CN209126964U - Hidden autonomous flight miniature drone - Google Patents
Hidden autonomous flight miniature drone Download PDFInfo
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- CN209126964U CN209126964U CN201821430959.9U CN201821430959U CN209126964U CN 209126964 U CN209126964 U CN 209126964U CN 201821430959 U CN201821430959 U CN 201821430959U CN 209126964 U CN209126964 U CN 209126964U
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Abstract
The utility model provides a kind of hidden autonomous flight miniature drone, comprising: wing, electronic building brick, fuselage, rudder face, empennage, steering engine, connecting rod and battery；Wing is made of pcb board；Electronic building brick is welded on wing lower surface, and electronic building brick is evenly distributed on wing central axis two sides；Fuselage is located on electronic building brick, and is connect with wing lower surface；Rudder face is connected with wing tail portion；Empennage is connected with the tail portion of upper surface of the airfoil；Steering engine is embedded at the mounting hole that fuselage two sides are reserved；Connecting rod first end is connect with steering engine, and connecting rod second end is connect with rudder face；Battery is arranged in fuselage interior.The utility model is not provided with power device and is launched using high-altitude, and the design of autonomous gliding flight allows unmanned plane to work the longer time, increases the serious forgiveness of task execution；Simultaneously because the advantage of material and size, can also keep preferable concealment, substantially increase practical value and tactical value.
Description
Technical field
The utility model relates to unmanned plane field more particularly to a kind of hidden autonomous flight miniature drone.
Background technique
The world today, unmanned plane play the role of can not be substituted in military and civil field.Wherein, miniature drone by
In good concealment and practicability, there are immeasurable potentiality on military value.
Miniature drone is due to its small size (general wingspan length is less than 30 centimetres), (run-of-the-mill the characteristics of lightweight
Less than 200 grams), there is harsh requirement in the selection of energy power system and electronic component.The energy of miniature drone is dynamic
Force system carries out active flight, current miniature drone drive flight time one frequently with the mode of battery driving propeller
As be below 30 minutes, speed is lower than 20m/s and can not having long-distance flight ability.It necessarily requires operator when emitting
It carries assembly and comes to the completion operation of target location near zone personally.Meanwhile frequently with the methods of die sinking manufacture fuselage in manufacture
And wing, manufacturing process is relatively complicated, and costly, and electronic component needs to be manually installed into fuselage interior price, this is caused
The difficulty that miniature drone mass quickly produces.Since weight demands of the miniature drone for load are also more stringent,
If load is heavier, lead to not fly it will cause aircraft takeoff weight is excessive.
Although current miniature drone has immeasurable military and civilian potentiality, from current technology angle
See, it is more difficult that it in the existing stage is put to application, be mainly reflected in: (1) battery power it is limited cause flight endurance short and
Voyage is short；(2) dynamical system consumption mass energy leads to the limited energy for distributing to mission payload, mission payload operating time compared with
It is short；(3) to lightweight, this requirement is extremely harsh, and the mission payload that can meet weight demands is limited；(4) low-speed operations cause
Flight control difficulty is big under complicated wind field environment；(5) cores such as production processing is relatively complicated, and machining accuracy is low, and fabrication cycle is long
Problem need technical staff and further captures.
Utility model content
(1) technical problems to be solved
The utility model provides a kind of hidden autonomous flight miniature drone, set forth above at least partly to solve
The technical issues of.
(2) technical solution
One aspect according to the present utility model, provide a kind of hidden autonomous flight miniature drone include: wing,
Electronic building brick, fuselage, rudder face, empennage, steering engine, connecting rod and battery；Wing is made of pcb board；Electronic building brick welds under the wings of an airplane
On surface, and electronic building brick is evenly distributed on wing central axis two sides；Fuselage is located on electronic building brick, and with wing following table
Face connection；Rudder face is connected with wing tail portion, is made of pcb board；Empennage is connected with the tail portion of upper surface of the airfoil, is made of pcb board；
Steering engine is embedded at the mounting hole that fuselage two sides are reserved；Connecting rod first end is connect with steering engine, and connecting rod second end is connect with rudder face；Electricity
Pond is arranged in fuselage interior, and close to the position of above-mentioned fuselage head.
In some embodiments, further includes: rudder foot and rocker arm；Rudder foot is arranged in the lower surface of rudder face, connecting rod second end with
Rudder face is connected by rudder foot；Rocker arm is arranged on steering engine side wall, and rocker arm is connect with connecting rod first end.
In some embodiments, further includes: clump weight and clump weight connecting rod；Clump weight connecting rod first end and clump weight
Connection, clump weight connecting rod second end are connect with fuselage head and wing head.
In some embodiments, further includes: multiple lightening holes and loss of weight rectangular channel, the setting of multiple lightening holes wing and/
Or on empennage, multiple lightening holes are evenly distributed on the aerofoil of wing and/or empennage, and each lightening hole is in wing and/or empennage
Aerofoil two sides be pasted with film；Loss of weight rectangular channel is arranged on wing, in the central axis and wing of loss of weight rectangular channel
Mandrel line is overlapped, and loss of weight rectangular channel is set to the middle and back of wing.
In some embodiments, electronic building brick includes: power module, interface module, boost module, antenna, GPS receiver
And main control chip；Power module is electronic components power supply；Interface module be provided with steering engine, battery and loading device for electrical connection
Mouthful；Boost module provides stable operating voltage for loading device；Antenna is connected with communication module, to the ground receiving station or balloon borne
Pass the flying quality of unmanned plane itself and the mission payload data of loading device acquisition back in base station；GPS receiver is micro-unmanned
Flight control program built in machine provides location information；Flight built in main control chip operation miniature drone controls program, with
Control the flight of miniature drone.
In some embodiments, loading device includes: camera, is embedded at the mounting hole that fuselage head is reserved.
In some embodiments, antenna fits in afterbody；GPS receiver is welded in unmanned chain-drive section.
In some embodiments, further includes: survey appearance module, be welded on the positive central axis of fuselage, be micro-unmanned
Flight control program built in machine provides posture information.
In some embodiments, miniature drone 20km height from super-pressure balloon carry out high-altitude across it is intercontinental projection or
Any height of 0~30km carries out short range projection from sounding ball.
In some embodiments, the shape of wing is the graceful aerofoil profile of anti-Zimmer；Afterbody is in hill-like structure.
(3) beneficial effect
It can be seen from the above technical proposal that the utility model hidden autonomous flight miniature drone at least have it is following
One of beneficial effect or in which a part:
(1) the utility model is not provided with power device, using the design of autonomous gliding flight, with the miniature nothing of traditional drive
Man-machine consume a large amount of electric power energies is compared in dynamical system, now by most of energy resource supply mission payload, makes unmanned plane can be with
It works the longer time, increases the serious forgiveness of task execution.
(2) emitted by the way of 20km high-altitude projection, miniature drone can be made to quickly enter equilibrium glide state, simultaneously
It is compared with traditional miniature drone, flying distance and flight time is significantly greatly increased, meanwhile, behaviour can be removed from using aerostat dispensing
Control personnel carrying equipment comes to target location personally and operates this drawback, and practical value and tactical value is greatly improved.
(3) remove power device, save the overall weight of unmanned plane, so as to divide the weight of script power device
Dispensing load allows unmanned plane to carry a greater variety of load, promotes unmanned plane lifting capacity.
(4) electronic building brick is evenly distributed on wing lower surface central axes two sides in the utility model, and is directly welded at machine
Wing lower surface, the reasonable Mass Distribution for carrying out unmanned plane are distributed in center of gravity on symmetry axis to guarantee left-right balance.
(5) the utility model body (including wing and fuselage) is all made of nonmetallic materials, and metal mirror is minimum, can have
Effect is avoided by radar detection, meanwhile, size is minimum, it is extremely difficult to visually be found, can keep good concealment.
(6) the utility model is not provided with power device, using the design of autonomous gliding flight, does not need to control in flight control
Pitch angle processed, it is only necessary to control side path (rolling), effectively reduce the difficulty of flight control.
(7) pcb board is selected in fin production, can manufacture fuselage by 3D printing technique, can be saved compared to traditional die sinking manufacture
Difficulty when saving a large amount of manufacturing time and manufacturing cost, while eliminating electronic component integration, improves manufacture assembly precision,
Be conducive to the batch production of miniature drone.
(8) setting of lightening hole and rectangle weight loss groove can greatly reduce useless weight, be conducive to center of gravity Forward, increase nothing
Man-machine longitudinal stability improves flying distance.
(9) GPS receiver and Antenna Design can reduce interference from each other, avoid in one and a tail of unmanned plane
It is influenced by electromagnetic compatibility problem.
(10) clump weight is connect by clump weight connecting rod with the leading edge of a wing, increases the arm of force of counterweight, so that increasing most
It may make center of gravity than original Forward under the premise of small weight, while obvious negative effect will not be generated to unmanned plane resistance, guarantee
Longitudinal static margin preset range；Compared to directlying adopt with the mode focused on fuselage, the distance of flight is effectively extended.
(11) afterbody hill-like structure plays rectified action, is conducive to reduce resistance when flight.
Detailed description of the invention
Fig. 1 is the schematic diagram of the utility model embodiment hidden autonomous flight miniature drone wing backside structure.
Fig. 2 is the schematic diagram of the utility model embodiment hidden autonomous flight miniature drone wing Facad structure.
Fig. 3 is the schematic diagram of the utility model embodiment hidden autonomous flight miniature drone airframe structure.
Fig. 4 is the schematic diagram of the utility model embodiment hidden autonomous flight miniature drone complete machine structure.
[the utility model embodiment main element symbol description in attached drawing]
1- wing；2- lightening hole；
3-GPS receiver；4- interface module；
5- boost module；6- power module；
7- communication module；8- main control chip；
9- antenna；10- rudder foot；
11- rudder face；12- surveys appearance module；
13- empennage；14- hinge；
15- weight linear meter jointing；16- lightening hole；
17- preformed hole；18- fuselage；
19- steering engine；20- battery；
21- camera；22- clump weight；
23- connecting rod.
Specific embodiment
The utility model provides a kind of hidden autonomous flight miniature drone, comprising: wing, electronic building brick, fuselage,
Rudder face, empennage, steering engine, connecting rod and battery；Wing is made of pcb board；Electronic building brick is welded on wing lower surface, and electronics group
Part is evenly distributed on wing central axis two sides；Fuselage is located on electronic building brick, and is connect with wing lower surface；Rudder face and machine
Wing tail portion is connected；Empennage is connected with the tail portion of upper surface of the airfoil；Steering engine is embedded at the mounting hole that fuselage two sides are reserved；Connecting rod
One end is connect with steering engine, and connecting rod second end is connect with rudder face；Battery is arranged in fuselage interior.The utility model is not provided with power dress
The design using autonomous gliding flight is set, so that unmanned plane is worked the longer time, increases the serious forgiveness of task execution；Electronics
Component is evenly distributed on wing lower surface central axes two sides, and the reasonable Mass Distribution for carrying out unmanned plane guarantees left-right balance, together
When can also keep preferable concealment.
For the purpose of this utility model, technical solution and advantage is more clearly understood, below in conjunction with specific embodiment, and
Referring to attached drawing, the utility model is further described.
The utility model some embodiments will be done referring to appended attached drawing in rear and more comprehensively describe to property, some of but simultaneously
Not all embodiment will be shown.In fact, the various embodiments of the utility model can be realized in many different forms, without
It should be construed as limited to this several illustrated embodiment；Relatively, it theses embodiments are provided so that the utility model meets to be applicable in
Legal requirement.
In first exemplary embodiment of the utility model, it is micro-unmanned to provide a kind of hidden autonomous flight
Machine.Fig. 1 is the schematic diagram of the utility model embodiment hidden autonomous flight miniature drone wing backside structure.Fig. 2 is this
The schematic diagram of utility model embodiment hidden autonomous flight miniature drone wing Facad structure.Fig. 3 is that the utility model is real
Apply a schematic diagram for hidden autonomous flight miniature drone airframe structure.Fig. 4 is that the utility model embodiment hidden is autonomous
The schematic diagram of flight miniature drone complete machine structure.As shown in Figures 1 to 4, the miniature nothing of the utility model hidden autonomous flight
Man-machine includes: wing 1, electronic building brick, fuselage 18, rudder face 11, empennage 13, steering engine 19, connecting rod 23 and battery 20.
Specifically, electronic building brick is welded on 1 lower surface of wing, and electronic building brick is evenly distributed on 1 central axis of wing
Two sides.Fuselage 18 is located on electronic building brick, and is connect with 1 lower surface of wing, and bolt passes through the preformed hole 17 being arranged on wing 1
Connect wing 1 and fuselage 18.Rudder face 11 and wing 1 are connect by hinge 14, there are the gap of 1mm between rudder face 11 and wing 1,
To guarantee that rudder face 11 normally can upwardly or downwardly make rudder.The mode that empennage 13 directlys adopt gluing is connected on 1 tail portion of wing
In the reserved narrow slot in surface.Steering engine 19 is embedded at the mounting hole that 18 two sides of fuselage are reserved.23 first end of connecting rod and steering engine 19 connect
It connects, 23 second end of connecting rod is connect with rudder face 11.Battery 20 is arranged inside fuselage 18, and close to the position on 18 head of fuselage.
Wherein electronic building brick is welded on 1 lower surface of wing, and electronic building brick is evenly distributed on 1 central axis two sides of wing；
Electronic building brick includes: power module 6, interface module 4, boost module 5, antenna 9, communication module 7, GPS receiver 3, master control core
Piece 8.Power module 6 is electronic components power supply.Interface module 4 is provided with the power supply connector of steering engine 19 and loading device.Boosting
Module 5 provides stable operating voltage for loading device.Antenna 9 is connected with communication module 7, to the ground receiving station or balloon borne base station
Pass the flying quality of unmanned plane itself and the mission payload data of loading device acquisition back.The communication selected in a specific embodiment
7 frequency band of module is 433mhz, and effective communication distance is about 150km；Antenna 9 is having a size of thick 1mm, wide 16mm, long 190mm.
GPS receiver 3 controls program for the flight built in miniature drone and provides location information, specifically optional u-blox6 model.It is main
It controls the flight built in 8 operation miniature drone of chip and controls program, to control the autonomous flight of miniature drone.
Specifically, loading device includes: camera 21, is embedded at the mounting hole that 18 head of fuselage is reserved.Camera 21
Miniature webcam can be selected, voltage stabilization work is guaranteed by boost module 5.
Specifically, antenna 9 fits in 18 tail portion of fuselage；GPS receiver 3 is welded in unmanned chain-drive section.3 He of GPS receiver
Antenna 9 designs one and a tail in unmanned plane, can reduce interference from each other, avoid the shadow by electromagnetic compatibility problem
It rings.
Specifically, further includes: rudder foot 10 and rocker arm；Rudder foot 10 is arranged in the lower surface of rudder face 11,23 second end of connecting rod with
Rudder face 11 is connected by rudder foot 10；Rocker arm is arranged on 19 side wall of steering engine, and rocker arm is connect with 23 first end of connecting rod, and steering engine 19 turns
It is dynamic that the control rotation of rudder face 11 of rudder face 11 is transmitted to by connecting rod 23.
Specifically, further includes: clump weight 22 and clump weight connecting rod, clump weight connecting rod first end pass through with clump weight 22
Circlip connection, clump weight connecting rod second end are connect with the weight linear meter jointing 15 on 18 head of fuselage.Clump weight 22 is by matching
Pouring weight connecting rod is connect with 1 leading edge of wing, increases the arm of force of counterweight, so that may make center of gravity under the premise of increasing minimum weight
It moves forward than originally, guarantees longitudinal static margin preset range；Compared to directlying adopt with the mode focused on fuselage 18, effectively prolong
The distance of flight is grown.
In one embodiment, since the heavier-weight of pcb board makes drone center of unmanned aerial vehicle preposition in aerodynamic center, so
It can not ensure longitudinal stability.If directlying adopt with the mode focused on fuselage 18, the weight for needing to increase 60g could reach
To the effect of same forward moved centre-of-gravity, the distance of flight is substantially reduced.It in order to solve this problem, will be before 10g clump weight 22
It is placed in 1 leading edge 10cm of wing, fuselage 18 is connected to by the lightweight iron of a 1.5mm diameter.The design increases the arm of force of counterweight,
So that may make center of gravity than original Forward 1cm under the premise of increasing minimum weight, guarantee that longitudinal static margin reaches 10%.
Clump weight 22 selects streamlined body, and when flight can be ignored the increase of resistance, does not influence flying quality.Meanwhile
Distance of the clump weight away from the leading edge of a wing can also be adjusted according to the demand of concrete configuration position of centre of gravity.
Specifically, wing 1, empennage 13 are directly cut by pcb board.Multiple lightening holes 2, empennage are set on wing 1
Multiple lightening holes 16 are set on 13, and multiple lightening holes 2 are evenly distributed on the aerofoil of wing 1, and multiple lightening holes 16 are uniformly distributed
On the aerofoil of empennage 13, lightening hole 2 and lightening hole 16 are pasted with film in aerofoil two sides, can not only keep the wing of design
Area is constant, moreover it is possible to effectively prevent leaking out.The setting of lightening hole 2 and lightening hole 16 can greatly reduce useless weight, improve and fly
Row distance.Pcb board laser cutting made of wing 1, with a thickness of 1mm, although this is because less than 1mm pcb board weight reduce,
But intensity can not enough deform easily, the pcb board preponderance greater than 1mm, therefore select the pcb board of 1mm as 1 material of wing
It is proper.In addition, loss of weight rectangular channel is additionally provided on wing 1, the central axis of loss of weight rectangular channel and the central axis weight of wing 1
It closes, and loss of weight rectangular channel is set to the middle and back of wing 1.Lightening hole and loss of weight rectangular channel are provided with the weight for being conducive to make unmanned plane
Heart Forward, increases longitudinal stability.
Specifically, further includes: survey appearance module 12, survey appearance module 12 and be welded on the positive central axis of fuselage 18, be micro-
Flight control program built in type unmanned plane provides posture information.Here the survey appearance module 12 selected is nine axis inertia measurement lists
Member.
Specifically, the specification of battery 20 can select capacity 2200mah, and the lithium battery of 4.2V can ensure unmanned plane load
With 3 hours of 19 stable operation of steering engine.Due to 20 heavier-weight of battery, battery 20 is arranged inside fuselage 18, and close to machine
The position on 18 head of body makes drone center of unmanned aerial vehicle Forward to increase longitudinal stability.
Specifically, the shape of wing 1 is the graceful aerofoil profile of anti-Zimmer, length 30cm, chord length 15cm, aspect ratio 2.In this aspect ratio
Lower aircraft can keep preferable concealment, be not easy to be found, while lift resistance ratio is also larger, and flying distance is farther out.Selection is anti-
The graceful shape of Zimmer is because it can provide best aeroperformance for flat profile (shows as higher lift resistance ratio and biggish
Stall angle).Fuselage 18 is manufactured by 3D printing technique, plays the role of rectification and heat preservation for the element on circuit board,
Tail portion is in hill-like structure, to reduce form drag when flight.
Since the utility model eliminates the dynamical system of traditional miniature drone, be changed into miniature gliding type nobody
Machine.Mode of taking off is changed to the dispensing of batch sounding balloon by traditional single rack ground release or aerostat is launched, and release altitude exists
Between 0km-30km.If only needing short range projection, do not need miniature drone landing it is too far, then with sounding ball carry in 0km-
The projection of 30km arbitrary height.To must then be projected in 20km across intercontinental projection, because making across intercontinental projection needs
It is carried with high-altitude super-pressure balloon, and super-pressure balloon must fly in this height of 20km, because existing in 20km height above sea level
Wind speed Minimum Area, this region are known as zero stratification of wind.Gliding initial segment keeps stablizing after height discharges certifiable release herein, thus
Quickly enter equilibrium glide state.Wing 1 is directly manufactured by pcb board, and aerofoil profile is deck aerofoil profile, and full machine maximum lift-drag ratio is 5.2,
About 120km can be slided by launching under 20km height above sea level under this lift resistance ratio, coasting time about 40 minutes, and traditional miniature drone
Compared to considerably increasing flying distance and flight time.
So far, attached drawing is had been combined the utility model embodiment is described in detail.It should be noted that in attached drawing
Or in specification text, the implementation for not being painted or describing is shape known to a person of ordinary skill in the art in technical field
Formula is not described in detail.In addition, the above-mentioned definition to each element and method be not limited in mentioning in embodiment it is various
Specific structure, shape or mode, those of ordinary skill in the art simply can be changed or be replaced to it, such as:
(1) wing shapes could alternatively be other shapes, such as: rectangle is trapezoidal；
(2) twin-finned layout is also with single vertical fin layout substitution；
(3) size and shape of fuselage design according to specific needs, such as: if necessary to carry two pieces of batteries, then may be used
To increase fuselage；
(4) camera of fore-body can need to replace with other loading devices according to task, such as: temperature sensor, shake
Dynamic sensor etc.；
(5) connection type of rudder face and wing also can be replaced other forms, such as: adhesive tape is pasted.
According to above description, those skilled in the art should have the utility model hidden autonomous flight miniature drone
Clear understanding.
In conclusion the utility model provides a kind of hidden autonomous flight miniature drone, designed using autonomous flight,
Compared with traditional drive miniature drone consumes a large amount of electric power energies in dynamical system, now by most of energy resource supply task
Load allows unmanned plane to work the longer time, increases the serious forgiveness of task execution.
It should also be noted that, the direction term mentioned in embodiment, for example, "upper", "lower", "front", "rear", " left side ",
" right side " etc. is only the direction with reference to attached drawing, not is used to limit the protection scope of the disclosure.Through attached drawing, identical element by
Same or similar appended drawing reference indicates.When may cause understanding of this disclosure and cause to obscure, conventional structure will be omitted
Or construction.
And the shape and size of each component do not reflect actual size and ratio in figure, and only illustrate the embodiment of the present disclosure
Content.In addition, in the claims, any reference symbol between parentheses should not be configured to the limit to claim
System.
It unless there are known entitled phase otherwise anticipates, the numerical parameter in this specification and appended claims is approximation, energy
Enough bases pass through the resulting required characteristic changing of content of this disclosure.Specifically, all be used in specification and claim
The middle content for indicating composition, the number of reaction condition etc., it is thus understood that repaired by the term of " about " in all situations
Decorations.Under normal circumstances, the meaning expressed refers to include by specific quantity ± 10% variation in some embodiments, some
± 5% variation in embodiment, ± 1% variation in some embodiments, in some embodiments ± 0.5% variation.
Furthermore word "comprising" does not exclude the presence of element or step not listed in the claims.It is located in front of the element
Word "a" or "an" does not exclude the presence of multiple such elements.
The word of ordinal number such as " first ", " second ", " third " etc. used in specification and claim, with modification
Corresponding element, itself is not meant to that the element has any ordinal number, does not also represent the suitable of a certain element and another element
Sequence in sequence or manufacturing method, the use of those ordinal numbers are only used to enable an element and another tool with certain name
Clear differentiation can be made by having the element of identical name.
Similarly, it should be understood that in order to simplify the disclosure and help to understand one or more of each open aspect,
Above in the description of the exemplary embodiment of the disclosure, each feature of the disclosure is grouped together into single implementation sometimes
In example, figure or descriptions thereof.However, the disclosed method should not be interpreted as reflecting the following intention: i.e. required to protect
The disclosure of shield requires features more more than feature expressly recited in each claim.More precisely, as following
Claims reflect as, open aspect is all features less than single embodiment disclosed above.Therefore,
Thus the claims for following specific embodiment are expressly incorporated in the specific embodiment, wherein each claim itself
All as the separate embodiments of the disclosure.
Particular embodiments described above has carried out further in detail the purpose of the disclosure, technical scheme and beneficial effects
Describe in detail it is bright, it is all it should be understood that be not limited to the disclosure the foregoing is merely the specific embodiment of the disclosure
Within the spirit and principle of the disclosure, any modification, equivalent substitution, improvement and etc. done should be included in the guarantor of the disclosure
Within the scope of shield.
Claims (10)
1. a kind of hidden autonomous flight miniature drone characterized by comprising
Wing is made of pcb board；
Electronic building brick is welded on the wing lower surface, and the electronic building brick is evenly distributed on the wing central axis
Two sides；
Fuselage is located on the electronic building brick, and is connect with the wing lower surface；
Rudder face is connected with the wing tail portion, is made of pcb board；
Empennage is connected with the tail portion of the upper surface of the airfoil, is made of pcb board；
Steering engine is embedded at the mounting hole that the fuselage two sides are reserved；
Connecting rod, the connecting rod first end are connect with the steering engine, and the connecting rod second end is connect with the rudder face；
Battery is arranged in the fuselage interior, and close to the position of above-mentioned fuselage head.
2. miniature drone according to claim 1, which is characterized in that further include:
Rudder foot, is arranged in the lower surface of the rudder face, and the connecting rod second end is connected with the rudder face by the rudder foot；
Rocker arm is arranged on the steering engine side wall, and the rocker arm is connect with the connecting rod first end.
3. miniature drone according to claim 1, which is characterized in that further include:
Clump weight；
Clump weight connecting rod, the clump weight connecting rod first end are connect with the clump weight, the clump weight connecting rod second
End is connect with the fuselage head and wing head.
4. miniature drone according to claim 1, which is characterized in that further include:
Multiple lightening holes are arranged on the wing and/or the empennage, and the multiple lightening hole is evenly distributed on the wing
And/or on the aerofoil of the empennage, each lightening hole is pasted with thin in the aerofoil two sides of wing and/or the empennage
Film；
Loss of weight rectangular channel is arranged on the wing, the central axis of the loss of weight rectangular channel and the central axis of the wing
It is overlapped, and the loss of weight rectangular channel is set to the middle and back of the wing.
5. miniature drone according to claim 1, which is characterized in that the electronic building brick includes:
Power module is the electronic components power supply；
Interface module is provided with the power supply connector of the steering engine, battery and loading device；
Boost module provides stable operating voltage for loading device；
Antenna is connected with communication module, and receiving station or balloon borne base station pass the flying quality and load of unmanned plane itself back to the ground
The mission payload data of equipment acquisition；
GPS receiver controls program for the flight built in the miniature drone and provides location information；
Main control chip, the flight built in miniature drone described in operation controls program, to control the flight of the miniature drone.
6. miniature drone according to claim 5, which is characterized in that the loading device includes:
Camera is embedded at the mounting hole that the fuselage head is reserved.
7. miniature drone according to claim 5, which is characterized in that the antenna fits in afterbody；The GPS
Receiver is welded in unmanned chain-drive section.
8. miniature drone according to any one of claims 1 to 7, which is characterized in that further include:
Appearance module is surveyed, is welded on the positive central axis of the fuselage, is that the flight built in the miniature drone controls journey
Sequence provides posture information.
9. miniature drone according to any one of claims 1 to 7, which is characterized in that the miniature drone is in 20km
Height from super-pressure balloon carry out high-altitude across it is intercontinental projection or 0~30km any height from sounding ball carry out short distance throwing
It penetrates.
10. miniature drone according to claim 1, which is characterized in that the shape of the wing is the graceful aerofoil profile of anti-Zimmer；
The afterbody is in hill-like structure.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821430959.9U CN209126964U (en) | 2018-08-31 | 2018-08-31 | Hidden autonomous flight miniature drone |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201821430959.9U CN209126964U (en) | 2018-08-31 | 2018-08-31 | Hidden autonomous flight miniature drone |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229368A (en) * | 2018-08-31 | 2019-01-18 | 中国科学院光电研究院 | Hidden autonomous flight miniature drone |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229368A (en) * | 2018-08-31 | 2019-01-18 | 中国科学院光电研究院 | Hidden autonomous flight miniature drone |
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Granted publication date: 20190719 Termination date: 20200831 |