CN210977704U - Engine ignition oxygen supplement device for bomb - Google Patents
Engine ignition oxygen supplement device for bomb Download PDFInfo
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- CN210977704U CN210977704U CN201922166531.9U CN201922166531U CN210977704U CN 210977704 U CN210977704 U CN 210977704U CN 201922166531 U CN201922166531 U CN 201922166531U CN 210977704 U CN210977704 U CN 210977704U
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Abstract
The embodiment of the utility model discloses bullet is with engine ignition oxygenating device, include: the flame-throwing nozzle, the oxygen supply nozzle, the igniter, the oxygen storage device and the electric connector are arranged on the aircraft engine; one end of the electric connector is respectively connected with the igniter and the oxygen storage device, the other end of the electric connector is connected with the engine control system, the flame jet is connected with the igniter, the oxygen supply port is connected with the oxygen storage device, and the flame jet and the oxygen supply port are arranged in a combustion chamber of the aircraft engine; and receiving a current instruction sent by an engine control system through an electric connector, and carrying out ignition operation and oxygen supplement operation according to the current instruction. The embodiment of the utility model provides an increase the function of storing oxygen in bullet engine point firearm, when the engine was igniteed at the high altitude, oxygen released simultaneously, made the engine fire successfully, solved current bullet engine oxygenating device and needed certain space installation oxygen cylinder and pipeline to and there is the gas leakage risk scheduling problem in the pipe connection department.
Description
Technical Field
The application relates to the technical field of engine accessories, in particular to an ignition oxygenating device of an engine for bombs.
Background
When the air-surface missile engine is ignited and started at high altitude, the engine cannot be fully combusted due to insufficient oxygen at the high altitude, so that ignition and starting failure is caused.
In order to improve the reliability of high-altitude ignition of the missile engine, oxygen is supplemented to the engine in the ignition starting stage of the missile engine, so that the oxygen can be fully combusted, and the engine can be successfully ignited. The traditional engine oxygen supplementing device for the bomb generally adopts a high-pressure oxygen cylinder installed on a bomb body and is connected with the engine through a pipeline to supplement oxygen for the engine. The method can solve the problem of oxygen deficiency when the engine is started, but has certain defects, the missile needs a certain space to install an oxygen cylinder and a pipeline, and the joint of the pipeline has the risk of air leakage, so a new technical scheme is needed to solve the problem.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the embodiment of the utility model provides an engine ignition oxygenating device is used to bullet to solve current engine oxygenating device is used to bullet and need certain space installation oxygen cylinder and pipeline, and there is the risk scheduling problem of leaking gas in the tube coupling department.
The embodiment of the utility model provides an engine ignition oxygenating device for bullet, include: the flame-throwing nozzle, the oxygen supply nozzle, the igniter, the oxygen storage device and the electric connector are arranged on the aircraft engine;
one end of the electric connector is respectively connected with the igniter and the oxygen storage device, the other end of the electric connector is connected to the engine control system, the flame jet is connected with the igniter, the oxygen supply port is connected with the oxygen storage device, and the flame jet and the oxygen supply port are arranged in a combustion chamber of the aircraft engine.
Alternatively, in the bomb engine ignition oxygenating device as described above,
the electric connector is configured to receive a current instruction sent by an engine control system and carry out ignition operation and oxygen supplement operation according to the current instruction.
Optionally, in the bomb engine ignition oxygenating device as described above, the current instruction includes an instruction for instructing the igniter to ignite and an instruction for instructing the oxygen reservoir to oxygenate.
Optionally, in the bomb engine ignition oxygenating device as described above, the electrical connector performs an ignition operation and an oxygenating operation according to the current command, and includes:
and the electric connector is configured to supply power to the igniter and the oxygen storage device through the electric connector according to a current instruction received from the engine control system, so that the igniter and the oxygen storage device work according to the current instruction respectively, flame is sprayed out from the igniter, and oxygen is sprayed out from the oxygen supply port.
Optionally, in the bomb engine ignition oxygenating device as described above, the port of the electrical connector is disposed on an oxygen reservoir, and a passage for housing a circuit of the electrical connector is provided in the oxygen reservoir, and the circuit of the electrical connector is connected to the igniter through the passage.
Optionally, in the bomb engine ignition oxygen supplement device as described above, the ends of the flame ports and the oxygen supply ports are disposed on an igniter, a channel for installing a line of the oxygen supply ports is disposed in the igniter, and the line of the oxygen supply ports is connected to the oxygen storage device through the channel.
Alternatively, in the bomb engine ignition oxygenating device as described above, the port of the electrical connector is provided in the igniter in which the passage for housing the electrical connector wiring is provided, and the electrical connector wiring is connected to the oxygen reservoir through the passage.
Optionally, in the bomb engine ignition oxygenating device as described above, the ends of the fire-jet and the oxygen supply port are disposed on an oxygen storage device, a channel for placing a fire-jet line is disposed in the oxygen storage device, and the fire-jet line is connected to the igniter through the channel.
The embodiment of the utility model provides an engine ignition oxygenating device for bullet, include: the flame-throwing nozzle, the oxygen supply nozzle, the igniter, the oxygen storage device and the electric connector are arranged on the aircraft engine; one end of the electric connector is respectively connected with the igniter and the oxygen storage device, the other end of the electric connector is connected with the engine control system, the flame jet is connected with the igniter, the oxygen supply port is connected with the oxygen storage device, and the flame jet and the oxygen supply port are arranged in a combustion chamber of the aircraft engine; and receiving a current instruction sent by an engine control system through an electric connector, and carrying out ignition operation and oxygen supplement operation according to the current instruction. The embodiment of the utility model provides an increase the function of storing oxygen in bullet engine point firearm, when the engine was igniteed at the high altitude, oxygen released simultaneously, made the engine fire successfully, solved current bullet engine oxygenating device and needed certain space installation oxygen cylinder and pipeline to and there is the gas leakage risk scheduling problem in the pipe connection department.
Drawings
The accompanying drawings are included to provide a further understanding of the embodiments of the present 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 embodiments of the invention and not to limit the embodiments of the invention.
Fig. 1 is a schematic structural view of an ignition oxygenating device of an engine for bombs provided by an embodiment of the present invention;
fig. 2 is a schematic structural diagram of another bomb engine ignition oxygenating device provided by the embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The technical solution provided by the present invention is explained in detail by several specific embodiments below. The present invention provides that several specific embodiments below may be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.
Fig. 1 is a schematic structural view of an ignition oxygenating device of an engine for bombs provided by an embodiment of the present invention. The ignition oxygenating device for the bomb engine provided by the embodiment can comprise: the device comprises a fire nozzle 2, an oxygen supply port 3, an igniter 4, an oxygen storage device 5 and an electric connector 6 which are arranged on the aircraft engine.
The embodiment of the utility model provides an electric connector 6's one end is connected with some firearm 4 and oxygen storage ware 5 respectively, and the other end is connected to engine control system, and bocca 2 is connected with some firearm 4, and oxygen suppliment mouth 3 is connected with oxygen storage ware 5, and bocca 2 and oxygen suppliment mouth 3 set up in aeroengine's combustion chamber 1.
The embodiment of the utility model provides an electric connector 6 is configured to the electric current instruction that receives engine control system and sends to carry out ignition operation and oxygenating operation according to the electric current instruction.
Optionally, the current command in the embodiment of the present invention includes a command for instructing the igniter to ignite and a command for instructing the oxygen reservoir to perform oxygen replenishment.
In one implementation of the embodiment of the present invention, referring to fig. 1, the port of the electrical connector 6 is disposed on the oxygen storage device 5, a channel for installing the circuit of the electrical connector is disposed in the oxygen storage device 5, and the circuit of the electrical connector 6 is connected to the igniter 4 through the channel.
In this embodiment, as also shown in fig. 1, the ends of the burner port 2 and the oxygen supply port 3 are provided on an igniter 4, and a passage for housing a line of the oxygen supply port 3 is provided in the igniter 4, and the oxygen supply port line is connected to an oxygen reservoir 5 through the passage.
In another implementation manner of the embodiment of the present invention, as shown in fig. 2, the present invention provides a schematic structural diagram of another bomb engine ignition oxygen supplement device. In this implementation, the port of the electrical connector 6 is configured in the igniter 4, and a passage is provided in the igniter 4 for housing the electrical connector 6 wiring, which is connected with the oxygen reservoir 5 through the passage.
In this embodiment, referring to fig. 2, the ends of the burner 2 and the oxygen supply port 3 are disposed on an oxygen storage device 5, a channel for installing the line of the burner 2 is disposed in the oxygen storage device 5, and the line of the burner 2 is connected to the igniter 4 through the channel.
The embodiment of the utility model provides an engine ignition oxygenating device for bullet needs certain space installation oxygen cylinder and pipeline to current bullet engine oxygenating device for to and there is gas leakage risk scheduling problem in the pipe connection department, designed a guided missile engine point firearm and oxygenating device integrated oxygenating device, oxygenating device supplements oxygen for the engine when guided missile engine ignites, helps its ignition to succeed.
In order to achieve the purpose, the engine ignition oxygen supplement device provided by the embodiment of the utility model increases the function of storing oxygen in the bomb engine igniter, and when the engine is ignited at high altitude, the oxygen is released simultaneously, so that the engine is ignited successfully. The igniter and the oxygen storage device of the engine are integrated, namely the igniter and the oxygen storage device are integrated, as shown in figure 1, when the engine starts and ignites, an engine control system sends out a command, current supplies power to the igniter 4 through the electric connector 6, the igniter 4 starts to work, flame is sprayed out from the flame spraying port 2, the engine starts to ignite, meanwhile, the current command supplies power to the oxygen storage device 5 through the electric connector 6, the oxygen storage device 5 starts to work, oxygen is sprayed out from the oxygen supply port 3, the engine is fully combusted, and the engine is successfully ignited and started.
The embodiment of the utility model provides an install on the engine with 5 integrated devices of oxygen storage ware in some firearm 4, bocca 2 and oxygen suppliment mouth 3 stretch into in the engine combustion chamber 1, it is connected with electric connector 6 to play the cable, when the engine ignition starts, engine control system sends the current instruction, the electric current passes through electric connector 6 and supplies power for some firearm 4 and oxygen storage ware 5, some firearm (4) and oxygen storage ware 5 begin work according to the instruction respectively, flame and oxygen are respectively from bocca and oxygen suppliment mouth blowout, the engine is the work of igniteing in the oil-gas mixture.
The embodiment of the utility model provides an engine ignition oxygenating device is used to bullet specifically is for being applied to the oxygenating device of air-surface missile engine, not only is applicable to the oxygenating device of the engine for bullet or unmanned aerial vehicle, but also is applicable to the oxygenating device of all other types that use similar device.
Although the embodiments of the present invention have been described above, the description is only for the convenience of understanding the present invention, and the present invention is not limited thereto. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. An ignition oxygenating device for a bullet engine, comprising: the flame-throwing nozzle, the oxygen supply nozzle, the igniter, the oxygen storage device and the electric connector are arranged on the aircraft engine;
one end of the electric connector is respectively connected with the igniter and the oxygen storage device, the other end of the electric connector is connected to the engine control system, the flame jet is connected with the igniter, the oxygen supply port is connected with the oxygen storage device, and the flame jet and the oxygen supply port are arranged in a combustion chamber of the aircraft engine.
2. The bomb engine ignition oxygenating device of claim 1,
the electric connector is configured to receive a current instruction sent by an engine control system and carry out ignition operation and oxygen supplement operation according to the current instruction.
3. The bomb engine ignition oxygenating device of claim 2, wherein the current instructions include instructions for instructing an igniter to ignite and instructions for instructing an oxygen reservoir to oxygenate.
4. The bomb engine ignition oxygenating device of claim 3, wherein the electrical connector performs ignition operation and oxygenating operation in accordance with the current command, comprising:
and the electric connector is configured to supply power to the igniter and the oxygen storage device through the electric connector according to a current instruction received from the engine control system, so that the igniter and the oxygen storage device work according to the current instruction respectively, flame is sprayed out from the igniter, and oxygen is sprayed out from the oxygen supply port.
5. The bomb engine ignition oxygenating device according to any one of claims 1 to 4, wherein a port of an electrical connector is arranged on an oxygen reservoir, a passage for accommodating an electrical connector line is provided in the oxygen reservoir, and the electrical connector line is connected with an igniter through the passage.
6. The bomb engine ignition oxygenating device according to claim 5, wherein the ends of the burner ports and the oxygen supply ports are disposed on an igniter, the igniter is provided with a channel for installing an oxygen supply port line, and the oxygen supply port line is connected with the oxygen storage device through the channel.
7. The bomb engine ignition oxygenating device according to any one of claims 1 to 4, wherein a port of an electrical connector is provided in an igniter in which a passage for housing an electrical connector line is provided, the electrical connector line being connected to an oxygen reservoir through the passage.
8. The bomb engine ignition oxygenating device according to claim 7, wherein the ends of the flame ports and the oxygen supply ports are arranged on an oxygen storage device, a channel for arranging the flame port line is arranged in the oxygen storage device, and the flame port line is connected with an igniter through the channel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922166531.9U CN210977704U (en) | 2019-12-05 | 2019-12-05 | Engine ignition oxygen supplement device for bomb |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922166531.9U CN210977704U (en) | 2019-12-05 | 2019-12-05 | Engine ignition oxygen supplement device for bomb |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210977704U true CN210977704U (en) | 2020-07-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922166531.9U Active CN210977704U (en) | 2019-12-05 | 2019-12-05 | Engine ignition oxygen supplement device for bomb |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210977704U (en) |
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2019
- 2019-12-05 CN CN201922166531.9U patent/CN210977704U/en active Active
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