CN206664921U - Launch the wing synchronous expansion system of unmanned vehicle folding wings - Google Patents
Launch the wing synchronous expansion system of unmanned vehicle folding wings Download PDFInfo
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- CN206664921U CN206664921U CN201720012713.9U CN201720012713U CN206664921U CN 206664921 U CN206664921 U CN 206664921U CN 201720012713 U CN201720012713 U CN 201720012713U CN 206664921 U CN206664921 U CN 206664921U
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Abstract
It the utility model is related to a kind of wing synchronous expansion system for launching unmanned vehicle folding wings, including two sets of wing stretch units and synchromesh gear mechanism；The wing stretch unit of left and right wing makes it be rotated around master gear axis by elastic restoring force caused by compression spring during folded wing, 0~90 degree of the anglec of rotation, to complete the folding and expanding function of wing；Left and right cover plate is connected by the block with auricle with fuselage；The design of synchromesh gear mechanism ensure that the synchronous expansion of left and right wing.In order to mitigate construction weight, flight efficiency is improved, under conditions of structural strength is ensured, unit has done loss of weight processing.The utility model can be reliably achieved being accurately positioned and reliably deploying for the left and right wing of folding wings unmanned vehicle, improve the success rate of unmanned vehicle ejection, and then the reliability of full machine is greatly improved, and with it is reasonable in design, implement easily, cost it is low, folding mode is simple, quick, profile is regular, attractive in appearance after folding, the features such as being easy to carrying.
Description
Technical field
The invention belongs to the folding wings unmanned vehicle designing technique of catapult-assisted take-off, and in particular to one kind ejection unmanned flight
The wing synchronous expansion system of device folding wings.
Background technology
Ejection folds rotor flying robot has many advantages compared with traditional guided missile and large-scale unmanned vehicle.With conventional pilot
Bullet is compared, its small volume, handling strong, is adapted to anti-terrorism, city war.Compared with reconnaissance version unmanned vehicle, it has small-sized
Change, individual soldier can carry, and rapidly enter combat zone, the tactics advantage such as flexibly.Compared with attack unmanned vehicle, it can be accurate
The features such as dispensing bomb, reduces not guilty injures and deaths, reduces war negative effect, has good portability, and cost is low, and disguise is strong.Value
Obtain it is noted that one of key technology of this kind of unmanned vehicle is exactly the synchronous expansion technology of the folding wings in ejection process.
One side folding wings synchronous expansion system connects wing and fuselage, concentrates the load born during flight suffered by wing；On the other hand,
Also to realize storage during wing-folding state, the function such as position locking of rapid deployment and expansion during ejection.
The driving force mode of folding wings.1 spring force formula.The spring force formula unfolded wing deploys by power of elastic force such as springs
Wing.It is characterized in simple in construction, without power set.Dynamic formula is made in 2 combustion gas.Combustion gas is made dynamic formula missile wing development mechanism and deployed with it
Rapidly, power is big, reliability is high in place for expansion.But required device is complicated, it is difficult to which operation is implemented, and security is low.3 motors drive
Formula.Be characterized in easily controllable, precision of expansion is higher, after repacking can active folding wing, its shortcoming is that speed is relatively slow, it is necessary to volume
Outer power input.
Synchronous drive mechanism.The structure of the synchronous drive mechanism of high reliability is mostly more complicated in existing machinery, and into
This is higher, but simple in construction, and the low mechanism of cost often has the synchronously technical problem such as unreliable again.
The content of the invention
Technical problems to be solved
In order to avoid the shortcomings of the prior art, the present invention proposes that a kind of wing for launching unmanned vehicle folding wings is same
Development system is walked, solves above-mentioned contradiction and defect existing for the battlefield demand and prior art under existing situation, there is provided Yi Zhongjie
Structure is simple, inexpensive and high reliability, the folding wings synchronous expansion system suitable for launching unmanned vehicle.
Technical scheme
A kind of wing synchronous expansion system for launching unmanned vehicle folding wings, it is characterised in that stretched including two sets of wings
Unit and synchromesh gear mechanism；The wing stretch unit includes cover plate, compression spring and wing connection unit；Compression spring position
In non-interconnected annular groove between cover plate and wing connection unit, one end of compression spring is fixed on the end of non-interconnected annular groove
On mouth wall, the other end is fixed on the sliding block of cover plate lower end, and the center of cover plate and wing connection unit is provided with through hole；Two sets of wings
Stretch unit is outer using cover plate, and wing connection unit is set for interior layout, and D gears 13 and C gears 12 coaxially pass through two sets of wings
The through hole at stretch unit center, it is connected respectively at two wing connection units；The D gears 13 of the synchromesh gear mechanism and A teeth
The gear external toothing of wheel 1, C gears 12 and the external toothing of B gears 4, lower gear and the external toothing of B gears 4 of A gears 1；The C teeth
The gearratio of wheel 12 and D gears 13 is -1.
The number of teeth of the synchromesh gear mechanism, which is matched somebody with somebody, to be combined into：The gear of A gears 1 is that the lower gear of 18, A gears 1 is 12, B
Gear 4 is that 40, C gears 12 are that 40, D gears 13 are 60.
Cover plate and the wing connection unit is provided with multiple lightening holes.
The auricle of the cover plate is provided with the block 3 that limitation wing connection unit expanded angle is no more than 90 degree.
The connection unit of the left and right wing and the block with auricle use polypropylene plastics.
The cover plate is made of carbon fiber board.
Four gears use aluminium alloy.
Beneficial effect
A kind of wing synchronous expansion system for launching unmanned vehicle folding wings proposed by the present invention, including two sets of wings are stretched
Open up unit and synchromesh gear mechanism；The wing stretch unit of left and right wing passes through caused by compression spring during folded wing
Elastic restoring force makes it be rotated around master gear axis, 0~90 degree of the anglec of rotation, to complete the folding and expanding function of wing；It is left and right
Cover plate is connected by the block with auricle with fuselage；The design of synchromesh gear mechanism ensure that the synchronous expansion of left and right wing.
In order to mitigate construction weight, flight efficiency is improved, under conditions of structural strength is ensured, unit has done loss of weight processing.
The present invention can be reliably achieved being accurately positioned and reliably deploying for the left and right wing of folding wings unmanned vehicle, improve nobody
The success rate of aircraft catapult, and then the reliability of full machine is greatly improved, and with it is reasonable in design, implement easily, cost
Low, folding mode is simple, quick, and profile is regular, attractive in appearance after folding, the features such as being easy to carrying.
Compared with prior art, the present invention have substantive distinguishing features prominent as follows and it is notable the advantages of：1. through reality of taking a flight test
Checking, the present invention effectively increase the launching success rate of the folding wings unmanned vehicle of catapult-assisted take-off, and increase is system-wide can
By property；2. it is simple in construction, it is in light weight, it is easy to maintain；3. reasonable in design, it is easy to implement, and cost is low；4. folding mode is simple, fast
Speed, machine shape is regular, attractive in appearance after folding, is easy to carrying and individual soldier to carry.
Brief description of the drawings
Fig. 1 to Fig. 3 is the overall structure diagram of the present invention；
Fig. 4 is the structural representation of wing connection unit；
Fig. 5 and Fig. 6 is the structural representation for the cover plate that vertical direction fixes wing connection unit；
Fig. 7 is wing connection unit positive stop schematic diagram；
Fig. 8 is the transmission schematic diagram of geared rotor system；
Fig. 9 is the structural representation of gear D；
Figure 10 is that gear shaft fixes plug；
Figure 11 and Figure 12 is the structural representation of system before folding；
1- gear As, 2- upper cover plates, 3- wing connection unit positive stops, 4- gear Bs, 5- fuselage attachment lugs, 6- pressures
Contracting spring A, 7- starboard wing connection unit, 8- steering wheel lines walk hole, 9- lower covers, 10- lightening grooves, 11- port wing connection units,
12- gear Cs, 13- gear Ds, 14- sliding blocks A, 15- gear shaft fix plug, 16- slide block Bs, 17- spring Bs, 18- lightening holes, 19- circles
Pin through hole A, 20- straight pin through hole B, 21- straight pin through hole C, 22- steering wheel line walks hole.
Embodiment
In conjunction with embodiment, accompanying drawing, the invention will be further described：
The synchronous expansion system of the ejection unmanned vehicle folding wings of the present embodiment, including the 1. connection list of left and right wing
Member, it is connected respectively with left and right wing, drives wing to pack up and deploy, in order to mutual during preventing left and right wing from packing up and deploy
Interference, added with pad between unit；2. vertical direction fixes the left and right cover plate of wing connection unit, on the one hand ensure that wing connects
Big displacement and deformation do not occur for the support rigidity of order member, in the vertical direction, on the other hand, two couple that fuselage axial direction Shen goes out
Auricle can be connected with fuselage, and being delivered to fuselage for the aerodynamic loading on wing provides Path of Force Transfer；3. the block with auricle, can
To be affixed to fuselage together with left and right cover plate by auricle, effect is that limitation wing connection unit expanded angle is no more than 90 degree,
It is accurately positioned；4. compression spring, why using compression spring without using torsion spring, being because outside identical material, geometry
Under shape, the stiffness coefficient of stage clip is bigger, and elastic restoring force is bigger.Spring is placed in the conduit of wing connection unit, is being occurred
During deformation, elastic restoring force is transmitted to pass to fuselage, according to the mutual of power by cover plate by the sliding block being connected with left and right cover plate
Action rule, wing complete expansion action under the driving of elastic restoring force；5. synchronous expansion gear train actuation mechanism, due to folding
Folded system is limited by space and construction weight, and the present invention realizes the synchronous backward start of wing using gear train.
The connection unit of left and right wing and block with auricle are made of polypropylene plastics, the density of the material
It is smaller, and moderate strength, it is therefore an objective to reduce construction weight while structural strength is ensured.Above and below fixed wing connection unit
Cover plate is made of carbon fiber board, and the material specific strength is big, and specific stiffness is big, it is ensured that the bonding strength of wing root and support are firm
Degree.In addition, synchronous expansion gear train actuation mechanism is made of aluminium alloy.The machine-shaping of above each unit is all added using machine
Work technique.
In order to mitigate construction weight, flight efficiency is improved, each unit has made loss of weight processing.In guarantee structural strength and outside
While shape is attractive in appearance, lightening hole, lightening grooves etc. are provided with.
Specific embodiment：
As shown in Figure 1 to Figure 3, a kind of synchronous expansion system for launching unmanned vehicle folding wings, including left and right wing
Connection unit (as shown in Figure 4), in the vertical direction fix wing connection unit upper and lower cover plate (as shown in Fig. 5 and Fig. 6),
Synchronous expansion gear train actuation mechanism (as shown in Figure 8) and gear shaft fix plug (as shown in Figure 10).
Left and right wing connection unit main body shown in Fig. 3 is made up of polypropylene material, wherein placing the conduit of compression spring
Size determine that by the size of spring and the size of spring is determined according to the elastic restoring force needed for wing expansion.
The radius of gear shaft through-hole is 8mm, circumferential that straight pin through hole of the radius for 1mm is furnished with every 90 degree, as in Fig. 4 and Fig. 9 19 to
Shown in 21.The design of upper and lower cover plate 2 and 9 is to prevent spring 6 and 17 from departing from conduit in deformation process, influences wing and normally opens up
Open.The design of lightening grooves 10 and lightening hole 18 is to reduce construction weight, improves flight efficiency, and its shape is in order to suitable mostly
Peripheral limit shape is answered, part lightening hole is also cabling, wiring considers.Due to being provided with aileron steering wheel, steering wheel on folded wing
Line walk hole 8 be steering wheel line positioning hole.Circular gasket internal diameter 10mm, external diameter 30mm, be placed on left and right wing connection unit it
Between, reduce the friction in motion process.Vertical direction shown in Fig. 5 and Fig. 6 fixes the upper and lower cover plate of wing connection unit by carbon
Fiberboard is made.Wherein sliding block 14 and 16 is made of carbon fiber board, is connected respectively with upper and lower cover plate, dimension reference conduit
Sectional dimension, it is therefore an objective to make it the flexible motion in conduit.Fuselage attachment lug 5 and wing connection unit positive stop 3 are logical
The screw for crossing φ 2.5 (a diameter of 2.5mm) is connected with fuselage, and its main function is positioning, that is, limits wing connection unit and rotate
No more than 90 degree, it is the straight wing after deploying to ensure wing.
Synchronous expansion gear train actuation mechanism shown in Fig. 8 and Fig. 9 is made up of aluminium alloy.D gears 13 and C gears 12 are same
Axle is connected through the through hole at two sets of wing stretch unit centers respectively at two wing connection units；D gears 13 and A gears 1
Gear external toothing, C gears 12 and the external toothing of B gears 4, lower gear and the external toothing of B gears 4 of A gears 1；The C gears
12 with the gearratios of D gears 13 be -1.Wherein 12 gear Cs and 13 gear Ds are coaxial through left and right wing connection unit and upper and lower
The axis positioning hole of cover plate, at the same it is connected with the connection unit 11 and 7 of left and right wing respectively by φ 2 straight pin, and together
Step rotates backward.The number of teeth of the synchromesh gear mechanism, which is matched somebody with somebody, to be combined into：The gear of A gears 1 is that the lower gear of 18, A gears 1 is
12, B gears 4 are that 40, C gears 12 are that 40, D gears 13 are 60.Designed also for cabling is easy in the steering wheel line hole 22 that walks.
Gear shaft shown in Figure 10 is fixed plug and is made up of polypropylene plastics, is positioned with wing connection unit by type face, while pass through circle
Pin is connected with gear D, limits the axial displacement of gear D.
The course of work of whole system can be divided into two parts：Folding process and expansion process.Operation principle difference is as follows
It is described：
1. folding process：Wing is folded under external force driving, and external force acting is saved as elastic potential energy by compression spring, then
Whole system is put into launching tube, wing is constrained because of type face.
2. deploy process：After ejecting cylinder, spring 6 and 17 produces elastic restoring force because being released wing constraint, leads to
Cross sliding block 14 and 16 to be transmitted to cover plate and then be transmitted to fuselage, at the same time, wing completes expansion action, and the synchronism of expansion is to pass through
What synchronous expansion gear train was realized.As shown in Figure 4 and Figure 6, one end of spring is against in the conduit of starboard wing connection unit, another
End and the shoe contact on cover plate, during restraint release, spring elongation, because cover plate and fuselage are connected, so the connection of starboard wing
Unit and fuselage have relative rotation, because starboard wing connection unit is connected with gear D, therefore gear D concomitant rotation.As shown in figure 8,
Gear D and gear A external toothing, turn to opposite；Gear A and gear B external toothing, turn to opposite, then gear D turns to gear B
It is identical；Gear B and gear C external toothing, turn to opposite, then gear D is turned to C on the contrary, and gear C and port wing connection unit
It is connected, then left and right wing rotation direction is opposite.And the synchronism being driven then makes transmission by reasonably choosing the number of teeth of gear
Than being realized for 1.In summary, the left and right wing of whole system realizes synchronous backward expansion, such as Figure 11 and figure after expansion
Shown in 12.
Claims (7)
1. a kind of wing synchronous expansion system for launching unmanned vehicle folding wings, it is characterised in that single including two sets of wing stretching, extensions
Member and synchromesh gear mechanism；The wing stretch unit includes cover plate, compression spring and wing connection unit；Compression spring is located at
In non-interconnected annular groove between cover plate and wing connection unit, one end of compression spring is fixed on the port of non-interconnected annular groove
On wall, the other end is fixed on the sliding block of cover plate lower end, and the center of cover plate and wing connection unit is provided with through hole；Two sets of wings are stretched
It is outer that unit, which is opened up, using cover plate, and wing connection unit is set for interior layout, and D gears (13) and C gears (12) coaxially pass through two sets of machines
The through hole at wing stretch unit center, it is connected respectively at two wing connection units；The D gears (13) of the synchromesh gear mechanism with
The gear external toothing of A gears (1), C gears (12) and B gears (4) external toothing, the lower gear and B gears (4) of A gears (1) are outside
Engagement；The gearratio of the C gears (12) and D gears (13) is -1.
2. the wing synchronous expansion system of unmanned vehicle folding wings is launched according to claim 1, it is characterised in that：It is described
The number of teeth of synchromesh gear mechanism, which is matched somebody with somebody, to be combined into：The gear of A gears (1) is that the lower gear of 18, A gears (1) is that 12, B gears (4) are
40, C gears (12) are that 40, D gears (13) are 60.
3. the wing synchronous expansion system of unmanned vehicle folding wings is launched according to claim 1, it is characterised in that：It is described
Cover plate and wing connection unit are provided with multiple lightening holes.
4. the wing synchronous expansion system of unmanned vehicle folding wings is launched according to claim 1, it is characterised in that：It is described
The auricle of cover plate is provided with the block (3) that limitation wing connection unit expanded angle is no more than 90 degree.
5. the wing synchronous expansion system of unmanned vehicle folding wings is launched according to claim 1, it is characterised in that：It is described
The connection unit of left and right wing and block with auricle use polypropylene plastics.
6. the wing synchronous expansion system of unmanned vehicle folding wings is launched according to claim 1, it is characterised in that：It is described
Cover plate is made of carbon fiber board.
7. the wing synchronous expansion system of unmanned vehicle folding wings is launched according to claim 1, it is characterised in that：It is described
Four gears use aluminium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720012713.9U CN206664921U (en) | 2017-01-06 | 2017-01-06 | Launch the wing synchronous expansion system of unmanned vehicle folding wings |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720012713.9U CN206664921U (en) | 2017-01-06 | 2017-01-06 | Launch the wing synchronous expansion system of unmanned vehicle folding wings |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631686A (en) * | 2018-12-11 | 2019-04-16 | 彩虹无人机科技有限公司 | A kind of scout missile folding wing mechanism |
| US11644287B2 (en) | 2019-06-13 | 2023-05-09 | Raytheon Company | Single-actuator rotational deployment mechanism for multiple objects |
-
2017
- 2017-01-06 CN CN201720012713.9U patent/CN206664921U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109631686A (en) * | 2018-12-11 | 2019-04-16 | 彩虹无人机科技有限公司 | A kind of scout missile folding wing mechanism |
| US11644287B2 (en) | 2019-06-13 | 2023-05-09 | Raytheon Company | Single-actuator rotational deployment mechanism for multiple objects |
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