CN205352204U - A intercepting device for aircraft interception - Google Patents
A intercepting device for aircraft interception Download PDFInfo
- Publication number
- CN205352204U CN205352204U CN201620139734.2U CN201620139734U CN205352204U CN 205352204 U CN205352204 U CN 205352204U CN 201620139734 U CN201620139734 U CN 201620139734U CN 205352204 U CN205352204 U CN 205352204U
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- CN
- China
- Prior art keywords
- silk thread
- body shell
- thread portion
- parachute
- backing plate
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Abstract
The utility model discloses an intercepting device for aircraft interception, including the body and be used for the launching tube of body transmission, the body includes the body shell, body shell and launching tube are one end open -ended beta -barrel structure, open end to cecum by the body shell in the body shell has set gradually the parachute, has weighed down the body, silk thread portion and transmit section, it connects on the free end of parachute umbrella rope through first acting as go -between to weigh down the body, silk thread portion includes the multi -filament line, silk thread portion acts as go -between through the second and connects on weighing down the body, transmit section is used for providing power for parachute, the weight body and silk thread portion break away from the body shell. This intercepting device compares in modes such as current guided missile, antiaircraft guns, and destruction that production and transmission be with low costs, caused the environment is little, mobility good.
Description
Technical field
This utility model relates to flying object Interception Technology field, particularly relates to a kind of blocking apparatus intercepted for aircraft.
Background technology
From the development of history, human social development process occurs in that countless chaos caused by war, particularly in modern age, in the World War I, World War II, the Pacific War, aircraft has played very important effect in war, in the big bombing in Chongqing, Pearl Harbor Incident, the War to Resist US Aggression and Aid Korea, aircraft all causes shocking destructive power.Miniature self-service machine technology develops rapidly in recent years, and fixed-wing unmanned plane, many rotor wing unmanned aerial vehicles, composite wing unmanned plane all can have for individual easily, the field such as above unmanned plane can be used for environmental monitoring, take photo by plane, and brings many facilities for mankind's productive life.Also just because of the mobility of existing unmanned plane and motility, also allow for lawless person and utilize it to peep business secret, carry out illegal shooting etc..
In prior art, land-air aircraft interception mode can pass through the mode such as guided missile, antiaircraft gun, and the Cost Of Arms used with interception mode of boarding a plane is high, destructive power is huge；The U.S. also have developed the aircraft blocking apparatus of a kind of " space mine " by name, and owing to this device adopts balloon to coordinate steel cable or balloon to coordinate the form of ballast, this blocking apparatus there is also the defect that mobility is not strong.Develop a kind of use flexibly, cost is low, deterrent force is big aircraft blocking apparatus, offer means more easily can be trespassed for opposing territorial sky.
Utility model content
For above-mentioned develop a kind of use flexibly, cost is low, deterrent force is big aircraft blocking apparatus, can be trespassed, for opposing territorial sky, the problem that means more easily are provided, this utility model provides a kind of blocking apparatus intercepted for aircraft.
For the problems referred to above, a kind of blocking apparatus intercepted for aircraft that this utility model provides is achieved the goal by techniques below main points: a kind of blocking apparatus intercepted for aircraft, including body and for body launch launching tube, described body includes body shell, described body shell and launching tube are the barrel-like structure of one end open, are disposed with parachute, falling body, silk thread portion and emission part by opening to the cecum of body shell in described body shell；
Described falling body is connected on the free end of parachute rope by the first bracing wire；
Described silk thread portion includes multi-filament line, and described silk thread portion is connected on falling body by the second bracing wire；
Described emission part provides power for departing from body shell for parachute, falling body and silk thread portion.
Concrete, the launching tube of setting is as the emission element of body, and to be launched by body to specified altitude assignment, the emission part of setting is for, after body arrives specified altitude assignment, dishing out parachute, falling body and silk thread portion by body shell.After parachute, falling body and silk thread portion are spilled over, parachute is stretched out under the gravity of falling body, and so, three slowly declines, and being arranged on the multi-filament line in silk thread portion under the effect of air stream, can wave with the wind, and the length of silk thread can determine the sphere of action of body.When aircraft is by the sphere of action of body, no matter it is put down to fly propeller, vertical lift propeller and screw-rudder, all silk thread can be had suction effect, after above propeller is wound around silk thread, the power of corresponding propeller is destroyed, thus having reached the interception purpose to aircraft.
This blocking apparatus, compared to modes such as existing guided missile, antiaircraft guns, produces and launch cost destruction low, that environment is caused is little, mobility is good.
The transmitting of body can be adopted the mode such as explosive thrust, electric field force by launching tube.
Further technical scheme is:
Being easy to erection as a kind of and shift this blocking apparatus and launch the implementation of body at any time, also including the first powder chamber being arranged at bottom launching tube, described first powder chamber provides power for launching body for launching tube；
Described emission part is be arranged at the second powder chamber bottom body shell.
For making parachute, falling body and silk thread portion in the process being pushed out body shell, uniform force on each point of body shell cross section, in order to can scatter smoothly in parachute, silk thread portion, it is additionally provided with the second balance backing plate between described emission part and silk thread portion；
The first balance backing plate it is additionally provided with between described silk thread portion and falling body；
Described second balance backing plate and the first balance backing plate are slab construction, and the second balance backing plate and the first balance backing plate are all vertical with the axis of body shell.
For avoiding when the rainy day uses this blocking apparatus; body emission process cause parachute to soak and can not scatter smoothly because drenching with rain; or avoid playing in flight course because of barrier; parachute is caused to be damaged; also including the protection backing plate being arranged in body shell, described protection backing plate is arranged at body shell opener end between parachute top.
For ease of changing the transmitting angle of body, also including the base for fixed transmission cylinder, the axis of described launching tube is adjustable with the angle of base.
For ease of realizing maintenance spiraling state in projectile flight process, so that final body can fly to specifying position, the internal face of described launching tube is additionally provided with helicla flute, the outer wall of described body shell is provided with the helical raised coordinated with described helicla flute.
This utility model has the advantages that
In this utility model, the launching tube of setting is as the emission element of body, and to be launched by body to specified altitude assignment, the emission part of setting is for, after body arrives specified altitude assignment, dishing out parachute, falling body and silk thread portion by body shell.After parachute, falling body and silk thread portion are spilled over, parachute is stretched out under the gravity of falling body, and so, three slowly declines, and being arranged on the multi-filament line in silk thread portion under the effect of air stream, can wave with the wind, and the length of silk thread can determine the sphere of action of body.When aircraft is by the sphere of action of body, no matter it is put down to fly propeller, vertical lift propeller and screw-rudder, all silk thread can be had suction effect, after above propeller is wound around silk thread, the power of corresponding propeller is destroyed, thus having reached the interception purpose to aircraft.
This blocking apparatus, compared to modes such as existing guided missile, antiaircraft guns, produces and launch cost destruction low, that environment is caused is little, mobility is good.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of one specific embodiment of blocking apparatus intercepted for aircraft described in the utility model.
Label in figure represents respectively: 1, launching tube, and 2, body shell, the 3, second bracing wire, 4, parachute, the 5, first bracing wire; 6, falling body, the 7, first balance backing plate, the 8, silk thread portion, 9, second balance backing plate; 10, base, the 11, first powder chamber, the 12, second powder chamber, 13, protection backing plate.
Detailed description of the invention
Below in conjunction with embodiment, the utility model is described in further detail, but structure of the present utility model is not limited only to following example.
Embodiment 1:
As shown in Figure 1, a kind of blocking apparatus intercepted for aircraft, including body and for body launch launching tube 1, described body includes body shell 2, described body shell 2 and launching tube 1 are the barrel-like structure of one end open, are disposed with parachute 4, falling body 6, silk thread portion 8 and emission part by opening to the cecum of body shell 2 in described body shell 2；
Described falling body 6 is connected on the free end of parachute 4 umbrella rope by the first bracing wire 5；
Described silk thread portion 8 includes multi-filament line, and described silk thread portion 8 is connected on falling body 6 by the second bracing wire 3；
Described emission part provides power for departing from body shell 2 for parachute 4, falling body 6 and silk thread portion 8.
Concrete, the launching tube 1 of setting is as the emission element of body, and to be launched by body to specified altitude assignment, the emission part of setting is for, after body arrives specified altitude assignment, dishing out parachute 4, falling body 6 and silk thread portion 8 by body shell 2.After parachute 4, falling body 6 and silk thread portion 8 are spilled over, parachute 4 is stretched out under the gravity of falling body 6, so, three slowly declines, being arranged on the multi-filament line in silk thread portion 8 under the effect of air stream, to wave with the wind, the length of silk thread can determine the sphere of action of body.When aircraft is by the sphere of action of body, no matter it is put down to fly propeller, vertical lift propeller and screw-rudder, all silk thread can be had suction effect, after above propeller is wound around silk thread, the power of corresponding propeller is destroyed, thus having reached the interception purpose to aircraft.
This blocking apparatus, compared to modes such as existing guided missile, antiaircraft guns, produces and launch cost destruction low, that environment is caused is little, mobility is good.
The transmitting of body can be adopted the mode such as explosive thrust, electric field force by launching tube 1.
Embodiment 2:
As shown in Figure 1, the present embodiment is further qualified on the basis of embodiment 1: is easy to erection as a kind of and shift this blocking apparatus and launch the implementation of body at any time, also including the first powder chamber 11 being arranged at bottom launching tube 1, described first powder chamber 11 provides power for launching body for launching tube 1；
Described emission part is be arranged at the second powder chamber 12 bottom body shell 2.
In this case, also include the height sensor being arranged in body and the igniter ignited for explosive in the second powder chamber 12, the measurement signal of level above sensor is as the enabling signal of igniter, to discharge parachute 4, falling body 6 and silk thread portion 8 in specified altitude assignment.
For making parachute 4, falling body 6 and silk thread portion 8 in the process being pushed out body shell 2, uniform force on each point of body shell 2 cross section, so that can scatter smoothly in parachute 4, silk thread portion 8, between described emission part and silk thread portion 8, it is additionally provided with the second balance backing plate 9；
The first balance backing plate 7 it is additionally provided with between described silk thread portion 8 and falling body 6；
Described second balance backing plate 9 and the first balance backing plate 7 are slab construction, and the second balance backing plate 9 and the first balance backing plate 7 are all vertical with the axis of body shell 2.
For avoiding when the rainy day uses this blocking apparatus; body emission process cause parachute 4 to soak and can not scatter smoothly because drenching with rain; or avoid playing in flight course because of barrier; parachute 4 is caused to be damaged; also including the protection backing plate 13 being arranged in body shell 2, described protection backing plate 13 is arranged at body shell 2 opening between parachute 4 top.
For ease of changing the transmitting angle of body, also including the base 10 for fixed transmission cylinder 1, the axis of described launching tube 1 is adjustable with the angle of base 10.
Embodiment 3:
The present embodiment is further qualified on the basis of any one technical scheme of one embodiment offer of any of the above: for ease of realizing maintenance spiraling state in projectile flight process, so that final body can fly to specifying position, the internal face of described launching tube 1 is additionally provided with helicla flute, the outer wall of described body shell 2 is provided with the helical raised coordinated with described helicla flute.
Above content is further description this utility model made in conjunction with concrete preferred implementation, it is impossible to assert that detailed description of the invention of the present utility model is confined to these explanations.For this utility model person of an ordinary skill in the technical field, without departing from other embodiments drawn under the technical solution of the utility model, should be included in protection domain of the present utility model.
Claims (6)
1. the blocking apparatus intercepted for aircraft, including body and for body launch launching tube (1), it is characterized in that, described body includes body shell (2), described body shell (2) and launching tube (1) are the barrel-like structure of one end open, are disposed with parachute (4), falling body (6), silk thread portion (8) and emission part by opening to the cecum of body shell (2) in described body shell (2)；
Described falling body (6) is connected on the free end of parachute (4) umbrella rope by the first bracing wire (5)；
Described silk thread portion (8) includes multi-filament line, and described silk thread portion (8) is connected on falling body (6) by the second bracing wire (3)；
Described emission part is used for as parachute (4), falling body (6) and silk thread portion (8) disengaging body shell (2) offer power.
2. a kind of blocking apparatus intercepted for aircraft according to claim 1, it is characterised in that also include the first powder chamber (11) being arranged at launching tube (1) bottom, described first powder chamber (11) provides power for launching body for launching tube (1)；
Described emission part is the second powder chamber (12) being arranged at body shell (2) bottom.
3. a kind of blocking apparatus intercepted for aircraft according to claim 2, it is characterised in that be additionally provided with the second balance backing plate (9) between described emission part and silk thread portion (8)；
The first balance backing plate (7) it is additionally provided with between described silk thread portion (8) and falling body (6)；
Described second balance backing plate (9) and the first balance backing plate (7) are slab construction, and the second balance backing plate (9) and the first balance backing plate (7) are all vertical with the axis of body shell (2).
4. according in claim described in 1 a kind of for aircraft intercept blocking apparatus; it is characterized in that; also including the protection backing plate (13) being arranged in body shell (2), described protection backing plate (13) is arranged at body shell (2) opening between parachute (4) top.
5. a kind of blocking apparatus intercepted for aircraft according to claim 1, it is characterised in that also including the base (10) for fixed transmission cylinder (1), the axis of described launching tube (1) is adjustable with the angle of base (10).
6. a kind of blocking apparatus intercepted for aircraft as claimed in any of claims 1 to 5, it is characterized in that, the internal face of described launching tube (1) is additionally provided with helicla flute, the outer wall of described body shell (2) is provided with the helical raised coordinated with described helicla flute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620139734.2U CN205352204U (en) | 2016-02-25 | 2016-02-25 | A intercepting device for aircraft interception |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620139734.2U CN205352204U (en) | 2016-02-25 | 2016-02-25 | A intercepting device for aircraft interception |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205352204U true CN205352204U (en) | 2016-06-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620139734.2U Expired - Fee Related CN205352204U (en) | 2016-02-25 | 2016-02-25 | A intercepting device for aircraft interception |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205352204U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106403718A (en) * | 2016-12-07 | 2017-02-15 | 华南农业大学 | Recoverable electric rocket for intercepting small aircraft |
| CN108981473A (en) * | 2018-07-27 | 2018-12-11 | 广州中国科学院工业技术研究院 | A kind of hold-up interception method of pair of rotor wing unmanned aerial vehicle |
| CN112556508A (en) * | 2018-11-27 | 2021-03-26 | 耿飞 | Fireworks type ammunition with delivery system |
-
2016
- 2016-02-25 CN CN201620139734.2U patent/CN205352204U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106403718A (en) * | 2016-12-07 | 2017-02-15 | 华南农业大学 | Recoverable electric rocket for intercepting small aircraft |
| CN108981473A (en) * | 2018-07-27 | 2018-12-11 | 广州中国科学院工业技术研究院 | A kind of hold-up interception method of pair of rotor wing unmanned aerial vehicle |
| CN112556508A (en) * | 2018-11-27 | 2021-03-26 | 耿飞 | Fireworks type ammunition with delivery system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160629 Termination date: 20180225 |
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| CF01 | Termination of patent right due to non-payment of annual fee |