CN216198592U - Large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system - Google Patents
Large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system Download PDFInfo
- Publication number
- CN216198592U CN216198592U CN202122496948.9U CN202122496948U CN216198592U CN 216198592 U CN216198592 U CN 216198592U CN 202122496948 U CN202122496948 U CN 202122496948U CN 216198592 U CN216198592 U CN 216198592U
- Authority
- CN
- China
- Prior art keywords
- module
- ignition
- starting
- engine
- magneto
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The utility model provides a large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system, which comprises a starting module, wherein the starting module is respectively connected with a power supply module and a circuit switching module, the circuit switching module is connected with an ignition module, and the circuit switching module and the ignition module are also connected with an electromagnet; the starting module is used for starting the engine; the power supply module is used for supplying electric energy to the starting module and the ignition module; the circuit switching module is used for controlling the on-off of the starting module, the ignition module and the power supply module; the ignition module is used for being connected with the engine to start the engine; the electromagnet is used for controlling whether the starting module is connected with the engine or not. The utility model provides an ignition electric system of a large and medium-sized fixed wing unmanned aerial vehicle engine, which realizes ignition starting of the engine by using a simpler circuit. The installation verifies that the electric system is safe, simple and reliable.
Description
Technical Field
The utility model belongs to the technical field of switching power supplies, and particularly relates to an engine ignition electrical system of a large and medium-sized fixed wing unmanned aerial vehicle.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be better suited to perform those dangerous tasks than manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.
The ignition system of an aircraft engine is the key technology of the aircraft engine, and when the engine is started, a power supply charges a capacitor, and when the voltage of the capacitor reaches a preset high voltage, the capacitor discharges to enable a spark plug to generate a spark which ignites the mixture of air and fuel in the engine.
The battery system of the large and medium-sized fixed wing unmanned aerial vehicle is complex in an ignition system when an engine based on an airplane is started at present, so that the problems of cost increase and failure probability increase are caused.
Disclosure of Invention
Aiming at the defects in the prior art, the utility model aims to provide an ignition electrical system of a large and medium-sized fixed wing unmanned aerial vehicle engine, which solves the problems of increased cost and increased failure probability caused by more complex fire systems in the prior art.
In order to solve the technical problems, the utility model adopts the following technical scheme: the engine ignition electrical system of the large and medium-sized fixed wing unmanned aerial vehicle comprises a starting module, wherein the starting module is respectively connected with a power supply module and a circuit switching module, the circuit switching module is connected with an ignition module, and the circuit switching module and the ignition module are also connected with an electromagnet;
the starting module is used for starting an engine;
the power supply module is used for supplying electric energy to the starting module and the ignition module;
the circuit switching module is used for controlling the on-off of the starting module and the ignition module and the power supply module;
the ignition module is used for being connected with the engine to start the engine;
the electromagnet is used for controlling whether the starting module is connected with the engine or not.
The utility model also has the following technical characteristics:
the starting module comprises a starting module contactor and a motor starting mechanism which are connected with each other, and the starting module contactor is respectively connected with the power supply module and the circuit switching module;
the ignition module comprises an ignition coil and a magneto which are connected with each other, the ignition coil is connected with the electromagnet and the circuit switching module, and the magneto is connected with the engine;
the magnetor includes first magnetor and the second magnetor of connecting through ignition change over switch, first magnetor is connected with ignition coil.
The engine is connected with the starting module and the ignition module, the engine is also connected with an engine state detection module, and the engine state detection module is connected with the circuit switching module;
the magneto comprises a first magneto with the end 1 connected with the end 3 of the ignition coil, and the end 2 of the first magneto is connected with the end 3 of the second magneto through an ignition change-over switch;
the starting module comprises a starting module contactor MZJ-400A, wherein the 1 end of the starting module contactor MZJ-400A is connected with the power supply module, the 2 end of the starting module contactor MZJ-400A is connected with one end of the motor starting mechanism RIM-U-24IR, and the other end of the motor starting mechanism RIM-U-24IR is grounded;
the coil end 3 of the starting module contactor MZJ-400A is grounded, and the coil end 4 is connected with the circuit switching module;
the power supply module comprises a main bus bar and a branch bus bar, wherein the 1 end of the starting module contactor MZJ-400A is connected with the main bus bar, the circuit switching module is connected with the branch bus bar, and the branch bus bar is connected with the main bus bar.
The circuit switching module comprises an ignition line switch DDB-20 connected with the branch bus bar and a starting pressing conversion switch AZK-1 connected with the ignition line switch DDB-20, wherein the end 1 of the starting pressing conversion switch AZK-1 is connected with the ignition line switch DDB-20, the end 2 of the starting pressing conversion switch AZK-1 is connected with the end 4 of a starting module contactor MZJ-400A, and the end 3 of the starting pressing conversion switch AZK-1 is connected with the ignition module.
The ignition module comprises ignition coils KP-4716 connected with the circuit switching module and a magneto connected with the ignition coils KP-4716;
the 4 end of the ignition coil KP-4716 is grounded, the 3 end is connected with a magneto, an electromagnet V is connected between the 1 end and the 2 end of the ignition coil KP-4716, and the end of the electromagnet V connected with the 2 end of the ignition coil KP-4716 is grounded;
and the 3 end of the starting pressing change-over switch AZK-1 is connected with the 1 end of the ignition coil KP-4716.
The magneto comprises a first magneto BSM-9E of which the 1 end is connected with the 3 end of an ignition coil KP-4716, and the 2 end of the first magneto BSM-9E is connected with the 3 end of a second magneto BSM-9E through an ignition transfer switch;
the 2 end of the first magneto BSM-9E is connected with the 2 end of the ignition change-over switch, and the 1 end of the ignition change-over switch is connected with the 3 end of the second magneto BSM-9E;
the 3 terminal of the first magneto BSM-9E and the 2 terminal of the second magneto BSM-9E are both grounded.
Compared with the prior art, the utility model has the following technical effects:
the utility model provides an ignition electrical system of a large and medium-sized fixed wing unmanned aerial vehicle engine, which realizes ignition starting of the engine by using a simpler circuit. The installation verifies that the electric system is safe, simple and reliable.
And (II) the utility model has the advantages of simple circuit, low cost, safety, stability and wide application prospect.
Drawings
FIG. 1 is a block diagram I of the present invention;
FIG. 2 is a block diagram II of the present invention;
FIG. 3 is a block diagram III of the present invention;
FIG. 4 is a circuit block diagram of the present invention;
the reference numbers in the figures represent:
the device comprises an I-starting module, an II-power supply module, an III-circuit switching module, an IV-ignition module, a V-electromagnet, a VI-engine and a VII-engine state detection module;
1-starting module contactor, 2-motor starting mechanism, 3-main bus bar, 4-branch bus bar, 5-ignition circuit switch, 6-starting press change-over switch, 7-ignition coil and 8-magneto;
8-1-the first magneto, 8-2-the ignition transfer switch, and 8-3-the second magneto.
The present invention will be explained in further detail with reference to examples.
Detailed Description
The following embodiments of the present invention are provided, and it should be noted that the present invention is not limited to the following embodiments, and all equivalent changes based on the technical solutions of the present invention are within the protection scope of the present invention.
Example 1:
the embodiment provides a large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system, as shown in fig. 1 to 4, comprising a starting module I, wherein the starting module I is respectively connected with a power supply module II and a circuit switching module III, the circuit switching module III is connected with an ignition module IV, and the circuit switching module III and the ignition module IV are also connected with an electromagnet V;
the starting module I is used for starting an engine VI;
the power supply module II is used for supplying electric energy to the starting module I and the ignition module IV;
the circuit switching module III is used for controlling the on-off of the starting module I, the ignition module IV and the power supply module II;
the ignition module IV is used for being connected with an engine VI to start the engine VI;
and the electromagnet V is used for controlling whether the starting module I is connected with the engine VI or not.
The ignition system of engine is composed of two shielded integral nozzles, ignition cable and two magnetors, which are positioned on each cylinder of engine. The right magneto is used for igniting the front row of nozzles of each cylinder, and the left magneto is used for igniting the rear row of nozzles. The mixed oil gas in the cylinder is ignited to enable the piston in the cylinder to start to work, so that the engine is started.
The schematic block diagram of fig. 1 mainly realizes the starting and ignition of the engine. The power supply module is provided by an on-board storage battery and provides power supply voltage for the starting and ignition module of the engine. The starting module consists of a starting module contactor and a motor starting mechanism. In the initial starting stage, the motor starting mechanism drives the flywheel on the engine to rotate for storing energy, when the rotating speed of the flywheel is uniform, the circuit is switched to switch on the electromagnet, the motor starting mechanism is combined with the crankshaft of the engine to drive the crankshaft of the engine to continue rotating, meanwhile, the ignition coil in the ignition module is switched on, the magnetor generates an instant high-voltage signal, sparks are formed in the cylinder, and mixed oil gas is ignited, so that the engine is started. In addition, one magneto may be turned on or off in sequence by an ignition switch according to the state of the engine.
As a preference of this embodiment:
the starting module I comprises a starting module contactor 1 and a motor starting mechanism 2 which are connected with each other, and the starting module contactor 1 is respectively connected with the power supply module II and the circuit switching module III;
the ignition module IV comprises an ignition coil 7 and a magneto 8 which are connected with each other, the ignition coil 7 is connected with an electromagnet V and a circuit switching module III, and the magneto 8 is connected with an engine VI;
as a preference of this embodiment:
the magneto 8 comprises a first magneto 8-1 and a second magneto 8-3 which are connected through an ignition change-over switch 8-2, and the first magneto 8-1 is connected with an ignition coil 7.
As a preference of this embodiment:
the engine VI is connected with the starting module I and the ignition module IV, the engine VI is also connected with an engine state detection module VII, and the engine state detection module VII is connected with the circuit switching module III;
as a preference of this embodiment:
the power supply module II comprises a main bus bar 3 and a branch bus bar 4, the end 1 of the starting module contactor 1 is connected with the main bus bar 3, the circuit switching module III is connected with the branch bus bar 4, and the branch bus bar 4 is connected with the main bus bar 3.
As a preference of this embodiment:
the circuit switching module III comprises an ignition line switch 5 connected with the branch bus bar 4 and a starting pressing change-over switch 6 connected with the ignition line switch 5, wherein the end 1 of the starting pressing change-over switch 6 is connected with the ignition line switch 5, the end 2 of the starting pressing change-over switch 6 is connected with the end 4 of the starting module contactor 1, and the end 3 of the starting pressing change-over switch 6 is connected with the ignition module IV.
As a preference of this embodiment:
the ignition module IV comprises an ignition coil 7 connected with the circuit switching module III and a magneto 8 connected with the ignition coil 7;
the 4 end of the ignition coil 7 is grounded, the 3 end of the ignition coil 7 is connected with the magneto 8, an electromagnet V is connected between the 1 end and the 2 end of the ignition coil 7, and the end of the electromagnet V connected with the 2 end of the ignition coil 7 is grounded;
the 3 end of the start push switch 6 is connected with the 1 end of the ignition coil 7.
As a preference of this embodiment:
the magneto 8 comprises a first magneto 8-1 of which the end 1 is connected with the end 3 of the ignition coil 7, and the end 2 of the first magneto 8-1 is connected with the end 3 of the second magneto 8-3 through an ignition change-over switch 8-2;
the 2 end of the first magneto 8-1 is connected with the 2 end of the ignition change-over switch 8-2, and the 1 end of the ignition change-over switch 8-2 is connected with the 3 end of the second magneto 8-3;
the 3 end of the first magneto 8-1 and the 2 end of the second magneto 8-3 are both grounded.
The starting module contactor 1 is MZJ-400A in model, the motor starting mechanism 2 is RIM-U-24IR in model, the ignition circuit switch 5 is DDB-20 in model, the starting press change-over switch 6 is AZK-1 in model, the ignition coil 7 is KP-4716 in model, the first magneto 8-1 and the second magneto 8-3 are BSM-9E in model, and the electromagnet V is RA-176D in model.
The ignition sequence for engine start is as follows:
before the engine is started, a check confirms that the pawl of the electric starter mechanism 2 RIM-U-24IR has disengaged from the crankshaft of the engine.
The 5-ignition circuit switch DDB-20 is switched on, the 6-starting pressing change-over switch AZK-1 is placed at an energy storage position, the 2 end is connected, the FQ2 circuit is conducted, the two ends of a 1-starting module contactor MZJ-400A coil are electrified, and the 2-electric starting mechanism RIM-U-24IR is connected with the on-machine network circuit;
the 2 electric starting mechanism RIM-U-24IR drives the flywheel to rotate, when the flywheel rotates uniformly for 9-13 seconds, the 6 starting push change-over switch AZK-1 is placed at the starting position, the 3 end is connected, the FQH2 line is conducted, the 2 electric starting mechanism RIM-U-24IR circuit is disconnected, the V electromagnet RA-176D is connected, and the pawl of the 2 electric starting mechanism RIM-U-24IR is combined with the engine crankshaft.
At the same time, 7 ignition coils KP4716 are turned on, 7 ignition coils KP4716 input a high voltage signal to the magneto 8, and the magneto 8 can generate a sufficiently high voltage to trigger a spark between the spark plug gaps in each cylinder, causing the oil in the cylinder to burn, thereby starting the engine. And an ignition change-over switch 8-2 for performing independent work of the first magneto or simultaneously operating the left first magneto.
The engine is started continuously by the electric mechanism for no more than 3 times, and after 3 times of starting, 30 minutes are required to be separated, and then the starting is continued to avoid the damage of the motor.
When the ignition device is used specifically, the engine VI is connected with the ignition module IV, the engine VI is also connected with an engine state detection module VII, the engine state detection module VII is connected with a circuit switching module III, and after the engine is started, the circuit switching module controls the starting module and the ignition module to be switched on and off based on a detection result of the engine state detection module VII. The detection items of the engine state detection module VII comprise at least one of vibration, temperature and preset time, for example, when the detection items are temperatures, when the temperature of an oil-gas mixture in the engine reaches the preset temperature, the circuit switching module III switches off the starting module and switches on the ignition module to ignite the engine. In another embodiment, the smooth degree of the rotation of the engine can be evaluated by detecting the vibration signal, and the switching from the starting module to the ignition module is carried out after the rotation is smooth. In addition, the switching can be performed based on the preset time length.
The above description is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be made by those skilled in the art without inventive work within the technical scope of the present invention are included in the scope of the present invention.
Claims (9)
1. The large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system is characterized by comprising a starting module (I), wherein the starting module (I) is respectively connected with a power supply module (II) and a circuit switching module (III), the circuit switching module (III) is connected with an ignition module (IV), and the circuit switching module (III) and the ignition module (IV) are also connected with an electromagnet (V);
the starting module (I) is used for starting an engine (VI);
the power supply module (II) is used for supplying electric energy to the starting module (I) and the ignition module (IV);
the circuit switching module (III) is used for controlling the on-off of the starting module (I), the ignition module (IV) and the power supply module (II);
the ignition module (IV) is used for being connected with an engine (VI) to start the engine (VI);
the electromagnet (V) is used for controlling whether the starting module (I) is connected with the engine (VI) or not.
2. The engine ignition electrical system of the large and medium-sized fixed wing unmanned aerial vehicle as claimed in claim 1, wherein the starting module (i) comprises a starting module contactor (1) and a motor starting mechanism (2) which are connected with each other, and the starting module contactor (1) is respectively connected with the power supply module (ii) and the circuit switching module (iii);
ignition module (IV) is including interconnect's ignition coil (7) and magneto (8), ignition coil (7) are connected with electro-magnet (V) and circuit switching module (III), and magneto (8) are connected with engine (VI).
3. The medium and large sized fixed wing drone engine ignition electrical system of claim 2, characterized in that the magneto (8) comprises a first magneto (8-1) and a second magneto (8-3) connected by an ignition transfer switch (8-2), the first magneto (8-1) being connected to an ignition coil (7).
4. The ignition electrical system of the engine of the large and medium-sized fixed wing unmanned aerial vehicle as claimed in claim 3, wherein the engine (VI) is connected with the starting module (I) and the ignition module (IV), the engine (VI) is further connected with an engine state detection module (VII), and the engine state detection module (VII) is connected with the circuit switching module (III).
5. The ignition electrical system of the large and medium sized fixed wing unmanned aerial vehicle engine according to claim 4, characterized in that the 1 end of the starting module contactor (1) is connected with the power supply module (II), the 2 end of the starting module contactor (1) is connected with one end of the motor starting mechanism (2), and the other end of the motor starting mechanism (2) is grounded;
and a coil end 3 of the starting module contactor (1) is grounded, and a coil end 4 is connected with the circuit switching module (III).
6. The medium and large-sized fixed-wing drone engine ignition electrical system according to claim 5, characterized in that the power supply module (II) comprises a main bus bar (3) and a branch bus bar (4), the 1 end of the starting module contactor (1) is connected with the main bus bar (3), the circuit switching module (III) is connected with the branch bus bar (4), and the branch bus bar (4) is connected with the main bus bar (3).
7. The ignition electrical system of the large and medium-sized fixed wing unmanned aerial vehicle engine according to claim 6, wherein the circuit switching module (III) comprises an ignition line switch (5) connected with the branch bus bar (4) and a starting push switch (6) connected with the ignition line switch (5), wherein one end 1 of the starting push switch (6) is connected with the ignition line switch (5), one end 2 of the starting push switch (6) is connected with one end 4 of the starting module contactor (1), and the other end 3 of the starting push switch (6) is connected with the ignition module (IV).
8. The medium and large sized fixed wing drone engine ignition electrical system according to claim 7, characterized in that the ignition module (iv) comprises an ignition coil (7) connected to the circuit switching module (iii) and a magneto (8) connected to the ignition coil (7);
the end 4 of the ignition coil (7) is grounded, the end 3 is connected with a magneto (8), an electromagnet (V) is connected between the end 1 and the end 2 of the ignition coil (7), and the end connected with the end 2 of the ignition coil (7) of the electromagnet (V) is grounded;
and the end 3 of the starting pressing change-over switch (6) is connected with the end 1 of the ignition coil (7).
9. The medium and large sized fixed wing drone engine ignition electrical system of claim 8, characterized in that the magneto (8) includes a first magneto (8-1) having 1 terminal connected to the 3 terminal of the ignition coil (7), the 2 terminal of the first magneto (8-1) being connected to the 3 terminal of the second magneto (8-3) through the ignition transfer switch (8-2);
the 2 end of the first magneto (8-1) is connected with the 2 end of the ignition change-over switch (8-2), and the 1 end of the ignition change-over switch (8-2) is connected with the 3 end of the second magneto (8-3);
and the 3 end of the first magneto (8-1) and the 2 end of the second magneto (8-3) are both grounded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122496948.9U CN216198592U (en) | 2021-10-15 | 2021-10-15 | Large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122496948.9U CN216198592U (en) | 2021-10-15 | 2021-10-15 | Large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216198592U true CN216198592U (en) | 2022-04-05 |
Family
ID=80883001
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122496948.9U Active CN216198592U (en) | 2021-10-15 | 2021-10-15 | Large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216198592U (en) |
-
2021
- 2021-10-15 CN CN202122496948.9U patent/CN216198592U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10371066B2 (en) | Unmanned aircraft and operation method for the same | |
| US9771162B1 (en) | On-board redundant power system for unmanned aerial vehicles | |
| US10196923B2 (en) | Operation of aircraft engines during transient conditions | |
| WO2002066323A3 (en) | Improved aircraft architecture with a reduced bleed aircraft secondary power system | |
| CN104619970A (en) | Flexible fuel generator and methods of use thereof | |
| CN111478418B (en) | Power conversion and power failure control system and method | |
| CN110831849B (en) | Method for starting an internal combustion engine of a hybrid propulsion system in a marine vessel and hybrid propulsion system in a marine vessel | |
| CN216198592U (en) | Large and medium-sized fixed wing unmanned aerial vehicle engine ignition electrical system | |
| JP2004177111A (en) | Ignition isolating interrupt circuit | |
| CN117485571A (en) | Safety control system and method for flight propeller | |
| CN202593850U (en) | Unmanned plane wing installing mechanism capable of being mounted and dismounted quickly | |
| CN114576042B (en) | Remote ignition device and ignition method suitable for solid rocket engine | |
| CN106532809A (en) | Civil interceptor electric detonating controller | |
| CN114056572A (en) | Air-drop type fuel oil power unmanned aerial vehicle, aerial vehicle and air-drop method | |
| CN110538408A (en) | fire fighting vehicle and method for operating a fire fighting vehicle | |
| CN111746806B (en) | Unmanned aerial vehicle heuristic system and integrated control method | |
| CN209524828U (en) | A kind of percussion lock of soft emission-type man-portable rocket | |
| CN216834293U (en) | Air-drop type fuel power unmanned aerial vehicle and aerial vehicle | |
| CN109556469A (en) | A kind of percussion lock of soft emission-type man-portable rocket | |
| US1362380A (en) | Electrical system for aeroplanes and the like | |
| CN204357614U (en) | A kind of engine at extreme rear passenger vehicle starting guard equipment | |
| CN202579007U (en) | Motorcycle igniting circuit with anti-theft function | |
| CN208718820U (en) | A kind of flameout of automobile engine control device | |
| CN203707822U (en) | Multipath output power supply device for unmanned aircraft | |
| Pranoto et al. | Electrical Power Budgeting Analysis for LSA-02 UAV Technology Demonstrator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |