CN111795610A - Folding wing bullet simulation launch test device - Google Patents
Folding wing bullet simulation launch test device Download PDFInfo
- Publication number
- CN111795610A CN111795610A CN202010736640.4A CN202010736640A CN111795610A CN 111795610 A CN111795610 A CN 111795610A CN 202010736640 A CN202010736640 A CN 202010736640A CN 111795610 A CN111795610 A CN 111795610A
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- folding wing
- launch
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- test
- bomb
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- 238000012360 testing method Methods 0.000 title claims abstract description 111
- 238000004088 simulation Methods 0.000 title claims abstract description 79
- 238000013016 damping Methods 0.000 claims abstract description 39
- 238000000034 method Methods 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 5
- 230000006978 adaptation Effects 0.000 claims description 2
- 230000009467 reduction Effects 0.000 claims description 2
- 230000007246 mechanism Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to a folding wing bomb simulation launch test device, which comprises a launch frame, a folding wing simulation test bomb, a simulation launch power system and high-speed photographic equipment, wherein the launch frame is provided with a launch tube, the launching tube has adjustable launching angle, a supporting rod extending to the upper part of the launching frame along the length direction of the launching tube is arranged on the launching tube, a damping device is arranged at the end part of the supporting rod at the upper part of the inclined angle corresponding to the position of the launching tube, the folding wing simulation test bomb is filled in the launching tube, the tail part of the folding wing simulation test bomb is provided with a foldable wing panel, the simulation launching power system is used for providing power for the folding wing simulation test bomb to slide out of the launching tube at high speed according to requirements, the high-speed camera equipment is arranged on one side of the launching frame, the device is used for acquiring the speed of the folding wing simulation test bomb after sliding out of the launching tube, the unfolding time of the folding wing and consistency data. The advantages are that: the safety is higher, and the test site requires lowly, and data acquisition is convenient, and the test bullet repeatedly usable, the test cost is lower.
Description
Technical Field
The invention relates to a launch test device, in particular to a folding wing bomb simulated launch test device.
Background
The discharge attitude, the unfolding synchronism of the wing surface, the unfolding time of the wing surface and the reliability of the unfolding mechanism of the folding wing projectile at various launching angles are important to the stability of the flying attitude of the projectile and the reliability of the mission of the projectile.
The reasonability of the structure of the elastic folding wing mechanism and the launching device needs to be verified by a large number of tests. At present, a kinetic energy test bomb mode is usually adopted for test verification, and the test verification mode needs a very wide test field; the process of managing, transporting and using the initiating explosive device is very strict, the danger is large, and the cost is high; the difficulty of data acquisition, recovery of kinetic energy test bullets and state analysis is high, so that the test cost is high.
Disclosure of Invention
The invention aims to solve the technical problem of providing a folding wing bomb simulated launch test device, which effectively overcomes the defects of the prior art.
The technical scheme for solving the technical problems is as follows:
a folding wing simulation launch test device comprises a launch frame, a folding wing simulation test bomb, a simulation launch power system and a high-speed photographic device, wherein the launch frame is provided with a launch tube matched with the folding wing simulation test bomb, the launch angle of the launch tube is adjustable, a support rod extending to the obliquely upper part of the launch frame along the length direction of the launch tube is further arranged on the launch frame, a damping device is arranged at the position, corresponding to the launch tube, of the end part, inclined upwards, of the support rod, the folding wing simulation test bomb is arranged in the launch tube and connected with the simulation launch power system, a foldable wing panel is arranged at the tail part of the folding wing simulation test bomb, the simulation launch power system is used for providing power for the folding wing simulation test bomb to slide out of the launch tube at high speed, and the high-speed photographic device is arranged on one side of the launch frame, the device is used for acquiring the speed of the folding wing simulation test bomb after sliding out of the launching tube, the unfolding time of the folding wing and consistency data.
On the basis of the technical scheme, the invention can be further improved as follows.
Further, the support rod is arranged above the launching tube, and the corresponding damping device is arranged below one end of the support rod which is inclined upwards.
Further, the damping device is a damping fin.
The folding wing simulation test bomb further comprises a limiting device, the limiting device is a limiting ring arranged at the lower end of the supporting rod, the limiting ring is close to the damping device, the folding wing simulation test bomb penetrates through the limiting ring in the launching process, the wing panel with the tail portion unfolded stops a certain distance away from the damping device at the limiting ring, and the head portion of the folding wing simulation test bomb decelerates and stops after colliding with the damping device.
Further, the launching power system comprises a power source, a pull rope and a pulley, wherein the pulley is mounted at the end part of the supporting rod, one end of the pull rope passes around the pulley and passes through the damping device and is fixedly connected with the head part of the folding wing simulation test bomb, the other end of the pull rope is connected with the power source, and the power source is used for acting on the pull rope to pull the folding wing simulation test bomb arranged in the launching tube out of the launching tube at a high speed.
Further, the power source is a free-fall counterweight.
Further, the power source is a shot.
The invention has the beneficial effects that: the safety is higher, and the test site requires lowly, and data acquisition is convenient, and the test bullet repeatedly usable, the test cost is lower.
Drawings
Fig. 1 is a schematic structural diagram of a folding wing projectile simulated launch test device of the invention.
In the drawings, the components represented by the respective reference numerals are listed below:
1. the device comprises a launching frame, 2 folding wing simulation test bullets, 3 launching power systems, 4 high-speed photographic equipment, 5 damping devices, 6 limiting devices, 11 launching cylinders, 12 supporting rods, 31 power sources, 32 pull ropes, 33 pulleys, 34 pulley mounting seats.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Example (b): as shown in fig. 1, the folding wing projectile simulation launch testing device of this embodiment includes a launch frame 1, a folding wing simulation test projectile 2, a launch power system 3 and a high-speed photography device 4, wherein the launch frame 1 has a launch tube 11 adapted to the folding wing simulation test projectile 2, and the launch angle of the launch tube 11 is adjustable, the launch frame 1 is further provided with a support rod 12 extending to the obliquely upper side of the launch frame 1 along the length direction of the launch tube 11, the end of the support rod 12 at the obliquely upper end is provided with a damping device 5 corresponding to the position of the launch tube 11, the folding wing simulation test projectile 2 is arranged in the launch tube 11 and connected with the launch power system 3, the tail of the folding wing simulation test projectile 2 is provided with a foldable wing 21, the launch power system 3 is used for providing power for the folding wing simulation test projectile 2 to slide out of the launch tube at high speed, the folding wing simulation test bomb 2 decelerates and stops after colliding with the damping device 5, and the high-speed camera 4 is arranged on one side of the launching frame 1 and used for acquiring the speed of the folding wing simulation test bomb 2 after sliding out of the launching tube 11, the unfolding time of the folding wing and consistency data.
The test launch procedure was as follows:
designing a launching speed according to the launching tube 11, calculating the ground clearance of the launching rack 1 according to the relevant information of the launching power system 3, and fixing the launching rack 1 on the height platform; adjusting the azimuth and the launch elevation (namely the launch angle) of the launch canister 11 on the launch frame 1, completing the assembly connection of the launch power system 3 and the folding wing simulation test bomb 2, and then folding the wing panel 21 at the tail part of the folding wing simulation test bomb 2 and sliding into the launch canister 11; starting the high-speed photographing apparatus 4; the launching power system 3 is started to act on the folding wing simulation test bomb 2, so that the folding wing simulation test bomb slides out of the launching tube 11 of the launching frame 1 at a high speed; after the folding wing simulation test bomb 2 slides out of the launcher 1, the wing 21 automatically unfolds, when the warhead of the folding wing simulation test bomb 2 is close to the damping device 5, the launching power system 3 stops providing power, the folding wing simulation test bomb 2 stops after the head part strikes the damping device 5 and decelerates under the action of the inertial force, the safety of the whole test device is higher, the requirement of a test field is low, data acquisition is convenient, the test bomb can be repeatedly used, and the test cost is lower.
The high-speed camera 4 is a product of the prior art, and only needs to use a high-frame camera with a bracket which is already on the market.
It should be noted that: above-mentioned launch canister 11 can adopt movable mounting's mode to assemble on launcher 1 so that manual regulation launch angle, also can adopt the adjustment mechanism of adaptation to assemble on launcher 1, realize automatic regulation, on the barrel one end of launch canister 11 articulates the launch pad that can rotate that sets up on launcher 1, the other end is connected with the launch pad through the telescopic machanism that can adjust the angle of elevation from top to bottom or other angle adjustment mechanism that have similar function (present to telescopic machanism have much to involve, do not do here and describe repeatedly).
In a preferred embodiment, the support rod 12 is disposed above the launch tube 11, and the damper device 5 is disposed below an end of the support rod 12 that is inclined upward.
In this embodiment, the support rods 11 are arranged reasonably, and the effective launching of the folding wing simulation test bomb 2 is facilitated.
In a preferred embodiment, the damper 5 is a damper.
In this embodiment, this damping fin is perpendicular with the axis of bracing piece 12, ensures folding wing analogue test bullet 2 at the effectual striking speed reduction of launching process, simultaneously, adopts conventional damping fin, and the installation is more convenient to, damping effect is also relatively good, and the later maintenance is simple.
As a preferable embodiment, the foldable wing simulation test bomb 2 further includes a limiting device 6, the limiting device 6 is a limiting ring disposed at the lower end of the support rod 12, the limiting ring is close to the damping device 5, the foldable wing simulation test bomb 2 penetrates through the limiting ring during launching, the wing 21 with its tail portion unfolded stops a certain distance away from the damping device 5 at the limiting ring, and the head portion of the wing collides with the damping device 5.
In this embodiment, the design of stop device 6 can make folding wing analogue test bullet 2 spacing its position after the transmission, is convenient for collect reuse again.
Preferably, the limiting ring (sheet) is perpendicular to the axis of the support rod 12, the ring shape is a circular ring, and the diameter of the circular ring is slightly larger than the diameter of the body of the folding wing simulation test bomb 2 and smaller than the diameter of the outer edge of the unfolded wing 21 of the folding wing simulation test bomb 2, so as to ensure that the folding wing simulation test bomb 2 can pass well, and the wing 21 can not pass after impacting the damping device 5, so that the folding wing simulation test bomb 2 can be well retained on the limiting device 5, in the launching process, after the folding wing simulation test bomb 2 slides out of the launching frame 1, the wing 21 is unfolded, the folding wing simulation test bomb 2 enters the limiting device 6 (limiting sheet), the free-falling body counterweight part falls to the ground when the head of the folding wing simulation test bomb 2 approaches the damping sheet, the inner ring of the limiting sheet is a circular ring, the diameter of the inner ring is slightly larger than the diameter of the body of the folding wing simulation test bomb 2, be less than the outer fringe diameter after wing 21 expandes for the wing 21 of folding wing analogue test bullet 2 afterbody can't pass, and, the distance of spacing piece and damping fin is shorter a little than folding wing analogue test bullet 2's bullet length, folding wing analogue test bullet 2 stops after launching the striking damping fin and keeps in stop device 6, and wing 21 can not contact the spacing piece of collision, can realize the nondestructive test of projectile body and folding wing, and, easily folding wing analogue test bullet 2's collection reuse.
In a preferred embodiment, the launch power system 3 includes a power source 31, a rope 32, and a pulley 33, the pulley 33 is mounted on an end of the support rod 12, one end of the rope 32 passes around the pulley 33, passes through the damping device 5, and is connected and fixed to a head of the folding wing simulation test bomb 2, the other end of the rope 32 is connected to the power source 31, and the power source 31 is used for applying the rope 32 to pull out and launch the folding wing simulation test bomb 2 placed in the launch tube 11 at a high speed.
More specifically, the power source 31 is a free-fall counterweight.
In the embodiment, the ground clearance and the stay cord length of the launcher 1 are calculated according to the design speed of the launching tube 11 and the elongation rate of the stay cord 32 during launching, and the launcher 1 is fixed on the height platform; one end of a pull rope 32 is fixed on the free falling body counterweight, and the other end of the pull rope 32 passes through a pulley 33 and the damping device 5 and then is connected with the center of the warhead of the folding wing simulation test bomb 2; folding the wing panel 21 of the folding wing simulation test bomb 2 and sliding the folded wing simulation test bomb into the launching tube 11; starting the high-speed photographing apparatus 4; releasing the free-falling body counterweight, accelerating the free-falling body of the free-falling body counterweight, and when the free-falling body counterweight reaches a set height from the ground, buffering and drawing the folding wing simulation test bomb 2 through the pull rope 32 to accelerate the folding wing simulation test bomb to slide out of the launching rack 1 (particularly the launching tube 11) at a high speed; after the folding wing simulation test bomb 2 slides out of the launcher 1, the wing 21 is unfolded, the free falling body counterweight part falls to the ground when the warhead of the folding wing simulation test bomb 2 is close to the damping device 5, the folding wing simulation test bomb 2 stops after the warhead impacts the damping device 5 to decelerate under the action of inertia force, the whole launching power system 3 makes full use of the self falling body motion to provide power, the use is more flexible, and the environment-friendly, pollution-free, less energy consumption and low cost are realized.
The following are specifically mentioned: the speed of the folding wing simulation test bomb 2 is controlled by the mass of the free-fall weight, the height from the ground, the elongation of the pull rope 32 and the length of the pull rope 32.
The pulley 33 is mounted to the lower end of the one end of the support rod 12, which is inclined upward, via a pulley mounting seat 34.
Preferably, the power source 31 is a shot, but other types of weights may be used.
Of course, when the position-limiting device 6 is disposed on the supporting rod 12, one end of the pulling rope 32 connected to the folding wing simulation test bomb 2 should sequentially pass through the damping device 5 (damping sheet) and the position-limiting device 6 (position-limiting sheet).
The power source 31 may be any other product or mechanism capable of outputting power (pulling force), as long as the action rope 32 can pull the folding wing simulation test bomb 2 to launch at a high speed.
The following are specifically mentioned: the height of the launching cradle 1 and the elevation angle of the launching tube 11 can be adjusted according to actual conditions, so that the optimal test state of launching the folding wing simulation test bomb 2 is achieved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (7)
1. The utility model provides a folding wing bullet simulation launch test device which characterized in that: including launching cradle (1), folding wing analogue test bullet (2), simulated launch driving system (3) and high-speed photography equipment (4), launching cradle (1) have with launching tube (11) of folding wing analogue test bullet (2) adaptation, and this launching tube (11) launch angle is adjustable, still be equipped with on launching cradle (1) and follow launching tube (11) length direction extends to bracing piece (12) of launching cradle (1) oblique top, bracing piece (12) one end tip that inclines upwards corresponds the position of launching tube (11) is equipped with damping device (5), folding wing analogue test bullet (2) pack in launching tube (11), and with simulated launch driving system (3) are connected, folding wing analogue test bullet (2) afterbody has folding fin (21), simulated launch driving system (3) are used for providing the dynamic roll-off launching tube of folding wing analogue test bullet (2) high-speed roll-off launching tube Force, folding wing analogue test bullet collision the speed reduction stops behind damping device (5), high-speed camera equipment (4) set up launching cradle (1) one side is used for acquireing speed and folding wing deployment opportunity and the uniformity data behind folding wing analogue test bullet (2) roll-off launching tube.
2. The folding wing bomb simulation launch test device of claim 1, characterized in that: the supporting rod (12) is arranged above the launching tube (11), and the corresponding damping device (5) is arranged below one inclined end of the supporting rod (12).
3. The folding wing bomb simulation launch test device of claim 2, characterized in that: the damping device (5) is a damping fin.
4. The folding wing bomb simulation launch test device of claim 3, characterized in that: the folding wing simulation test bomb comprises a supporting rod (12), and is characterized by further comprising a limiting device (6), wherein the limiting device (6) is arranged on a limiting ring at the lower end of the supporting rod (12), the limiting ring is close to the damping device (5), the folding wing simulation test bomb (2) penetrates through the limiting ring in the launching process, the tail of the folding wing simulation test bomb is unfolded, the wing (21) blocks the limiting ring to deviate from a certain distance of the damping device (5), and the head of the folding wing simulation test bomb decelerates and stops after the damping device (5) collides.
5. The folding projectile simulation launch test device of any one of claims 1 to 4, wherein: launch driving system (3) include power supply (31), stay cord (32) and pulley (33), pulley (33) install in the tip of bracing piece (12), stay cord (32) one end is walked around pulley (33), and pass damping device (5), and with the head of folding wing simulation test bullet (2) is connected fixedly, the other end of stay cord (32) with power supply (31) are connected, power supply (31) are used for acting on stay cord (32) will be arranged in folding wing simulation test bullet (2) in launch canister (11) are according to the high-speed launch canister that pulls out of set speed.
6. The folding wing bomb simulation launch test device of claim 5, characterized in that: the power source (31) is a free-fall counterweight.
7. The folding wing bomb simulation launch test device of claim 6, characterized in that: the power source (31) is a shot.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010736640.4A CN111795610A (en) | 2020-07-28 | 2020-07-28 | Folding wing bullet simulation launch test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010736640.4A CN111795610A (en) | 2020-07-28 | 2020-07-28 | Folding wing bullet simulation launch test device |
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| Publication Number | Publication Date |
|---|---|
| CN111795610A true CN111795610A (en) | 2020-10-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010736640.4A Withdrawn CN111795610A (en) | 2020-07-28 | 2020-07-28 | Folding wing bullet simulation launch test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111795610A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112504668A (en) * | 2020-12-25 | 2021-03-16 | 湖南高至科技有限公司 | Ground unfolding test device and method for foldable rudder |
| CN114485262A (en) * | 2022-01-29 | 2022-05-13 | 重庆零壹空间航天科技有限公司 | System for guided missile inclined launching reliability verification |
-
2020
- 2020-07-28 CN CN202010736640.4A patent/CN111795610A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112504668A (en) * | 2020-12-25 | 2021-03-16 | 湖南高至科技有限公司 | Ground unfolding test device and method for foldable rudder |
| CN112504668B (en) * | 2020-12-25 | 2023-02-28 | 湖南高至科技有限公司 | Ground unfolding test device and method for foldable rudder |
| CN114485262A (en) * | 2022-01-29 | 2022-05-13 | 重庆零壹空间航天科技有限公司 | System for guided missile inclined launching reliability verification |
| CN114485262B (en) * | 2022-01-29 | 2024-03-29 | 重庆零壹空间航天科技有限公司 | System for verifying missile oblique launching reliability |
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Application publication date: 20201020 |