CN205675213U - A kind of multi-rotor aerocraft time delay, synergy, save external member from damage - Google Patents
A kind of multi-rotor aerocraft time delay, synergy, save external member from damage Download PDFInfo
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- CN205675213U CN205675213U CN201620578354.9U CN201620578354U CN205675213U CN 205675213 U CN205675213 U CN 205675213U CN 201620578354 U CN201620578354 U CN 201620578354U CN 205675213 U CN205675213 U CN 205675213U
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- rotor aerocraft
- air bag
- floatage air
- external member
- synergy
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Abstract
The utility model relates to unmanned air vehicle technique field, is specifically related to a kind of multi-rotor aerocraft time delay, synergy, saves external member from damage.This external member includes: floatage air bag (1), connection hitch (2) and multi-rotor aerocraft；Wherein, the centrally disposed vacancy section of floatage air bag (1), connects hitch (2) and is arranged on the vacancy section of floatage air bag (1), and floatage air bag (1) is connected to multi-rotor aerocraft；The relative multi-rotor aerocraft axle rotary limited centered on X-axis, Y-axis respectively of floatage air bag (1), the orthogonality of center shaft of the central shaft of X-axis limit hinge (24) and Y-axis limit hinge (25)；The outer surface of floatage air bag (1) is provided with more than one charge valve (4).The utility model can extend the flight time of multi-rotor aerocraft, improves payload, and plays a protective role multi-rotor aerocraft itself and the public.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, in particular to a kind of multi-rotor aerocraft time delay, synergy,
Save external member from damage.
Background technology
Multi-rotor aerocraft is a class multipurpose vertically taking off and landing flyer.Compared with tradition single-rotor helicopter, many rotors
Aircraft do not have complexity pitch-changing mechanism, maintenance simplicity, easy to use efficiently.At present, the application of multi-rotor aerocraft is
Through cover agriculture, woods, herd, fishing, industry, building, scientific research, traffic, multiple industry such as amusement.Aeroplane photography, medical treatment can be performed
The task such as rescue, meteorological detection, aerial inspection, aerial seeding aerial sowing, aerial fertilising, plays very important work in national economy
With.
Multi-rotor aerocraft is frequently with driven by power, by the low restriction of energy content of battery storage density, its flight time
The active demand that social development is applied to can not be met far away with voyage.In the last few years, existing Some Enterprises was by fuel cell
Apply on multi-rotor aerocraft so that it is the flight time is risen to about one by use conventional lithium-ion battery about 20 minutes
About individual hour.But fuel cell technology is still immature, use cost is high, on consumer level multi-rotor aerocraft temporarily without
Method large-scale promotion.How on the basis of existing technology, in the case of not changing original power set, low cost is significantly
Extending the flight time of multi-rotor aerocraft, increasing payload becomes one extremely urgent demand of the art.
The security of aircraft platforms and job stabilization are also to pay special attention in current multi-rotor aerocraft technical field
Problem.Multi-rotor aerocraft uses multiple rotor High Rotation Speed to produce lift and control power, once breaks down, High Rotation Speed
Rotor blade and the fuselage of high-speed motion can be to periphery object with self cause serious harm.Have the notably entail dangers to public's
The security of the lives and property.In this technical field, engineers is made that certain effort, have employed rotor redundancy, failure compensation etc.
Control method.But, the fuselage of the rotor blade and high-speed motion that can not solve High Rotation Speed on physical layer carries dynamic
Energy parts are to periphery object and the harm self causing.Some multi-rotor aerocrafts are equipped with the machine such as crash-proof bracket and parachute
Structure, can reduce to periphery object and the injury of self to a certain extent when aircraft loses efficacy, but both the above mechanism reliability
Not high, and multi-rotor aerocraft payload can be reduced.
Utility model content
The purpose of this utility model is to provide a kind of multi-rotor aerocraft time delay, synergy, saves external member from damage, can extend many
The flight time of rotor craft, improve payload, and multi-rotor aerocraft itself and the public are played a protective role.
The utility model embodiment provides a kind of multi-rotor aerocraft time delay, synergy, saves external member from damage, comprising: buoyancy gas
Capsule, connection hitch and multi-rotor aerocraft；Wherein, the centrally disposed vacancy section of described floatage air bag, described connection is hung
Mechanism is arranged on the vacancy section of described floatage air bag, and described floatage air bag is connected to multi-rotor aerocraft；Described buoyancy gas
The relatively described multi-rotor aerocraft of capsule axle rotary limited centered on X-axis, Y-axis respectively, the central shaft of described X-axis limit hinge with
The orthogonality of center shaft of described Y-axis limit hinge；The outer surface of described floatage air bag is provided with more than one charge valve.
In certain embodiments, being preferably, the described suspension framework that connects includes: rigidly connected with multi-rotor aerocraft many
Rotor craft connects support, and floatage air bag rigidly connected with described floatage air bag is connected ring, and is connected to described many rotations
Rotor aircraft connects the intermediate connecting ring that support is connected between ring with described floatage air bag；The connection of described multi-rotor aerocraft
Frame, described floatage air bag connect ring and described intermediate connecting ring three for concentric ring-type setting.Described multi-rotor aerocraft
Connect and be connected by two coaxial X-axis limit hinges between support and described intermediate connecting ring；Described intermediate connecting ring and institute
State floatage air bag connection ring to be connected by two coaxial Y-axis limit hinges that have；The central shaft of described X-axis limit hinge and institute
State the orthogonality of center shaft of Y-axis limit hinge.Described floatage air bag after exhaust and described connection hitch are folded state.Institute
State the airbag structure that floatage air bag is circular ring.Described floatage air bag is made up of one or more chambers.Adjacent two institutes
State and on the connection air flue between chamber, air pressure double-beat drop valve is set.Each described chamber is provided with a most described charge valve.
The utility model embodiment provide a kind of multi-rotor aerocraft time delay, synergy, save external member from damage, with prior art phase
Ratio, multi-rotor aerocraft connects floatage air bag, and in using, floatage air bag is internal is full of the gas being lighter than air, can be many rotors
Aircraft provides extra lift, extends the flight time of multi-rotor aerocraft, improves the flight load of multi-rotor aerocraft.And
Floatage air bag has cushioning effect, can reduce collision when accident to rotor craft self loss and the wound to personnel
Evil.Charge valve is for floatage air bag inflation and exhaust, also allowing for depositing and carrying when not using.
Brief description
Fig. 1 is multi-rotor aerocraft time delay, synergy, the structural representation saving external member from damage in one embodiment of the utility model
Figure；
Fig. 2 is the structural representation connecting hitch in the utility model Fig. 1；
Fig. 3 is the structural representation of air pressure double-beat drop valve in the utility model Fig. 1；
Fig. 4 is the appearance schematic diagram of air pressure double-beat drop valve in the utility model Fig. 1.
Note: the 1st, floatage air bag；2nd, hitch is connected；3rd, air pressure double-beat drop valve；4th, charge valve, the 5th, air accumulator；10th, chamber；
21st, multi-rotor aerocraft connects support；22nd, intermediate connecting ring；23rd, floatage air bag connects ring；24th, X-axis limit hinge；25th, Y-axis
Limit hinge；26th, X-axis；27th, Y-axis；31st, valve body；32nd, piston sheet；33rd, spring；34th, valve
Detailed description of the invention
Combine accompanying drawing below by specific embodiment to be described in further detail the utility model.
The utility model provides a kind of multi-rotor aerocraft time delay, synergy, saves external member from damage, as shown in Figure 1, comprising: floating
The 1st, strength capsule connects hitch 2 and multi-rotor aerocraft；Wherein, the centrally disposed vacancy section of floatage air bag 1, connects suspension machine
Structure 2 is arranged on the vacancy section of floatage air bag 1, and is connected to floatage air bag 1 on multi-rotor aerocraft.Floatage air bag 1 and many rotations
The association of rotor aircraft is referred to as associating aircraft.Floatage air bag 1 is internal is full of the gas being lighter than air, is multi-rotor aerocraft
Extra lift is provided.Floatage air bag 1 provides different magnitude of buoyancy according to the difference of appearance and size, but maximum buoyancy is less than many
The flight full weight of rotor craft.Due to the lift-rising effect of buoyancy, in the case that multi-rotor aerocraft carries same load, required
Power output can reduce accordingly.In the case of not changing original dynamical system and deposit gross energy, multi-rotor aerocraft will
Obtain longer flight time and voyage.Under similarity condition, in the case of exporting original power, effective load of associating aircraft
Lotus can increase accordingly.Floatage air bag 1 also has the effect of buffering energy-absorbing.When multi-rotor aerocraft occurs unexpected, floatage air bag 1
Multi-rotor aerocraft itself can be protected, significantly reduce the infringement to fuselage and equipment for the intense impact.Meanwhile, buoyancy gas
The security of the lives and property of the public is also played the guarantee of essence by the buffering energy-absorbing function of capsule 1.For beginner, protect work(
Can be most important, air crash risk can be reduced greatly, it is to avoid bigger damage.
Connect the bindiny mechanism that hitch 2 is multi-rotor aerocraft and floatage air bag 1.As in figure 2 it is shown, this mechanism will float
The buoyancy that strength capsule 1 produces passes to multi-rotor aerocraft.Connect hitch 2 to be made up of three concentric circular ring structures.?
Internal layer is that multi-rotor aerocraft connects support 21, and intermediate layer is intermediate connecting ring 22, and outermost layer is that floatage air bag connects ring 23.Many
Rotor craft connects support 21 and is rigidly connected with multi-rotor aerocraft.Floatage air bag connects ring 23 and connects with floatage air bag 1 rigidity
Connect.Multi-rotor aerocraft is connected support 21 and is connected by two coaxial X-axis limit hinges 24 with intermediate connecting ring 22, and above two
Ring can relatively rotate in certain angle around X-axis 26.It is coaxial by two that intermediate connecting ring 22 is connected ring 23 with floatage air bag
Y-axis limit hinge 25 connect, above two rings can relatively rotate in certain angle around Y-axis 27.X-axis limit hinge 24 center
Axle and Y-axis limit hinge 25 orthogonality of center shaft.Connection hitch 2 is used to connect multi-rotor aerocraft and floatage air bag 1, so that it may
To realize the limited change of multi-rotor aerocraft and floatage air bag 1 relative attitude, such as with X-axis as rotary shaft, or with Y-axis for rotation
Relatively rotating of rotating shaft.
The relative multi-rotor aerocraft of floatage air bag 1 axle rotary limited centered on X-axis the 26th, Y-axis 27 respectively, and X-axis is spacing
The central shaft of hinge 24 and the orthogonality of center shaft of Y-axis limit hinge 25, connect ring 23 and floatage air bag 1 by changing floatage air bag
Between link position, it is possible to realize to relative position between floatage air bag 1 buoyancy point and multi-rotor aerocraft center of gravity
Regulation.Connect hitch 2 and keep the center of gravity of the buoyancy point of floatage air bag 1 close to multi-rotor aerocraft.Connect and hang
Mechanism 2 allows multi-rotor aerocraft to change relative attitude within the specific limits, in the case of not change of flight control method, and fall
The energy that low control associating aircraft is paid.
Being provided with charge valve 4 on the outer surface of floatage air bag 1, user uses air accumulator 5 will be lighter than the gas (ratio of air
As: hydrogen, helium etc.) poured in floatage air bag 1 by charge valve 4, make floatage air bag 1 expand acquisition buoyancy.Work as use
When finishing, user can open charge valve 4 and discharge gas.Empty flat floatage air bag 1 and connection hitch 2 can fold,
Easy to carry and transport, it is easy to support the use with multi-rotor aerocraft.
In order to reduce the resistance to it for the air under floatage air bag 1 floating state, in the present embodiment floatage air bag 1 is arranged
For circular airbag structure.
As it is shown in figure 1, floatage air bag 1 is made up of one or more chambers 10, connection is set between adjacent two chambers 10
Air flue, connection air flue arranges air pressure double-beat drop valve 3, and air pressure double-beat drop valve 3 is internal multiple chamber 10 air pressure of neutral buoyancy air bag 1
Adjusting means, with the lift-launch improving the reliability of floatage air bag 1 and adapt to various different many rotors.As shown in Figure 3,4, air pressure
Balanced valve 3 is made up of the spring 33 of valve body the 31st, piston sheet 32 and two supporting piston pieces 32.Piston sheet 32 passes through two springs
33 are connected with valve body 31, can move left and right, thus open or close valve 34 in valve body 31 inner chamber.When by valve body 31
When air velocity is unhappy, piston sheet 32 is in the centre position of valve body 31 inner chamber under the support of two compression springs 33, now
The gas of the left and right sides is connected, and both sides air pressure is basically identical.When gas flow rate is very fast, aerodynamic force makes piston sheet 32 to side
Motion, and then close valve 34.
In using air pressure double-beat drop valve 3 to connect floatage air bag 1 during adjacent two chambers 10, if air pressure double-beat drop valve 3 connection
Two chambers 10 are intact, and air pressure double-beat drop valve 3 Neng Shiliang side cavity 10 connects, and plays equilibrium air pressure effect；If one of them chamber
There is breakage in room 10, air pressure declines rapidly, has high velocity air and passes through air pressure double-beat drop valve 3, compression spring under Aerodynamic force action
33 make valve 34 close.The intact side cavity 10 of air pressure double-beat drop valve 3 self-closed, plays a protective role, can be greatly improved floating
The reliability of strength capsule 1.The shape of chamber 10 is specifically arranged according to the structure of the multi-rotor aerocraft being connected.
The seriation repacking external member design of different size and outward appearance is provided, can adapt to different users ' individualized requirement,
Meet variation job task and multiple meteorological condition uses and requires.
These are only preferred embodiment of the present utility model, be not limited to the utility model, for this area
Technical staff for, the utility model can have various modifications and variations.It is all within spirit of the present utility model and principle,
Any modification, equivalent substitution and improvement etc. made, should be included within protection domain of the present utility model.
Claims (8)
1. a multi-rotor aerocraft time delay, synergy, save external member from damage, it is characterised in that include: floatage air bag (1), connect and hang
Mechanism (2) and multi-rotor aerocraft；Wherein, the centrally disposed vacancy section of described floatage air bag (1), described connection hitch
(2) it is arranged on the vacancy section of described floatage air bag (1), and described floatage air bag (1) is connected to multi-rotor aerocraft；Described floating
The relatively described multi-rotor aerocraft of strength capsule (1) axle rotary limited centered on X-axis, Y-axis respectively, described X-axis limit hinge
(24) central shaft and the orthogonality of center shaft of described Y-axis limit hinge (25)；The outer surface of described floatage air bag (1) is provided with one
Individual above charge valve (4).
2. as claimed in claim 1 multi-rotor aerocraft time delay, synergy, save external member from damage, it is characterised in that described connection is hung
Mechanism (2) includes: multi-rotor aerocraft rigidly connected with multi-rotor aerocraft is connected support (21), with described floatage air bag
(1) rigidly connected floatage air bag connect ring (23), and be connected to described multi-rotor aerocraft connect support (21) with described
Floatage air bag (1) connects the intermediate connecting ring (22) between ring；Described multi-rotor aerocraft connects support (21), described buoyancy gas
Capsule connects ring (23) and described intermediate connecting ring (22) three for concentric ring-type setting.
3. as claimed in claim 2 multi-rotor aerocraft time delay, synergy, save external member from damage, it is characterised in that described many rotors fly
Row device is connected and is connected by two coaxial X-axis limit hinges (24) between support (21) and described intermediate connecting ring (22)；Institute
State intermediate connecting ring (22) and be connected ring (23) with described floatage air bag by two coaxial Y-axis limit hinges (25) connections；Institute
State the central shaft of X-axis limit hinge (24) and the orthogonality of center shaft of described Y-axis limit hinge (25).
4. as claimed in claim 1 multi-rotor aerocraft time delay, synergy, save external member from damage, it is characterised in that described after exhaust
Floatage air bag (1) and described connection hitch (2) are in folded state.
5. as claimed in claim 1 multi-rotor aerocraft time delay, synergy, save external member from damage, it is characterised in that described floatage air bag
(1) it is circular airbag structure.
6. the multi-rotor aerocraft time delay as described in any one of claim 1-5, synergy, save external member from damage, it is characterised in that described
Floatage air bag (1) is made up of one or more chambers (10).
7. as claimed in claim 6 multi-rotor aerocraft time delay, synergy, save external member from damage, it is characterised in that described in adjacent two
Air pressure double-beat drop valve (3) is set on the connection air flue between chamber.
8. as claimed in claim 6 multi-rotor aerocraft time delay, synergy, save external member from damage, it is characterised in that each described chamber
(10) it is provided with a most described charge valve (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620578354.9U CN205675213U (en) | 2016-06-13 | 2016-06-13 | A kind of multi-rotor aerocraft time delay, synergy, save external member from damage |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620578354.9U CN205675213U (en) | 2016-06-13 | 2016-06-13 | A kind of multi-rotor aerocraft time delay, synergy, save external member from damage |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105966592A (en) * | 2016-06-13 | 2016-09-28 | 北京瀚科瑞杰科技发展有限公司 | Delay, efficiency-increasing and protection kit of multi-rotor aircraft |
-
2016
- 2016-06-13 CN CN201620578354.9U patent/CN205675213U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105966592A (en) * | 2016-06-13 | 2016-09-28 | 北京瀚科瑞杰科技发展有限公司 | Delay, efficiency-increasing and protection kit of multi-rotor aircraft |
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