CN103552692B - Small flexible wing unmanned plane feedway - Google Patents
Small flexible wing unmanned plane feedway Download PDFInfo
- Publication number
- CN103552692B CN103552692B CN201310556380.2A CN201310556380A CN103552692B CN 103552692 B CN103552692 B CN 103552692B CN 201310556380 A CN201310556380 A CN 201310556380A CN 103552692 B CN103552692 B CN 103552692B
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- China
- Prior art keywords
- closing appliance
- canister launcher
- push pedal
- fixed
- breech block
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Abstract
A kind of cartridge type feedway that can realize small flexible wing unmanned plane and launch.Utilizing about the be centrosymmetric elastic potential energy of elastic element of distribution of canister launcher cross-section center is propulsion source, and aircraft is launched cylinder.When not launching, aircraft is subject to the constraint of locking mechanism in cylinder, and during transmitting, aircraft is subject to the effect of shoe and directed button in cylinder, makes it keep correct attitude.Manual control closing appliance, thus determine whether aircraft is launched.
Description
Art
The present invention relates to a kind of feedway of small flexible wing unmanned plane, especially with the cartridge type ejection firing device that the elastic potential energy of material is propulsion source.
Background technology
Because the transmitting problem of flex-wing unmanned plane also belongs to more blank field at home, therefore, the bibliography can searching comparison about flex-wing unmanned plane feedway is few.At present, the U.S. has a flex-wing unmanned plane to be in the prototype design stage, and its launch mode adopted utilizes gunpowder to produce q.s high temperature and high pressure gas at canister launcher base burning, promotes unmanned plane and goes out cylinder, complete emission process as propulsion source.The shortcoming of this launch mode be to canister launcher material and canister launcher inner wall surface roughness requirements higher, directly cause the cost of manufacture of canister launcher higher, and the service life of canister launcher is very short.
Summary of the invention
The present invention is made up of three groups of elastic elements, three spacing pipes, three groups of fixed pulley assemblies, three groups of push pedal slideways, push pedal, canister launcher, bulkhead, stringer, shoe, closing appliance, closing appliance screened housings.Closing appliance is made up of spring, Breech block, Breech block rotating shaft, connecting rod, trigger, trigger slide rail.
The technical scheme that technical solution problem of the present invention adopts is:
1, five identical bulkheads are arranged in parallel along direction, canister launcher axis, are connected on each contact surface with canister launcher with flathead screw; Three spacing pipes are connected with flathead screw with bulkhead with the groove that three groups of push pedal slideways are each passed through the correspondence on each bulkhead on each contact surface; The axis of spacing pipe, the long limit of push pedal slideway and canister launcher axis parallel; Canister launcher overlaps respectively for the sideline, long limit of the groove of push pedal campaign and the sideline, push pedal slideway long limit after fixing; The pedestal lower end of fixed pulley assembly is helicitic texture, for being fixed on first bulkhead from canister launcher nozzle, often organizing the fixing direction of fixed pulley assembly and this group elastic element should be made simultaneously to move along corresponding spacing pipe axis and push pedal slideway axis.
2, three groups of elastic elements adopt identical method to fix, and often organize elastic element one end and be fixed in spacing pipe, the other end walks around fixed pulley, are fixed on blade face on the canister launcher nozzle face parallel with canister launcher cross-sectional plane; Three groups of elastic elements to be centrosymmetric distribution about canister launcher cross-section center, and push pedal does translation along push pedal slideway.
3, closing appliance screened housing, trigger slide rail are positioned at canister launcher afterbody; the two is all fixed on a stringer; closing appliance screened housing is also connected with canister launcher, and stringer and canister launcher are connected with closing appliance screened housing and with the inner square groove that all has, the locking effect of closing appliance can be applied on aircraft.Spring in closing appliance, Breech block, Breech block rotating shaft are positioned at closing appliance screened housing all the time.Breech block rotating shaft is fixed in closing appliance screened housing, and Breech block freely can rotate around it.Spring one end is fixed in closing appliance screened housing, and the other end is fixed on Breech block.Connecting rod one end connects Breech block, and one end is stretched out closing appliance screened housing and connected trigger, and form moving sets between trigger and trigger slide rail, trigger all the time can only along the translation of trigger slide rail.
4, when the present invention launches, the rear directed button of flex-wing aircraft snaps in closing appliance, pulls trigger, and make the directed button of aircraft depart from the constraint of Breech block, then aircraft moves together with push pedal to nozzle under the effect of elastic element elastic force, thus realizes emission process.
Beneficial effect
The invention has the beneficial effects as follows: the invention provides a kind of flex-wing unmanned plane canister launcher, canister launcher major part assembly all can use plastics, carbon fiber is made, and use elastic potential energy to be converted into the ejection mode of kinetic energy, do not adopt high temperature and high pressure gas as ejection power source, reduce the cost of manufacture of canister launcher, there is no the ablation of high-temperature gas, canister launcher and assembly thereof can Reusabilities, add the service life of canister launcher.The transmitting under multiple load-up condition can be realized by the elastic element changing different stiffness factor.
Accompanying drawing explanation
Fig. 1 is feedway elastic element assembling relationship figure.
Fig. 2 is feedway outward appearance axonometric drawing (trigger does not draw)
Fig. 3 is feedway outward appearance front elevation (closing appliance screened housing, trigger does not draw)
Fig. 4 is feedway outward appearance left view
Fig. 5 is bulkhead front elevation
Fig. 6 is closing appliance and trigger schematic diagram
Fig. 7 is Breech block and cocking mechanism axonometric drawing
Fig. 8 is canister launcher axonometric drawing
Fig. 9 is feedway elastic element practical set graph of a relation
Figure 10 is the assembly axis mapping removing canister launcher and stringer
In figure, 1. canister launcher, 2. bulkhead; 3. stringer, 4. fixed pulley assembly, 5. elastic element; 6. shoe, 7. push pedal, 8. push pedal slideway; 9. spacing pipe, 10. spring, 11. Breech blocks; 12. connecting rods, 13. triggers, 14. trigger slide rails; the rear directed button of 15. aircrafts, 16. Breech block rotating shafts, 17. closing appliance screened housings
Detailed description of the invention:
Below in conjunction with accompanying drawing, the present invention is further described.
According to 1,2, as shown in Figure 1, elastic element (5) one end is fixed in spacing pipe (9), and the other end walks around pulley, is fixed in push pedal (7), and three groups of elastic elements to be centrosymmetric layout about canister launcher (1) cross-section center;
According to 1,2, as shown in Figure 2, Figure 3, Figure 4, canister launcher nozzle is towards paper lower-left, canister launcher (1) overall length 105 centimetres, is wherein positioned at long 10 centimetres of the part that first bulkhead (2) is front, is positioned at long 5 centimetres of part after last bulkhead (2), distance between intermediate-frame (2) to be calculated successively to cylinder tail by nozzle and is respectively 20 centimetres, 20 centimetres, 20 centimetres, 30 centimetres; Bulkhead is faced as shown in Figure 5.
Canister launcher (1) is connected with bulkhead (2) successively, and connected in turn by two kinds of stringers (3) between bulkhead, radical is respectively 6,3.Spacing pipe (9) and push pedal slideway (8) vertically, are connected in the groove of each bulkhead (2) in turn.From nozzle, first bulkhead (2) is connected with three fixed pulley assemblies (4) respectively.Elastic element (5) one end is fixed in spacing pipe (9), and the other end walks around pulley, is fixed in push pedal (7), and three groups of elastic elements are evenly arranged along launching inner core (1) axis.Push pedal (7) only can make motion of translation in push pedal slideway (8);
According to 3, as shown in Fig. 6, Fig. 7, spring (10), Breech block (11), Breech block rotating shaft (16) are all arranged in closing appliance screened housing (17).Stringer (3) and the canister launcher (1) at closing appliance screened housing (17) and this place are connected, and canister launcher (1) connects at closing appliance screened housing and has square groove with inner, is convenient to Breech block (11) and contacts with the rear directed button (15) of aircraft;
The stiffness factor of spring (10) should make spring (10) under small deformation condition (as 5 millimeters), the elastic force produced is greater than the pulling force of elastic element (5), ensure that aircraft is not launched away, trigger (13) is connected with Breech block (11) by connecting rod (12), during transmitting, pull trigger (13), make Breech block (11) that large rotation angle occur, rear directed button (15) then on aircraft will depart from locking, and aircraft is launched cylinder.
Fig. 8, Fig. 9, Figure 10 are used for auxiliary clear and definite feedway inner structure and annexation.
The above, be preferred embodiment of the present invention, should be confined to the content disclosed in the present embodiment and accompanying drawing.Every do not depart from spirit disclosed in this invention under the equivalence that completes or amendment, all fall into the scope of protection of the invention.
Claims (2)
1. a small flexible wing aircraft feedway, be made up of three groups of elastic elements, three spacing pipes, three groups of fixed pulley assemblies, three groups of push pedal slideways, push pedal, canister launcher, bulkhead, stringer, shoe, closing appliance, closing appliance screened housings, wherein, shoe is fixed on canister launcher inwall; Closing appliance is made up of spring, Breech block, Breech block rotating shaft, connecting rod, trigger, trigger slide rail, it is characterized in that:
Five identical bulkheads are arranged in parallel along direction, canister launcher axis, are connected on each contact surface with canister launcher with flathead screw; Three spacing pipes are connected with flathead screw with bulkhead with the groove that three groups of push pedal slideways are each passed through the correspondence on each bulkhead on each contact surface; The axis of spacing pipe, the long limit of push pedal slideway and canister launcher axis parallel; Canister launcher overlaps respectively for the sideline, long limit of the groove of push pedal campaign and the sideline, push pedal slideway long limit after fixing; The pedestal lower end of fixed pulley assembly is helicitic texture, for being fixed on first bulkhead from canister launcher nozzle, often organizing the fixing direction of fixed pulley assembly and these three groups of elastic elements should be made simultaneously to move along corresponding spacing pipe axis and push pedal slideway axis;
Three groups of elastic elements adopt identical method to fix, and often organize elastic element one end and be fixed in spacing pipe, the other end walks around fixed pulley, are fixed on blade face on the canister launcher nozzle face parallel with canister launcher cross-sectional plane; Three groups of elastic elements to be centrosymmetric distribution about canister launcher cross-section center, and push pedal does translation along push pedal slideway;
Closing appliance screened housing, trigger slide rail are positioned at canister launcher afterbody, the two is all fixed on a stringer, closing appliance screened housing is also connected with canister launcher, and stringer and canister launcher are connected with closing appliance screened housing and with the inner square groove that all has, the locking effect of closing appliance can be applied on aircraft; Spring in closing appliance, Breech block, Breech block rotating shaft are positioned at closing appliance screened housing all the time; Breech block rotating shaft is fixed in closing appliance screened housing, and Breech block freely can rotate around it; Spring one end is fixed in closing appliance screened housing, and the other end is fixed on connecting rod one end on Breech block and connects Breech block, and one end is stretched out closing appliance screened housing and connected trigger, and form moving sets between trigger and trigger slide rail, trigger all the time can only along the translation of trigger slide rail.
2. small flexible wing aircraft feedway as claimed in claim 1, elastic potential energy is used to be converted into the ejection mode of kinetic energy, do not adopt high temperature and high pressure gas as ejection power source, the rear directed button of flex-wing aircraft snaps in closing appliance, pull trigger, make the rear directed button of aircraft depart from the constraint of Breech block, then aircraft moves together with push pedal to nozzle under the effect of elastic element elastic force, thus realizes emission process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310556380.2A CN103552692B (en) | 2013-11-11 | 2013-11-11 | Small flexible wing unmanned plane feedway |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310556380.2A CN103552692B (en) | 2013-11-11 | 2013-11-11 | Small flexible wing unmanned plane feedway |
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| Publication Number | Publication Date |
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| CN103552692A CN103552692A (en) | 2014-02-05 |
| CN103552692B true CN103552692B (en) | 2016-01-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310556380.2A Expired - Fee Related CN103552692B (en) | 2013-11-11 | 2013-11-11 | Small flexible wing unmanned plane feedway |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516148B (en) * | 2016-11-10 | 2019-01-11 | 北京华信宇航科技有限公司 | Cartridge type emitter and its bullet support mechanism for vehicle launch |
| CN106643292B (en) * | 2017-01-06 | 2018-11-16 | 南京壹诺为航空科技有限公司 | A kind of small drone load emitter |
| CN107310727B (en) * | 2017-06-27 | 2020-07-28 | 广东军缆信息技术有限公司 | Unmanned aerial vehicle with conflagration first aid function |
| CN107719686A (en) * | 2017-10-10 | 2018-02-23 | 北京航空航天大学 | A kind of unmanned plane emitter |
| CN108132000B (en) * | 2017-12-22 | 2019-08-13 | 北京理工大学 | A kind of Small cartridge and its implementation with deformable flexible empennage |
| CN110065634B (en) * | 2019-04-23 | 2021-05-14 | 北京理工伺服科技有限公司 | Unmanned flying robot based on compressed gas cold-assisted launching |
| CN112078815A (en) * | 2020-10-22 | 2020-12-15 | 广东寻米科技有限公司 | Unmanned aerial vehicle recovery system and working method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201149465Y (en) * | 2007-11-28 | 2008-11-12 | 北京农业职业学院 | Gun barrel type transmitting mechanism for target-practice robot |
| CN102785778A (en) * | 2012-07-17 | 2012-11-21 | 王�华 | Tubular transmitting fire-extinguishing unmanned plane and fire-extinguishing control methods |
| CN203727655U (en) * | 2013-11-11 | 2014-07-23 | 北京理工大学 | Flexible wing unmanned aerial vehicle launching cylinder |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8530809B2 (en) * | 2011-08-03 | 2013-09-10 | Raytheon Company | Ring gear control actuation system for air-breathing rocket motors |
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2013
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201149465Y (en) * | 2007-11-28 | 2008-11-12 | 北京农业职业学院 | Gun barrel type transmitting mechanism for target-practice robot |
| CN102785778A (en) * | 2012-07-17 | 2012-11-21 | 王�华 | Tubular transmitting fire-extinguishing unmanned plane and fire-extinguishing control methods |
| CN203727655U (en) * | 2013-11-11 | 2014-07-23 | 北京理工大学 | Flexible wing unmanned aerial vehicle launching cylinder |
Non-Patent Citations (1)
| Title |
|---|
| 战斧导弹发射系统的发展;张玲翔;《飞航导弹》;19921126(第11期);全文 * |
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| CN103552692A (en) | 2014-02-05 |
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