CN111301716B - Power supply and distribution system of multistage carrier rocket - Google Patents
Power supply and distribution system of multistage carrier rocket Download PDFInfo
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- CN111301716B CN111301716B CN202010207531.3A CN202010207531A CN111301716B CN 111301716 B CN111301716 B CN 111301716B CN 202010207531 A CN202010207531 A CN 202010207531A CN 111301716 B CN111301716 B CN 111301716B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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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
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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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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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
- 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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Abstract
The application provides a power supply and distribution system of a multistage carrier rocket, wherein independent batteries are respectively adopted at two ends of the multistage carrier rocket for power supply. The power supply and distribution system has the advantages that the characteristics of multiple stages and long length of the multi-stage carrier rocket are combined, the power supply mode at two ends is adopted, the weight of the power supply and distribution system is reduced, and the weight reduction amplitude is not less than 30%.
Description
Technical Field
The application relates to the technical field of rockets, in particular to a power supply and distribution system of a multistage carrier rocket.
Background
The liquid carrier rocket is mainly used as a carrier rocket in China, and with the rapid development of microsatellites in recent years and the increasing demand on rapid response of the rocket, the solid carrier rocket gradually ascends the historical stage, and the launching times are gradually increased. Due to the limitation of specific impulse and working time of the engine, the solid launch vehicle generally needs to adopt a four-stage engine series design to realize the orbit entering of the payload with considerable weight.
For a power supply and distribution system of a solid carrier rocket, centralized power supply is mostly adopted at present, a centralized power supply mode is mostly evolved from two-stage missile or even single-stage missile, but for the solid carrier rocket needing a four-stage engine, the power supply system is not easy to worry, especially for the requirement of long-distance instantaneous large current, the voltage drop is overlarge due to the fact that the circuit is long and the resistance is large, in order to guarantee small voltage drop, the number of wires needing to be thickened or the number of wires needing to be connected in parallel is increased, and the weight of a cable network on the rocket is greatly increased.
In addition, in the existing power supply mode, the types of the electric loads are not distinguished, namely the steady-state electric load and the instantaneous electric load are supplied with power by the same battery, the power supply mode has no great problem for a cabin section with short flight time, however, due to the launching requirements of different satellites, the upper stage of the carrier rocket possibly needs to fly for long time, and the large-current discharge capacity of the battery is reduced along with the increase of the power consumption time, and the power supply mode is particularly obvious for a lithium battery, so that the working reliability of the transient large-current electric load is reduced. In order to ensure the reliability of the operation, the existing measures are often to adopt a method for increasing the battery capacity, which greatly increases the weight of the battery of the upper stage and reduces the carrying capacity of the effective load.
Disclosure of Invention
The power supply and distribution system of the multi-stage carrier rocket is characterized in that the power supply and distribution system of the multi-stage carrier rocket is combined with the characteristics of multiple stages and long length of the multi-stage carrier rocket, the power is supplied from two ends, the weight of the power supply and distribution system is reduced, and the weight reduction amplitude is not less than 30%.
The application provides a power supply and distribution system of a multistage carrier rocket, wherein independent batteries are respectively adopted at two ends of the multistage carrier rocket for power supply.
Preferably, the multistage launch vehicle comprises a first-stage instrument cabin, a second-stage instrument cabin, a third-stage instrument cabin, a fourth-stage instrument cabin and a head, all the electric loads of the first-stage instrument cabin and the second-stage instrument cabin are powered by first batteries, and all the electric loads of the third-stage instrument cabin, the fourth-stage instrument cabin and the head are powered by second batteries.
Preferably, the multistage launch vehicle comprises a first-stage instrument cabin, a second-stage instrument cabin, a third-stage instrument cabin, a fourth-stage instrument cabin and a head, all loads of the first-stage instrument cabin and the second-stage instrument cabin are powered by third batteries, inductive loads and instantaneous pulse loads of the third-stage instrument cabin, the fourth-stage instrument cabin and the head are powered by fourth batteries, and resistive loads of the third-stage instrument cabin, the fourth-stage instrument cabin and the head are powered by fifth batteries.
Preferably, the fifth battery supplies power to a plurality of resistive loads through a power distributor, and a plurality of solid-state switches are installed in the power distributor, and each solid-state switch is connected with one resistive load; the distributor controls the solid-state switches in a time-sharing power-on mode, so that the resistive loads are powered on step by step.
Preferably, the distributor controls the solid-state switches to be powered on in a time-sharing mode through the digital bus.
Wherein, preferably, the positive end and the negative end of the instantaneous pulse load are both provided with a switch; at the moment of emission, the negative side switch of the transient pulse load is switched on.
Wherein, preferably, the negative end switch of all transient pulse loads is uniformly controlled by the total controller of the multi-stage launch vehicle.
Preferably, the transient pulse load is provided with a test circuit, and the test circuit comprises a battery, an optical coupler, a resistor and a negative terminal switch of the transient pulse load which are connected in series and used for supplying power to the transient pulse load.
Preferably, the multistage launch vehicle comprises a first-stage instrument cabin, a second-stage instrument cabin, a third-stage instrument cabin, a fourth-stage instrument cabin and a head, wherein the electric loads of the first-stage instrument cabin and the second-stage instrument cabin comprise resistive loads and instantaneous pulse loads, the electric loads of the third-stage instrument cabin, the fourth-stage instrument cabin and the head comprise resistive loads, inductive loads and instantaneous pulse loads, and the resistive loads comprise computer equipment, inertia sensitive equipment, measuring equipment and a servo mechanism; the instantaneous pulse load, the computer equipment, the inertia sensitive equipment and the measuring equipment of the first-stage instrument cabin and the second-stage instrument cabin are powered by a sixth battery; the third-level instrument cabin, the fourth-level instrument cabin and the inductive load and the instantaneous pulse load of the head are powered by a seventh battery, and the third-level instrument cabin, the fourth-level instrument cabin, the computer equipment, the inertia sensitive equipment and the measuring equipment of the head are powered by an eighth battery; the servo mechanisms of the first-stage instrument cabin, the second-stage instrument cabin, the third-stage instrument cabin and the fourth-stage instrument cabin are respectively supplied with power by adopting independent high-voltage servo thermal batteries.
The beneficial effect of this application is as follows:
1. the power supply and distribution system has the advantages that the characteristics of multiple stages and long length of the multi-stage carrier rocket are combined, the power supply mode at two ends is adopted, the weight of the power supply and distribution system is reduced, and the weight reduction amplitude is not less than 30%.
2. The power supply battery is divided according to the characteristics of different loads, the load which needs to work for a long time and needs to use the instantaneous large current and the steady-state resistive load adopt different batteries to supply power independently, the capacity of the batteries is fully utilized to the maximum extent, and the safety and the reliability of a power supply system are ensured.
3. The power distribution device adopts a time-sharing power-on strategy for a plurality of resistive loads on the same power supply battery, reduces damage to the power distribution device, and prolongs the service life of the power distribution device.
4. The negative end of the instantaneous pulse load is provided with the switch, the on state of the instantaneous pulse load is tested through the test circuit at the emission moment, and the safety of the ignition circuit of the instantaneous pulse load is ensured.
5. This application uses the thermal battery to supply power for servo, but thermal battery angle arbitrary activation, work, are suitable for servo's multi-angle motion.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings can be obtained by those skilled in the art according to the drawings.
Fig. 1 is a structural diagram of a power supply and distribution system according to an embodiment of the present application;
fig. 2 is a structural diagram of a power supply and distribution system according to a second embodiment of the present application;
fig. 3 is a power supply and distribution system structure diagram provided in the third embodiment of the present application.
Detailed Description
The technical solutions in the embodiments of the present application are clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The electric load of the multi-stage carrier rocket mainly comprises seven types of computer equipment, inertia sensitive equipment, a servo mechanism, attitude control equipment, measuring equipment, an electric separation device, initiating explosive devices and the like, wherein the computer equipment comprises a flight control machine, controllers at all stages and the like, and the attitude control equipment comprises attitude control equipment, rail control equipment, rolling control equipment and the like.
These seven classes of electrical devices can be divided into three main classes: resistive load, inductive load, and transient pulse load. The resistive load comprises computer equipment, inertia sensitive equipment, a servo mechanism and measuring equipment, the inductive load comprises attitude control equipment and an electric separation device, and the transient pulse load mainly refers to initiating explosive devices.
Because the length of multistage carrier rocket is big, long distance power supply can cause the pressure drop great, consequently, in this application, the both ends of multistage carrier rocket adopt independent battery power supply respectively to reduce the length of power supply cable, reduce the weight of cable network when improving the reliability.
In the present application, the battery is preferably a lithium battery.
The following is an example of a four-stage solid launch vehicle. The four-stage solid carrier rocket comprises a first-stage instrument cabin, a second-stage instrument cabin, a third-stage instrument cabin, a four-stage instrument cabin and a head, wherein the electric loads of the first-stage instrument cabin and the second-stage instrument cabin comprise resistive loads and instantaneous pulse loads, and the electric loads of the third-stage instrument cabin, the four-stage instrument cabin and the head comprise resistive loads, inductive loads and instantaneous pulse loads.
Example one
Fig. 1 is a power supply and distribution system structure diagram according to an embodiment of the present application. As shown in fig. 1, the resistive load and the transient pulse load of the primary instrument chamber and the secondary instrument chamber are all powered by the same battery-secondary lithium battery, and the resistive load, the inductive load and the transient pulse load of the tertiary instrument chamber, the quaternary instrument chamber and the head are all powered by the same battery-head lithium battery.
Compared with the prior art, the length of the power supply cable is reduced, the reliability of the launch vehicle is improved, and meanwhile the weight of the cable network is reduced.
Example two
Fig. 2 is a power supply and distribution system structure diagram provided in the second embodiment of the present application. As shown in fig. 2, the resistive load and the transient pulse load of the first-stage instrument chamber and the second-stage instrument chamber are both powered by the same battery-second lithium battery, the resistive load of the third-stage instrument chamber, the fourth-stage instrument chamber and the head is powered by the same battery-first head lithium battery, and the inductive load and the transient pulse load of the third-stage instrument chamber, the fourth-stage instrument chamber and the head are powered by the same battery-second head lithium battery.
The flight time of the rocket head cabin section is longer, and the phenomenon of more serious voltage head lowering can be caused when the lithium battery provides pulse current after working for a long time, and other electric equipment can be influenced. Inductive loads such as an electromagnetic coil with inductive characteristics can generate electromagnetic pulse interference signals due to sudden current change, the electromagnetic interference signals have large instantaneous current, but have short action time and low energy, can influence the normal work of electronic components, and are not enough to electrically explode the initiating explosive devices.
Therefore, the same battery is used for supplying power to an inductive load with large instantaneous current and short action time and an instantaneous pulse load working for a long time, and the other battery is used for supplying power to a resistive load, so that the stability and purity of the working voltage of the resistive load are ensured to the greatest extent, and the reliability of the system is improved.
The electric loads of the multi-stage carrier rocket are mostly concentrated at the head, the power supply current of the power distributor is larger, and particularly the pulse current at the power-on moment is larger. Along with the increase of electromagnetic interference and protection requirements, a large number of capacitors are added to the power supply module end of a plurality of power loads for electromagnetic filtering, and the electrified instantaneous pulse current is further increased.
Preferably, a plurality of solid-state switches are installed in the power distributor, each solid-state switch is connected with one resistive load, and the power distributor controls the plurality of solid-state switches in a time-sharing power-on mode to enable the plurality of resistive loads to be powered on step by step, so that the reliability of components is improved, and the service life of the components is prolonged.
For example, the total current of the distributor is distributed to a plurality of resistive loads controlled by the distributor, and the plurality of resistive loads are controlled to be sequentially powered on by sequentially switching on the solid-state switches, so that damage of an overlarge instantaneous current to circuit devices such as a relay is avoided.
Further, the distributor controls the solid-state switches to be powered on in a time-sharing mode through the digital bus.
Preferably, the positive end and the negative end of the instantaneous pulse load are both provided with a switch, and the master controller uniformly controls the positive end switch and the negative end switch of the instantaneous pulse load so as to ensure the safety of the ignition circuit of the instantaneous pulse load. During the ignition process of the instantaneous pulse load, the master controller simultaneously controls the positive end switch and the negative end switch of the instantaneous pulse load. Near the moment of transmission, the negative side switch of the momentary pulse load is switched on.
Further, a test circuit is arranged on the instantaneous pulse load to test the circuit-on state of the instantaneous pulse load at the moment of transmission.
Specifically, the testing circuit of the transient pulse load is that a parallel circuit is added on an ignition circuit of the transient pulse load, the ignition circuit of the transient pulse load at least comprises a lithium battery, the transient pulse load and a positive end switch and a negative end switch of the transient pulse load, the lithium battery, an optical coupler, a resistor and the negative end switch of the transient pulse load are connected in series to form the testing circuit, one end of the optical coupler is connected with the negative end switch and the negative end of the transient pulse load, the other end of the optical coupler is connected with one end of the resistor, and the other end of the resistor is connected with the positive end of the lithium battery. And after the negative terminal switch is switched on, the optical coupler is switched on, so that the test of the ignition circuit is realized.
EXAMPLE III
Fig. 3 is a power supply and distribution system structure diagram provided in the third embodiment of the present application. As shown in fig. 3, the servomechanisms of the first-stage instrument capsule, the second-stage instrument capsule, the third-stage instrument capsule and the fourth-stage instrument capsule are respectively powered by independent thermal batteries; instantaneous pulse loads of the primary instrument cabin and the secondary instrument cabin and resistive loads outside the servo mechanism (namely computer equipment, inertia sensitive equipment and measuring equipment) are powered by the same battery-secondary lithium battery; resistive loads (namely computer equipment, inertia sensitive equipment and measuring equipment) outside the servo mechanisms of the third-stage instrument cabin, the fourth-stage instrument cabin and the head are powered by the same battery-third head lithium battery, and inductive loads and instantaneous pulse loads of the third-stage instrument cabin, the fourth-stage instrument cabin and the head are powered by the same battery-fourth head lithium battery.
The thermal battery is a molten salt electrolyte storage battery, the electrolyte is non-conductive solid at normal temperature, and when the thermal battery is used, a fire cap is impacted or an electric ignition head is ignited to ignite a firework heat source in the thermal battery unit, so that the electrolyte is molten, and the thermal battery pack is activated. The battery has short activation time (less than or equal to 1.5s), wide use temperature range (minus 55 to +85 ℃), strong heavy current pulse discharge capacity and long storage time, needs to be used immediately after the battery is activated, can be activated and operated at any angle, and is particularly suitable for supplying power to high-power high-voltage electric equipment on arrows, such as electric servos and the like.
The beneficial effect of this application is as follows:
1. the power supply and distribution system has the advantages that the characteristics of multiple stages and long length of the multi-stage carrier rocket are combined, the power supply mode at two ends is adopted, the weight of the power supply and distribution system is reduced, and the weight reduction amplitude is not less than 30%.
2. The power supply battery is divided according to the characteristics of different loads, the load which needs to work for a long time and needs to use the instantaneous large current and the steady-state resistive load adopt different batteries to supply power independently, the capacity of the batteries is fully utilized to the maximum extent, and the safety and the reliability of a power supply system are ensured.
3. The power distribution device adopts a time-sharing power-on strategy for a plurality of resistive loads on the same power supply battery, reduces damage to the power distribution device, and prolongs the service life of the power distribution device.
4. The negative end of the instantaneous pulse load is provided with the switch, the on state of the instantaneous pulse load is tested through the test circuit at the emission moment, and the safety of the ignition circuit of the instantaneous pulse load is ensured.
5. This application uses the thermal battery to supply power for servo, but thermal battery angle arbitrary activation, work, are suitable for servo's multi-angle motion.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application. It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (9)
1. The power supply and distribution system of the multistage carrier rocket is characterized in that two ends of the multistage carrier rocket are respectively supplied with power by adopting independent batteries;
the multistage carrier rocket comprises a first-stage instrument cabin, a second-stage instrument cabin, a third-stage instrument cabin, a fourth-stage instrument cabin and a head, wherein all loads of the first-stage instrument cabin and the second-stage instrument cabin are powered by third batteries, inductive loads and instantaneous pulse loads of the third-stage instrument cabin, the fourth-stage instrument cabin and the head are powered by fourth batteries, and resistive loads of the third-stage instrument cabin, the fourth-stage instrument cabin and the head are powered by fifth batteries;
the resistive load comprises computer equipment, inertia sensitive equipment and measuring equipment; the inductive load comprises attitude control equipment and an electric separation device, and the instantaneous pulse load refers to an initiating explosive device;
and servo mechanisms of the first-stage instrument cabin, the second-stage instrument cabin, the third-stage instrument cabin and the fourth-stage instrument cabin are respectively supplied with power by adopting independent high-voltage servo thermal batteries.
2. The power supply and distribution system of claim 1, wherein the multi-stage launch vehicle comprises a primary instrument bay, a secondary instrument bay, a tertiary instrument bay, a quaternary instrument bay, and a head, all electrical loads of the primary instrument bay and the secondary instrument bay being powered by a first battery, and all electrical loads of the tertiary instrument bay, the quaternary instrument bay, and the head being powered by a second battery.
3. The power supply and distribution system of claim 1, wherein the fifth battery supplies power to a plurality of resistive loads through a power distributor having a plurality of solid state switches mounted therein, each of the solid state switches being connected to one of the resistive loads;
and the distributor controls the solid-state switches in a time-sharing power-on mode to enable the resistive loads to be powered on step by step.
4. The power supply and distribution system of claim 3, wherein the power distributor controls the plurality of solid state switches to power up in a time-shared manner via a digital bus.
5. The power supply and distribution system of claim 2 wherein the positive and negative terminals of the pulsed transient load are each provided with a switch; and at the transmitting moment, a negative terminal switch of the instantaneous pulse load is switched on.
6. The power supply and distribution system of claim 1 wherein the positive and negative terminals of the pulsed transient load are each provided with a switch; and at the transmitting moment, a negative terminal switch of the instantaneous pulse load is switched on.
7. The power supply and distribution system according to claim 5 or 6, wherein the negative side switches of all transient pulse loads are uniformly controlled by the general controller of the multi-stage launch vehicle.
8. The power distribution system of claim 5 or 6, wherein the pulsed transient load is provided with a test circuit comprising a battery, an optocoupler, a resistor and a negative side switch of the pulsed transient load connected in series for powering the pulsed transient load.
9. The power supply and distribution system of claim 1, wherein the multi-stage launch vehicle comprises a primary instrument bay, a secondary instrument bay, a tertiary instrument bay, a quaternary instrument bay, and a head, the electrical loads of the primary and secondary instrument bays comprising resistive loads and transient impulse loads, the electrical loads of the tertiary instrument bay, the quaternary instrument bay, and the head comprising resistive loads, inductive loads, and transient impulse loads, the resistive loads comprising computer equipment, inertial sensitive equipment, measurement equipment, servomechanisms;
the instantaneous pulse load, the computer equipment, the inertia sensitive equipment and the measuring equipment of the primary instrument cabin and the secondary instrument cabin are powered by a sixth battery;
the third-level instrument cabin, the fourth-level instrument cabin and the inductive load and the transient pulse load of the head are powered by a seventh battery, and the third-level instrument cabin, the fourth-level instrument cabin and the computer equipment, the inertia sensitive equipment and the measuring equipment of the head are powered by an eighth battery.
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| CN202010207531.3A CN111301716B (en) | 2020-03-23 | 2020-03-23 | Power supply and distribution system of multistage carrier rocket |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112165141B (en) * | 2020-10-15 | 2022-05-20 | 北京中科宇航技术有限公司 | Carrier rocket digital power supply and distribution control system and test method thereof |
| CN112462273B (en) * | 2020-10-23 | 2023-03-28 | 北京空间飞行器总体设计部 | Flight event driven upper-level satellite assembly power supply capability verification system and method |
| CN114759621B (en) * | 2022-06-14 | 2023-02-21 | 东方空间技术(北京)有限公司 | Power supply and distribution method for multistage bundled carrier rocket and multistage bundled carrier rocket |
| CN116110268B (en) * | 2023-04-17 | 2023-07-07 | 北京星途探索科技有限公司 | Signal simulation equipment for teaching of carrier rocket measurement system |
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