CN103552692A - Launching device for small-sized flexible-wing unmanned plane - Google Patents
Launching device for small-sized flexible-wing unmanned plane Download PDFInfo
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- CN103552692A CN103552692A CN201310556380.2A CN201310556380A CN103552692A CN 103552692 A CN103552692 A CN 103552692A CN 201310556380 A CN201310556380 A CN 201310556380A CN 103552692 A CN103552692 A CN 103552692A
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- closing appliance
- push pedal
- canister launcher
- breech block
- trigger
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Abstract
The invention discloses a barrel type launching device capable of realizing launching of a small-sized flexible-wing unmanned plane. The plane can be emitted out of a barrel by taking elastic potential energy of elastic elements which are symmetrically distributed in a central symmetry manner about the center of a cross section of the launching barrel as a power source. In a non-launching state, the plane is constrained in the barrel by a locking mechanism; in a launching state, the plane can be kept in a correct posture under the action of a launching guide rail and an orientation button. The locking device is controlled by a person to determine whether the plane is launched.
Description
Affiliated technical field
The present invention relates to a kind of feedway of small flexible wing unmanned plane, the cartridge type ejection firing device that the elastic potential energy of material of especially take 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 that can search 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 adopting is to utilize gunpowder to produce q.s high temperature and high pressure gas at canister launcher base burning, promotes unmanned plane go out cylinder as propulsion source, completes emission process.The shortcoming of this launch mode is canister launcher material and canister launcher inner wall surface roughness to have relatively high expectations, and 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 comprised 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 comprised 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 canister launcher axis direction, are connected on each contact surface with canister launcher with flathead screw; Three spacing pipes are connected with flathead screw with bulkhead through the corresponding groove on each bulkhead respectively with three groups of push pedal slideways on each contact surface; The long limit of the axis of spacing pipe, push pedal slideway is parallel with canister launcher axis; On canister launcher for the sideline, long limit of the groove of push pedal campaign and fixing after sideline, the long limit of push pedal slideway overlap respectively; The support lower end of fixed pulley assembly is helicitic texture, be used for being fixed on first bulkhead from canister launcher nozzle, every group of fixing direction of fixed pulley assembly should make this group elastic element along corresponding spacing pipe axis and push pedal slideway axis, to move simultaneously.
2, three groups of elastic elements adopt identical method to fix, and every group of elastic element one end is fixed in spacing pipe, and the other end is walked around fixed pulley, are fixed on blade face on the face of canister launcher nozzle and canister launcher transverse cross-section parallel; Three groups of elastic elements are about the distribution that is centrosymmetric of canister launcher cross-section center, and push pedal is done 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 is connected with closing appliance screened housing with canister launcher with the inner square groove that all has the locking interaction energy of closing appliance is 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 can freely 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, between trigger and trigger slide rail, forms moving sets, and trigger all the time can only be along the translation of trigger slide rail.
When 4, the present invention launches, the rear directed button of flex-wing aircraft snaps in closing appliance, pulls trigger, makes the constraint of the directed button disengaging Breech block of aircraft, and aircraft will move to nozzle together with push pedal under the effect of elastic element elastic force, thereby realize emission process.
Beneficial effect
The invention has the beneficial effects as follows: the invention provides a kind of flex-wing unmanned plane canister launcher, the most of assembly of canister launcher all can be used 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, reduced the cost of manufacture of canister launcher, there is no the ablation of high-temperature gas, canister launcher and assembly thereof can Reusabilities, increased the service life of canister launcher.By changing the elastic element of different stiffness factors, can realize the transmitting under multiple load-up condition.
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 that removes 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
The specific embodiment:
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 is walked around pulley, is fixed on push pedal (7) upper, and three groups of elastic elements are about canister launcher (1) the cross-section center layout that is centrosymmetric;
According to 1,2, as shown in Figure 2, Figure 3, Figure 4, canister launcher nozzle is towards paper lower-left, 105 centimetres of canister launcher (1) overall lengths, are wherein positioned at long 10 centimetres of the front part of first bulkhead (2), are positioned at long 5 centimetres of last bulkhead (2) part afterwards, distance between intermediate-frame (2) is calculated successively and is respectively 20 centimetres to cylinder tail by nozzle, 20 centimetres, 20 centimetres, 30 centimetres; Bulkhead is faced as shown in Figure 5.
Canister launcher (1) is connected with bulkhead (2) successively, between bulkhead, by two kinds of stringers (3), is connected in turn, and 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 is walked around pulley, is fixed on push pedal (7) above, and three groups of elastic elements are evenly arranged along transmitting inner core (1) axis.Push pedal (7) only can be made motion of translation in push pedal slideway (8);
According to 3, as Fig. 6, shown in Fig. 7, spring (10), Breech block (11), Breech block rotating shaft (16) are all arranged in closing appliance screened housing (17).Closing appliance screened housing (17) is connected with stringer (3) and the canister launcher (1) at this place, and canister launcher (1) connects with the inner square groove that has at closing appliance screened housing, 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 producing is greater than the pulling force of elastic element (5), guarantee 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, the rear directed button (15) on aircraft will depart from locking, and aircraft is launched cylinder.
Fig. 8, Fig. 9, Figure 10 are for auxiliary clear and definite feedway inner structure and annexation.
The above, be preferred embodiment of the present invention, should not be confined to the disclosed content of the present embodiment and accompanying drawing.Everyly do not depart from the equivalence completing under spirit disclosed in this invention or revise, all falling into the scope of protection of the invention.
Claims (2)
1. a small flexible wing aircraft feedway; by 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, closing appliance screened housings, formed; closing appliance is comprised 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 canister launcher axis direction, are connected on each contact surface with canister launcher with flathead screw; Three spacing pipes are connected with flathead screw with bulkhead through the corresponding groove on each bulkhead respectively with three groups of push pedal slideways on each contact surface; The long limit of the axis of spacing pipe, push pedal slideway is parallel with canister launcher axis; On canister launcher for the sideline, long limit of the groove of push pedal campaign and fixing after sideline, the long limit of push pedal slideway overlap respectively; The support lower end of fixed pulley assembly is helicitic texture, be used for being fixed on first bulkhead from canister launcher nozzle, every group of fixing direction of fixed pulley assembly should make this group elastic element along corresponding spacing pipe axis and push pedal slideway axis, to move simultaneously;
Three groups of elastic elements adopt identical method to fix, and every group of elastic element one end is fixed in spacing pipe, and the other end is walked around fixed pulley, are fixed on blade face on the face of canister launcher nozzle and canister launcher transverse cross-section parallel; Three groups of elastic elements are about the distribution that is centrosymmetric of canister launcher cross-section center, and push pedal is done 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 is connected with closing appliance screened housing with canister launcher with the inner square groove that all has the locking interaction energy of closing appliance is 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 can freely 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, between trigger and trigger slide rail, forms moving sets, and trigger all the time can only be along the translation of trigger slide rail.
2. the small flexible wing aircraft feedway as described in right 1, 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, the rear directed button of flex-wing aircraft snaps in closing appliance, pull trigger, make the constraint of the directed button disengaging Breech block of aircraft, aircraft will move to nozzle together with push pedal under the effect of elastic element elastic force, thereby realize 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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| CN103552692A true CN103552692A (en) | 2014-02-05 |
| CN103552692B CN103552692B (en) | 2016-01-06 |
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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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516148A (en) * | 2016-11-10 | 2017-03-22 | 北京华信宇航科技有限公司 | Tubular launching device for aircraft launching and missile support mechanism of tubular launching device |
| CN106643292A (en) * | 2017-01-06 | 2017-05-10 | 南京壹诺为航空科技有限公司 | Small unmanned aerial vehicle load launching device |
| CN107310727A (en) * | 2017-06-27 | 2017-11-03 | 深圳市雷凌广通技术研发有限公司 | A kind of unmanned plane with fire emergency function |
| CN107719686A (en) * | 2017-10-10 | 2018-02-23 | 北京航空航天大学 | A kind of unmanned plane emitter |
| CN108132000A (en) * | 2017-12-22 | 2018-06-08 | 北京理工大学 | A kind of Small cartridge and its implementation with deformable flexible empennage |
| CN110065634A (en) * | 2019-04-23 | 2019-07-30 | 北京理工伺服科技有限公司 | Unmanned flight robot based on the cold power-assisted transmitting of compressed gas |
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| 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 |
| US20130032659A1 (en) * | 2011-08-03 | 2013-02-07 | Raytheon Company | Ring gear control actuation system for air-breathing rocket motors |
| CN203727655U (en) * | 2013-11-11 | 2014-07-23 | 北京理工大学 | Flexible wing unmanned aerial vehicle launching cylinder |
-
2013
- 2013-11-11 CN CN201310556380.2A patent/CN103552692B/en not_active Expired - Fee Related
Patent Citations (4)
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| 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 |
| US20130032659A1 (en) * | 2011-08-03 | 2013-02-07 | Raytheon Company | Ring gear control actuation system for air-breathing rocket motors |
| CN102785778A (en) * | 2012-07-17 | 2012-11-21 | 王�华 | Tubular transmitting fire-extinguishing unmanned plane and fire-extinguishing control methods |
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Non-Patent Citations (1)
| Title |
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| 张玲翔: "战斧导弹发射系统的发展", 《飞航导弹》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106516148A (en) * | 2016-11-10 | 2017-03-22 | 北京华信宇航科技有限公司 | Tubular launching device for aircraft launching and missile support mechanism of tubular launching device |
| 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 |
| CN106643292A (en) * | 2017-01-06 | 2017-05-10 | 南京壹诺为航空科技有限公司 | Small unmanned aerial vehicle load launching device |
| 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 |
| CN107310727A (en) * | 2017-06-27 | 2017-11-03 | 深圳市雷凌广通技术研发有限公司 | A kind of unmanned plane with fire emergency function |
| 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 |
| CN108132000A (en) * | 2017-12-22 | 2018-06-08 | 北京理工大学 | A kind of Small cartridge and its implementation with deformable flexible empennage |
| 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 |
| CN110065634A (en) * | 2019-04-23 | 2019-07-30 | 北京理工伺服科技有限公司 | Unmanned flight robot based on the cold power-assisted transmitting of compressed gas |
| 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 |
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| CN103552692B (en) | 2016-01-06 |
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Granted publication date: 20160106 Termination date: 20201111 |