CN102374828A - Curtain type aircraft intercepting equipment without collateral damages - Google Patents
Curtain type aircraft intercepting equipment without collateral damages Download PDFInfo
- Publication number
- CN102374828A CN102374828A CN2010102647925A CN201010264792A CN102374828A CN 102374828 A CN102374828 A CN 102374828A CN 2010102647925 A CN2010102647925 A CN 2010102647925A CN 201010264792 A CN201010264792 A CN 201010264792A CN 102374828 A CN102374828 A CN 102374828A
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- frame
- mount pad
- interception
- wing
- base plate
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Abstract
The invention discloses curtain type aircraft intercepting equipment without collateral damages. The curtain type aircraft intercepting equipment without the collateral damages comprises intercepting frames with pull rod grooves, silk cluster driver groups, reversed C-shaped bed plates with pull rod holes, pull rods, on-frame mounting bases, locking pins, wing upper mounting bases, buffering washers, supporting rods, cushion pads, backblow-prevention supporting seats, loose-prevention nuts and synchronous explosion and ignition devices. The curtain type aircraft intercepting equipment without the collateral damages, disclosed by the invention, has the advantages of simple structure, small size, light weight, stereoscopic distribution uniformity of a silk bundle curtain in the air, high reliability in cellosilk bundle molding, fewer steps of a using program, rapidness and convenience for mounting, low cost, and excellent comprehensive performance, and can be used for efficiently intercepting aircrafts in an altitude range from dozens of meters to hundreds of meters without the collateral damages..
Description
Technical field
The present invention relates to a kind of interception aircraft equipment, particularly a kind of curtain formula interception aircraft equipment that does not have collateral damage belongs to aerial security field, city.
Background technology
In some important athletic meeting and important events; In order to prevent that the lawless person from adopting aircraft to split the meeting venue or critical event generation place sabotages; From safety of environment is needed to adopt the mode of injuring destruction firmly to tackle; Need to adopt the soft destruction mode that these small aircrafts are effectively tackled, make its flight disabler and then lose predetermined wildcat operation purpose, and can not produce any subsidiary destruction surrounding building or personnel.This soft destruction mode requires that program step is few, simple in structure, reliability is high, installation is succinct and cost is low; Developed a kind of curtain formula interception aircraft equipment that does not have collateral damage for this reason; When can effectively tackle the other side's aircraft, realize destroying to the nothing of surrounding enviroment is subsidiary.Do not see the subsidiary unmanned plane intercepting system that destroys aircraft of the nothing that duplicates with the present invention at present both at home and abroad.
Summary of the invention
The problem that the present invention will solve provides a kind of curtain formula interception aircraft equipment that does not have a collateral damage, have simple in structure, volume is little, in light weight, characteristics such as function reliability is high, cost is low, installation is simple and convenient.
The curtain formula interception aircraft equipment of no collateral damage of the present invention; Comprise on the interception frame that has pull rod slot, silk group driver bank,
the type base plate that has tie rod hole, pull bar, the frame mount pad on mount pad, locking pin, the wing, buffering spacer, support bar, cushion pad, anti-recoil supporting seat, stop nut and exploding primer device synchronously, the exploding primer device comprises slide block and detonator assembly device, short circuit and igniter and primacord assembly synchronously; Launch hole is arranged on the frame, and mount pad is the cylinder that has chassis and counterbore on the frame, and bar-shaped trough is arranged on it, and mount pad is the cylinder that has plush copper and chassis on the wing, and anti-recoil supporting seat is the cylinder that has chassis and U type groove; Silk group driver bank is connected in the launch hole of interception frame; The interception frame is fixed in
type base plate; Pass the tie rod hole, the pull rod slot of interception on the frame of
type base plate successively with pull bar after, the pull bar two ends are fixed; Mount pad is fixed on
type base plate upper surface on the frame, in the counterbore of mount pad buffering spacer is housed on the frame; Mount pad and wing are connected on the wing, and the plush copper of mount pad stretches in the counterbore of mount pad on the frame and contact with buffering spacer on the wing, and pin with locking mount pad on mount pad on the frame and the wing is fixedly connected, and lock nut fully tightly; Anti-recoil supporting seat is fixedly connected on the side of
type base plate, and cushion pad is connected in the U type groove of anti-recoil supporting seat; Support bar passes fuselage and fixing, and its two terminal circle cylinder snaps on the cushion pad in the U type groove of anti-recoil supporting seat, the U type bottom land plane contact of its right ends face and anti-recoil supporting seat, and support bar, cushion pad, prevent being connected between the supporting seat of recoil; The slide block of exploding primer device and detonator assembly device and short circuit and igniter are fixed on the bottom surface of
type base plate synchronously; Slide block is connected with the primacord assembly contact of passing
type base plate with detonator assembly device one side, and another side is connected with lead with igniter with short circuit; The primacord assembly passes all silk group's driver bank successively and is fixed in the interception frame;
The curtain formula interception aircraft equipment of above-mentioned no collateral damage, the fore-and-aft direction angle of silk group driver bank changes in 180 ° of scopes, and the above-below direction angle changes in 90 ° of scopes, equidistantly is distributed in the scope at 90 ° of angles between the silk group driver.
Beneficial effect:
The curtain formula of no collateral damage of the present invention interception aircraft equipment configuration is simple, volume is little, in light weight, tow curtain three-dimensionally is evenly distributed in the air, fibre bundle moulding reliability height, few, the quick for installation convenience of service routine step, cost is low and high comprehensive performance, can efficiently tackle at tens meters aircraft to hundreds of rice scope highly.
The curtain formula interception aircraft equipment of no collateral damage of the present invention comprises the following steps:
(1) arming, the safety isolation is removed in the slide block assembly action, makes detonator assembly aim at the termination of primacord assembly;
(2) control system provides ignition signal; By cap sensitive primacord assembly, some group's driver bank are synchronized and detonate, after driving silk group flies out along the preset direction impelling; Silk group launches and forms three-dimensional, large tracts of land, the slow fibre bundle curtain of falling speed aloft, with interception the other side aircraft.
Description of drawings
Fig. 1 is the front view of the curtain formula interception aircraft equipment of no collateral damage of the present invention;
Fig. 2 is that the A of mount pad on the dismounting wing of curtain formula interception aircraft equipment of no collateral damage of the present invention is to view;
Fig. 3 is that ground floor silk group driver bank is arranged the C-C sectional drawing in the interception frame of the present invention;
Fig. 4 is that second layer silk group driver bank is arranged the D-D sectional drawing in the interception frame of the present invention;
Fig. 5 is the anti-recoil clamping support figure of the curtain formula interception aircraft equipment of no collateral damage shown in Figure 1;
Fig. 6 is a mount pad structure chart on the frame of curtain formula interception aircraft equipment of no collateral damage shown in Figure 1;
Fig. 7 is that silk of the present invention is rolled into a ball driver bank at interception frame fore-and-aft direction angle of departure arrangement method sketch map in the interception frame.
Among the figure: 1-tackles frame; 2-silk group driver bank; 3-
type base plate; The 4-pull rod slot; The 5-pull bar; The 6-launch hole; The 7-nut; Mount pad on the 8-frame; 9-locks pin; Mount pad on the 10-wing; The 11-lock nut; The 12-buffering spacer; The 13-support bar; The 14-holding screw; The 15-cushion pad; The anti-recoil of 16-supporting seat; The 17-stop nut; The synchronous exploding primer device of 18-; 19-slide block and detonator assembly device; 20-short circuit and igniter; 21-primacord assembly; The 22-bar-shaped trough.
The specific embodiment
Below in conjunction with accompanying drawing the present invention is done further explain.
Like the curtain formula interception aircraft equipment of Fig. 1 to no collateral damage shown in Figure 6, it comprises on the interception frame 1 that has pull rod slot, silk group driver bank 2,
the type base plate 3 that has tie rod hole, pull bar 5, the frame mount pad 10, buffering spacer 12, support bar 13, cushion pad 15, anti-recoil supporting seat 16, stop nut 17 and synchronous exploding primer device 18 on mount pad 8, locking pin 9, the wing; On the interception frame 1 launch hole 6 is arranged; Mount pad 8 is for having the cylinder of chassis and counterbore on the frame; Bar-shaped trough 22 is arranged on it; Mount pad 10 is for having the cylinder on plush copper and chassis on the wing, and anti-recoil supporting seat 16 is for having the cylinder of chassis and U type groove, and exploding primer device 18 comprises slide block and detonator assembly device 19, short circuit and igniter 20 and primacord assembly 21 synchronously; Silk group driver bank 2 sticks in the launch hole 6 of interception frame 1; Interception frame 1 is installed in
type base plate 3; After passing the pull rod slot on tie rod hole on
type base plate 3, the interception frame 1 successively with pull bar 5, pull bar 5 two ends are strained and fixed with nut 7; Mount pad 8 is fixed on
type base plate 3 upper surfaces on the frame, and buffering spacer 12 is housed in the counterbore of mount pad 8 on the frame; Mount pad 10 is connected with wing on the wing, and the plush copper of mount pad 33 stretches in the counterbore of mount pad 8 on the frame and contact with buffering spacer 12 on the wing, and pins with locking and 32 mount pad 10 on mount pad on the frame 8 and the wing to be fixedly connected, and lock nut 11 fully tightly; Anti-recoil supporting seat 16 is fixedly connected on the side of
type base plate 3; The cushion pad 15 that is connected in the U type groove of anti-recoil supporting seat 16, the quantity of anti-recoil supporting seat 16 is 3; Support bar 13 passes fuselage and fixing; Its two terminal circle cylinder snaps on the cushion pad 16 in the U type groove of preventing recoil supporting seat 16; The U type bottom land plane contact of its right ends face and anti-recoil supporting seat 16; And be connected between support bar 13, cushion pad 15, the anti-recoil supporting seat 16, support bar 13 quantity are 3, can also reinforce with A-frame between the support bar 13; Slide block and detonator assembly device 19, short circuit and the igniter 20 of exploding primer device 18 all are fixed on the bottom surface of
type base plate 3 synchronously; Slide block is connected with the primacord assembly that passes
type base plate 3 21 contacts with detonator assembly device 19 one sides, and another side is connected with igniter 20 usefulness leads with short circuit; Primacord assembly 21 passes all silk group's driver bank 2 successively and is fixed in the interception frame 1.
Fig. 7 for the angle of departure method for arranging sketch map of the silk group driver bank 2 in the curtain formula of the no collateral damage of the present invention interception aircraft equipment (with about 10 silks group driver bank 2 layers be distributed as example; X representes silk group driver number among the figure; Y representes range; θ represents the angle of silk group driver); Arrange evenly that at 0 °～90 ° circumference range internal thread group drivers the range that obtains 10 drivers should reach the position, with the crossing pairing emission angle theta of each driver that obtains of circumference; Be respectively 0 °, 6 °, 13 °, 20 °, 26 °, 34 °, 42 °, 51 °, 63 ° and 90 °; The respective angles that scalable was launched forward or backward when emission angle theta was arranged on the interception frame, silk are rolled into a ball the angle of putting in the 180 ° of scopes in driver front and back and be followed successively by: 0 °, 13 °, 26 °, 42 °, 63 °, 90 °, 129 °, 146 °, 160 ° and 174 °, silk group driver 2 layers of angle of putting of 90 ° of interior branches of scopes up and down is followed successively by 10 ° and 20 °.
Claims (2)
1. a curtain formula interception aircraft that does not have collateral damage is equipped; Comprise on the interception frame (1) that has pull rod slot, silk group driver bank (2),
the type base plate (3) that has tie rod hole, pull bar (5), the frame mount pad (10) on mount pad (8), locking pin (9), the wing, buffering spacer (12), support bar (13), cushion pad (15), anti-recoil supporting seat (16), stop nut (17) and exploding primer device (18) synchronously, synchronous exploding primer device (18) comprises slide block and detonator assembly device (19), short circuit and igniter (20) and primacord assembly (21); It is characterized in that: on the interception frame (1) launch hole (6) is arranged; Mount pad on the frame (8) is for having the cylinder of chassis and counterbore; Bar-shaped trough (22) is arranged on it, and mount pad on the wing (10) is for having the cylinder on plush copper and chassis, and anti-recoil supporting seat (16) is for having the cylinder of chassis and U type groove; Silk group's driver bank (2) is connected in the launch hole (6) of interception frame (1); Interception frame (1) is fixed in
type base plate (3); After passing the tie rod hole of
type base plate (3), pull rod slot in interception frame (1) successively with pull bar (5), pull bar (5) two ends are fixed; Mount pad on the frame (8) is fixed on
type base plate (3) upper surface, and buffering spacer (12) is housed in the counterbore of mount pad on the frame (8); Mount pad on the wing (10) is connected with wing; The plush copper of mount pad on the wing (33) stretches in the counterbore of mount pad on the frame (8) and contacts with buffering spacer (12); And with locking pin (32) mount pad (10) on mount pad on the frame (8) and the wing is fixedly connected, lock nut (11) is fully tightly; Anti-recoil supporting seat (16) is fixedly connected on the side of
type base plate (3), and cushion pad (15) is connected in the U type groove of anti-recoil supporting seat (16); Support bar (13) passes fuselage and fixing; Its two terminal circle cylinder snaps on the cushion pad (16) in the U type groove of preventing recoil supporting seat (16); The U type bottom land plane contact of its right ends face and anti-recoil supporting seat (16), and be connected between support bar (13), cushion pad (15), the anti-recoil supporting seat (16); The slide block of exploding primer device (18) and detonator assembly device (19) and short circuit and igniter (20) are fixed on the bottom surface of
type base plate (3) synchronously; Slide block is connected with primacord assembly (21) contact of passing
type base plate (3) with detonator assembly device (19) one side, and another side is connected with lead with igniter (20) with short circuit; Primacord assembly (21) passes all silk group's driver bank (2) successively and is fixed in the interception frame (1); Intercepting system is to hang under the wing with symmetric form.
2. a kind of curtain formula interception aircraft equipment that does not have collateral damage according to claim 1; It is characterized in that: the fore-and-aft direction angle of silk group's driver bank (2) changes in 180 ° of scopes; The above-below direction angle changes in 90 ° of scopes, equidistantly is distributed in the scope at 90 ° of angles between the silk group driver.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102647925A CN102374828A (en) | 2010-08-27 | 2010-08-27 | Curtain type aircraft intercepting equipment without collateral damages |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102647925A CN102374828A (en) | 2010-08-27 | 2010-08-27 | Curtain type aircraft intercepting equipment without collateral damages |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102374828A true CN102374828A (en) | 2012-03-14 |
Family
ID=45793781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010102647925A Pending CN102374828A (en) | 2010-08-27 | 2010-08-27 | Curtain type aircraft intercepting equipment without collateral damages |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102374828A (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 |
| US9896221B1 (en) * | 2012-11-21 | 2018-02-20 | Lockheed Martin Corporation | Unmanned aerial vehicle (UAV) having a deployable net for capture of threat UAVs |
| CN111216890A (en) * | 2014-07-28 | 2020-06-02 | 英西图公司 | System and method for counterattacking unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1956333A (en) * | 1931-03-18 | 1934-04-24 | Olmo Enrico | Submarine barrier and launching and arming means therefor |
| GB529623A (en) * | 1939-06-05 | 1940-11-25 | Maria Wocher | Method of fighting aircraft from other aircraft and means for carrying into effect this method |
| JP2000199699A (en) * | 1999-01-04 | 2000-07-18 | Yoshio Abe | Flying body catcher employing several sheets of net |
| CN201242408Y (en) * | 2008-05-21 | 2009-05-20 | 卢振东 | Multi-warhead guided missile of sub-gasbag-loaded interceptor missile |
-
2010
- 2010-08-27 CN CN2010102647925A patent/CN102374828A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1956333A (en) * | 1931-03-18 | 1934-04-24 | Olmo Enrico | Submarine barrier and launching and arming means therefor |
| GB529623A (en) * | 1939-06-05 | 1940-11-25 | Maria Wocher | Method of fighting aircraft from other aircraft and means for carrying into effect this method |
| JP2000199699A (en) * | 1999-01-04 | 2000-07-18 | Yoshio Abe | Flying body catcher employing several sheets of net |
| CN201242408Y (en) * | 2008-05-21 | 2009-05-20 | 卢振东 | Multi-warhead guided missile of sub-gasbag-loaded interceptor missile |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9896221B1 (en) * | 2012-11-21 | 2018-02-20 | Lockheed Martin Corporation | Unmanned aerial vehicle (UAV) having a deployable net for capture of threat UAVs |
| US10800546B2 (en) | 2012-11-21 | 2020-10-13 | Lockheed Martin Corporation | Unmanned aerial vehicle (UAV) and system and method for capture of threat UAVs |
| CN111216890A (en) * | 2014-07-28 | 2020-06-02 | 英西图公司 | System and method for counterattacking unmanned aerial vehicle |
| CN111216890B (en) * | 2014-07-28 | 2024-02-02 | 英西图公司 | System and method for countering a drone |
| CN106403718A (en) * | 2016-12-07 | 2017-02-15 | 华南农业大学 | Recoverable electric rocket for intercepting small aircraft |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120314 |