CN104290913A - Delay detaching mechanism of unmanned plane and parachute - Google Patents
Delay detaching mechanism of unmanned plane and parachute Download PDFInfo
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- CN104290913A CN104290913A CN201410521760.7A CN201410521760A CN104290913A CN 104290913 A CN104290913 A CN 104290913A CN 201410521760 A CN201410521760 A CN 201410521760A CN 104290913 A CN104290913 A CN 104290913A
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- electromagnet
- parachute
- unmanned plane
- pipe link
- armature
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Abstract
The invention discloses a delay detaching mechanism of an unmanned plane and a parachute. The delay detaching mechanism of the unmanned plane and the parachute comprises an electromagnet and a locking device. When the locking device is in locking status, the electromagnet is powered off, an electromagnet armature can not stretch out, a drive rod and a connection rod of a hinge four link mechanism are located on a straight line, and a driven rod of the hinge four link mechanism, which bears pull force of the parachute, can not rotate by using a dead center position of the hinge four link mechanism. When the locking device is unlocked, the electromagnet armature can stretch out, drives the drive rod of the hinge four link mechanism to rotate, and destroys the dead center position of the hinge four link mechanism, and then connection positions of the unmanned plane and the recovery parachute are alternated. The delay detaching mechanism of the unmanned plane and the parachute has the advantages of being strong in bearing capacity due to the fact that the large pull force of the parachute is borne by components of the drive rod, the connection rod, the driven rod and the like of the hinge four link mechanism, being capable of effectively reducing boundary dimensions and weight of the electromagnet and the delay detaching mechanism due to the fact that value of thrust output by the electromagnet is small, and being high in reliability and large in application value due to the fact that the delay detaching mechanism is simple and practical in structure principle.
Description
Technical field
The present invention relates to a kind of disengagement gear, specifically a kind of time delay separation device for unmanned plane and parachute.
Background technology
In unmanned aircraft parachute descent process, in the incipient stage, unmanned plane needs to decline fast, requires the afterbody of connecting portion at aircraft of parachute and unmanned plane for this reason, makes unmanned plane head down; After decline certain distance, the connecting portion of parachute and unmanned plane must be transformed in the middle part of aircraft.For this reason, need to develop the time delay separation device between a kind of parachute of solving the problem and unmanned plane.
Summary of the invention
The object of the invention is to overcome deficiency of the prior art, a kind of time delay separation device for unmanned plane and parachute rational in infrastructure is provided.
The time delay separation device of this unmanned plane and parachute, comprises electromagnet and latching device; When latching device is in locking state, electromagnet no power, electromagnet armature does not stretch out, and driving lever and connecting rod in line, utilize four-bar linkage dead center position, and the follower lever by parachute pulling force cannot rotate; When latching device unlocks, electromagnet armature stretches out, and the driving lever promoting four-bar linkage rotates, and destroys four-bar linkage dead center position, and unmanned plane converts with recovery parachute connection location.
As preferably: described electromagnet is made up of armature, coil and iron core; Limiting stopper is for limiting the retracted position of electromagnet armature, and the right side unshakable in one's determination of electromagnet contacts with frame, realizes the right side axial location of electromagnet; The left side unshakable in one's determination of electromagnet contacts with limiting stopper, and limiting stopper contacts with end cap, and end cap is fixedly connected with frame by set pin, thus realizes the left side axial location of electromagnet; Electromagnet action during energising, its armature stretches out, thrust output.
As preferably: described latching device adopts four-bar linkage, and be made up of driving lever, connecting rod, follower lever, frame, driving lever, connecting rod, follower lever are connected with frame respectively by hinge axis; Pipe link is equipped with in the front end of latching device, and pipe link is connected with frame by rotating shaft, and pipe link is connected with parachute by umbrella band, and the other end of umbrella band is fixed on the medium position of unmanned plane; Compress Spring is placed on spring perch, and spring perch is fixed in frame.
As preferably: when described latching device is in locking state, unmanned plane is positioned at unmanned plane afterbody by the point of connection of umbrella band and parachute, i.e. pipe link place, electromagnet no power, electromagnet armature does not stretch out, driving lever and connecting rod are in line, pipe link and follower lever have part contact, pipe link is positioned at the left side of follower lever, utilize four-bar linkage dead center position, follower lever by parachute pulling force can not rotate, and Compress Spring is in compressive state simultaneously, and the power output of Compress Spring guarantees that four-bar linkage is in dead center position; During electromagnet energising, electromagnet armature stretches out, overcome the elastic pressure of Compress Spring, promotion driving lever turns an angle, and destroys four-bar linkage dead center position, and locking state removed by latching device, follower lever turns over certain angle relative to frame, pipe link is separated with follower lever, and the umbrella band of parachute skids off from pipe link, and unmanned plane is positioned in the middle part of unmanned plane by the point of connection of umbrella band and parachute.
The invention has the beneficial effects as follows: when 1, time delay separation device is in locking state, utilize four-bar linkage dead center position characteristic, the component such as driving lever, connecting rod, follower lever of the larger pulling force four-bar linkage of parachute bears, and the intensity of component itself is higher, and load-carrying capacity is stronger.2, when time delay separation device unlocks, electromagnet armature exports the driving lever rotation that less power just can promote four-bar linkage, destroy four-bar linkage dead center position, the umbrella band realizing parachute skids off from pipe link, realize unmanned plane and the conversion of reclaiming parachute connection location, because electromagnet thrust output value is less, oad and the quality of electromagnet and time delay separation device can be effectively reduced.3, the structural principle of mechanism is simple and practical, and reliability is high, has larger using value.
Accompanying drawing explanation
Fig. 1 is locking state schematic diagram of the present invention.
Fig. 2 is released state schematic diagram of the present invention.
Fig. 3 is locking state using state schematic diagram of the present invention.
Fig. 4 is released state using state schematic diagram of the present invention.
Description of reference numerals: end cap 1, set pin 2, limiting stopper 3, armature 4, coil 5, iron core 6, frame 7, driving lever 8, hinge axis 9, connecting rod 10, follower lever 11, pipe link 12, rotating shaft 13, Compress Spring 14, spring perch 15, unmanned plane 16, umbrella band 17, parachute 18.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described further.Although the present invention will be described in conjunction with preferred embodiment, should know, and not represent and limit the invention in described embodiment.On the contrary, the present invention will contain can be included in attached claims limit scope of the present invention in alternative, improved type and equivalent.
Shown in Fig. 2, the time delay separation device for unmanned plane and parachute of the present embodiment is made up of electromagnet and latching device two parts.End cap 1 is fixedly connected with frame 7 by set pin 2.
Electromagnet is made up of armature 4, coil 5, unshakable in one's determination 6.Limiting stopper 3, for limiting the retracted position of electromagnet armature 4, contacts with frame 7 on the right side of the iron core 6 of electromagnet, realizes the right side axial location of electromagnet; Contact with limiting stopper 3 on the left of the iron core 6 of electromagnet, limiting stopper 3 contacts with end cap 1, and end cap 1 is fixedly connected with frame 7 by set pin 2, thus realizes the left side axial location of electromagnet.Electromagnet action during energising, its armature 4 stretches out, thrust output.Input power is source of AC, then adopt alternating electromagnet; Input power is direct supply, then adopt DC electromagnet.
Latching device adopts four-bar linkage, and be made up of driving lever 8, connecting rod 10, follower lever 11, frame 7, driving lever 8, connecting rod 10, follower lever 11 are connected with frame 7 respectively by hinge axis 9.Pipe link 12 is equipped with in the front end of latching device, and pipe link 12 is connected with frame 7 by rotating shaft 13, and pipe link 12 is connected with parachute 18 by umbrella band 17, and the other end of umbrella band 17 is fixed on the medium position of unmanned plane 16.Compress Spring 14 is placed on spring perch 15, and spring perch 15 is fixed in frame 7.
When latching device is in locking state, unmanned plane 16 is positioned at unmanned plane 16 afterbody by umbrella band 17 and the point of connection of parachute 18, i.e. pipe link 12 place, electromagnet no power, electromagnet armature 4 does not stretch out, driving lever 8 and connecting rod 10 are in line, pipe link 12 and follower lever 11 have part contact, pipe link 12 is positioned at the left side of follower lever 11, utilize four-bar linkage dead center position, follower lever 11 by parachute 18 pulling force can not rotate, and Compress Spring 14 is in compressive state simultaneously, and the power output of Compress Spring 14 guarantees that four-bar linkage is in dead center position.
Electromagnet is energized, electromagnet armature 4 stretches out, overcome the elastic pressure of Compress Spring 14, promote driving lever 8 to turn an angle, destroy four-bar linkage dead center position, locking state removed by latching device, follower lever 11 turns over certain angle relative to frame 7, pipe link 12 is separated with follower lever 11, and the umbrella band 17 of parachute 18 skids off from pipe link 12, and unmanned plane 16 is positioned in the middle part of unmanned plane 16 by the point of connection of umbrella band 17 with parachute 18.As shown in Figure 3 to Figure 4.
Claims (4)
1. a time delay separation device for unmanned plane and parachute, is characterized in that: comprise electromagnet and latching device; When latching device is in locking state, electromagnet no power, electromagnet armature (4) does not stretch out, driving lever (8) and connecting rod (10) are in line, utilize four-bar linkage dead center position, the follower lever (11) by parachute pulling force cannot rotate; When latching device unlocks, electromagnet armature (4) stretches out, and the driving lever (8) promoting four-bar linkage rotates, and destroys four-bar linkage dead center position, and unmanned plane converts with recovery parachute connection location.
2. the time delay separation device of unmanned plane according to claim 1 and parachute, is characterized in that: described electromagnet is made up of armature (4), coil (5) and iron core (6); Limiting stopper (3) is for limiting the retracted position of electromagnet armature (4), and iron core (6) right side of electromagnet contacts with frame (7), realizes the right side axial location of electromagnet; Iron core (6) left side of electromagnet contacts with limiting stopper (3), limiting stopper (3) contacts with end cap (1), end cap (1) is fixedly connected with frame (7) by set pin (2), thus realizes the left side axial location of electromagnet; Electromagnet action during energising, its armature (4) stretches out, thrust output.
3. the time delay separation device of unmanned plane according to claim 1 and parachute, it is characterized in that: described latching device adopts four-bar linkage, be made up of driving lever (8), connecting rod (10), follower lever (11), frame (7), driving lever (8), connecting rod (10), follower lever (11) are connected with frame (7) respectively by hinge axis (9); Pipe link (12) is equipped with in the front end of latching device, pipe link (12) is connected with frame (7) by rotating shaft (13), pipe link (12) is connected with parachute (18) by umbrella band (17), and the other end of umbrella band (17) is fixed on the medium position of unmanned plane (16); Compress Spring (14) is placed on spring perch (15), and spring perch (15) is fixed in frame (7).
4. the time delay separation device of unmanned plane according to claim 3 and parachute, it is characterized in that: when described latching device is in locking state, unmanned plane (16) is positioned at unmanned plane (16) afterbody by umbrella band (17) and the point of connection of parachute (18), i.e. pipe link (12) place, electromagnet no power, electromagnet armature (4) does not stretch out, driving lever (8) and connecting rod (10) are in line, pipe link (12) and follower lever (11) have part contact, pipe link (12) is positioned at the left side of follower lever (11), utilize four-bar linkage dead center position, follower lever (11) by parachute (18) pulling force can not rotate, Compress Spring (14) is in compressive state simultaneously, the power output of Compress Spring (14) guarantees that four-bar linkage is in dead center position, during electromagnet energising, electromagnet armature (4) stretches out, overcome the elastic pressure of Compress Spring (14), promote driving lever (8) to turn an angle, destroy four-bar linkage dead center position, locking state removed by latching device, follower lever (11) turns over certain angle relative to frame (7), pipe link (12) is separated with follower lever (11), the umbrella band (17) of parachute (18) skids off from pipe link (12), unmanned plane (16) is positioned at unmanned plane (16) middle part by umbrella band (17) and the point of connection of parachute (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410521760.7A CN104290913B (en) | 2014-09-30 | 2014-09-30 | A kind of time delay separating mechanism of unmanned plane and parachute |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410521760.7A CN104290913B (en) | 2014-09-30 | 2014-09-30 | A kind of time delay separating mechanism of unmanned plane and parachute |
Publications (2)
| Publication Number | Publication Date |
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| CN104290913A true CN104290913A (en) | 2015-01-21 |
| CN104290913B CN104290913B (en) | 2017-05-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410521760.7A Expired - Fee Related CN104290913B (en) | 2014-09-30 | 2014-09-30 | A kind of time delay separating mechanism of unmanned plane and parachute |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108466696A (en) * | 2018-05-29 | 2018-08-31 | 山西天时利和智能科技有限公司 | A kind of unmanned plane parabolic device |
| CN115420144A (en) * | 2022-08-30 | 2022-12-02 | 上海机电工程研究所 | Electromagnetic opening type cover opening device with self-locking function and cover opening device combination |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU94028541A (en) * | 1994-07-28 | 1997-05-20 | Войсковая часть 75360 | Device for remote control of gliding-type parachute |
| CN201951713U (en) * | 2011-03-17 | 2011-08-31 | 太原航友航空科技有限公司 | Mechanism for automatically separating parachute from unmanned aerial vehicle |
| CN102556354A (en) * | 2011-12-13 | 2012-07-11 | 江西洪都航空工业集团有限责任公司 | Pull-press type triggering parachuting protector |
| CN202783782U (en) * | 2012-08-17 | 2013-03-13 | 董韬 | Parachute disconnecting device for unmanned aircraft |
| US20140231585A1 (en) * | 1999-07-23 | 2014-08-21 | Advanced Aerospace Technologies, Inc. | Launch and recovery system for unmanned aerial vehicles |
| CN204124372U (en) * | 2014-09-30 | 2015-01-28 | 浙江工业大学之江学院 | The time delay separation device of unmanned plane and parachute |
-
2014
- 2014-09-30 CN CN201410521760.7A patent/CN104290913B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU94028541A (en) * | 1994-07-28 | 1997-05-20 | Войсковая часть 75360 | Device for remote control of gliding-type parachute |
| US20140231585A1 (en) * | 1999-07-23 | 2014-08-21 | Advanced Aerospace Technologies, Inc. | Launch and recovery system for unmanned aerial vehicles |
| CN201951713U (en) * | 2011-03-17 | 2011-08-31 | 太原航友航空科技有限公司 | Mechanism for automatically separating parachute from unmanned aerial vehicle |
| CN102556354A (en) * | 2011-12-13 | 2012-07-11 | 江西洪都航空工业集团有限责任公司 | Pull-press type triggering parachuting protector |
| CN202783782U (en) * | 2012-08-17 | 2013-03-13 | 董韬 | Parachute disconnecting device for unmanned aircraft |
| CN204124372U (en) * | 2014-09-30 | 2015-01-28 | 浙江工业大学之江学院 | The time delay separation device of unmanned plane and parachute |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108466696A (en) * | 2018-05-29 | 2018-08-31 | 山西天时利和智能科技有限公司 | A kind of unmanned plane parabolic device |
| CN115420144A (en) * | 2022-08-30 | 2022-12-02 | 上海机电工程研究所 | Electromagnetic opening type cover opening device with self-locking function and cover opening device combination |
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| Publication number | Publication date |
|---|---|
| CN104290913B (en) | 2017-05-31 |
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