CN110057253A - Aviation submunition parachute-opening minusg simulation system - Google Patents
Aviation submunition parachute-opening minusg simulation system Download PDFInfo
- Publication number
- CN110057253A CN110057253A CN201910294704.7A CN201910294704A CN110057253A CN 110057253 A CN110057253 A CN 110057253A CN 201910294704 A CN201910294704 A CN 201910294704A CN 110057253 A CN110057253 A CN 110057253A
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- Prior art keywords
- parachute
- opening
- minusg
- submunition
- test products
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses aviation submunition parachute-opening minusg simulation systems, including firing mount, pickup automobile, power-up component, relieving mechanism, control switch and limitation cylinder, restricted cylinder is arranged in firing mount upper surface one end, and the firing mount upper surface other end is provided with relieving mechanism.The beneficial effects of the present invention are: when test, vehicle should move in a straight line, first at the uniform velocity accelerate when starting, drag parachute in deceleration component is filled under Aerodynamic force action, and high speed rotation, bullet is set to obtain simulating trajectory " flying speed ", test products are powered on by power-up component after reaching desin speed, it powered off after meeting the requirements, start submunition workflow, relieving mechanism release test product, so that test products is slowed down rapidly under the action of drag parachute, generates trajectory and shed parachute-opening minusg, test products complete task under the effect of parachute-opening minusg.The system structure is simple, simulated environment power high reliablity.
Description
Technical field
The present invention relates to a kind of simulation systems, specially aviation submunition parachute-opening minusg simulation system, belong to aviation
Mother plays applied technical field.
Background technique
At present when studying aviation cluster bomb product, such product trajectory parachute-opening environmental forces can not be verified on ground.Usually
It is that test products are shed using Airborne Dispenser or are tested using rocket bomb transmitting to aerial release parachute-opening, tests process
Complexity, technical difficulty is big, and time is long, with high costs.
Summary of the invention
The object of the invention is that in order to solve such product trajectory parachute-opening at present when studying aviation cluster bomb product
Environmental forces can not be verified on ground, usually shed test products or using rocket bomb transmitting in the air using Airborne Dispenser
Release parachute-opening is tested, and test process is complicated, and technical difficulty is big, and time is long, problem with high costs, and proposes aviation
Submunition parachute-opening minusg simulation system.
The purpose of the present invention can be achieved through the following technical solutions: aviation submunition parachute-opening minusg simulation system, packet
It includes firing mount, pickup automobile, power-up component, relieving mechanism, control switch and limitation cylinder, the firing mount and is vertically provided at the pick up
In the wagon box of automobile one end, and the firing mount is cuboid structure, and restricted cylinder, and institute is arranged in firing mount upper surface one end
It states the firing mount upper surface other end and is provided with relieving mechanism, be provided with connecting rod and rope between the limitation cylinder and the relieving mechanism
Rope limits test products by limiting cylinder, makes it will not random play in vehicle operation；
Wherein, described limitation cylinder one end is provided with deceleration component.
Further technological improvement of the invention is: the limitation cylinder is cylindrical structure, and test products are set in limit
Inside cylinder processed, limitation cylinder one end is provided with the opening for facilitating test products pass-out, facilitates test products when being tested from limitation
Launch in cylinder outer.
Further technological improvement of the invention is: the connecting rod setting connects in the middle part of limitation cylinder one end side wall
Bar is connect by one end of rope with relieving mechanism.
Further technological improvement of the invention is: drag parachute, and pickup automobile and bullet are provided in the deceleration component
Frame and deceleration component are movably connected, and when test, vehicle is moved in a straight line, and when starting first at the uniform velocity accelerates, in deceleration component
Drag parachute is filled under Aerodynamic force action, and high speed rotation, and remain a constant speed linear motion after arrival setting value, and bullet is made to obtain mould
Quasi- trajectory " flying speed " is powered on test products by power-up component after reaching desin speed, powers off, starts after meeting the requirements
Submunition workflow, relieving mechanism release test product, makes test products slow down rapidly under the action of drag parachute, generates bullet
Parachute-opening minusg is shed in road, and test products complete task under the effect of parachute-opening minusg.
Further technological improvement of the invention is: passing through several bolts and pickup automobile at the firing mount bottom margin
Wagon box bottom be fixedly connected, guarantee firing mount more consolidate when in use it is firm, and be more convenient for installation, disassembly.
Further technological improvement of the invention is: the roof upper surface of the pickup automobile be provided with relieving mechanism and
The control switch that limitation cylinder matches, and control switch passes through conducting wire and is electrically connected with relieving mechanism and limitation cylinder, passes through control
Switch control relieving mechanism and limitation cylinder start or stop work.
The operating method of the simulation system specifically includes the following steps:
Step 1: test products being mounted on limitation cylinder, then install deceleration component, will be tested with connecting rod and rope
Product is fixed on relieving mechanism, is limited by limiting cylinder test products, is made test products in vehicle operation
It will not play；
Step 2: when test, pickup automobile is moved in a straight line, and is first at the uniform velocity accelerated when starting, the drag parachute in deceleration component
It is filled under Aerodynamic force action, and high speed rotation, remain a constant speed linear motion after arrival setting value, and bullet is made to obtain simulating trajectory
" flying speed "；
Step 3: test products are powered on by power-up component after reaching desin speed, power-off, promoter after meeting the requirements
Ammunition workflow, relieving mechanism release test product, makes test products slow down rapidly under the action of drag parachute, generates trajectory
Parachute-opening minusg is shed, test products complete task under the effect of parachute-opening minusg.
Compared with prior art, the beneficial effects of the present invention are:
1, in the use of the present invention, test products are mounted on limitation cylinder, then install deceleration component, with connecting rod and
Test products are fixed on relieving mechanism by rope, are limited by limiting cylinder test products, are run it in vehicle
It will not random play in journey.When test, vehicle should be moved in a straight line, and first at the uniform velocity be accelerated when starting, the drag parachute in deceleration component
It is filled under Aerodynamic force action, and high speed rotation, remain a constant speed linear motion after arrival setting value, and bullet is made to obtain simulating trajectory
" flying speed " is powered on test products by power-up component after reaching desin speed, powers off after meeting the requirements, starts submunition
Workflow, relieving mechanism release test product, makes test products slow down rapidly under the action of drag parachute, generates trajectory and sheds
Parachute-opening minusg, test products complete task under the effect of parachute-opening minusg.The system structure is simple, and simulated environment power can
By property height.
2, the system components are easily assembled, easy to use, and the device simple in the system, low in cost.
Detailed description of the invention
In order to facilitate the understanding of those skilled in the art, the present invention will be further described below with reference to the drawings.
Fig. 1 is overall structure of the present invention.
Fig. 2 is relieving mechanism of the present invention and the stereochemical structure connection schematic diagram for limiting cylinder.
Fig. 3 is relieving mechanism of the present invention and the connection front view for limiting cylinder.
In figure: 1, deceleration component；2, firing mount；3, pickup automobile；4, it is powered on component；5, connecting rod；51, rope；6, it discharges
Mechanism；7, control switch；8, cylinder is limited；9, test products.
Specific embodiment
Technical solution of the present invention is clearly and completely described below in conjunction with embodiment, it is clear that described reality
Applying example is only a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, this field is general
Logical technical staff all other embodiment obtained without creative efforts belongs to what the present invention protected
Range.
It please refers to shown in Fig. 1-3, aviation submunition parachute-opening minusg simulation system, including firing mount 2, pickup automobile 3, power-up
Component 4, relieving mechanism 6, control switch 7 and limitation cylinder 8, firing mount 2 is vertically provided in the wagon box of 3 one end of pickup automobile, and bullet
Frame 2 is cuboid structure, and restricted cylinder 8 is arranged in 2 upper surface one end of firing mount, and the 2 upper surface other end of firing mount is provided with release
Mechanism 6 limits and is provided with connecting rod 5 and rope 51 between cylinder 8 and relieving mechanism 6, is limited by limiting 8 pairs of test products of cylinder
System, makes it will not random play in vehicle operation；
Wherein, limitation 8 one end of cylinder is provided with deceleration component 1.
As preferred embodiments of the present invention, limitation cylinder 8 is cylindrical structure, and test products 9 are set in limitation cylinder 8
Portion, limitation 8 one end of cylinder are provided with the opening for facilitating 9 pass-out of test products, facilitate test products when being tested from limitation cylinder 8
Launch outer.
As preferred embodiments of the present invention, the setting of connecting rod 5 is in the middle part of limitation 8 one end side wall of cylinder, and connecting rod 5 passes through
One end of rope 51 is connect with relieving mechanism 6.
As preferred embodiments of the present invention, it is provided with drag parachute in deceleration component 1, and pickup automobile 3 and firing mount 2 and subtracts
Fast component 1 is movably connected, and when test, vehicle is moved in a straight line, and when starting first at the uniform velocity accelerates, the deceleration in deceleration component 1
Umbrella is filled under Aerodynamic force action, and high speed rotation, and remain a constant speed linear motion after arrival setting value, and bullet is made to obtain imitating shell
Road " flying speed " is powered on test products 9 by power-up component 4 after reaching desin speed, power-off, promoter after meeting the requirements
Ammunition workflow, 6 release test product 9 of relieving mechanism, makes test products 9 slow down rapidly under the action of drag parachute, generates
Trajectory sheds parachute-opening minusg, and test products complete task under the effect of parachute-opening minusg.
As preferred embodiments of the present invention, pass through the wagon box of several bolts and pickup automobile 3 at 2 bottom margin of firing mount
Bottom is fixedly connected, and it is firm to guarantee that firing mount 2 more consolidates when in use, and installation of being more convenient for, disassembly.
As preferred embodiments of the present invention, the roof upper surface of pickup automobile 3 is provided with and relieving mechanism 6 and limitation cylinder
8 control switches 7 to match, and control switch 7 is electrically connected by conducting wire with relieving mechanism 6 and limitation cylinder 8, is opened by control
It closes 7 control relieving mechanisms 6 and limitation cylinder 8 starts or stops work.
The operating method of the simulation system specifically includes the following steps:
Step 1: test products 9 are mounted on limitation cylinder 8, then install deceleration component 1, with connecting rod 5 and rope 51
Test products 9 are fixed on relieving mechanism 6, is limited by limiting 8 pairs of test products 9 of cylinder, makes test products 9 in vehicle
It will not play in operational process；
Step 2: when test, pickup automobile 3 is moved in a straight line, and is first at the uniform velocity accelerated when starting, the deceleration in deceleration component 1
Umbrella is filled under Aerodynamic force action, and high speed rotation, and remain a constant speed linear motion after arrival setting value, and bullet is made to obtain imitating shell
Road " flying speed "；
Step 3: test products 9 are powered on by power-up component 4 after reaching desin speed, powers off, start after meeting the requirements
Submunition workflow, 6 release test product 9 of relieving mechanism, makes test products 9 slow down rapidly under the action of drag parachute, produces
Raw trajectory sheds parachute-opening minusg, and test products 9 complete task under the effect of parachute-opening minusg.
Working principle: in the use of the present invention, firstly, the safety of each component of the present invention is checked, then by test products 9
It is mounted on limitation cylinder 8, then installs deceleration component 1, test products 9 are fixed on relieving mechanism 6 with connecting rod 5 and rope 51
On, limited by limiting 8 pairs of test products 9 of cylinder, make test products 9 in vehicle operation will not play, when test,
Pickup automobile 3 moves in a straight line, and first at the uniform velocity accelerates when starting, and the drag parachute in deceleration component 1 is filled under Aerodynamic force action, and
High speed rotation remains a constant speed linear motion after reaching setting value, and bullet is made to obtain simulating trajectory " flying speed ", and it is fast to reach design
Test products 9 are powered on by power-up component 4 after degree, powered off after meeting the requirements, start submunition workflow, relieving mechanism 6
Release test product 9 makes test products 9 slow down rapidly under the action of drag parachute, generates trajectory and sheds parachute-opening minusg, tests
Product 9 completes task under the effect of parachute-opening minusg.
Present invention disclosed above preferred embodiment is only intended to help to illustrate the present invention.There is no detailed for preferred embodiment
All details are described, are not limited the invention to the specific embodiments described.Obviously, according to the content of this specification,
It can make many modifications and variations.These embodiments are chosen and specifically described to this specification, is in order to better explain the present invention
Principle and practical application, so that skilled artisan be enable to better understand and utilize the present invention.The present invention is only
It is limited by claims and its full scope and equivalent.
Claims (7)
1. aviation submunition parachute-opening minusg simulation system, it is characterised in that: including firing mount (2), pickup automobile (3), power-up portion
Part (4), relieving mechanism (6), control switch (7) and limitation cylinder (8), the firing mount (2) are vertically provided at the pickup automobile (3)
In the wagon box of one end, and the firing mount (2 be cuboid structure, and restricted cylinder (8) is arranged in described firing mount (2) upper surface one end,
And firing mount (2) upper surface other end is provided with relieving mechanism (6), between the limitation cylinder (8) and the relieving mechanism (6)
It is provided with connecting rod (5) and rope (51)；
Wherein, described limitation cylinder (8) one end is provided with deceleration component (1).
2. aviation submunition parachute-opening minusg simulation system according to claim 1, which is characterized in that the limitation cylinder
It (8) is cylindrical structure, and test products (9) are set in limitation cylinder (8) inside, limitation cylinder (8) one end, which is provided with, facilitates test
The opening of product (9) pass-out.
3. aviation submunition parachute-opening minusg simulation system according to claim 1, which is characterized in that the connecting rod
(5) it is arranged in the middle part of limitation cylinder (8) one end side wall, and connecting rod (5) is connected by the one end of rope (51) and relieving mechanism (6)
It connects.
4. aviation submunition parachute-opening minusg simulation system according to claim 1, which is characterized in that the deceleration component
(1) drag parachute is provided on, and pickup automobile (3) is movably connected with firing mount (2) and deceleration component (1).
5. aviation submunition parachute-opening minusg simulation system according to claim 1, which is characterized in that the firing mount (2)
It is fixedly connected by several bolts with the wagon box bottom of pickup automobile (3) at bottom margin.
6. aviation submunition parachute-opening minusg simulation system according to claim 1, which is characterized in that the pickup automobile
(3) roof upper surface is provided with the control switch (7) to match with relieving mechanism (6) and limitation cylinder (8), and control switch
(7) it is electrically connected by conducting wire with relieving mechanism (6) and limitation cylinder (8).
7. aviation submunition parachute-opening minusg simulation system according to claim 1, which is characterized in that the simulation system
Operating method specifically includes the following steps:
Step 1: test products (9) being mounted in limitation cylinder (8), then install deceleration component (1), with connecting rod (5) and rope
Test products (9) are fixed on relieving mechanism (6) by rope (51), are limited by limiting cylinder (8) test products (9), are made
Test products (9) will not play in vehicle operation；
Step 2: when test, pickup automobile (3) is moved in a straight line, and is first at the uniform velocity accelerated when starting, the deceleration in deceleration component (1)
Umbrella is filled under Aerodynamic force action, and high speed rotation, and remain a constant speed linear motion after arrival setting value, and bullet is made to obtain imitating shell
Road " flying speed "；
Step 3: test products (9) are powered on by power-up component (4) after reaching desin speed, powers off, start after meeting the requirements
Submunition workflow, relieving mechanism (6) release test product (9), subtracts test products (9) rapidly under the action of drag parachute
Speed generates trajectory and sheds parachute-opening minusg, and test products (9) complete task under the effect of parachute-opening minusg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910294704.7A CN110057253B (en) | 2019-04-12 | 2019-04-12 | Aviation ammunition parachute opening load and overload simulation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910294704.7A CN110057253B (en) | 2019-04-12 | 2019-04-12 | Aviation ammunition parachute opening load and overload simulation system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110057253A true CN110057253A (en) | 2019-07-26 |
| CN110057253B CN110057253B (en) | 2021-10-01 |
Family
ID=67317769
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910294704.7A Active CN110057253B (en) | 2019-04-12 | 2019-04-12 | Aviation ammunition parachute opening load and overload simulation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110057253B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111272028A (en) * | 2020-01-23 | 2020-06-12 | 西安现代控制技术研究所 | Ground test system for connecting rope aerial maximum straightening force for shrapnel |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5188315A (en) * | 1991-07-27 | 1993-02-23 | Rheinmetall Gmbh | Submunition unit including a rotary parachute |
| CN104597280A (en) * | 2015-01-27 | 2015-05-06 | 北京空间机电研究所 | Negative pressure ejection cover pull umbrella testing device and method |
| CN104677662A (en) * | 2015-02-10 | 2015-06-03 | 中国工程物理研究院总体工程研究所 | Non-stabilized projectile airdrop parachute-opening simulation test device and test method |
-
2019
- 2019-04-12 CN CN201910294704.7A patent/CN110057253B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5188315A (en) * | 1991-07-27 | 1993-02-23 | Rheinmetall Gmbh | Submunition unit including a rotary parachute |
| CN104597280A (en) * | 2015-01-27 | 2015-05-06 | 北京空间机电研究所 | Negative pressure ejection cover pull umbrella testing device and method |
| CN104677662A (en) * | 2015-02-10 | 2015-06-03 | 中国工程物理研究院总体工程研究所 | Non-stabilized projectile airdrop parachute-opening simulation test device and test method |
Non-Patent Citations (1)
| Title |
|---|
| 余元元 等: "基于火箭撬试验的阻力伞试验平台研究", 《中国空气动力学会测控技术专委会第六届四次学术交流会论文集》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111272028A (en) * | 2020-01-23 | 2020-06-12 | 西安现代控制技术研究所 | Ground test system for connecting rope aerial maximum straightening force for shrapnel |
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| Publication number | Publication date |
|---|---|
| CN110057253B (en) | 2021-10-01 |
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