A dangerous gas detection missile and its launching system

Abstract

The application provides a dangerous gas detection missile and a launching system thereof. The missile comprises a lip, an air inlet cover, an air inlet channel, an air filter, a gas detection instrument, an air outlet shell, a battery cabin and a parachute compartment. The lip is sleeved on the air inlet cover. The inner wall of the lip is streamlined. The tail end of the air inlet cover is connected with the front end of the air outlet shell. The air inlet channel is pushed into the rear end of the air outlet shell, and the front end of the air inlet channel abuts against the boss of the air outlet shell. The air filter is pushed into the rear end of the air outlet shell, and the air filter is pressed on the air inlet channel. The gas detection instrument is arranged at the rear end of the air filter. The rear end of the air outlet shell is connected with the battery cabin. The battery cabin is further connected with the parachute compartment. The application can make a large amount of air flow into the missile head, pass through the gas detection sensor and improve the accuracy of measurement data.

Description

Technical Field

[0001] This invention relates to the field of model design, and in particular to a dangerous gas detection missile and its ejection system. Background Technology

[0002] Existing unpowered missiles consist of a warhead, a missile bay, a tail section, fins, and a parachute. The warhead is bullet-shaped to reduce drag and incorporates shock-absorbing structures to prevent fragmentation. The missile bay carries mission equipment to fulfill mission requirements. Tail fins are fixed to the tail section to stabilize flight attitude. The parachute slows descent and protects the mission payload. However, because the missile's outer shell is sealed and the mission payload is located entirely within the missile bay, the gas exposure to measuring instruments is limited, resulting in unreliable measurement values.

[0003] Existing cylindrical catapults consist of a launch frame, launch tubes, a gas storage device, a gas filling device, and an electrical control box. The launch frame is a rectangular frame with a rotating structure, allowing for free adjustment of the launch angle. The launch tubes are aligned at both ends and arranged parallel to each other on the launch frame. Inside each launch tube is a piston, end cap, and aircraft mounting bracket; the end cap is connected to a solenoid valve. The gas storage and filling devices provide the launch tubes with gas at a specified pressure. The electrical control box enables switching between cluster launch and single-tube launch, allowing for both all launches and individual launches. The multiple launch tubes of the catapult share the same gas tank, and the launch angles of all launch tubes are the same, making it difficult to rapidly launch missiles at various angles and pressures in unmanned environments. Furthermore, existing catapults are designed for use in low-wind, hard-surface environments and are unsuitable for deserts and high-wind conditions. Summary of the Invention

[0004] In order to overcome the shortcomings of the prior art, the purpose of this invention is to provide a dangerous gas detection missile and its ejection system.

[0005] To achieve the above objectives, the present invention provides the following solution:

[0006] A hazardous gas detection missile includes: a lip, an air intake cover, an air intake duct, an air filter, a gas detection instrument, an exhaust port casing, a battery compartment, and a parachute compartment;

[0007] The lip is fitted onto the air intake cover; the inner wall of the lip is streamlined; the end of the air intake cover is connected to the front end of the exhaust port housing; the air intake duct is pushed in from the rear end of the exhaust port housing, and the front end of the air intake duct abuts against the protrusion of the exhaust port housing; the air filter is pushed in from the rear end of the exhaust port housing, and the air filter is pressed onto the air intake duct; the gas detection instrument is located at the rear end of the air filter; the rear end of the exhaust port housing is connected to the battery compartment; the battery compartment is also connected to the parachute compartment.

[0008] Preferably, the end of the air intake cover is machined with an internal thread, and the front end of the exhaust port housing is machined with an external thread. The air intake cover and the exhaust port housing are connected by the internal thread and the external thread.

[0009] Preferably, the air intake is an aluminum tube with a funnel-shaped inner hole.

[0010] Preferably, the air filter is an aluminum cup with numerous small holes, and the inside is filled with filter cotton, which is used to filter impurities in the air.

[0011] Preferably, the exhaust port housing is a fiberglass cylinder with aluminum rings bonded to both ends.

[0012] A launch system for the aforementioned hazardous gas detection missile includes a launch frame and multiple launch tubes mounted on the launch frame; each launch tube includes a welded tube, a solenoid valve, an aluminum end cap, a piston, a piston baffle, a mounting and fixing rectangular tube, and two gas storage tanks.

[0013] Each of the gas storage tanks is connected by a welded pipe; a solenoid valve, an aluminum end cap, a piston, and a piston baffle are installed sequentially from back to front in the middle of the welded pipe; the mounting and fixing rectangular tube is welded to the gas storage tank, and the mounting and fixing rectangular tube is fixed to the catapult frame through screw holes.

[0014] Preferably, the catapult includes a base plate, a ground anchor, a welding frame, an electric push rod, and a shock absorber;

[0015] The base plate is a platform structure; the ground anchor is inserted into the ground through a hexagonal hole in the base plate to fix the catapult frame; the welding frame is connected to the base plate through the shock absorber; multiple sets of the launch tubes are installed on the welding frame; the electric push rod is set on the welding frame and is used to change the angle between the welding frame and the horizontal plane.

[0016] According to specific embodiments provided by the present invention, the present invention discloses the following technical effects:

[0017] This invention provides a hazardous gas detection missile and its ejection system. The missile includes: a lip, an air intake cover, an air intake duct, an air filter, a gas detection instrument, an exhaust port shell, a battery compartment, and a parachute compartment. The lip is fitted onto the air intake cover; the inner wall of the lip is streamlined; the end of the air intake cover is connected to the front end of the exhaust port shell; the air intake duct is pushed in from the rear end of the exhaust port shell, and the front end of the air intake duct abuts against a protrusion on the exhaust port shell; the air filter is pushed in from the rear end of the exhaust port shell and pressed against the air intake duct; the gas detection instrument is located at the rear end of the air filter; the rear end of the exhaust port shell is connected to the battery compartment; the battery compartment is also connected to the parachute compartment. This invention allows a large amount of air to flow in from the missile head, passing through the gas detection sensor, thus improving the accuracy of the measurement data. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of a missile structure provided in an embodiment of the present invention;

[0020] Figure 2 This is a schematic diagram of the launching tube structure provided in an embodiment of the present invention;

[0021] Figure 3 This is a schematic diagram of the catapult structure provided in an embodiment of the present invention;

[0022] Explanation of reference numerals in the attached figures:

[0023] ①-Lip, ②-Intake cover, ③-Intake duct, ④-Air filter, ⑤-Gas detection instrument, ⑥-Exhaust port housing, ⑦-Battery compartment, ⑧-Parasol compartment, ⑨-Gas storage tank, ⑩-Welded pipe, -Solenoid valve, - Aluminum end caps -piston, - Piston baffle -Install and fix the rectangular tube, -Base plate - Ground anchor, - Welding frame, - Electric linear actuator - Vibration damper. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] The purpose of this invention is to provide a hazardous gas detection missile and its ejection system, which allows a large amount of air to flow in from the missile head and pass through the gas detection sensor, thereby improving the accuracy of the measurement data.

[0026] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0027] Main components of the invention: missile (lip ①, air intake cap ②, air intake duct ③, air filter ④, gas detection instrument ⑤, exhaust port shell ⑥, battery compartment ⑦, parachute compartment ⑧), launch tube (gas tank ⑨, welded pipe ⑩, solenoid valve) Aluminum end cap piston Piston baffle and installation of fixed rectangular tubes ) and catapult (base plate) Ground anchor Welding frame Electric linear actuator and shock absorber )

[0028] The lip ① is a cylindrical rubber sleeve that fits onto the air intake cover ②. The shape of the inner wall facilitates airflow into the air intake cover ②.

[0029] The air intake cover ② has internal threads at its end, and the exhaust port housing ⑥ has external threads at its front end. The two are connected by threads.

[0030] The air intake duct ③ is an aluminum tube with a funnel-shaped inner hole, which is pushed in from the rear end of the exhaust port housing ⑥ and abuts against the protrusion of the housing.

[0031] The air filter ④ is an aluminum cup with numerous small holes, filled with filter cotton to filter impurities in the air. It is pushed in from the rear end of the exhaust port housing ⑥ and pressed against the intake duct ③.

[0032] Gas detector ⑤ is a custom-made instrument, attached directly behind air filter ④.

[0033] The exhaust port outer shell ⑥ is a fiberglass cylinder with aluminum rings glued to both ends, and the front and rear are connected by threads on the aluminum rings.

[0034] The battery compartment ⑦ and the parachute compartment ⑧ are located in the tail section of the missile. A mounting plate is bonded to the area where the inner diameter of the tail changes. The battery compartment ⑦ is fixed to the front end of the mounting plate, and the parachute compartment ⑧ is installed at the rear end of the mounting plate.

[0035] Launch tube: Two gas tanks ⑨ are located at both ends of the launch tube and connected by a welded pipe ⑩. Solenoid valves are installed sequentially from back to front along the middle of the welded pipe ⑩. Aluminum end cap piston Piston baffle

[0036] Install fixed rectangular tube It is welded to the gas storage tank ⑨ and fixed to the catapult frame through the provided screw holes.

[0037] Catapult frame: base plate Designed as a platform, it can be stabilized by securing sandbags inside, or its lower half can be buried underground. In windy weather, it can help stabilize the platform's position. Ground anchor. Through the base plate The hexagonal hole at the top is inserted into soft ground to secure the catapult frame. (Welded frame) A total of 4 sets of launching tubes are installed on it, when the electric push rod When not elongated, welding frame The angles between the launch tubes and the horizontal plane are 0°, 5°, 10°, and 15° respectively. Electric actuator. After elongation, the entire welding frame It will rotate around an axis, with a rotation angle range of 0° to 45°, meaning the maximum launch angle of the uppermost launch tube is 60°. (Welding frame) With base plate Between them via shock absorbers The connection effectively reduces vibration across the entire frame when the missile is ejected from the launcher.

[0038] The working principle of this embodiment:

[0039] Missile: Air enters through the lip ① and exits through the exhaust port ⑥, passing through the air intake cover ②, air intake duct ③, air filter ④, and gas detection instrument ⑤. The air intake cover ② is spring-loaded and remains closed during storage to prevent contamination. The air intake duct ③ is designed to be wider on the outside and narrower on the inside to facilitate airflow. The air filter ④ filters out dust and other impurities from the air.

[0040] Gas detection instrument ⑤ measures and records the concentration of hazardous gases in filtered air.

[0041] The parachute compartment ⑧ is installed in the tail of the missile and is controlled by a gyroscope. When the missile's angle of elevation reaches the specified value, the parachute deploys.

[0042] Launch preparation stage of the launch tube: the gas in the gas storage tank ⑨ is rushed to the specified pressure, the solenoid valve is in the closed state, the piston is located at the bottom of the launch tube and is attached to the aluminum end cap.

[0043] Launching phase of the launch tube: The solenoid valve opens, and the gas passes through the aluminum end cap and acts on the piston. The piston and the missile accelerate together in the launch tube. Finally, the piston hits the piston baffle. The missile does not interfere with the piston baffle and is ejected directly.

[0044] Specifically, the catapult in this embodiment, under remote control, can launch missiles to different heights above the same location. The catapult can be deployed in deserts and has a certain degree of wind resistance. Furthermore, the missile's shape allows a large amount of air to flow into the warhead, passing through gas detection sensors for accurate data measurement.

[0045] The beneficial effects of this invention are as follows:

[0046] (1) The angle difference between the catapult launch tubes is fixed by welding. By adjusting the pressure, the missile can fly over the same location at different heights.

[0047] (2) The catapult is suitable for wasteland and windy weather. It is equipped with shock absorption devices to reduce overall shaking.

[0048] (3) A large flow of gas can pass through the middle of the missile, which can detect specific gases in the surrounding air.

[0049] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0050] This document uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A hazardous gas detection missile, characterized in that, include: Lip, air intake cover, air intake duct, air filter, gas detection instrument, exhaust port housing, battery compartment and parachute compartment; The lip is fitted onto the air intake cover; the inner wall of the lip is streamlined; the end of the air intake cover is connected to the front end of the exhaust port housing; the air intake duct is pushed in from the rear end of the exhaust port housing, and the front end of the air intake duct abuts against the protrusion of the exhaust port housing; the air filter is pushed in from the rear end of the exhaust port housing, and the air filter is pressed onto the air intake duct; the gas detection instrument is located at the rear end of the air filter; the rear end of the exhaust port housing is connected to the battery compartment; the battery compartment is also connected to the parachute compartment; The air intake is an aluminum tube with a funnel-shaped inner hole. The air filter is an aluminum cup with numerous small holes and filled with filter cotton, which is used to filter impurities in the air.

2. The hazardous gas detection missile according to claim 1, characterized in that, The air intake cover has an internal thread at its end, and the exhaust port housing has an external thread at its front end. The air intake cover and the exhaust port housing are connected by the internal thread and the external thread.

3. The hazardous gas detection missile according to claim 1, characterized in that, The exhaust port housing is a fiberglass cylinder with aluminum rings bonded to both ends.

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