CN212085877U - Large-scale unmanned aerial vehicle power supply redundancy system - Google Patents
Large-scale unmanned aerial vehicle power supply redundancy system Download PDFInfo
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- CN212085877U CN212085877U CN202020329107.1U CN202020329107U CN212085877U CN 212085877 U CN212085877 U CN 212085877U CN 202020329107 U CN202020329107 U CN 202020329107U CN 212085877 U CN212085877 U CN 212085877U
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Abstract
A power supply redundancy system of a large unmanned aerial vehicle comprises a power supply module A, wherein the power supply module A comprises a generator module A1 and an emergency battery module A2 which are mutually connected in parallel, the generator module A1 at least comprises a No. 1 generator A11 and a No. 2 generator A12 which are connected in parallel, and the redundancy design of the power supply module is realized; the power supply system also comprises a circuit distribution module B which is connected with the power supply module A in series, wherein the circuit distribution module B is provided with a bus bar, and the functions of convergence and distribution of the circuit of the power supply module A and system fault isolation and switching are realized through the bus bar; the circuit distribution module B is also provided with a voltage acquisition module and a control module B12, the voltage acquisition module is connected with the bus bar in series, and the control module B12 acquires signals from the voltage acquisition module. The arrangement of the structure greatly improves the flight safety, and through the design of the redundancy of the power supply system, the fault tolerance of the power supply equipment is improved, so that the reliability of the airplane is improved.
Description
Technical Field
The utility model belongs to unmanned aerial vehicle power supply field, concretely relates to large-scale unmanned aerial vehicle power supply redundancy system.
Background
With the development of unmanned aerial vehicle technology in China, the unmanned aerial vehicle technology in China is developed rapidly in recent years. According to the application characteristics of different industry fields, the development of unmanned aerial vehicles has also appeared. There are generally two categories according to the height of use: one type is a medium and low altitude unmanned aerial vehicle, generally has the characteristics of low, small and slow, and has small use radius and relatively low whole manufacturing cost. The other type is a medium-high altitude unmanned aerial vehicle, the use radius is large, the manufacturing cost is high, the integration level is complex, and higher requirements are provided for the flight safety of the aircraft. If there is not reliable stable power supply, unmanned aerial vehicle entire system will be unable to work, and in unmanned aerial vehicle development history, because the accident that power supply trouble caused does not take a winner of the number, especially well high altitude, long endurance class unmanned aerial vehicle.
The unmanned aerial vehicle electrical system generally comprises three parts of a power supply, a power distribution system and electric equipment, wherein the combination of the power supply and the power distribution system is collectively called a power supply system. The power supply system has the function of providing electric energy meeting the preset design requirements for each electric system or equipment of the unmanned aerial vehicle, the electric system of the unmanned aerial vehicle can be divided into an airborne electric system and a ground electric system according to the position of the electric system, and the airborne electric system mainly comprises a main power supply, an emergency power supply and a control protection device and auxiliary equipment of the electric equipment. The power supply of the airborne electrical system generally refers to a power generation device directly driven by a main power device of the unmanned aerial vehicle, and a power battery of the electric unmanned aerial vehicle provides power for the unmanned aerial vehicle. On large-scale unmanned aerial vehicle, power battery for the adaptation with electric unmanned aerial vehicle is unmanned aerial vehicle power supply promptly. On some large-scale unmanned aerial vehicles, in order to adapt to different requirements of power utilization systems or equipment on power supply types, a conversion power supply is further arranged according to needs, once a main power supply system breaks down, an emergency power supply is needed, and sufficient electric energy is provided for the systems or equipment which are needed by safe flight and return landing of the unmanned aerial vehicle. Power distribution systems should deliver power reliably and efficiently to various electrical systems and devices. The power distribution system consists of transmission wires and a control and protection device. For important systems or equipment, multiple independent power supply measures are also needed. When local faults occur in the power distribution system, the parts which do not have faults cannot be influenced in an expanding mode, and the safety of the unmanned aerial vehicle cannot be endangered.
Because large-scale unmanned aerial vehicle flying height generally is at high-altitude, and the time of endurance is long, adopts the scheme of independent battery power supply infeasible, adopts aeroengine to drive the generator and generates electricity usually, lasts to the airborne equipment power supply. However, the phenomena that the engine stops at high altitude and the rotating speed of the engine is lower than that required by the work of the generator occur, power supply faults are caused, and great threats are brought to flight safety. At present, the power supply system of the domestic unmanned aerial vehicle generally adopts a single equipment power supply mode. The single power supply mode is simple in design and single in control, but the safety factor is lower. Once the power supply fails, the airplane can be out of control and even crashed.
Disclosure of Invention
In view of the above problems, the present invention provides a power supply redundancy system for a large unmanned aerial vehicle, which changes the scheme of mutual backup switching of two generators into automatic switching, automatically detects the power supply failure of the generators, and automatically switches to another generator when one generator fails; the design of the emergency battery is added, when the two generators have power supply faults simultaneously, the emergency battery supplies power, the flight safety is greatly improved, and the fault tolerance of the power supply equipment is improved through the design of the redundancy of the power supply system, so that the reliability of the airplane is improved.
In order to achieve the above object, the utility model discloses the technical scheme who takes includes:
a power supply redundancy system of a large unmanned aerial vehicle comprises a power supply module, wherein the power supply module comprises a generator module and an emergency battery module which are connected in parallel, the generator module at least comprises a No. 1 generator and a No. 2 generator which are connected in parallel, and the redundancy design of the power supply module is realized; the power supply module is connected with the power supply module in series, and the power supply module is provided with a bus bar which is used for realizing the functions of convergence and distribution of a power supply module circuit, system fault isolation and switching; the circuit distribution module is also provided with a voltage acquisition module and a control module, the voltage acquisition module is connected with the bus bar in series, and the control module acquires signals from the voltage acquisition module.
Optionally, the voltage acquisition module comprises a voltage acquisition module No. 1 and a voltage acquisition module No. 2, and the bus bar comprises a bus bar No. 1 and a bus bar No. 2; no. 1 generator, No. 1 voltage acquisition module and No. 1 busbar establish ties in proper order, and No. 2 generators, No. 2 voltage acquisition module and No. 2 busbars establish ties in proper order.
Optionally, a contactor 1 is connected between the generator 1 and the voltage acquisition module 1B 6.
Optionally, the No. 1 generator is connected in series with the No. 2 bus bar, and the No. 2 contactor is connected between the No. 1 generator and the No. 2 bus bar.
Optionally, the emergency battery module is connected in series with the bus bar No. 2, and a switch is connected between the emergency battery module and the bus bar No. 2.
The system further comprises a solid-state power control module which is connected with the circuit distribution module in series, wherein the solid-state power control module realizes on-off control of a load power supply, overload and short-circuit protection of a load and acquisition and report of electrical parameters of the load.
Optionally, the solid state power control module is divided into type I SSPCs including type 1 SSPCs, type 2 SSPCs, and type II SSPCs including type 4 SSPCs.
And the power supply processing module is connected with the circuit distribution module, collects signals of the power supply module and sends instructions to the No. 1 contactor, the No. 2 contactor and the switch.
Optionally, the bus bar B4 # 1 divides the circuit into a line (a) and a line (c); the line (4) is connected with the 4# SSPC in series; line (c) is in series connection with No. 4 contactor, No. 3 busbar and No. 3 SSPC in proper order.
Optionally, the bus bar B5 # 2 divides the circuit into a first line and a second line; a circuit is connected with a 1# SSPC in series; line 2 is connected in series with No. 3 contactor, No. 4 bus bar and No. 2 SSPC.
Compared with the prior art, the utility model, following technological effect has:
(1) the utility model discloses a large-scale unmanned aerial vehicle power supply redundancy system, change the scheme of the mutual backup switching of two generators into automatic switching, the automatic detection generator power supply trouble, when a generator breaks down, automatic switching to another generator; the design of the emergency battery is added, when the two generators have power supply faults at the same time, the emergency battery supplies power, and the flight safety is greatly improved.
(2) The utility model discloses a large-scale unmanned aerial vehicle power supply redundancy system, the design method is novel, and the traditional design theory of change through the design of power supply system redundancy, improves the power supply unit fault-tolerance, and then provides the reliability of aircraft.
(3) The utility model discloses a large-scale unmanned aerial vehicle power supply redundancy system, the design of circuit distribution module has very big promotion to the stability that provides the power supply, and switching value signal acquisition handles's design provides very accurate parameter for the switching between the entire system.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a functional block diagram of the system of the present invention;
fig. 2 is a functional block diagram of a primary power distribution apparatus provided by the present invention;
a power supply module; a1 generator module; a111 generator; a generator No. A122; a2 emergency battery module; a21 emergency battery; a22 constant voltage current limiting module; b, a circuit distribution module; contactor number B11; contactor number B22; a B3 switch; bus bar No. B41; bus bar No. B52; a voltage acquisition module No. B61; a voltage acquisition module No. B72; contactor number B83; contactor number B94; bus bar No. B103; bus bar No. B114; a B12 control module; c, a solid-state power control module; c11 # SSPC; c22 # SSPC; c33 # SSPC; c44 # SSPC; d, a power supply processing module; and E, a flight control platform.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings, which are provided for purposes of illustration and not limitation.
A power supply redundancy system of a large unmanned aerial vehicle comprises a power supply module A, wherein the power supply module A comprises a generator module A1 and an emergency battery module A2 which are mutually connected in parallel, the generator module A1 at least comprises a No. 1 generator A11 and a No. 2 generator A12 which are connected in parallel, and the redundancy design of the power supply module is realized; the power supply system also comprises a circuit distribution module B which is connected with the power supply module A in series, wherein the circuit distribution module B is provided with a bus bar, and the functions of convergence and distribution of the circuit of the power supply module A and system fault isolation and switching are realized through the bus bar; the circuit distribution module B is also provided with a voltage acquisition module and a control module B12, the voltage acquisition module is connected with the bus bar in series, and the control module B12 acquires signals from the voltage acquisition module. Three-phase alternating current output by the No. 1 generator A11 and the No. 2 generator A12 is rectified, input filtered and then output into 28V direct current through isolation transformation and filtering. The emergency battery module a2 is that the ac power output by the emergency battery a21 outputs 28V dc power through the constant voltage current limiting module a 22. The bus bar is divided into a No. 1 bus bar B4 and a No. 2 bus bar B5, the No. 1 bus bar B4 is used for the convergence of No. 1 generator A11 electric energy, the No. 2 bus bar B5 is used for the convergence of No. 1 generator A11, No. 2 generator A12 and emergency battery module A2 electric energy, the centralized electric energy distribution and the line protection are realized by adopting the relay and contactor technology, and the electric energy is respectively supplied to different airborne equipment. The control module B12 is used for acquiring signals from the voltage acquisition module, the scheme of mutual backup switching of the double generators is changed into automatic switching, the power supply fault of the generators is automatically detected, and when one generator has a fault, the other generator is automatically switched to; the design of the emergency battery is increased, when the two generators have power supply faults simultaneously, the emergency battery supplies power, and through the design of the redundancy of the power supply system, the fault tolerance of the power supply equipment is improved, the reliability of the airplane is further improved, and the flight safety is greatly improved.
The voltage acquisition modules comprise a No. 1 voltage acquisition module B6 and a No. 2 voltage acquisition module B7, and the bus bars comprise a No. 1 bus bar B4 and a No. 2 bus bar B5; the No. 1 generator A11, the No. 1 voltage acquisition module B6 and the No. 1 bus bar B4 are sequentially connected in series, and the No. 2 generator A12, the No. 2 voltage acquisition module B7 and the No. 2 bus bar B5 are sequentially connected in series. And a No. 1 contactor B1 is connected between the No. 1 generator A11 and the No. 1 voltage acquisition module B6. Generator No. 1 a11 and bus bar No. 2B 5 are connected in series, and contactor No. 2B 2 is connected between generator No. 1 a11 and bus bar No. 2B 5. The control module B12 can be selected from a control board. The No. 1 generator A11, the No. 1 contactor B1, the No. 1 voltage acquisition module B6 and the No. 1 bus bar B4 which are sequentially connected in series form a first line; the contact No. 1B 1 is used for controlling connection/disconnection of the first line. The No. 2 generator A12, the No. 2 voltage acquisition module B7 and the No. 2 bus bar B5 which are connected in series in sequence form a second line. The No. 1 generator A11, the No. 2 contactor B2 and the No. 2 bus bar B5 which are sequentially connected in series form a third line, and the No. 2 contactor B2 is used for controlling connection/disconnection of the third line. When the contactor B1 works normally, the output voltages of the generator A11 and the generator A12 are basically consistent, the voltages of the bus bar B4 and the bus bar B5 of the No. 1 and the bus bar B2, which are acquired by the voltage acquisition module B6 and the voltage acquisition module B7 of the No. 1 and the voltage acquisition module B7, are basically consistent, and at the moment, the two generators simultaneously supply power to airborne equipment and respectively bear the load of part of the airborne equipment; when the generator a11 or the generator a12 has a fault, that is, when the voltage difference between the bus bar B4 acquired by the voltage acquisition module B6 and the voltage acquisition module B7B 2 and the bus bar B5B 1 is large, the control module B12 controls the contactor B2B 2 to be closed, at this time, the bus bar B4 and the bus bar B5B 2 are communicated, and the load is completely switched to the normal generator. The system changes the scheme of mutual backup switching of the double generators into automatic switching, automatically detects the power supply fault of the generators, and automatically switches to the other generator when one generator has a fault through the redundancy design of a power supply system, so that the fault tolerance of power supply equipment is improved, the reliability of an airplane is further improved, and the flight safety is greatly improved.
The emergency battery module A2 and the No. 2 bus bar B5 are connected in series, and a switch B3 is connected between the emergency battery module A2 and the No. 2 bus bar B5. The emergency battery module A2, the switch B3 and the No. 2 bus bar B5 which are connected in series in sequence form a fourth circuit. When the No. 1 generator A11 and the No. 2 generator A12 simultaneously have faults or the load capacity is not enough to cause serious voltage drop, the emergency battery module A2 is communicated with the No. 2 bus bar B5, the first line, the third line and the fourth line are sequentially connected in series, and the load is completely transferred to the emergency battery module A2. The emergency battery A21 meets the power consumption requirement of key equipment on the airplane for at least 60min under the condition that the airplane generator module A1 fails, and the safe recovery of the airplane is guaranteed; the emergency battery module A2 is responsible for monitoring the charge-discharge state of the emergency battery of the unmanned aerial vehicle, controlling the charging current of the storage battery, and starting and turning off the storage battery heating function according to the temperature of the storage battery. When two generators have power supply faults simultaneously, the emergency battery supplies power, and the design of the redundancy of the power supply system improves the fault tolerance of power supply equipment, further improves the reliability of the airplane and greatly improves the flight safety.
The load power supply switching control circuit also comprises a solid power control module C connected with the circuit distribution module B in series, wherein the solid power control module C realizes the switching control of a load power supply, the overload and short-circuit protection of a load and the collection and report of electrical parameters of the load. The solid state power control module C is classified into type I SSPCs, including 1# SSPCC1, 2# SSPC C2, and 3# SSPC C3, and type II SSPCs, including 4# SSPCC 4. The I-type SSPC solid-state power control module C is externally connected with each airborne device or platform to monitor the working state of the externally connected device.
The power supply processing module D collects signals of the power supply module A and sends instructions to the No. 1 contactor B1, the No. 2 contactor B2 and the switch B3. And the power supply processing module D converts the collected analog models into digital signals and sends the digital signals to the externally connected flight control platform E.
The No. 1 bus bar B4 divides the circuit into a circuit (a) and a circuit (c); line 4# SSPCC4 in series; line (c) is connected in series with contactor No. 4B 9, bus bar No. 3B 10 and SSPCC # 3B 3. The bus bar B5 No. 2 divides the circuit into a first line and a second line; line (1) is connected with 1# SSPCC1 in series; line 2 connects in series, in order, contactor No. 3B 8, busbar No. 4B 11 and SSPCC # 2B 2. SSPCs with different powers are selected according to different airborne equipment in actual use. The circuit I and the circuit IV are externally connected with airborne key equipment and always kept electrified; and the circuit II and the circuit III control the opening/closing of the No. 3 contactor B8 and the No. 4 contactor B9 by the control module B12 according to the actual requirements of externally connected equipment, so that whether the circuit II and the circuit III are communicated and electrified is realized. Namely, the emergency battery A21 loads the power consumption requirement of the whole unmanned aerial vehicle under the condition that the aircraft generator module A1 fails, so that on the premise of ensuring the flight safety of the aircraft, the power consumption of some unnecessary airborne equipment is avoided, and the emergency battery A21 is ensured to meet the power consumption requirement of the key equipment on the aircraft for at least 60 min.
The preferred embodiments of the present disclosure are described in detail with reference to the accompanying drawings, however, the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solution of the present disclosure within the technical idea of the present disclosure, and these simple modifications all belong to the protection scope of the present disclosure.
It should be noted that, in the foregoing embodiments, various features described in the above embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, various combinations that are possible in the present disclosure are not described again.
In addition, any combination of the various embodiments of the present disclosure can be made, and the same should be considered as the inventive content of the present disclosure, as long as the combination does not depart from the spirit of the present disclosure.
Claims (10)
1. The power supply redundancy system of the large unmanned aerial vehicle is characterized by comprising a power supply module (A), wherein the power supply module (A) comprises a generator module (A1) and an emergency battery module (A2) which are connected in parallel, the generator module (A1) at least comprises a No. 1 generator (A11) and a No. 2 generator (A12) which are connected in parallel, and the redundancy design of the power supply module is realized;
the circuit distribution module (B) is connected with the power supply module (A) in series, and is provided with a bus bar, so that the functions of convergence and distribution of the circuit of the power supply module (A) and system fault isolation and switching are realized through the bus bar;
the circuit distribution module (B) is also provided with a voltage acquisition module and a control module (B12), the voltage acquisition module is connected with the bus bar in series, and the control module (B12) acquires signals from the voltage acquisition module.
2. The large unmanned aerial vehicle power supply redundancy system of claim 1, wherein the voltage acquisition modules comprise voltage acquisition module No. 1 (B6) and voltage acquisition module No. 2 (B7), and the bus bars comprise bus bar No. 1 (B4) and bus bar No. 2 (B5);
no. 1 generator (A11), No. 1 voltage acquisition module (B6) and No. 1 busbar (B4) connect in series in proper order, No. 2 generator (A12), No. 2 voltage acquisition module (B7) and No. 2 busbar (B5) connect in series in proper order.
3. The power supply redundancy system for large unmanned aerial vehicles according to claim 2, wherein a contactor 1 (B1) is connected between the generator 1 (a11) and the voltage acquisition module 1 (B6).
4. The power supply redundancy system for large unmanned aerial vehicles according to claim 3, wherein the No. 1 generator (A11) and the No. 2 bus bar (B5) are connected in series, and the No. 2 contactor (B2) is connected between the No. 1 generator (A11) and the No. 2 bus bar (B5).
5. The power supply redundancy system for large unmanned aerial vehicles according to claim 4, wherein the emergency battery module (A2) and the No. 2 bus bar (B5) are connected in series, and a switch (B3) is connected between the emergency battery module (A2) and the No. 2 bus bar (B5).
6. The power supply redundancy system of the large unmanned aerial vehicle according to claim 5, further comprising a solid state power control module (C) connected in series with the circuit distribution module (B), wherein the solid state power control module (C) implements on-off control of a load power supply, overload and short circuit protection of a load, and acquisition and reporting of electrical parameters of the load.
7. The large drone power redundancy system according to claim 6, wherein the solid state power control modules (C) are divided into type I SSPCs comprising 1# SSPC (C1), 2# SSPC (C2) and 3# SSPC (C3) and type II SSPC comprising 4# SSPC (C4).
8. The power supply redundancy system for large unmanned aerial vehicles according to claim 7, further comprising a power supply processing module (D) connected to the circuit distribution module (B), wherein the power supply processing module (D) collects signals of the power supply module (a) and sends commands to the contactor No. 1 (B1), the contactor No. 2 (B2) and the switch (B3).
9. The large unmanned aerial vehicle power supply redundancy system of claim 8, wherein the number 1 bus bar (B4) divides a circuit into line (a) and line (a);
line 4# SSPC (C4) in series;
line (C) is connected in series with contactor No. 4 (B9), bus bar No. 3 (B10) and SSPC No. 3 (C3).
10. A large unmanned aerial vehicle powered redundancy system according to claim 8 or 9, wherein the No. 2 bus bar (B5) divides the circuit into line (r) and line (ii);
line (r) is connected in series with # 1 SSPC (C1);
line (C) connects in series the contactor No. 3 (B8), the busbar No. 4 (B11) and the SSPC No. 2 (C2) in this order.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114348279A (en) * | 2021-12-24 | 2022-04-15 | 石家庄飞机工业有限责任公司 | General aircraft distribution device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114348279A (en) * | 2021-12-24 | 2022-04-15 | 石家庄飞机工业有限责任公司 | General aircraft distribution device |
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