Small cluster rocket boosting ground controller

Abstract

The utility model provides a small cluster rocket boosting ground controller. The controller comprises a man-machine interaction interface, a measurement and control terminal and an on-site fuse box. The human-computer interaction interface and the measurement and control terminal are connected through an Ethernet cable 1, a loop resistance test cable and a switch signal cable; the measurement and control terminal is connected with the on-site fuse box through an ignition cable. According to the utility model, the requirements of each loop state detection and time sequence ignition function of the small-sized cluster rocket are met, and meanwhile, the system has the characteristics of improving the maintainability, reducing the cost, shortening the development period, ensuring the safety, the reliability and the integration and modularization degree of the system, and the like.

Description

Technical Field

[0001] The utility model relates to the field of rocket booster ground controllers, in particular to a small cluster rocket booster ground controller. Background Art

[0002] Rocket boost is one of the ways to launch drones / target drones. In combat applications, the launch phase is often considered to be one of the most difficult phases, which directly affects whether the drone / target drone can fly smoothly. Currently, due to the needs of large-scale combat transportation, clusters have become a research hotspot. The rocket-assisted launch test and control system has put forward requirements from individual launch to higher-demand cluster launch.

[0003] The drivers of existing small cluster launch control devices are mostly distributed on launch vehicles or launch pads. The huge impact force generated when a certain circuit is launched will cause the relays in the remaining standby circuits to malfunction. At the same time, logical isolation is used between the circuits, and the degree of physical isolation is insufficient. The circuits are very likely to affect each other, causing false launches. Utility Model Content

[0004] The utility model provides a small cluster rocket booster ground controller, which meets the requirements of various circuit status detection and timing ignition function of small cluster (less than 40 circuits) rockets, and at the same time has the characteristics of improving maintainability (average repair time at the grassroots level is not more than 0.5h), reducing costs, shortening development cycle, and ensuring safety, reliability and high integration and modularization of the system.

[0005] In order to solve the above technical problems, the utility model provides a small cluster rocket booster ground controller, including: a human-computer interaction interface, a measurement and control terminal, and an on-site fuse box; the human-computer interaction interface and the measurement and control terminal are connected via an Ethernet cable 1, a loop resistance test cable, and a switch signal cable; the measurement and control terminal and the on-site fuse box are connected via an ignition cable.

[0006] Preferably, the human-machine interaction interface includes a human-machine interaction interface front panel and a human-machine interaction interface rear panel; the human-machine interaction interface front panel is provided with a touch screen, a loop resistance detector, an emergency stop button, a test loop selection switch, a test button, an ignition permission switch, an ignition button, and an ignition voltage digital display; the human-machine interaction interface rear panel is provided with an Ethernet aviation connector 1, an aviation connector 1 for loop resistance test, and an aviation connector 1 for switch signal, and the touch screen is connected to the Ethernet aviation connector 1 via an Ethernet cable 2.

[0007] Preferably, the test port of the loop resistance detector is connected to the output port of the test loop selection switch, the input ends of the test loop selection switch are respectively connected to the core points of the aviation connector 1 for loop resistance testing, the connection points of the emergency stop button, the test loop selection switch, the test button, the ignition permission switch, the ignition button, and the ignition voltage digital display are respectively connected to the aviation connector 1 for the switch signal, and the touch screen is connected to the Ethernet aviation connector 1 via an Ethernet cable 2.

[0008] Preferably, the measurement and control terminal includes a measurement and control terminal front panel, a measurement and control terminal rear panel, a measurement and control terminal left panel, a measurement and control terminal right panel, a measurement and control terminal upper panel, and a measurement and control terminal bottom panel; the measurement and control terminal bottom panel is provided with a DC regulated power supply, a programmable logic controller and a control circuit board assembly; the measurement and control terminal front panel is provided with an AC220V power indicator light, a DC24V power indicator light, a DC48V power indicator light, a power-on switch assembly, and a switch door assembly; the measurement and control terminal rear panel is provided with a power supply aviation connector, an Ethernet aviation connector 2, an aviation connector 2 for loop resistance testing, an aviation connector 2 for switch signals, and an ignition output aviation connector assembly; the programmable logic controller and the Ethernet aviation connector 2 are connected via an Ethernet cable 3.

[0009] Preferably, the Ethernet aviation connector 1 of the human-machine interaction interface is connected to the Ethernet aviation connector 2 of the measurement and control terminal via an Ethernet cable 1, the aviation connector 1 for loop resistance testing of the human-machine interaction interface is connected to the aviation connector 2 for loop resistance testing of the measurement and control terminal via a loop resistance testing cable, and the aviation connector 1 for switch signal of the human-machine interaction interface is connected to the aviation connector 2 for switch signal of the measurement and control terminal via a switch signal cable.

[0010] Preferably, the ignition output aviation connector components of the measurement and control terminal are respectively connected to the ignition input aviation connectors of the corresponding on-site fuse boxes through ignition cables.

[0011] Preferably, the AC220V electricity powers the system through the power supply aviation connector of the measurement and control terminal, and then converts the voltage to DC24V and DC48V through the power-on switch component in the measurement and control terminal to the DC regulated power supply; the DC24V is connected from the DC24V output end of the DC regulated power supply to the power supply input end of the programmable logic controller and the control circuit board component in the measurement and control terminal for power supply, and at the same time is connected to the switch signal aviation connector 2 through a cable and then connected to the switch signal aviation connector 1 on the human-machine interaction interface through a switch signal cable to power the touch screen on the human-machine interaction interface; the DC48V is connected to the control circuit board component from the 48V output end of the DC regulated power supply; the DC48V signal display output cable of the DC regulated power supply in the measurement and control terminal is connected to the switch signal aviation connector 2 through a switch signal cable and then connected to the switch signal aviation connector 1 on the human-machine interaction interface, and then connected to the ignition voltage digital display on the human-machine interaction interface.

[0012] Preferably, the digital input port of the programmable logic controller is respectively connected to the corresponding core points of the aviation connector 2 for the switch signal, the digital output port of the programmable logic controller is respectively connected to the corresponding input core points of the control circuit board assembly, the Ethernet of the programmable logic controller is connected to the Ethernet aviation connector 2 through the Ethernet cable 3, the output core points of the control circuit board assembly are respectively connected to the corresponding core points of the ignition output aviation connector assembly, and the core points of the aviation connector 2 for loop resistance testing are respectively connected to the corresponding core points of the ignition output aviation connector assembly.

[0013] Preferably, the on-site fuse box includes an on-site fuse box front panel, an on-site fuse box rear panel, an on-site fuse box left panel, an on-site fuse box right panel, an on-site fuse box upper panel, and an on-site fuse box bottom panel; the on-site fuse box front panel is provided with a button switch and an ignition input aviation connector; the on-site fuse box rear panel is provided with an ignition output aviation connector.

[0014] Preferably, a normally closed contact of the toggle switch is connected in parallel between the ignition output aviation connector and the ignition input aviation connector, and a normally open contact of the toggle switch is connected in series between the ignition output aviation connector and the ignition input aviation connector.

[0015] The above one or more technical solutions of the utility model have at least one or more of the following technical effects:

[0016] The small cluster rocket booster ground controller provided by the utility model can realize the long-distance (not less than 100m) large current (10A~20A) ignition function. The test control circuit and the ignition control circuit of the utility model are independent of each other and physically isolated. The test function and the ignition function are interlocked to ensure the safety of use. The circuit resistance test adopts a special tester. The tester is connected to the control circuit through a banana plug socket and installed on the operation panel. It is simple to disassemble and assemble, convenient for measurement and verification, and ensures the accuracy of the test. The on-site fuse box has two states: insurance and release. In the insurance state, the ignition circuit is cut off and the booster rocket pyrotechnics are in a short-circuit state. In the release state, the ignition circuit is connected and the short-circuit state of the booster rocket pyrotechnics is released; the absolute safety of the operator when connecting the pyrotechnics is guaranteed. It can work in a vehicle-mounted mode and can also be used at any location with an external power supply. It has high engineering practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 , one A small cluster rocket booster ground controller connection diagram;

[0018] Figure 2 , schematic diagram of the front panel of the human-computer interaction interface;

[0019] Figure 3 , schematic diagram of the rear panel of the human-computer interaction interface;

[0020] Figure 4 , schematic diagram of the measurement and control terminal structure;

[0021] Figure 5 , Schematic diagram of the rear panel of the measurement and control terminal;

[0022] Figure 6 , top view of the on-site fuse box;

[0023] Figure 7 , side view of the on-site fuse box;

[0024] Figure 8 , Schematic diagram of the front panel of the on-site fuse box;

[0025] Fig. 9 , Schematic diagram of the rear panel of the on-site fuse box;

[0026] Among them, 1-human-machine interaction interface, 2-measurement and control terminal, 3-on-site fuse box, 4-ignition cable, 5-Ethernet cable 1, 6-loop resistance test cable, 7-switch signal cable, 8-human-machine interaction interface front panel, 9-human-machine interaction interface rear panel, 10-Ethernet cable 2, 11-touch screen, 12-loop resistance tester, 13-emergency stop button, 14-test loop selection switch, 15-test button, 16-ignition permission switch, 17-ignition button, 18-ignition voltage digital display, 19-switch signal aviation connector 1, 20-Ethernet aviation connector, 21-loop resistance test aviation connector 1, 22-measurement and control terminal front panel, 23-measurement and control terminal rear panel, 24-measurement and control terminal left panel, 25-measurement and control terminal right panel, 26-measurement and control terminal upper panel, 27-measurement and control terminal bottom panel, 28-DC regulated power supply, 29-programmable logic controller, 30-control circuit board assembly, 31-AC220V power indicator light, 32-power-on switch assembly, 33-switch door assembly, 34-power supply aviation connector, 35-Ethernet aviation connector 2, 36-loop resistance test aviation connector 2, 37-switch signal aviation connector 2, 38-ignition output aviation connector assembly, 39-Ethernet cable 3, 40-on-site fuse box front panel, 41-on-site fuse box rear panel, 42-on-site fuse box left panel, 43-on-site fuse box right panel, 44-on-site fuse box upper panel, 45-on-site fuse box bottom panel, 46-button switch, 47-ignition input aviation connector, 48-ignition output aviation connector, 49-DC24V power indicator light, 50-DC48V power indicator light. DETAILED DESCRIPTION

[0027] The embodiment of the utility model provides a small cluster rocket booster ground controller and control method, which meets the requirements of each circuit status detection and timing ignition function of small cluster (less than 40 circuits) rockets, and at the same time has the characteristics of improving maintainability (the average repair time at the grassroots level is not more than 0.5h), reducing costs, shortening the development cycle, and ensuring safety, reliability and high integration and modularization of the system.

[0028] Below is a combination of the utility model embodiment and Figure 1-9 , the technical scheme in the embodiment of the utility model is clearly and completely described. Obviously, the described embodiment is only a part of the embodiment of the utility model, not all the obtained embodiments. Based on the embodiment of the utility model, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of the utility model.

[0029] like Figure 1As shown, a small cluster rocket booster ground controller includes: a human-computer interaction interface, a measurement and control terminal, and an on-site fuse box; the human-computer interaction interface and the measurement and control terminal are connected via an Ethernet cable 1, a loop resistance test cable, and a switch signal cable; the measurement and control terminal and the on-site fuse box are connected via an ignition cable.

[0030] like Figure 2-3 As shown, the small cluster rocket booster ground controller includes a human-machine interface. The test port of the loop resistance detector on the human-machine interface is connected to the output port of the test loop selection switch through a banana plug, the input end of the test loop selection switch is respectively connected to the core point of the aviation connector 1 for loop resistance test, the connection points of the emergency stop button, the test loop selection switch, the test button, the ignition permission switch, the ignition button, and the ignition voltage digital display are respectively connected to the corresponding core points of the switch signal aviation connector 1, and the touch screen is connected to the Ethernet aviation connector 1 through the Ethernet cable 2.

[0031] like Figure 4-5 As shown, the small cluster rocket booster ground controller includes a measurement and control terminal. The digital input port of the programmable logic controller in the measurement and control terminal is respectively connected to the corresponding core points of the switch signal aviation connector 2, the digital output port of the programmable logic controller is respectively connected to the corresponding input core points of the control circuit board assembly, the Ethernet of the programmable logic controller is connected to the Ethernet aviation connector 2 through the Ethernet cable 3, the output core point of the control circuit board assembly is respectively connected to the corresponding core point of the ignition output aviation connector assembly, and the core point of the loop resistance test aviation connector 2 is respectively connected to the corresponding core point of the ignition output aviation connector assembly.

[0032] like Figure 6-Figure 9 As shown, the small cluster rocket booster ground controller includes an on-site fuse box. In the on-site fuse box, the toggle switch is a double-position two-position locking type, the normally closed contact of the first position of the toggle switch is connected in parallel between the ignition output aviation connector and the ignition input aviation connector, and the normally open contact of the second position of the toggle switch is connected in series between the ignition output aviation connector and the ignition input aviation connector.

[0033] The small cluster rocket booster ground controller adopts AC220V power supply, and is connected to the power-on switch component in the measurement and control terminal through the measurement and control terminal power supply aviation connector, connected to the AC220V power indicator light component, and connected to the DC regulated power supply for voltage conversion, which is converted into DC24V and DC48V; DC24V is connected from the DC24V output end of the DC regulated power supply to the DC24V power indicator light, and is connected to the power supply input end of the programmable logic controller and the power supply end of the control circuit board component in the measurement and control terminal, and is connected to the switch signal aviation connector 2 through a cable, and then connected to the switch signal aviation connector 1 on the human-machine interaction interface through the switch signal cable, so as to power the touch screen on the human-machine interaction interface; DC48V is connected from the 48V output end of the DC regulated power supply to the DC48V power indicator light, and is connected to the ignition voltage power supply end of the control circuit board component; the DC48V signal display output cable of the DC regulated power supply in the measurement and control terminal is connected to the switch signal aviation connector 1 on the human-machine interaction interface through the switch signal aviation connector 2 and then through the switch signal cable, and then connected to the ignition voltage digital display on the human-machine interaction interface.

[0034] like Figure 1 As shown, the small cluster rocket booster ground controller is connected in the following manner when in use: the Ethernet aviation connector 1 of the human-machine interaction interface is connected to the Ethernet aviation connector 2 of the measurement and control terminal via an Ethernet cable 1, the loop resistance test aviation connector 1 of the human-machine interaction interface is connected to the loop resistance test aviation connector 2 of the measurement and control terminal via a loop resistance test cable, the switch signal aviation connector 1 of the human-machine interaction interface is connected to the switch signal aviation connector 2 of the measurement and control terminal via a switch signal cable; the ignition output aviation connector components of the measurement and control terminal are respectively connected to the ignition input aviation connectors of the corresponding on-site fuse boxes via ignition cables.

[0035] The small cluster rocket booster ground controller has the following steps for testing the loop resistance: the power-on switch component in the measurement and control terminal is turned to the power-on state, which is manifested by the AC220V power indicator light, the DC24V power indicator light, and the DC48V power indicator light all being on; the button switch on the on-site fuse box is turned to the "released" state; the ignition permission switch on the human-computer interaction interface is turned to the "safety" gear, the test loop selection switch is turned to the corresponding loop number, the loop resistance tester is turned to the corresponding detection gear, and then the test button and the test button on the loop resistance tester are pressed at the same time, and the loop resistance tester can display the tested loop resistance status.

[0036] The ignition steps of the small cluster rocket booster ground controller are as follows: the power switch component in the measurement and control terminal is turned to the power-on state, which is manifested by the AC220V power indicator light, the DC24V power indicator light, and the DC48V power indicator light all being on; the ignition sequence is set on the touch screen on the human-computer interaction interface, and the ignition permission switch is turned to the "release" position; the button switch on the on-site fuse box is turned to the "release" position; finally, the "ignition" button on the human-computer interaction interface is pressed.

Claims

1. A small cluster rocket booster ground controller, characterized in that: include: A human-machine interaction interface (1), a measurement and control terminal (2), and an on-site fuse box (3); the human-machine interaction interface (1) and the measurement and control terminal (2) are connected via an Ethernet cable 1 (5), a loop resistance test cable (6), and a switch signal cable (7); and the measurement and control terminal (2) and the on-site fuse box (3) are connected via an ignition cable (4).

2. The small cluster rocket booster ground controller according to claim 1, characterized in that: The human-machine interaction interface (1) comprises a human-machine interaction interface front panel (8) and a human-machine interaction interface rear panel (9); the human-machine interaction interface front panel (8) is provided with a touch screen (11), a loop resistance detector (12), an emergency stop button (13), a test loop selection switch (14), a test button (15), an ignition permission switch (16), an ignition button (17), and an ignition voltage digital display (18); the human-machine interaction interface rear panel (9) is provided with an Ethernet aviation connector 1 (20), an aviation connector 1 (21) for loop resistance value testing, and an aviation connector 1 (19) for switch signals; the touch screen (11) and the Ethernet aviation connector 1 (20) are connected via an Ethernet cable 2 (10).

3. The small cluster rocket booster ground controller according to claim 2, characterized in that: The test port of the loop resistance detector (12) is connected to the output port of the test loop selection switch (14), the input end of the test loop selection switch (14) is respectively connected to the core point of the aviation connector 1 (21) for loop resistance value testing, the connection points of the emergency stop button (13), the test loop selection switch (14), the test button (15), the ignition permission switch (16), the ignition button (17), and the ignition voltage digital display (18) are respectively connected to the aviation connector 1 (19) for switch signal, and the touch screen (11) is connected to the Ethernet aviation connector 1 (20) via the Ethernet cable 2 (10).

4. The small cluster rocket booster ground controller according to claim 1, characterized in that: The measurement and control terminal (2) comprises a measurement and control terminal front panel (22), a measurement and control terminal rear panel (23), a measurement and control terminal left panel (24), a measurement and control terminal right panel (25), a measurement and control terminal upper panel (26), and a measurement and control terminal bottom panel (27); the measurement and control terminal bottom panel (27) is provided with a DC regulated power supply (28), a programmable logic controller (29), and a control circuit board assembly (30); the measurement and control terminal front panel (22) is provided with an AC220V power indicator light (31), a DC24V power indicator light (49), a DC48V power indicator light (50), a power-on switch assembly (32), and a switch door assembly (33); the measurement and control terminal rear panel (23) is provided with a power supply aviation connector (34), an Ethernet aviation connector 2 (35), a loop resistance test aviation connector 2 (36), a switch signal aviation connector 2 (37), and an ignition output aviation connector assembly (38); the programmable logic controller (29) is connected to the Ethernet aviation connector 2 (35) via an Ethernet cable 3 (39).

5. The small cluster rocket booster ground controller according to claim 4 is characterized in that: The Ethernet aviation connector 1 (20) of the human-machine interaction interface (1) is connected to the Ethernet aviation connector 2 (35) of the measurement and control terminal (2) via an Ethernet cable 1 (5); the loop resistance test aviation connector 1 (21) of the human-machine interaction interface (1) is connected to the loop resistance test aviation connector 2 (36) of the measurement and control terminal (2) via a loop resistance test cable (6); and the switch signal aviation connector 1 (19) of the human-machine interaction interface (1) is connected to the switch signal aviation connector 2 (37) of the measurement and control terminal (2) via a switch signal cable (7).

6. The small cluster rocket booster ground controller according to claim 5, characterized in that: The ignition output aviation connector assembly (38) of the measurement and control terminal (2) is respectively connected to the ignition input aviation connector (47) of the corresponding on-site fuse box (3) via an ignition cable (4).

7. The small cluster rocket booster ground controller according to claim 4, characterized in that: The AC220V power is supplied to the system through the power supply aviation connector (34) of the measurement and control terminal (2), and then is converted to DC24V and DC48V through the power switch assembly (32) in the measurement and control terminal (2); the DC24V is connected from the DC24V output end of the DC regulated power supply (28) to the power supply input end of the programmable logic controller (29) and the control circuit board assembly (30) in the measurement and control terminal (2) for power supply, and is connected to the switch signal aviation connector 2 (37) through a cable, and then connected to the human body through the switch signal cable (7). The switch signal aviation connector 1 (19) on the human-machine interaction interface (1) supplies power to the touch screen (11) on the human-machine interaction interface (1); DC48V is connected from the 48V output end of the DC regulated power supply (28) to the control circuit board assembly (30); the DC48V signal display output cable of the DC regulated power supply (28) in the measurement and control terminal (2) is connected to the switch signal aviation connector 1 (19) on the human-machine interaction interface (1) via the switch signal aviation connector 2 (37) and then via the switch signal cable (7), and then connected to the ignition voltage digital display (18) on the human-machine interaction interface (1).

8. The small cluster rocket booster ground controller according to claim 7, characterized in that: The digital input port of the programmable logic controller (29) is respectively connected to the corresponding core points of the switch signal aviation connector 2 (37), the digital output port of the programmable logic controller (29) is respectively connected to the corresponding input core points of the control circuit board assembly (30), the Ethernet of the programmable logic controller (29) is connected to the Ethernet aviation connector 2 (35) via the Ethernet cable 3 (39), the output core points of the control circuit board assembly (30) are respectively connected to the corresponding core points of the ignition output aviation connector assembly (38), and the core points of the loop resistance test aviation connector 2 (36) are respectively connected to the corresponding core points of the ignition output aviation connector assembly (38).

9. The small cluster rocket booster ground controller according to claim 1, characterized in that: The on-site fuse box (3) comprises an on-site fuse box front panel (40), an on-site fuse box rear panel (41), an on-site fuse box left panel (42), an on-site fuse box right panel (43), an on-site fuse box upper panel (44), and an on-site fuse box bottom panel (45); the on-site fuse box front panel (40) is provided with a button switch (46) and an ignition input aviation connector (47); the on-site fuse box rear panel (41) is provided with an ignition output aviation connector (48).

10. The small cluster rocket booster ground controller according to claim 9, characterized in that: A normally closed contact of the toggle switch (46) is connected in parallel between the ignition output aviation connector (48) and the ignition input aviation connector (47), and a normally open contact of the toggle switch (46) is connected in series between the ignition output aviation connector (48) and the ignition input aviation connector (47).

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