CN103591857A - Rocket composite simulation test device - Google Patents
Rocket composite simulation test device Download PDFInfo
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- CN103591857A CN103591857A CN201310603818.8A CN201310603818A CN103591857A CN 103591857 A CN103591857 A CN 103591857A CN 201310603818 A CN201310603818 A CN 201310603818A CN 103591857 A CN103591857 A CN 103591857A
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Abstract
The invention particularly relates to a rocket composite simulation test device which solves the problem that an existing micro-miniature rocket flight process is affected by environmental forces and sequentially, simulation is difficult. The rocket composite simulation test device comprises an organic glass intake pipeline with a flaring-shaped upper end portion. A rocket carrier is arranged in the organic glass intake pipeline and a high-speed motor is arranged above the rocket carrier. A suspension wire is connected to the output shaft of the high-speed motor and the other end of the suspension wire is connected with the rocket carrier. A laser source which aligns with the tail end of the rocket carrier is arranged beside the high-speed motor. An electromagnet is arranged on the outer side wall of the organic glass intake pipe. A blind hole is formed in the middle of the tail end of the rocket carrier. Dry ice is put into the blind hole and a tail stopper is arranged at one end portion of the blind hole and provided with an exhaust hole. The bottom of the organic glass intake pipeline is connected with a ventilation pipeline in a threaded mode. The other end of the ventilation pipeline is provided with an adjustable air valve which is communicated with the ventilation pipeline. The other end of the adjustable air valve is connected with an air source through a pipeline. Posture variation of the rocket carrier when the rocket carrier is disturbed can be visually observed with the rocket composite simulation test device.
Description
Technical field
The present invention relates to play model rocket and intend technical field of measurement and test, be specially the bullet arrow composite analogy experimental rig of a kind of microminiature bullet flight High Rotation Speed, high-speed flight, high velocity jet for attitude-simulating.
Background technology
Along with the extensive utilization of various high and new technologies in military field, the performance of weaponry has had tremendous development, to playing flight test, also has higher requirement.The content measurements such as flight attitude that play arrow also become more and more important.Under different flight environment of vehicle, the flight attitude, the track that play arrow are very large to its performance and control effect, cause and play flight changed condition complexity, and be difficult to reproduce in theoretical simulation.
Aspect the test of bullet arrow, domestic current related application has: missile-borne storage test, optical measurement and radar test etc.Wherein, missile-borne storage test is fragile, reclaims difficulty, is difficult for looking for bullet; The easy climate of optical measurement and barrier impact and operating distance are near; Radar test is easily disturbed, precision is poor and have phenomenons such as blind area and black barrier when remote.
Aspect test, existing bullet arrow adopts simulated test and two aspects of ball firing conventionally simultaneously, and ball firing high cost normally adopts when playing the final test of arrow or checking and accepting.In the development stage, normally by simulated test, test or analyze the various parameters that play arrow.Aspect simulated test, the flight attitude simulation employing wind tunnel test simulation conventionally for large-scale bullet arrow, utilizes wind tunnel test relative consumption excessive for small-sized bullet, is also relatively difficult to the flight attitude of imitating shell simultaneously.During wind tunnel test, underproof bullet arrow is normally in relative static conditions, and the principle simulation bullet arrow that utilizes relative motion be aloft the hit by a bullet attitude of arrow of flight course changes and the variation of surface gas pressure.But for small-sized bullet, if the bullet of 20mm shell and 17.5mm etc. is because its motion process exists the high speed rotation around self axle, in existing wind tunnel test, be difficult to realize its rotation, simultaneously, radially both direction is unfettered or be only subject to micro-constraint be difficult to guarantee underproof bullet, therefore, need to study new pilot system, to adapt to development and the development demand of microminiature bullet arrow.
Summary of the invention
The present invention causes in order to solve the suffered environmental forces impact of existing microminiature bullet flight process the problem that simulation is more difficult, and a kind of bullet arrow composite analogy experimental rig is provided.
The present invention adopts following technical scheme to realize: play arrow composite analogy experimental rig, comprise that upper end is the lucite admission line of enlarging shape, in lucite admission line, be provided with and play arrow carrier, play arrow carrier top and be provided with high-speed electric expreess locomotive, on the output shaft of high-speed electric expreess locomotive, be connected with the suspension that the other end is connected with bullet arrow carrier, high-speed electric expreess locomotive side is provided with aims at the lasing light emitter that plays arrow carrier tail end, lucite admission line lateral wall is provided with and the electromagnet that plays arrow carrier horizontal level and align, play arrow carrier tail end middle part and have blind hole, in blind hole, be placed with dry ice, it is stifled that blind bore end is provided with the tail being threaded with it, tail blocks and has steam vent, the bottom thread of lucite admission line is connected with breather line, the other end of breather line is provided with the adjustable air valve being communicated with it, the other end of adjustable air valve is connected with source of the gas by pipeline.
While playing the test of flight attitude-simulating, regulate the isometric assurance bullet of suspension arrow carrier straight down, start subsequently high-speed electric expreess locomotive, make it slowly accelerate to rotate, the high-speed electric expreess locomotive band arrow carrier of moving accelerate to rotate and to reach desired speed, because suspension is flexible, therefore can think suspension to the restraining force that plays arrow a little less than, and when suspension is installed, suspension is distributed in the same cross-sectional periphery that plays arrow carrier, therefore suspension does not have restraining force to playing other position of arrow, other position that plays arrow can freely swing, this process can imitating shell arrow the gyrocompassing flight course that produces of high speed rotation.
While irradiate playing arrow carrier with lasing light emitter, the dry ice gasification that can make to play in arrow carrier is gases at high pressure, by playing the fumarole that the tail of arrow carrier tail end blocks, sprays, and now can realize high speed rotation process and the rocket engine course of injection of imitating shell arrow.Then open adjustable valve, put into gases at high pressure, can realize imitating shell arrow flight course in air, by external test macro, can measure the attitude parameter that now plays arrow.By controlling magnet switching, can realize and produce radially gravitation interference to playing arrow carrier, make to play arrow carrier generation lateral deflection, realize imitating shell arrow in flight course, air agitation is to playing the horizontal disturbance physical process of arrow.
Can realize the orientation process of the high speed spin generation of simulation microminiature bullet arrow simultaneously, rocket engine course of injection, air side changes process to interfering process and air to the attitude of bullet.Overcome the suffered environmental forces impact of existing microminiature bullet flight process and caused the problem that simulation is more difficult.
The quantity of suspension is 4-8 bar, and suspension is the some metal steel wires that length is identical.
Structural design of the present invention is reliable, high speed during by the flight of high-speed electric expreess locomotive imitating shell spins, regulate gases at high pressure air inflow, air-flow during imitating shell flight, electromagnet causes diametral interference through switching electricity to playing arrow carrier, the attitude influence process of the crossflow of imitating shell arrow to the bullet that spins at a high speed.Play dry ice in arrow carrier and be excited light source and irradiate gasification, and the aperture discharge process blocking by tail, the jet adjustment process of engine that can imitating shell arrow.Whole process of the test whole process can effectively be observed, and can get off by setting up camera recordings, can intuitively reflect that air-flow is to playing the influence process of arrow attitude of carrier.It is simple in structure, easy to operate and cost is low that the present invention has advantages of.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is the partial enlarged drawing at A place in Fig. 1.
In figure: 1-lucite admission line, 2-bullet arrow carrier, 3-high-speed electric expreess locomotive, 4-suspension, 5-lasing light emitter, 6-electromagnet, 7-tail is stifled, 8-dry ice, 9-breather line, 10-source of the gas, 11-adjustable air valve.
The specific embodiment
Play arrow composite analogy experimental rig, comprise that upper end is the lucite admission line 1 of enlarging shape, in lucite admission line 1, be provided with and play arrow carrier 2, play arrow carrier 2 tops and be provided with high-speed electric expreess locomotive 3, on the output shaft of high-speed electric expreess locomotive 3, be connected with the suspension 4 that the other end is connected with bullet arrow carrier 2, high-speed electric expreess locomotive 3 sides are provided with aims at the lasing light emitter 5 that plays arrow carrier 2 tail ends, lucite admission line 1 lateral wall is provided with and the electromagnet 6 that plays arrow carrier 2 horizontal levels and align, play arrow carrier 2 tail end middle parts and have blind hole, in blind hole, be placed with dry ice 8, blind bore end is provided with the tail stifled 7 being threaded with it, on tail stifled 7, have steam vent, the bottom thread of lucite admission line 1 is connected with breather line 9, the other end of breather line 9 is provided with the adjustable air valve 11 being communicated with it, the other end of adjustable air valve 11 is connected with source of the gas 10 by pipeline.
The quantity of suspension 4 is 4-8 bar, and suspension 4 is the some metal steel wires that length is identical.
In specific implementation process, the quantity of steam vent is 4-8, and suspension 4 be take and played the uniform setting as the center of circle of arrow carrier 2, guarantees bullet arrow carrier 2 straight down; The internal diameter of lucite admission line 1 is for more than playing the twice of arrow carrier diameter; Source of the gas 10 adopts compressed nitrogen, or the inert gas of other compression and air.
Claims (2)
1. a bullet arrow composite analogy experimental rig, it is characterized in that: comprise that upper end is the lucite admission line (1) of enlarging shape, in lucite admission line (1), be provided with and play arrow carrier (2), play arrow carrier (2) top and be provided with high-speed electric expreess locomotive (3), on the output shaft of high-speed electric expreess locomotive (3), be connected with the suspension (4) that the other end is connected with bullet arrow carrier (2), high-speed electric expreess locomotive (3) side is provided with aims at the lasing light emitter (5) that plays arrow carrier (2) tail end, lucite admission line (1) lateral wall is provided with and the electromagnet (6) that plays arrow carrier (2) horizontal level and align, play arrow carrier (2) tail end middle part and have blind hole, in blind hole, be placed with dry ice (8), blind bore end is provided with the tail stifled (7) being threaded with it, tail has steam vent on stifled (7), the bottom thread of lucite admission line (1) is connected with breather line (9), the other end of breather line (9) is provided with the adjustable air valve (11) being communicated with it, the other end of adjustable air valve (11) is connected with source of the gas (10) by pipeline.
2. bullet arrow composite analogy experimental rig according to claim 1, is characterized in that: the quantity of suspension (4) is 4-8 bar, and suspension (4) is the some metal steel wires that length is identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310603818.8A CN103591857B (en) | 2013-11-26 | 2013-11-26 | Rocket composite simulation test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310603818.8A CN103591857B (en) | 2013-11-26 | 2013-11-26 | Rocket composite simulation test device |
Publications (2)
| Publication Number | Publication Date |
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| CN103591857A true CN103591857A (en) | 2014-02-19 |
| CN103591857B CN103591857B (en) | 2015-06-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310603818.8A Expired - Fee Related CN103591857B (en) | 2013-11-26 | 2013-11-26 | Rocket composite simulation test device |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2620453C1 (en) * | 2016-01-26 | 2017-05-25 | Акционерное общество "Корпорация "Тактическое ракетное вооружение" | Method of carrier equipment check with connection line control and information exchange registration |
| CN110132070A (en) * | 2019-04-24 | 2019-08-16 | 中国人民解放军陆军工程大学 | A kind of prominent amount detecting device of cannon firing pin and the prominent quantity measuring method of cannon firing pin |
| CN110146750A (en) * | 2019-06-10 | 2019-08-20 | 西安现代控制技术研究所 | Play the static electrical detecting tool of arrow |
| CN111366481A (en) * | 2020-03-12 | 2020-07-03 | 南京航空航天大学 | High-speed impact test device and method for simulating airflow action |
| CN113176069A (en) * | 2021-04-20 | 2021-07-27 | 哈尔滨工程大学 | Multi-stage transmission small-disturbance high-speed ice discharge test device and method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2489294A (en) * | 1947-06-21 | 1949-11-29 | Kenyon Gyro & Electronics Corp | Flight attitude indicating instrument |
| JPH0350500A (en) * | 1989-07-17 | 1991-03-05 | Nissan Motor Co Ltd | Tester for missile |
| CH688388A5 (en) * | 1993-05-13 | 1997-08-29 | Karl Sutterlin Mechanische Wer | Device for testing and alignment of weapon cartridges |
| CN102819976A (en) * | 2012-09-10 | 2012-12-12 | 施胜南 | Water injection and air inflation integrated water rocket launching device |
| CN203349714U (en) * | 2013-06-19 | 2013-12-18 | 中国人民解放军军械工程学院 | Multiple-freedom-degree full-automatic fuze electromagnetic irradiation test stand |
-
2013
- 2013-11-26 CN CN201310603818.8A patent/CN103591857B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2489294A (en) * | 1947-06-21 | 1949-11-29 | Kenyon Gyro & Electronics Corp | Flight attitude indicating instrument |
| JPH0350500A (en) * | 1989-07-17 | 1991-03-05 | Nissan Motor Co Ltd | Tester for missile |
| CH688388A5 (en) * | 1993-05-13 | 1997-08-29 | Karl Sutterlin Mechanische Wer | Device for testing and alignment of weapon cartridges |
| CN102819976A (en) * | 2012-09-10 | 2012-12-12 | 施胜南 | Water injection and air inflation integrated water rocket launching device |
| CN203349714U (en) * | 2013-06-19 | 2013-12-18 | 中国人民解放军军械工程学院 | Multiple-freedom-degree full-automatic fuze electromagnetic irradiation test stand |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2620453C1 (en) * | 2016-01-26 | 2017-05-25 | Акционерное общество "Корпорация "Тактическое ракетное вооружение" | Method of carrier equipment check with connection line control and information exchange registration |
| CN110132070A (en) * | 2019-04-24 | 2019-08-16 | 中国人民解放军陆军工程大学 | A kind of prominent amount detecting device of cannon firing pin and the prominent quantity measuring method of cannon firing pin |
| CN110132070B (en) * | 2019-04-24 | 2024-04-12 | 中国人民解放军陆军工程大学 | Gun firing pin protrusion detection device and gun firing pin protrusion detection method |
| CN110146750A (en) * | 2019-06-10 | 2019-08-20 | 西安现代控制技术研究所 | Play the static electrical detecting tool of arrow |
| CN110146750B (en) * | 2019-06-10 | 2021-07-02 | 西安现代控制技术研究所 | Static electric detection tool for rocket |
| CN111366481A (en) * | 2020-03-12 | 2020-07-03 | 南京航空航天大学 | High-speed impact test device and method for simulating airflow action |
| CN113176069A (en) * | 2021-04-20 | 2021-07-27 | 哈尔滨工程大学 | Multi-stage transmission small-disturbance high-speed ice discharge test device and method |
| CN113176069B (en) * | 2021-04-20 | 2022-07-15 | 哈尔滨工程大学 | Multi-stage transmission small-disturbance high-speed ice discharge test device and method |
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| Publication number | Publication date |
|---|---|
| CN103591857B (en) | 2015-06-17 |
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Granted publication date: 20150617 Termination date: 20161126 |