CN207649451U - Air weapon training system - Google Patents
Air weapon training system Download PDFInfo
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- CN207649451U CN207649451U CN201721805954.5U CN201721805954U CN207649451U CN 207649451 U CN207649451 U CN 207649451U CN 201721805954 U CN201721805954 U CN 201721805954U CN 207649451 U CN207649451 U CN 207649451U
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- air
- simulation
- combustion chamber
- air intake
- intake duct
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Abstract
The utility model belongs to air weapon technical field.A kind of air weapon training system, including rack, start simulation of engine system, sustainer simulation system, air-channel system simulator and electric control cabinet, the startup simulation of engine system includes motor body, solid rocket fuel, igniter and jet pipe；The sustainer simulation system includes fuel tank and the combustion chamber of correspondence setting, is laid with multiple air intake ducts on the combustion box, combustion chamber rear end is provided with radome fairing；The air-channel system simulator includes the nitrogen cylinder and safety device being laid on the outside of combustion chamber；The electric control cabinet is arranged in rack.The utility model is related to a kind of air weapon training systems, pass through the Main Tectonic Characteristics to certain type air-to-ground guided missile engine, pass through the modes such as the imitated, functional simulation of structure, realize construction and operation principle teaching displaying function, the funding problems in place, environmental problem and army when solving the problems, such as trained.
Description
Technical field
The utility model belongs to air weapon technical field, and in particular to a kind of air weapon training system.
Background technology
Growing day by day with weaponry new and high technology, training time and difficulty also greatly increase, and traditional actual load is real
Bullet training brings prodigious burden in place construction and input to army, and training opportunity is affected by environment, instruction
Practice subject by constraint based on sites, there is also hidden dangers for actual load training in addition.
Invention content
The purpose of this utility model is in view of the above problems and insufficient, provide it is a kind of reasonable in design, can
By the Main Tectonic Characteristics of air-to-ground guided missile engine, pass through the imitated religion that structure and function principle is realized with functional simulation of structure
Learn the air weapon training system of simulation loop.
In order to achieve the above objectives, it is adopted the technical scheme that：
A kind of air weapon training system, including rack, startup simulation of engine system, sustainer simulation system, gas
Road system simulator and electric control cabinet, the startup simulation of engine system include motor body, are arranged in engine
Solid rocket fuel in shell and the igniter and jet pipe for being separately positioned on motor body rear and front end；The master
Simulation of engine system includes fuel tank and the combustion chamber of correspondence setting, and multiple air intake ducts are laid on the combustion box,
Combustion chamber rear end is provided with radome fairing；The air-channel system simulator includes nitrogen cylinder and the insurance being laid on the outside of combustion chamber
Device；The electric control cabinet is arranged in rack.
The motor body is half-sectional structure, and pad has thermal insulation layer in engine shell body.
The motor body rear end is provided with tail-hood, and the jet pipe is connected solid by the threaded hole being opened on tail-hood
It is fixed.
The igniter is mounted on by screw thread on motor body, and igniter front end is provided with squib, institute
Squib to be stated to connect with radiating circuit by cable, the igniter rear end is tubular structure, internal to be filled with ignition charge,
And multiple fire output hole roads are provided on the tube wall of igniter rear end.
It is laid on the combustion box there are four air intake duct, is provided with fiaring cone in the air intake duct, is provided in combustion chamber
Pressure sensor, photoelectric sensor and internal shield cover have air-inlet cover in the end set of air intake duct, are also set up on air intake duct
It includes electric igniter and piston to have canopy jettison mechanism, the canopy jettison mechanism, and air-inlet cover is dished out by canopy jettison mechanism.
The air-channel system simulator includes three nitrogen cylinders, and three nitrogen cylinders are correspondingly arranged at a left side for combustion chamber respectively
Top, upper right side and lower right.
The blue light air inlet mark of movement is provided on the air intake duct, the nacelle at the air intake duct rear portion is in half-sectional structure,
The half-sectional position at the air intake duct rear portion is provided with igniting powder column mark and ignition location mark, and the ignition location mark is located at
The injector junction of air intake duct and fuel tank.
The bottom of the frame is provided with universal wheel and shores stabilizer blade.
Using above-mentioned technical proposal, acquired advantageous effect is：
1. the utility model is related to a kind of air weapon training system, pass through the main structure to certain type air-to-ground guided missile engine
Feature is made, by modes such as the imitated, functional simulations of structure, construction and operation principle teaching displaying function is realized, solves instruction
Place problem, environmental problem and the funding problems of army when practicing.
2. certain type air weapon training system of the utility model, fuel tank, combustion chamber in sustainer simulation system,
Air intake duct is used in combination the blue light mark of movement, is electrically combined to simulate a whole set of system using pressure inductor and photoelectric sensor
The displaying of the operation principle and internal structure of system eliminates unsafe hidden danger when training.
Description of the drawings
Fig. 1 is the structural schematic diagram of the utility model.
Fig. 2 is the overlooking structure diagram of Fig. 1.
Fig. 3 is the left view structural representation of Fig. 1.
Fig. 4 is the right side structural representation of Fig. 1.
Serial number in figure：100 be start simulation of engine system, 101 be motor body, 102 be solid rocket fuel,
103 be igniter, 104 be jet pipe, 200 be main simulation of engine system, 201 be fuel tank, 202 be combustion chamber, 203 for into
Air flue, 204 be radome fairing, 301 be nitrogen cylinder, 400 be electric control cabinet, 500 be rack, 501 be universal wheel, 502 to shore
Stabilizer blade.
Specific implementation mode
It elaborates to specific embodiment of the present utility model below in conjunction with attached drawing.
Referring to Fig. 1-Fig. 4, a kind of air weapon training system include mainly start simulation of engine system 100, master starts
Machine simulation system 200 and air-channel system simulator.Its main implementation method includes detachable starting engine, sustainer
Component, body are half-sectional, simulate the displaying of the principles such as oil circuit, gas circuit, firing circuit and fuel system, are provided in 500 bottom of rack
Universal wheel 501 and stabilizer blade 502 is shored, electric control cabinet 400 is set in rack.
It includes motor body 101, solid rocket fuel 102, jet pipe 104, Yi Jidian to start simulation of engine system
Fire tool 103.
Wherein, motor body 101 mainly plays support, fixed function.In order to facilitate teaching, motor body is using half-sectional
Structure.Semicircle before entire shell front is welded as one, covering front form bowl-shape.There is aperture at rear portion, is glued on the inside of motor body
Paste heat-barrier material.Solid rocket fuel should be housed inside motor body.
Solid rocket fuel, the targeted startup engine of the application be solid propellant rocket, herein use it is wooden or
The column structure of plastic shaping.There is the inner passage in staged cylindrical shape in the front of cylinder, and rear portion is star-shaped, can be torn open
It unloads, imparts knowledge to students for convenience.
Jet pipe 104 is provided with rear cover, nozzle hole and liner composition on jet pipe 104.Rear cover acts the shell to charge
Protective effect；Jet pipe is installed in the screw thread mouth of rear cover, can be made of pressed material, inside is covered with semicircle film
Piece covers engine inner chamber；It is also equipped with insulation blanket in nozzle throat.
Igniter, igniter include fire tool shell, reinforce medicine and three cylindrical pyrotechnics medicine block compositions.Igniter is installed on
Motor body front end is connect by screw thread with motor body, and front is equipped with squib and passes through cable and transmitting electricity
Road is connected, and igniter rear portion is tubular shell, internal to fill ignition charge, has multiple ducts that can make igniter on tubular shell
Flame is transmitted to solid rocket fuel.Squib is made of the total head contact combination of 4 igniting shell, band conducting wires.It is each pair of to lead
Scorching hot electric bridge is welded between line, ignition charge and igniting gunpowder are pressed in shell of lighting a fire, and corking, casing, cap bag and reinforcing sleeve are used
Medicine is sealed.
Sustainer simulation system 200 is punching engine, and combustion chamber starts engine cavity.Sustainer is simulated
The critical piece of system has fuel tank 201, combustion chamber 202, air intake duct 203 and in the radome fairing 204 at combustion chamber rear portion.
Its fuel tank is used to supply and adjust the fuel into sustainer, and fuel supply is provided in fuel tank and is adjusted
Device.Fuel tank is the energy part of sustainer, and there are four air inlet and combustion chambers for dress on fuel tank.Wherein, air intake duct is
Four air intake duct compositions of tank bay are distributed in, installation fiaring cone in centre identifies airintake direction with the blue light of movement.
Combustion chamber, combustion chamber are made of burning chamber shell, internal shield cover, pressure inductor and photoelectric sensor.It will be into
Air flue rear portion hatchcover is splitted, and shows igniting powder column, is burnt with the sign powder column of yellow, corresponding ignition location is using yellow
Chromatic flicker sign, binding site of the ignition location in air intake duct and injector.
Air is carried out rectification by air intake duct, air intake duct, is sent into combustion chamber.Center cone, air inlet are provided on air intake duct
The part such as lid and canopy jettison mechanism forms.4 air intake ducts are distributed with, in each air inlet in the shell surrounding of sustainer simulation system
Have 1 center cone in road, inside sealed by air-inlet cover by baroceptor pipeline, air intake duct head, canopy jettison mechanism is by electricity
The part such as igniter and piston forms, and air-inlet cover can be dished out by it.
Air-channel system simulator is made of 3 nitrogen cylinders 301 and 1 safety device, and nitrogen cylinder is respectively arranged in along bullet
Body direction upper left, three air intake ducts of upper right and bottom right rear according to actual load simplify it is imitated.Safety device is located at the guided missile right side
The rear portion of enterprising air flue, carries out appearance and function is imitated.
The utility model is related to a kind of air weapon training systems, pass through the main construction to certain type air-to-ground guided missile engine
Feature realizes construction and operation principle teaching displaying function, solves training by modes such as the imitated, functional simulations of structure
When place problem, environmental problem and the funding problems of army.
Certain type air weapon training system of the utility model, fuel tank, combustion chamber in sustainer simulation system, into
Air flue is used in combination the blue light mark of movement, is electrically combined to simulate whole system using pressure inductor and photoelectric sensor
Operation principle and internal structure displaying, training when, eliminate unsafe hidden danger.
The basic principles, main features and advantages of the present invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and what is described in the above embodiment and the description is only the present invention
Principle, various changes and improvements may be made to the invention without departing from the spirit and scope of the present invention, these variation and
Improvement is both fallen in the range of claimed invention.The present invention claims protection domain by appended claims and its
Equivalent defines.
Claims (8)
1. a kind of air weapon training system, which is characterized in that including：
Rack；
Start simulation of engine system, the startup simulation of engine system includes motor body, is arranged in motor body
Interior solid rocket fuel and the igniter and jet pipe for being separately positioned on motor body rear and front end；
Sustainer simulation system, the sustainer simulation system include fuel tank and the combustion chamber of correspondence setting, institute
It states and is laid with multiple air intake ducts on combustion box, combustion chamber rear end is provided with radome fairing；
Air-channel system simulator, the air-channel system simulator include the nitrogen cylinder and insurance dress being laid on the outside of combustion chamber
It sets；
And electric control cabinet, the electric control cabinet are arranged in rack.
2. air weapon training system according to claim 1, which is characterized in that the motor body is half-sectional knot
Structure, pad has thermal insulation layer in engine shell body.
3. air weapon training system according to claim 1, which is characterized in that the motor body rear end is provided with
Tail-hood, the jet pipe are connected and fixed by the threaded hole being opened on tail-hood.
4. air weapon training system according to claim 1, which is characterized in that the igniter is set by screw thread installation
It sets on motor body, igniter front end is provided with squib, and the squib is connect by cable with radiating circuit,
The igniter rear end is tubular structure, internal to be filled with ignition charge, and be provided on the tube wall of igniter rear end it is multiple go out
Fire hole road.
5. air weapon training system according to claim 1, which is characterized in that on the combustion box lay there are four into
Air flue is provided with fiaring cone in the air intake duct, pressure sensor, photoelectric sensor and internal shield is provided in combustion chamber
Cover, has air-inlet cover in the end set of air intake duct, and canopy jettison mechanism is additionally provided on air intake duct, and the canopy jettison mechanism includes electric point
Firearm and piston are dished out air-inlet cover by canopy jettison mechanism.
6. air weapon training system according to claim 1, which is characterized in that the air-channel system simulator includes
Three nitrogen cylinders, three nitrogen cylinders are correspondingly arranged at the upper left side, upper right side and lower right of combustion chamber respectively.
7. air weapon training system according to claim 5, which is characterized in that be provided with movement on the air intake duct
Blue light air inlet identifies, and the nacelle at the air intake duct rear portion is in half-sectional structure, and the half-sectional position setting at the air intake duct rear portion is a little
Stick identifies and ignition location mark, and the ignition location mark is positioned at the injector junction of air intake duct and fuel tank.
8. air weapon training system according to claim 1, which is characterized in that the bottom of the frame is provided with universal wheel
With shore stabilizer blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721805954.5U CN207649451U (en) | 2017-12-21 | 2017-12-21 | Air weapon training system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721805954.5U CN207649451U (en) | 2017-12-21 | 2017-12-21 | Air weapon training system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207649451U true CN207649451U (en) | 2018-07-24 |
Family
ID=62877905
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721805954.5U Expired - Fee Related CN207649451U (en) | 2017-12-21 | 2017-12-21 | Air weapon training system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207649451U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114251984A (en) * | 2021-12-16 | 2022-03-29 | 中国人民解放军火箭军工程大学 | Equivalent target design method of solid propulsion device |
-
2017
- 2017-12-21 CN CN201721805954.5U patent/CN207649451U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114251984A (en) * | 2021-12-16 | 2022-03-29 | 中国人民解放军火箭军工程大学 | Equivalent target design method of solid propulsion device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180724 Termination date: 20201221 |