CN103926048B - Side direction perturbation is to Flight Projectile effect simulates testing table - Google Patents
Side direction perturbation is to Flight Projectile effect simulates testing table Download PDFInfo
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- CN103926048B CN103926048B CN201410180616.1A CN201410180616A CN103926048B CN 103926048 B CN103926048 B CN 103926048B CN 201410180616 A CN201410180616 A CN 201410180616A CN 103926048 B CN103926048 B CN 103926048B
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The present invention is specially a kind of side direction perturbation to Flight Projectile effect simulates testing table, solves the problem that existing bullet flight test does not have reasonable equipment.Test base is fixed with telescopic strut, telescopic strut is fixed with upper connecting rod and lower connecting rod, lower connecting rod is provided with high pressure spray valve, upper connecting rod is fixed with high-speed electric expreess locomotive, output shaft below high-speed electric expreess locomotive is connected with bullet rotation axis, the lower surface of bullet rotation axis has bullet hole, bullet jacking block and bullet spring is placed with in bullet hole, bullet rotation axis has ring groove and is installed with inserted link, the flexible tensioned lines of ring groove inner sleeve, inserted link afterbody is provided with balancing weight, telescopic strut is provided with the strong magnets with its axis rotation, telescopic strut is fixed with the weak magnet and high-speed camera that move left and right.The present invention can simulate bullet low speed, stabilized flight by magnetic force simulation side force on the impact of projectile flight attitude, obtain bullet and stablize and unstable structured data aloft.
Description
Technical field
The present invention relates to projectile flight attitude field, particularly relate to a kind of simulator stand, be specially a kind of side direction perturbation to Flight Projectile effect simulates testing table.
Background technology
In national defence and field of industrial production, projectile aerodynamics experiment point full-scale investigation and the large class of model experiment two.Full-scale investigation is as the experiment of guided missile live ammunition and aircraft flight experiment etc., can not the analog distortion such as generation model and environment problem, qualification bullet, flight vehicle aerodynamic performance and the final means of calibrating other experimental results always, the somewhat expensive of this kind of experiment, condition is also difficult to be controlled, and can not carry out in the starting stage of product development, therefore air stage combustion generally refers to model experiment more.
Although model experiment has limitation, there are following four advantages: 1, can Control release condition more exactly, as the speed, pressure, temperature etc. of air-flow; 2, test and carry out in indoor, the impact of climate condition and time is little, and the installation of model and testing tool, operation, use are more convenient; 3, experimental project and content varied, the degree of accuracy of experimental result is higher; 4, experiment is safer, and efficiency is high, cost is low.Therefore, this type of experiment in the development of aerodynamic research, various aircraft, and in industrial aerodynamics with other with in air-flow or the relevant field of wind, be all widely used.
The aerodynamics test of China is goed deep into already, especially to the wind tunnel test that the large-scale guided missiles such as airborne missile carry out in military field engineering.But this type of experiment also seldom relates in the flight of research bullet.Testing table of this design in-flight with different flying speed and go out thorax rotating speed, studies the impact of disturbance on bullet by simulation bullet, well compensate for that this is blank.
Summary of the invention
The present invention does not have the problem of reasonable equipment in order to solve existing bullet flight test, provide a kind of side direction perturbation to Flight Projectile effect simulates testing table.
The present invention adopts following technical scheme to realize: side direction perturbation is to Flight Projectile effect simulates testing table, comprise test base and the high-pressure gas cylinder being positioned at its right, test base is fixed with the telescopic strut vertically arranged, telescopic strut is fixed with upper connecting rod and lower connecting rod, lower connecting rod is provided with the high pressure spray valve be communicated with high-pressure gas cylinder, upper connecting rod is fixed with high-speed electric expreess locomotive, output shaft below high-speed electric expreess locomotive is connected with bullet rotation axis, the lower surface of bullet rotation axis has the stepped bullet hole that upper inner diameter is less than lower inner diameter, the bottom in bullet hole is placed with the bullet jacking block that outer cylinder is dentalation, the top in bullet hole is placed with the bullet spring that two ends are connected with bullet jacking block and bullet rotation axis respectively, the jack external cylindrical surface of bullet rotation axis having ring groove and be communicated with bullet hole, the inserted link inserted in bullet jacking block teeth groove is installed with in jack, ring groove inner sleeve has the elastic tension rope be connected with inserted link afterbody, inserted link afterbody is provided with balancing weight, telescopic strut is provided with the bullet fixed bar horizontally rotated along the wherein heart, bullet fixed bar is fixed with the strong magnets being positioned at bullet rotation axis lower periphery, telescopic strut is fixed with height between bullet rotation axis and high pressure spray valve and horizontally disposed telescopic advance lever, be provided with around bullet rotation axis the weak magnet that is fixed on telescopic advance lever outer end and with the high-speed camera of weak magnet in same level.
This testing table by high pressure spray valve ejection gas flow rate size adjustable high-velocity fluid, the continuous change of simulation bullet speed in-flight; Bullet is arranged in the bullet hole on the downside of bullet jacking block, and high-speed electric expreess locomotive drives bullet rotation axis High Rotation Speed, and when spin raie reaches certain value, bullet is injected into swiftly flowing air field from bullet rotation axis inside and does high speed gyration; Bullet does retarded motion in swiftly flowing air field, finally, air resistance suffered by bullet and gravitational equilibrium, bullet reaches steady state (SS) in swiftly flowing air field, only do gyration, now, by weak magnet, side force interference is carried out to bullet, high-speed camera record bullet, at different side force lower angle tilt value, overcomes the problem that existing bullet flight test does not have reasonable equipment.
Under test base, vertex angle part is screwed with the ball cap screw rod be threaded with it, and the lower end cover of ball cap screw rod has Rubber shock-absorbing pad, ball cap screw rod is fixed with adjusting knob, for the stability of warranty test platform.
Be disposed with high-pressure pump operation valve, high-pressure gas cylinder tensimeter, flow control valve, high pressure spray valve tensimeter between high-pressure gas cylinder and high pressure spray valve, the flow velocity size of high-velocity fluid is regulated.
Reasonable in design of the present invention is reliable, simulate bullet low speed aloft fast and accurately, stabilized flight also simulates side force to the impact of projectile flight attitude by magnetic force, and bullet can be simulated aloft with friction speed, when going out the flight of thorax rotating speed, side force size is on the impact of projectile flight attitude, simultaneously in conjunction with free flight (shooting lane) test and the advantage of wind tunnel test, the temperature of gas can be controlled preferably, speed and pressure and other parameters, obtain bullet to stablize and unstable structured data, there is structure simple, the better simply advantage of easy to process and data processing.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is the structural representation at bullet rotation axis place in Fig. 1.
In figure: 1-test base, 2-high-pressure gas cylinder, 3-telescopic strut, 4-upper connecting rod, 5-lower connecting rod, 6-high pressure spray valve, 7-high-speed electric expreess locomotive, 8-bullet rotation axis, 9-bullet hole, 10-bullet jacking block, 11-bullet spring, 12-ring groove, 13-jack, 14-inserted link, 15-elastic tension rope, 16-balancing weight, 17-bullet fixed bar, 18-strong magnets, 19-telescopic advance lever, the weak magnet of 20-, 21-high-speed camera, 22-ball cap screw rod, 23-Rubber shock-absorbing pad, 24-adjusting knob, 25-high-pressure pump operation valve, 26-high-pressure gas cylinder tensimeter, 27-flow control valve, 28-high pressure spray valve tensimeter.
Embodiment
Side direction perturbation is to Flight Projectile effect simulates testing table, comprise test base 1 and the high-pressure gas cylinder 2 being positioned at its right, test base 1 is fixed with the telescopic strut 3 vertically arranged, telescopic strut 3 is fixed with upper connecting rod 4 and lower connecting rod 5, lower connecting rod 5 is provided with the high pressure spray valve 6 be communicated with high-pressure gas cylinder 2, upper connecting rod 4 is fixed with high-speed electric expreess locomotive 7, output shaft below high-speed electric expreess locomotive 7 is connected with bullet rotation axis 8, the lower surface of bullet rotation axis 8 has the stepped bullet hole 9 that upper inner diameter is less than lower inner diameter, the bottom in bullet hole 9 is placed with the bullet jacking block 10 that outer cylinder is dentalation, the top in bullet hole 9 is placed with the bullet spring 11 that two ends are connected with bullet jacking block 10 and bullet rotation axis 8 respectively, the jack 13 external cylindrical surface of bullet rotation axis 8 having ring groove 12 and be communicated with bullet hole 9, the inserted link 14 inserted in bullet jacking block 10 teeth groove is installed with in jack 13, ring groove 12 inner sleeve has the elastic tension rope 15 be connected with inserted link 14 afterbody, inserted link 14 afterbody is provided with balancing weight 16, telescopic strut 3 is provided with the bullet fixed bar 17 horizontally rotated along the wherein heart, bullet fixed bar 17 is fixed with the strong magnets 18 being positioned at bullet rotation axis 8 lower periphery, telescopic strut 3 is fixed with height between bullet rotation axis 8 and high pressure spray valve 6 and horizontally disposed telescopic advance lever 19, be provided with around bullet rotation axis 8 the weak magnet 20 that is fixed on telescopic advance lever 19 outer end and with the high-speed camera 21 of weak magnet 20 in same level.
Test base 1 time vertex angle part is screwed with the ball cap screw rod 22 be threaded with it, and the lower end cover of ball cap screw rod 22 has Rubber shock-absorbing pad 23, ball cap screw rod 22 is fixed with adjusting knob 24; High-pressure pump operation valve 25, high-pressure gas cylinder tensimeter 26, flow control valve 27, high pressure spray valve tensimeter 28 is disposed with between high-pressure gas cylinder 2 and high pressure spray valve 6.
In specific implementation process, before using, rotate adjusting knob 24 and change Rubber shock-absorbing pad 23 and the distance of test base 1, make test-bed reach steady state (SS); Open high-pressure pump operation valve 25 and close flow control valve 27, for when high-pressure gas cylinder 2 gas storage is greater than 103 MPa to high-pressure gas cylinder tensimeter 26, stopping gas storage.
During installation, bullet is pushed in bullet hole 9, bullet drives bullet jacking block 10 to compress bullet spring 11, simultaneously under the effect of elastic tension rope 15, inserted link 14 inserts in the teeth groove of bullet jacking block 10, rotating bullet fixed bar 17 subsequently makes strong magnets 18 near bullet, the high-intensity magnetic field magnetic projectile rotation axis 8 that strong magnets 18 produces and bullet, magnetic field force between bullet rotation axis 8 and bullet provides the friction force of bullet, makes bullet keep synchronous rotational speed with bullet rotation axis 8 under without the condition of other external force.
When the rotating speed of high-speed electric expreess locomotive 7 reaches certain rotating speed, (this rotating speed is enough to for bullet provides friction force to overcome gravity, bullet is not fallen down, but be not enough to make inserted link 14 and balancing weight 16 produce deformation because centrifugal force overcomes elastic tension rope 15 elastic force), bullet fixed bar 17 is left bullet rotation axis 8, continue to tune up rotating speed, when high-speed electric expreess locomotive 7 rotating speed reaches a certain value, the centrifugal force that inserted link 14 and balancing weight 16 produce overcomes elastic tension rope 15 elastic force and produces deformation, bullet spring 11 extends promotion bullet jacking block 10 and clashes into bullet, bullet is pushed in high-speed gas flow field the most at last.
Adjust flux variable valve 27 opening and closing extent control high pressure spray valve 6 gas pressure value size can be passed through in described high-speed gas flow field, thus indirectly controls the gas flow rate in gas flowfield.In experimental bench system, high pressure spray valve 6 place gaseous tension can read from high pressure spray valve tensimeter 28, and gas flow rate calculates by Bernoulli equation.
In formula:
for valve tensimeter reads force value;
for gas density;
for gravity constant;
for air nozzle distance tensimeter relative height;
for gas flow rate;
for constant.
Bullet is because affecting by air resistance and gravity etc., finally in high-speed gas flow field, do stable gyration, distance now by regulating the length of telescopic advance lever 19 to control weak magnet 20 and bullet, and then control weak magnet 20 pairs of bullet side force sizes, and taken by high-speed camera 21, for the data processing in later stage is given information.
Claims (2)
1. a side direction perturbation is to Flight Projectile effect simulates testing table, it is characterized in that: comprise test base (1) and be positioned at the high-pressure gas cylinder (2) of its right, test base (1) is fixed with the telescopic strut (3) vertically arranged, telescopic strut (3) is fixed with upper connecting rod (4) and lower connecting rod (5), lower connecting rod (5) is provided with the high pressure spray valve (6) be communicated with high-pressure gas cylinder (2), upper connecting rod (4) is fixed with high-speed electric expreess locomotive (7), the output shaft of high-speed electric expreess locomotive (7) below is connected with bullet rotation axis (8), the lower surface of bullet rotation axis (8) has the stepped bullet hole (9) that upper inner diameter is less than lower inner diameter, the bottom in bullet hole (9) is placed with the bullet jacking block (10) that outer cylinder is dentalation, the top in bullet hole (9) is placed with the bullet spring (11) that two ends are connected with bullet jacking block (10) and bullet rotation axis (8) respectively, the jack (13) external cylindrical surface of bullet rotation axis (8) having ring groove (12) and be communicated with bullet hole (9), the inserted link (14) inserted in bullet jacking block (10) teeth groove is installed with in jack (13), ring groove (12) inner sleeve has the elastic tension rope (15) be connected with inserted link (14) afterbody, inserted link (14) afterbody is provided with balancing weight (16), telescopic strut (3) is provided with the bullet fixed bar (17) horizontally rotated along the wherein heart, bullet fixed bar (17) is fixed with the strong magnets (18) being positioned at bullet rotation axis (8) lower periphery, telescopic strut (3) is fixed with and is highly positioned between bullet rotation axis (8) and high pressure spray valve (6) and horizontally disposed telescopic advance lever (19), bullet rotation axis (8) be around provided with the weak magnet (20) that is fixed on telescopic advance lever (19) outer end and with the high-speed camera (21) of weak magnet (20) in same level.
2. side direction perturbation according to claim 1 is to Flight Projectile effect simulates testing table, it is characterized in that: under test base (1), vertex angle part is screwed with the ball cap screw rod (22) be threaded with it, the lower end cover of ball cap screw rod (22) has Rubber shock-absorbing pad (23), ball cap screw rod (22) is fixed with adjusting knob (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410180616.1A CN103926048B (en) | 2014-04-30 | 2014-04-30 | Side direction perturbation is to Flight Projectile effect simulates testing table |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410180616.1A CN103926048B (en) | 2014-04-30 | 2014-04-30 | Side direction perturbation is to Flight Projectile effect simulates testing table |
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| Publication Number | Publication Date |
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| CN103926048A CN103926048A (en) | 2014-07-16 |
| CN103926048B true CN103926048B (en) | 2016-02-24 |
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| CN201410180616.1A Expired - Fee Related CN103926048B (en) | 2014-04-30 | 2014-04-30 | Side direction perturbation is to Flight Projectile effect simulates testing table |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106197937B (en) * | 2016-06-24 | 2018-09-14 | 中国航天空气动力技术研究院 | high speed ejection model quick release device |
| CN109781515B (en) * | 2019-04-02 | 2024-04-26 | 山西省检验检测中心(山西省标准计量技术研究院) | Shot firing device for high-speed impact test |
| CN113720574B (en) * | 2021-09-02 | 2023-03-10 | 中国空气动力研究与发展中心超高速空气动力研究所 | Protection device of wind tunnel test attitude measurement system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3886793A (en) * | 1974-01-09 | 1975-06-03 | Us Navy | Projectile body testing machine |
| CH687479A5 (en) * | 1993-12-07 | 1996-12-13 | Ulrich Eggenberger | Device for checking centring of round in cartridge case |
| CN203163959U (en) * | 2013-03-26 | 2013-08-28 | 华南理工大学 | Simulation device for wind resistance of speed regulation air laminar flow test model |
| CN103353261A (en) * | 2013-07-30 | 2013-10-16 | 重庆长江电工工业集团有限公司 | Device for detecting powder amount of campaign bomb |
-
2014
- 2014-04-30 CN CN201410180616.1A patent/CN103926048B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3886793A (en) * | 1974-01-09 | 1975-06-03 | Us Navy | Projectile body testing machine |
| CH687479A5 (en) * | 1993-12-07 | 1996-12-13 | Ulrich Eggenberger | Device for checking centring of round in cartridge case |
| CN203163959U (en) * | 2013-03-26 | 2013-08-28 | 华南理工大学 | Simulation device for wind resistance of speed regulation air laminar flow test model |
| CN103353261A (en) * | 2013-07-30 | 2013-10-16 | 重庆长江电工工业集团有限公司 | Device for detecting powder amount of campaign bomb |
Non-Patent Citations (1)
| Title |
|---|
| 基于线圈式地磁传感器的高速旋转弹转速测试;张慧 等;《战术导弹技术》;20090731(第4期);第64-67页 * |
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| CN103926048A (en) | 2014-07-16 |
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