satellite also comprises a current limiting protection circuit which is used for carrying out current limiting protection on a comparator U1 in the delay circuit. The current-limiting protection circuit comprises a resistor RU1, a capacitor CU1 and a capacitor CU 2; one end of the resistor RU1 is connected with the A pole of the diode D1-1, and the other end of the resistor RU1 is connected with the pin 8 of the comparator U1; one end of the capacitor CU2 is connected with the negative end of the storage battery pack, the other end of the capacitor CU2 is connected with one end of the capacitor CU1, and the other end of the capacitor CU1 is connected with a pin 8 of the comparator U1.
The driving circuit comprises an input resistor R9, a signal control transistor QS1 and a pull-down resistor R10, one end of the input resistor R9 is connected with a pin 1 of a comparator U1, the other end of the input resistor R9 is connected with a B pole of the signal control transistor QS1, an E pole of the signal control transistor QS1 is connected with one end of the pull-down resistor R10, the other end of the pull-down resistor R10 is connected with the negative end of a storage battery pack, and a C pole of the signal control transistor QS1 serves as the output end of the driving circuit and is connected with the.
The initiating explosive device power supply circuit comprises drive control resistors RK1 and RK2, a PMOS field effect transistor QD1, a current-limiting resistor RP1 and an electrostatic discharge resistor RK3, one end of the drive control resistor RK1 is connected with the output end of the drive circuit (the C pole of a signal control transistor QS 1), the other end of the drive control resistor RK1 is simultaneously connected with the grid G of the PMOS field effect transistor QD1 and one end of the drive control resistor RK2, the other end of the drive control resistor RK2 is connected with the source S of the PMOS field effect transistor QD1, the source S of the PMOS field effect transistor QD1 is connected with the positive end of a storage battery pack, the drain D of the PMOS field effect transistor QD1 is connected with one end of a current-limiting resistor RP1, the other end of the current-limiting resistor RP1 is connected with one end of an electrostatic discharge resistor 3.
One end of the initiating explosive device bridge wire is connected with the output end of the initiating explosive device power supply circuit, and the other end of the initiating explosive device bridge wire is connected with the negative end of the storage battery pack.
In the invention, the storage battery pack provides energy for the whole circuit.
The working principle of the circuit for accurately delaying and separating the satellite is as follows: before the separation of the star and the arrow, the MOS tubes QY1 and QY2 are in a high-resistance turn-off state. After a main satellite separation signal or a separation signal provided by a rocket is received, the detonation separation switch is switched on, the MOS tubes QY1 and QY2 are in a low-resistance conduction state, the storage battery supplies power for the delay circuit, a delay capacitor C1 in the delay circuit is charged, when the charging voltage of the delay capacitor C1 reaches a preset value, the output level of the comparator U1 is inverted into a high level, the transistor QS1 is driven to be conducted, and therefore the initiating explosive power supply circuit QD1 is controlled to be conducted, power is further provided for an initiating explosive bridge wire, and detonation separation is conducted.
The invention has not been described in detail in part of the common general knowledge of those skilled in the art.
Claims (9)
1. A circuit for accurate time delay separation for satellites is characterized in that: the ignition system comprises a storage battery pack, an autonomous power supply circuit, a delay circuit, a driving circuit, an initiating explosive device power supply circuit, an ignition separation switch and an initiating explosive device bridge wire;
before the star and the rocket are separated, the detonation separation switch is in a disconnected state, and is switched on after a main star separation signal or a separation signal provided by the rocket is received;
after the detonation separation switch is switched on, the storage battery pack supplies power to the autonomous power supply circuit;
after the autonomous power supply circuit is powered on, the power is supplied to the delay circuit;
after the delay circuit carries out accurate delay, the drive circuit is triggered;
after the driving circuit is triggered, a trigger signal is provided for the initiating explosive device power supply circuit;
the initiating explosive device power supply circuit provides detonation energy for the initiating explosive device bridge wire under the control of the trigger signal of the drive circuit, and the initiating explosive device bridge wire unlocks the satellite separating mechanism.
2. The circuit for precision time delay separation for a satellite according to claim 1, wherein: the autonomous power supply circuit comprises a resistor RY1, a resistor RY2, a resistor RY3, a resistor RY4, a PMOS field-effect tube QY1 and a PMOS field-effect tube QY2, one end of the resistor RY2 is connected with the positive end of a storage battery, the other end of the resistor RY2 is connected with a grid G of the PMOS field-effect tube QY1, one end of the resistor RY4 is connected with the positive end of the storage battery, the other end of the resistor RY4 is connected with the grid G of the PMOS field-effect tube QY2, one end of the resistor RY1 is connected with the grid G of the PMOS field-effect tube QY1, one end of the resistor RY3 is connected with the grid G of the PMOS field-effect tube QY2, the resistor RY1 is connected with the other end of the resistor RY3 to serve as the input end of the autonomous power supply circuit and connected with the detonation separation switch K1, the source S of the PMOS field-effect tube QY1 and the source S of the PMOS field-effect tube.
3. The circuit for precision time delay separation for a satellite according to claim 1, wherein: one end of the detonation separation switch is connected with the input end of the autonomous power supply circuit, and the other end of the detonation separation switch is connected with the negative end of the storage battery pack.
4. The circuit for precision time delay separation for a satellite according to claim 1, wherein: the delay circuit comprises a diode D1-1, delay resistors R1, R2 and R3, a delay capacitor C1, a comparator U1, input resistors R4 and R6, a feedback resistor R7 and a pull-up resistor R8, wherein the A pole of the diode D1-1 is connected with the output end of the autonomous power supply circuit, the K pole of a diode D1-1 is connected with one end of the delay resistor R1, the other end of the delay resistor R1 is connected with the A pole of a diode D1-1, one end of the delay resistor R2 is connected with the A pole of the diode D2-1, the other end of the delay resistor R2 is simultaneously connected with one end of the delay resistor R2 and one end of the input resistor R2, the other end of the delay resistor R2 is connected with the negative pole of the storage battery pack, one end of the delay capacitor C2 is connected with the K pole of the diode D2-1, the other end of the delay capacitor C2 is connected with the negative pole of the input resistor R2, one end of the input resistor R2 is connected with the K pole of, the other end of the input resistor R6 is connected with a pin 2 of the comparator U1, the feedback resistor R7 is connected between a pin 1 and a pin 3 of the comparator U1, one end of the pull-up resistor R8 is connected with an A pole of the diode D1-1, and the other end of the pull-up resistor R8 is connected with a pin 1 of the comparator U1; pin 4 of the comparator U1 is connected with the negative terminal of the storage battery pack, and pin 1 of the comparator U1 is the output end of the delay circuit.
5. The circuit for precision time delay separation for a satellite according to claim 4, wherein: the satellite precise time delay separation circuit further comprises a current-limiting protection circuit, and the current-limiting protection circuit realizes current-limiting protection on the time delay circuit.
6. The circuit for precision time delay separation for a satellite according to claim 5, wherein: the current-limiting protection circuit comprises a resistor RU1, a capacitor CU1 and a capacitor CU 2; one end of the resistor RU1 is connected with the A pole of the diode D1-1, and the other end of the resistor RU1 is connected with the pin 8 of the comparator U1; one end of the capacitor CU2 is connected with the negative end of the storage battery pack, the other end of the capacitor CU2 is connected with one end of the capacitor CU1, and the other end of the capacitor CU1 is connected with a pin 8 of the comparator U1.
7. The circuit for precision time delay separation for a satellite according to claim 1, wherein: the driving circuit comprises an input resistor R9, a signal control transistor QS1 and a pull-down resistor R10, one end of the input resistor R9 is connected with the output end of the delay circuit, the other end of the input resistor R9 is connected with the B pole of the signal control transistor QS1, the E pole of the signal control transistor QS1 is connected with one end of the pull-down resistor R10, the other end of the pull-down resistor R10 is connected with the negative end of a storage battery pack, and the C pole of the signal control transistor QS1 serving as the output end of the driving circuit is connected with.
8. The circuit for precision time delay separation for a satellite according to claim 1, wherein: the initiating explosive device power supply circuit comprises drive control resistors RK1 and RK2, a PMOS field effect tube QD1, a current-limiting resistor RP1 and an electrostatic discharge resistor RK3, one end of the drive control resistor RK1 is connected with the output end of the drive circuit, the other end of the drive control resistor RK1 is simultaneously connected with a grid G of the PMOS field effect tube QD1 and one end of the drive control resistor RK2, the other end of the drive control resistor RK2 is connected with a source S of the PMOS field effect tube QD1, the source S of the PMOS field effect tube QD1 is connected with the positive end of a storage battery pack, a drain D of the PMOS field effect tube QD1 is connected with one end of a current-limiting resistor RP1, the other end of the current-limiting resistor RP1 is connected with one end of an electrostatic discharge resistor RK3 to serve.
9. The circuit for precision time delay separation for a satellite according to claim 1, wherein: one end of the initiating explosive device bridge wire is connected with the output end of the initiating explosive device power supply circuit, and the other end of the initiating explosive device bridge wire is connected with the negative end of the storage battery pack.
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| CN201910901440.7A CN110789742A (en) | 2019-09-23 | 2019-09-23 | Accurate time delay separation circuit for satellite |
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| CN201910901440.7A CN110789742A (en) | 2019-09-23 | 2019-09-23 | Accurate time delay separation circuit for satellite |
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Cited By (4)
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| CN111312175A (en) * | 2020-04-22 | 2020-06-19 | 南京中电熊猫平板显示科技有限公司 | Trigger driving circuit and organic light emitting display device |
| CN112018845A (en) * | 2020-08-26 | 2020-12-01 | 中国科学院微小卫星创新研究院 | Satellite autonomous power-on system and control method thereof |
| CN112018869A (en) * | 2020-08-07 | 2020-12-01 | 航天行云科技有限公司 | Star and arrow separation is from power-on circuit independently |
| CN114572425A (en) * | 2022-04-12 | 2022-06-03 | 星众空间(西安)科技有限公司 | Multi-satellite separation controller |
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| CN114572425A (en) * | 2022-04-12 | 2022-06-03 | 星众空间(西安)科技有限公司 | Multi-satellite separation controller |
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Application publication date: 20200214 |