Large fixed-wing aircraft for simulating flare

Abstract

This utility model belongs to the field of aircraft-based rain enhancement technology, and discloses a large-scale fixed-wing aircraft simulated flame strip for rain enhancement operations. It includes: a flame strip cavity, which has the same structure and dimensions as the flame strip being dispersed; an igniter, fixed inside the flame strip cavity and extending with an ignition electrode; an ignition indicator light, installed on the flame strip cavity and connected to the ignition electrode via an internal wire; and two signal electrodes connected in series with the igniter. This utility model solves the problems of large workload in existing operational testing preparation, high operating costs, and limited application scope. It can avoid the modification work required for testing the dispersed flame strip, greatly reducing test preparation work.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft rain enhancement operation technology, specifically relating to a simulated flame strip for a large fixed-wing aircraft used for rain enhancement operations. Background Technology

[0002] Rain enhancement aircraft are equipped with flare seeding systems for dispersing silver iodide. The silver iodide composite flare agent produces a large amount of silver iodide aerosol after electric combustion. This aerosol is then directed into the clouds by the aircraft, where its diffusion enhances the catalytic depth. The flare seeding system consists of an airborne flare seeding controller, an airborne flare seeder, and seeding flares. The seeding flares are mounted on the mounting bracket of the airborne flare seeder and inserted into the flare socket. Upon receiving the ignition signal from the airborne flare seeding controller, the airborne flare seeder emits an ignition current, igniting the seeding flares. The silver iodide flare agent within the seeding flares then combusts, forming an aerosol that diffuses into the clouds along the aircraft's trajectory.

[0003] During testing, after stripping the flare agent from the flare, test leads are drawn from inside the flare and connected to a small ignition charge. When the flare is applied, the airborne flare application controller outputs an ignition signal to the corresponding socket on the flare applicator. The ignition signal is generated by the igniter inside the flare and outputs an ignition current to the small ignition charge, causing it to ignite and explode, indicating that the application is complete.

[0004] The above method has the following drawbacks: 1. Removing the flaming agent from the flaming strip and leading out the test wire requires testing and modification of the flaming strip. After the test is completed, it needs to be restored and the flaming agent is refilled. This not only increases the workload of testing and modification, but also affects the sealing effect of the flaming strip, which can easily lead to problems such as poor contact of the flaming strip wire and moisture absorption of the flaming agent. 2. The external small incendiary packs are disposable. If the functional test requires repeated verification, the power must be turned off after the current dispersal operation is completed, and the small incendiary packs must be installed on the dispersal flame strips one by one. The workload is heavy. 3. External small pyrotechnic bags are classified as pyrotechnic items, which have strict requirements for transportation and storage, resulting in high usage costs. Furthermore, pyrotechnic items cannot meet the functional testing needs of laboratories or assembly workshops (where the use of flammable and explosive materials is prohibited in enclosed spaces), thus limiting their applicability. Utility Model Content

[0005] The purpose of this invention is to provide a large-scale fixed-wing rain enhancement aircraft simulated flame strip, which solves the problems of large workload in operation and testing preparation, high cost of use and limited scope of application of existing methods. It can avoid the test modification work of spreading flame strip during testing and greatly reduce the test preparation work.

[0006] The technical solution of this utility model is implemented as follows: A simulated flame strip for a large fixed-wing rain enhancement aircraft, comprising: The flame cavity is identical in structure and size to the flame spraying chamber; The igniter is fixed inside the flame strip cavity and extends out with ignition electrodes; The ignition indicator light is mounted on the flame strip cavity and is connected to the ignition electrode via an internal wire. Two signal electrodes are connected in series with the igniter.

[0007] As a further embodiment of this invention, a load resistor is connected in series between the igniter and the two signal electrodes.

[0008] As a further embodiment of this utility model: a flaming agent filling chamber is provided inside the flame strip cavity, and the igniter extends its ignition electrode into the flaming agent filling chamber.

[0009] As a further embodiment of this utility model: an insulating plug is provided at the front end of the flame strip cavity, and two signal electrodes are inserted into the insulating plug. The tail end is connected in series with a load resistor through an internal wire and then laid along the inner wall space of the flame strip cavity to the igniter at the rear of the flame strip cavity.

[0010] As a further embodiment of this invention: the igniter is fixed inside the flame strip cavity by a support plate.

[0011] As a further embodiment of this invention, an insulating plug is provided at the rear end of the flame strip cavity.

[0012] As a further embodiment of this utility model, the outer shell of the flame strip cavity is provided with a mounting pin.

[0013] The beneficial effects of this application are as follows: 1. This application can be directly loaded into the airborne flare dispenser and the simulated flare can be fixed on the airborne flare dispenser with the mounting clips for testing, without the need for testing modifications, thus reducing the amount of preparation work.

[0014] 2. The output wire of the built-in igniter of the simulated flame strip is connected to the ignition indicator light. The "lit" state of the ignition indicator light is used to replace the "ignition" state of the small ignition pack to indicate whether the flame strip is successfully ignited. There is no need to repeat the filling work during multiple verifications, and no testing or modification is required.

[0015] 3. The simulated flame strip of this application is equipped with sealing caps at both the front and rear ends, which improves the insulation and sealing effect of the simulated flame strip, reduces the risk of fire caused by static electricity in the environment, and also reduces the risk of foreign objects entering.

[0016] 4. The simulated flame strip of this application has the same structural parameters such as external dimensions and electrical parameters such as ignition current as the sprayed flame strip. No testing or modification is required during use, which reduces the amount of preparation work.

[0017] 5. The simulated flare of this application uses an indicator light instead of a small incendiary charge to indicate the flare's dispersal status, which avoids the problem of high transportation and storage costs for pyrotechnics; at the same time, it can be tested by powering on in a laboratory or assembly workshop, thus expanding its scope of application.

[0018] The present application will be further described in detail below with reference to the accompanying drawings of the embodiments. Attached Figure Description

[0019] Figure 1 This is a cross-sectional view of a simulated flame stripe of a large fixed-wing rain enhancement aircraft.

[0020] The numbers in the diagram are explained as follows: 1. Insulating plug; 2. Ignition indicator light; 3. Ignition device; 4. Ignition electrode; 5. Support plate; 6. Mounting pin; 7. Flame strip cavity; 8. Flame filling cavity; 9. Load resistor; 10. Internal wire; 11. Insulating plug; 12. Signal electrode. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions in the embodiments of this utility model will be described in more detail below with reference to the accompanying drawings.

[0022] In the accompanying drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of this utility model.

[0023] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0024] The following is in conjunction with the appendix Figure 1 The embodiments of this utility model will be described in detail below.

[0025] Example 1 This utility model provides a simulated flame bar for a large fixed-wing rain enhancement aircraft, comprising: The flame strip cavity 7 has the same structure and size as the flame strip spreading cavity; the rear end of the flame strip cavity 7 is equipped with an insulating plug 1, and the outer shell of the flame strip cavity 7 is provided with an installation pin 6.

[0026] Igniter 3 is fixed inside flame strip cavity 7 and extends out ignition electrode 4; igniter 3 is fixed inside flame strip cavity 7 by support plate 5.

[0027] Ignition indicator light 2 is installed on flame chamber 7 and connected to ignition electrode 4 via built-in wire 10; ignition indicator light 2 must protrude from the outer shell of flame chamber 7.

[0028] Two signal electrodes 12 are connected in series with the igniter 3.

[0029] Furthermore, a load resistor 9 is connected in series between the igniter 3 and the two signal electrodes 12. A propellant filling chamber 8 is provided inside the flame chamber 7, and the igniter 3 extends from the ignition electrode 4 into the propellant filling chamber 8. An insulating plug 11 is provided at the front end of the flame chamber 7, and both signal electrodes 12 are inserted into the insulating plug 11. Their tail ends are connected in series with the load resistor 9 via an internal wire 10 and laid along the inner wall of the flame chamber 7 to the igniter 3 at the rear of the flame chamber 7.

[0030] Example 2 See Figure 1 The simulated flame chamber 7 has the same structure and dimensions as the flame-spreading device, and the flame chamber 7 is equipped with mounting pins 6 on the outside. An insulating plug 11 is installed at the front end of the flame chamber 7, with two signal electrodes 12 fixed in the middle of the insulating plug 11. The tail ends of the signal electrodes 12 are connected in series with a load resistor 9 via an internal wire 10, and then laid along the inner wall of the chamber to the igniter 3 at the rear of the chamber. The igniter 3 is fixed inside the chamber by a support plate 5. The igniter 3 extends from the ignition electrode 4 to the flare filling chamber 8 in the middle of the chamber. The flare filling chamber 8 in the simulated flame is empty (not filled with flare). The ignition electrode 4 is connected to the ignition indicator light 2 via a wire, and an insulating cap 1 is installed at the rear end of the chamber.

[0031] A method for using simulated flame strips on a large fixed-wing rain enhancement aircraft: When testing the flare distribution system on a rain enhancement aircraft, a simulated flare is loaded onto the fixed frame of the airborne flare distributor and secured with mounting pins 6. The signal electrode 12 is inserted into the corresponding flare socket. The aircraft power supply is then turned on, activating the airborne flare distribution system. The airborne flare distributor automatically outputs a 0.02A detection current to the distributor socket. Sockets without a simulated flare cannot form a circuit, resulting in an open circuit signal. In sockets with a simulated flare, the detection current forms a circuit through the internal circuit signal electrode 12, built-in wire 10, load resistor 9, igniter 3, ignition indicator light 2, and signal electrode 12, feeding back a load signal to the airborne flare distribution controller. Upon receiving the load signal from the corresponding socket, the controller identifies the simulated flare's loading position and sends the loading information to the mission management computer, displaying it on the corresponding area of ​​the monitor. At this time, since the identification current is only 0.02A, it is insufficient to start the igniter 3 and the ignition indicator light 2, so neither of them has reached the working state.

[0032] When the tester selects the simulated flare on the human-machine interface and clicks the "Spread" button, the task management computer outputs a "Spread" signal to the airborne flare spreading controller. The airborne flare spreading controller outputs an ignition signal to the built-in ignition controller of the airborne flare spreader. The ignition controller outputs a 1A ignition current to the socket of the airborne flare spreader. Sockets without simulated flares cannot form a circuit and do not perform the ignition action. Sockets with simulated flares installed receive the ignition current through the signal electrode 12, the built-in wire 10, and the load resistor 9 to the igniter 3 located at the rear of the cavity. The igniter 3 generates an electric spark at the ignition electrode 4 due to the ignition current. The built-in wire 10 connected to the ignition electrode 4 converts the electric spark into current and transmits it to the ignition indicator light 2. The ignition indicator light 2 lights up instantly upon being energized, indicating that the flare has received the "ignition" signal and completed the "ignition" action.

[0033] According to the functional testing requirements of the flare spraying system, complete the loading identification of each flare socket on the airborne flare sprayer and verify the ignition control function of the flare spraying system. After the test, disconnect the power supply of the airborne flare spraying system, disconnect the power supply of the aircraft, and remove the simulated flares.

[0034] This invention utilizes a simulated flare with structural parameters such as dimensions and electrical parameters such as ignition current identical to those of the flare-spreading system. This simulated flare is mounted on an airborne flare spreader for functional testing, eliminating the need for modifications to the flare-spreading system during testing and significantly reducing preparation work. Furthermore, the use of indicator lights to show the ignition action avoids the use of pyrotechnic devices (small incendiary devices), greatly reducing storage and transportation costs and safety risks. Moreover, it meets the testing needs of relatively enclosed spaces such as laboratories or assembly workshops, expanding its application scope and providing a new solution for early-stage product development testing and later batch production assembly functional testing. This facilitates testing and troubleshooting, significantly shortening the development and production cycle and meeting development and production requirements.

[0035] Thus, the objective of this utility model has been achieved.

[0036] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A simulated flame strip for a large fixed-wing rain enhancement aircraft, characterized in that, include: The flame cavity is identical in structure and size to the flame spraying chamber; The igniter is fixed inside the flame strip cavity and extends out with ignition electrodes; The ignition indicator light is mounted on the flame strip cavity and is connected to the ignition electrode via an internal wire. Two signal electrodes are connected in series with the igniter.

2. The simulated flame strip of the large fixed-wing rain enhancement aircraft according to claim 1, characterized in that, A load resistor is also connected in series between the igniter and the two signal electrodes.

3. The simulated flame strip of the large fixed-wing rain enhancement aircraft according to claim 2, characterized in that, A flame filling chamber is provided inside the flame strip cavity, and the igniter extends its ignition electrode into the flame filling chamber.

4. The simulated flame strip of the large fixed-wing rain enhancement aircraft according to claim 3, characterized in that, An insulating plug is installed at the front end of the flame strip cavity, and two signal electrodes are inserted into the insulating plug. The tail end of the electrode is connected in series with a load resistor through an internal wire and then laid along the inner wall of the flame strip cavity to the igniter at the rear of the flame strip cavity.

5. The simulated flame strip of the large fixed-wing rain enhancement aircraft according to claim 4, characterized in that, The igniter is fixed inside the flame strip cavity by a support plate.

6. The simulated flame strip of the large fixed-wing rain enhancement aircraft according to claim 5, characterized in that, An insulating plug is installed at the rear end of the flame strip cavity.

7. The simulated flame strip of a large fixed-wing rain enhancement aircraft according to any one of claims 1-6, characterized in that, The flame strip cavity shell is provided with mounting pins.

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