CN110481779A - Umbellate form boosting Helios - Google Patents
Umbellate form boosting Helios Download PDFInfo
- Publication number
- CN110481779A CN110481779A CN201910820284.1A CN201910820284A CN110481779A CN 110481779 A CN110481779 A CN 110481779A CN 201910820284 A CN201910820284 A CN 201910820284A CN 110481779 A CN110481779 A CN 110481779A
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- CN
- China
- Prior art keywords
- umbellate form
- aircraft body
- aircraft
- helios
- retractable structure
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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- 238000004146 energy storage Methods 0.000 claims abstract description 13
- 238000013461 design Methods 0.000 claims abstract description 6
- 238000009434 installation Methods 0.000 claims abstract description 6
- 238000012360 testing method Methods 0.000 claims description 5
- 238000012856 packing Methods 0.000 claims 1
- 238000004064 recycling Methods 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229910001218 Gallium arsenide Inorganic materials 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- JBRZTFJDHDCESZ-UHFFFAOYSA-N AsGa Chemical compound [As]#[Ga] JBRZTFJDHDCESZ-UHFFFAOYSA-N 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000036632 reaction speed Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/023—Aircraft characterised by the type or position of power plants of rocket type, e.g. for assisting taking-off or braking
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S20/00—Supporting structures for PV modules
- H02S20/30—Supporting structures being movable or adjustable, e.g. for angle adjustment
- H02S20/32—Supporting structures being movable or adjustable, e.g. for angle adjustment specially adapted for solar tracking
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Photovoltaic Devices (AREA)
Abstract
The present invention provides a kind of umbellate form boosting Helios, including aircraft body, rocket engine, solar energy film, coaxial bispin wing mechanism, energy-storage battery and umbellate form retractable structure, the upper end of the aircraft body is installed by coaxial bispin wing mechanism, lower end is installed by rocket engine, umbellate form retractable structure, inside installation energy-storage battery are installed outside middle section；The umbellate form retractable structure is tightly attached to aircraft body outer wall when collapsing, in coniform and coaxial with aircraft body when expansion；The solar energy film is covered on umbellate form retractable structure upper surface, powers for energy-storage battery.The present invention is able to ascend launch velocity degree, reduces initial loss of energy, realizes the structure changes design of aircraft, keeps vehicle launch, recycling, storage more convenient.
Description
Technical field
The present invention relates to a kind of Helios, belong to test and the field of test technology.
Background technique
Helios technology has broad application prospects, such as aerial ocean weather station observation, scouting, early warning, blocker, height
Empty radar station, communication relay, border patrol, electronic countermeasure, battlefield monitoring, Aero Satellite, to environment and disaster condition monitoring, very
It is extremely anti-ballistic etc..
Aircraft currently used for scout-observation mainly has helicopter, dirigible etc., such as unmanned plane, the high-altitude of normal arrangement
Balloon, dirigible and conventional UAV system etc., they have the advantage of its own, but such aircraft is to rely on fossil combustion mostly
Material is used as major impetus source, masterly when executing short distance, short voyage and low clearance task, but faces higher
Business requires, such as overlength hang time, super remote flying distance etc., due to made by efficient energy offer condition steady in a long-term
About, conventional aircraft then seems unable to do what one wishes.In order to solve problem above, many scientists both at home and abroad start in eighties of last century
Helios is unfolded to study, relevant technology obtains significant achievement, such as the U.S. develop " sun challenger ",
" west wind 3 " aircraft etc. that " Apollo " number aircraft, Britain develop is what the country represented have " hoverer " number aircraft, " green
Color Pioneer " aircraft etc., but limited by photovoltaic battery conversion efficiency, to obtain biggish daylighting area, the existing sun
Energy aircraft still uses high aspect ratio structure, this directly results in the flexible of Flight Vehicle Structure and increases, and insufficient rigidity seriously affects
The flight safety of aircraft.In order to fundamentally solve the Helios rigidity of structure it is lower, it is bulky, storage recycling hair
The problems such as penetrating inconvenience, and the problems such as being directed to emergency and emergency event reaction speed low efficiency, need a kind of sun
Can aircraft, can satisfy using rapidly, recycling facilitates etc. and to require.
Summary of the invention
For overcome the deficiencies in the prior art, the present invention provides a kind of umbellate form boosting Helios, is able to ascend hair
Initial velocity is penetrated, initial loss of energy is reduced, the structure changes design of aircraft is realized, makes vehicle launch, recycling, storage more just
It is prompt.
The technical solution adopted by the present invention to solve the technical problems is: a kind of umbellate form boosting Helios, including
Aircraft body, rocket engine, solar energy film, coaxial bispin wing mechanism, energy-storage battery and umbellate form retractable structure.
Coaxial bispin wing mechanism is installed in the upper end of the aircraft body, and lower end is installed rocket engine, installed outside middle section
Umbellate form retractable structure, inside installation energy-storage battery；The umbellate form retractable structure is tightly attached to outside aircraft body when collapsing
Wall, in coniform and coaxial with aircraft body when expansion；The solar energy film is covered on table on umbellate form retractable structure
Face powers for energy-storage battery.
The umbellate form retractable structure is based on link mechanism and is mounted on aircraft body, pushes connecting rod by spring,
It drives umbellate form retractable structure to be unfolded outward, bullet is overcome by installation locking device between housing contractile ring or each connecting rod when gathering
Spring force.
It is connected between the rocket engine and aircraft body by separating mechanism, engine after separating mechanism is powered
It is separated with aircraft, engine falls off.
Installation quality square control system on the aircraft body adjusts aircraft body posture, makes solar energy film
The face sun.
The invention also includes bracket is emitted, transmitting support Design has leveling system, guarantees that aircraft body emits preceding and ground
Face is vertical；Angular transducer is installed on aircraft body, when aircraft body is perpendicular to the ground could by self-test so that
Engine has fired state.
The beneficial effects of the present invention are:
1) Helios in the present invention can be improved winged using tray type structure in such a way that coaxial DCB Specimen combines
The rigidity and stability of row device；And it can guarantee the operative orientation of aircraft
2) using coaxial bispin wing structure can be effectively ensured after aircraft is pushed into more than 500 meters by booster aircraft from
The direction that row is drawn high, and the hovering of aircraft is realized in flight during aloft work；
3) present invention controls solar energy film skeleton link mechanism using mass moment control system, guarantees that aircraft is working
The solar panel moment face sun in the process, improves the utilization efficiency of solar energy, while controlling aircraft crossrange maneuvering
Posture and daily attitude stabilization；
4) it is laid with solar energy film in link-type skeleton body structure surface, the folding of umbrella cover can be achieved by the movement of link mechanism
Folded expansion, reduces emission area, increases the convenience of recycling and storage；Realize the structure changes design form of aircraft；
5) launch assist is carried out using booster, increases launch velocity degree, save the energy content of battery, keep flight overall
It draws high speed and improves 40%；
6) using transmitting bracket in emission process, transmitting support Design has leveling system, guarantees perpendicular to the ground, aircraft
Angular transducer is installed on ontology, when angular transducer and emits when bracket guarantee angle is 90 degree and could be sent out by self-test
Motivation has fired state, thus guarantees launch angle.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is emission state structural schematic diagram of the invention；
Fig. 3 is state of flight structural schematic diagram of the invention；
Fig. 4 is flight logical schematic of the invention；
In figure, 1- DCB Specimen, 2- umbellate form retractable structure, solar energy film, 3- launcher, 4- rocket engine, 5- storage
It can battery and power-supply management system, load system.
Specific embodiment
Present invention will be further explained below with reference to the attached drawings and examples, and the present invention includes but are not limited to following implementations
Example.
Aircraft of the invention mainly by rocket engine, aircraft body, solar energy film, coaxial bispin wing mechanism,
The part such as energy-storage battery and power-supply management system, load system is constituted.One piece of front end of outer image has the fire of DCB Specimen before emitting
Aircraft is pushed to certain altitude by rocket engine by arrow, and release umbellate form Helios tightens mechanism, the sun
Energy umbrella is opened, and then, rocket engine falls off, and umbellate form aircraft starts with solar energy work.
Aircraft body structure is as shown in Figure 1, push link motion, realization umbrella shape by spring using connecting rod working principle
The folding and expanding of aircraft umbrella cover, before aircraft work, solar energy film passes through the folding and expanding knot of Helios ontology
Structure is folded into cylinder, is locked by tightening.Aircraft draws high the course of work and is divided into two stages, the first rank
Section is boost phase, this stage aircraft beveled structure is folded state, is lighted a fire using booster and aircraft is pushed to rise,
Engine operation is completed after 2.5s, and separating mechanism is powered after 3s, and engine is separated with aircraft, and engine falls off, umbrella body locking
Switch, which is powered, to be unlocked, and is unfolded by ontology folding and expanding mechanism umbrella cover, and entrance second draws high the stage, what this stage aircraft was equipped with
Battery is first begin to power for control system, and DCB Specimen is started to work, and continues to draw high aircraft, while being laid on umbrella cover soft
Property solar energy film absorb solar energy, be translated into electric energy as power source, energy-storage battery is for by solar panel
It converts obtained electric energy to store, in case night or other flights in special circumstances use.The aircraft is by being located at ontology
Mass moment control system on keel makes its solar panel face sun, improves the efficiency of solar energy, while controlling flight
The posture of device crossrange maneuvering and daily attitude stabilization.The electrical energy drive of energy-storage battery is aircraft mounted in umbrella tip DCB Specimen
Daily flight provides major impetus.Bispin wing mechanism is at the center of umbrella, also offer crossrange maneuvering power.Structural material novel light is high
Strong composite material meets Flight Vehicle Structure and functional requirement.
Helios gross weight 11kg in the embodiment of the present invention, wherein energy-storage battery weight 5kg, is equipped with 1 separate unit
The direct current generator of power 0.8kw, motor weight 4kg.4m is laid in umbrella shape fuselage upper surface2Gallium arsenide film, theoretical maximum turn
Change power 1.2kw, 2 layers of 4m of gallium arsenide film lower radiant2Flexible silion cell, battery gross weight 5kg, capacity 2kwh.Before taking off
Battery is full of on ground.Aircraft uses booster diameter for 125mm, and total punching is 5000Ns, working time 2s, weight
Amount is 3.6kg.Helios ontology skeleton uses carbon fiber truss structure, reduces structure overall weight.Originate promotion side
To for direction perpendicular to the ground, relying primarily on launcher to guarantee, installation is winged after launcher and ground are leveled by leveling system
For row device (band engine) to launcher, igniting starts launch assist, main after engine falls off, propeller is started to work
Direction is guaranteed by propeller.Aircraft is pushed into the high-altitude 300m, speed 270m/s by booster, and engine falls off, flight
Device utilizes coasting flight to 3000m；The expansion of solar energy folding panel, power supply system and control system work, and propeller starts work
Make, battery utilizes solar energy cycle charging, when the weight phase for the lift size and aircraft itself that propeller is generated by rotation
Whens equal, aircraft can keep hovering in the sky, and rotor uses tilting rotor, be flown using verting for rotor come change of flight device
Flying speed is improved in turn to pulling force before line direction and offer.The recycling navigation control system of aircraft, by propeller speed
Degree reduces, and when propeller is less than the weight of aircraft itself by the lift that rotation generates, aircraft is begun to decline, by leading
Control system of navigating obtains the position of decline, so that aircraft is fallen into recycling frame, umbrella frame and recycling frame support face contact, prevents machine
The collision of body and ground.
Claims (5)
1. a kind of umbellate form boosting Helios, including aircraft body, rocket engine, solar energy film, coaxial bispin
Wing mechanism, energy-storage battery and umbellate form retractable structure, it is characterised in that: the upper end of the aircraft body is installed by coaxial DCB Specimen
Rocket engine is installed in mechanism, lower end, and umbellate form retractable structure, inside installation energy-storage battery are installed outside middle section；The umbellate form
Retractable structure is tightly attached to aircraft body outer wall when collapsing, in coniform and coaxial with aircraft body when expansion；Described
Solar energy film is covered on umbellate form retractable structure upper surface, powers for energy-storage battery.
2. umbellate form boosting Helios according to claim 1, it is characterised in that: the umbellate form retractable structure
It is mounted on aircraft body based on link mechanism, connecting rod is pushed by spring, umbellate form retractable structure is driven to be unfolded outward, is received
Spring force is overcome by installing locking device between housing contractile ring or each connecting rod additional when holding together.
3. umbellate form boosting Helios according to claim 1, it is characterised in that: the rocket engine and fly
It is connected between row device ontology by separating mechanism, engine is separated with aircraft after separating mechanism is powered, and engine falls off.
4. umbellate form boosting Helios according to claim 1, it is characterised in that: pacify on the aircraft body
Packing quality square control system adjusts aircraft body posture, makes the solar energy film face sun.
5. umbellate form boosting Helios according to claim 1, it is characterised in that: further include transmitting bracket, transmitting
Support Design has leveling system, guarantees that aircraft body transmitting is preceding perpendicular to the ground；Angle sensor is installed on aircraft body
Device, could be by self-test, so that engine has fired state when aircraft body is perpendicular to the ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910820284.1A CN110481779A (en) | 2019-09-01 | 2019-09-01 | Umbellate form boosting Helios |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910820284.1A CN110481779A (en) | 2019-09-01 | 2019-09-01 | Umbellate form boosting Helios |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110481779A true CN110481779A (en) | 2019-11-22 |
Family
ID=68555880
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910820284.1A Pending CN110481779A (en) | 2019-09-01 | 2019-09-01 | Umbellate form boosting Helios |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110481779A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407241A (en) * | 2020-12-06 | 2021-02-26 | 西安长峰机电研究所 | Rotary folding mechanism |
| CN114166074A (en) * | 2021-01-07 | 2022-03-11 | 西安电子科技大学 | Expandable simulated projectile body device |
| CN116424529A (en) * | 2023-06-13 | 2023-07-14 | 青岛哈尔滨工程大学创新发展中心 | Underwater submarine vehicle and control method thereof |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102147217A (en) * | 2011-04-25 | 2011-08-10 | 哈尔滨开恩科技开发有限公司 | Solar-cell umbrella type aerial detonator |
| CN104470800A (en) * | 2012-02-13 | 2015-03-25 | 约翰内斯·赖特 | Wing adjusting mechanism |
| US9603422B1 (en) * | 2016-03-02 | 2017-03-28 | Droidbrella Technologies, Inc. | Automated hands-free umbrella |
| JP2017200821A (en) * | 2017-07-24 | 2017-11-09 | みこらった株式会社 | Protection apparatus and protection system |
| CN107434036A (en) * | 2016-05-25 | 2017-12-05 | 李然 | Ferried in the air without combustion powered arrow ship and float airport air transport system |
| CN107444638A (en) * | 2016-06-01 | 2017-12-08 | 许宏 | A kind of unmanned actuation means of umbrella shape airflight |
| CN206926841U (en) * | 2017-04-27 | 2018-01-26 | 李爱兵 | The outstanding winged device of rocket propulsion cabin recovery power |
| CN108284944A (en) * | 2018-03-16 | 2018-07-17 | 临沂大学 | A kind of mini foldable fixed-wing unmanned plane |
| CN109263977A (en) * | 2018-11-12 | 2019-01-25 | 浙江大学 | A kind of umbrella wing formula imitates dandelion cluster aircraft and its control method |
-
2019
- 2019-09-01 CN CN201910820284.1A patent/CN110481779A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102147217A (en) * | 2011-04-25 | 2011-08-10 | 哈尔滨开恩科技开发有限公司 | Solar-cell umbrella type aerial detonator |
| CN104470800A (en) * | 2012-02-13 | 2015-03-25 | 约翰内斯·赖特 | Wing adjusting mechanism |
| US9603422B1 (en) * | 2016-03-02 | 2017-03-28 | Droidbrella Technologies, Inc. | Automated hands-free umbrella |
| CN107434036A (en) * | 2016-05-25 | 2017-12-05 | 李然 | Ferried in the air without combustion powered arrow ship and float airport air transport system |
| CN107444638A (en) * | 2016-06-01 | 2017-12-08 | 许宏 | A kind of unmanned actuation means of umbrella shape airflight |
| CN206926841U (en) * | 2017-04-27 | 2018-01-26 | 李爱兵 | The outstanding winged device of rocket propulsion cabin recovery power |
| JP2017200821A (en) * | 2017-07-24 | 2017-11-09 | みこらった株式会社 | Protection apparatus and protection system |
| CN108284944A (en) * | 2018-03-16 | 2018-07-17 | 临沂大学 | A kind of mini foldable fixed-wing unmanned plane |
| CN109263977A (en) * | 2018-11-12 | 2019-01-25 | 浙江大学 | A kind of umbrella wing formula imitates dandelion cluster aircraft and its control method |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407241A (en) * | 2020-12-06 | 2021-02-26 | 西安长峰机电研究所 | Rotary folding mechanism |
| CN112407241B (en) * | 2020-12-06 | 2024-06-04 | 西安长峰机电研究所 | Rotary folding mechanism |
| CN114166074A (en) * | 2021-01-07 | 2022-03-11 | 西安电子科技大学 | Expandable simulated projectile body device |
| CN116424529A (en) * | 2023-06-13 | 2023-07-14 | 青岛哈尔滨工程大学创新发展中心 | Underwater submarine vehicle and control method thereof |
| CN116424529B (en) * | 2023-06-13 | 2023-09-05 | 青岛哈尔滨工程大学创新发展中心 | Underwater submarine vehicle and control method thereof |
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Application publication date: 20191122 |
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