CN107054668A - A kind of stealthy unmanned plane based on electronic Wo Pen VTOL Flying-wing - Google Patents
A kind of stealthy unmanned plane based on electronic Wo Pen VTOL Flying-wing Download PDFInfo
- Publication number
- CN107054668A CN107054668A CN201710040757.7A CN201710040757A CN107054668A CN 107054668 A CN107054668 A CN 107054668A CN 201710040757 A CN201710040757 A CN 201710040757A CN 107054668 A CN107054668 A CN 107054668A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- electronic
- wing
- pen
- vtol
- Prior art date
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/16—Aircraft characterised by the type or position of power plant of jet type
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
Abstract
The research is conceived to propulsion and control system using multiple electronic turbojet engine composition unmanned planes, is directed to solving those limited sizes but needs the real purposes of very big static lift, such as the landing of taking off vertically of aircraft.Such unmanned plane is used as main lift system in the take-off and landing stage using the spray of electronic whirlpool, it can take off vertically as helicopter, horizontal flight that again can be as fixed wing aircraft, and with good hovering performance, thus have the two-fold advantage of helicopter and fixed wing aircraft concurrently.
Description
Technical field
The research is conceived to propulsion and control system using multiple electronic turbojet engine composition unmanned planes, is directed to solution
Certainly those limited sizes but need the real purposes of very big static lift, such as the landing of taking off vertically of aircraft.Such nobody
Machine is sprayed as main lift system in the take-off and landing stage using electronic whirlpool, and it can take off vertically as helicopter,
Horizontal flight that again can be as fixed wing aircraft, and with good hovering performance, thus have helicopter and fixation concurrently
The two-fold advantage of wing aircraft.
Background technology
Electronic whirlpool spray unmanned plane is a member in unmanned plane extended familys, and unmanned plane militarily waits multiple fields hair with civilian
More and more important effect is waved, some are even irreplaceable.All size and the unmanned plane of type are with computer skill
The development of art, the communication technology, electronic technology etc. and flourish.The exploitation and development of unmanned plane are a kind of trends, more embody one
Individual national military affairs and the strength of science and technology, and in future can also occupy very important status.Unmanned plane is generally divided into
Fixed-wing and rotor wing unmanned aerial vehicle, also have flapping wing aircraft in small-sized and minute vehicle field.The unmanned plane application of each rank
Field is also different.Some large-scale unmanned planes are used in military affairs, and small-sized and miniature unmanned plane can be with dual-use.
Electronic whirlpool spray unmanned plane is the same with other kinds of unmanned plane, and his exploitation and development is related to many other keys
Technology development and progress, the control of such as aircraft and navigation system, the communication technology, payload, ground control platform and
It is exactly the structure of aircraft the characteristics of maximum for spraying unmanned plane in itself for electronic whirlpool in terms of vehicle aerodynamics
Design and flight control system, in this respect different from traditional fixed-wing and rotor craft.Sprayed and flown due to electronic whirlpool
The VTOL mode of device and similar to flying horizontal flight mode in other words before fixed-wing.The design load of its flight control system
It must pay close attention to.Electronic whirlpool spray unmanned plane can the VTOL as unmanned plane, and level can fly as fixed wing aircraft
OK.Further, since employing whirlpool spray, aircaft configuration is compact, safe, starts noise small.Electronic whirlpool spray unmanned plane can also
Different size is designed to as needed, to apply different occasions.From this, electronic whirlpool spray unmanned plane has helicopter concurrently and solid
Determine the advantage of wing aircraft, there is good applicability and application prospect.
The content of the invention
The invention main design thought, by the spray VUAV technology development of electronic whirlpool is ground both at home and abroad at present
Study carefully the structure type for determining that VUAV is sprayed in electronic whirlpool.A payload is designed for 10kg, it is small that cruising time is more than 1
When unmanned plane, flying height and cruise Mach number are respectively：H=10km, Ma=0.4.The characteristics of this money unmanned plane, is as follows：
1st, vector spray is replaced as the power resources of unmanned plane VTOL using the spouted power in electronic whirlpool；
2nd, existing turbojet engine (23kg thrusts) is replaced to be used as unmanned plane using small-size turbojet engine (9kg thrusts)
Cruising power；
3rd, remaining design target changes according to actual load-carrying is corresponding to flying condition progress.
The general design requirement of VUAV is sprayed for electronic whirlpool, overall plan is established, to the totality of unmanned plane
Parameter carries out primary Calculation.
1st, collectivity Scheme Design and Mass Distribution
Take electronic whirlpool spray as unmanned plane VTOL power resources, according to design requirement, this project is from 8 models
Sprayed for JP120 electronic whirlpool, the spray of single motor whirlpool maximum can provide 7.2kg thrusts, therefore unmanned plane maximum fullys loaded takeoff weight
For：
8*7.2kg=57.6kg
According to flight control experience, the unmanned plane VTOL time is 40s, therefore can spray working condition according to electronic whirlpool
It is 9.6kg to determine battery weight；The unmanned plane that the weight of remaining structural system is designed according to early stage is estimated.Therefore, the nothing
Man-machine total Mass Distribution is as shown in table 1, it is known that, the unmanned plane fullys loaded takeoff weight about 50kg, and by knowing 8 electronic whirlpools above
Spouted power is 57.6kg to the maximum, meets power demand, and Design of Aerodynamic Configuration can be carried out accordingly.
The unmanned plane oeverall quality distribution table of table 1.
2nd, unmanned plane Design of Aerodynamic Configuration
2.1 configuration design
Design of Aerodynamic Configuration is improved in early stage design, the main loading demand for considering 8 electronic whirlpool sprays, therefore,
While ensuring the spouted point of force application in electronic whirlpool with center of gravity on same vertical direction, fuselage is carried out after repairing type, can be obtained
To new aerodynamic configuration, simultaneously as changing smaller turbojet engine, also carried out as cruise thrust, therefore to air intake duct
Redesign.
2.2 aerodynamic characteristics numericals are simulated
Clean configuration progress aerodynamic analysis to final aerodynamic configuration can obtain the unmanned plane in H=10km, Ma=0.4 gas
As shown in table 2, wherein alpha is that the cruise angle of attack, L are that lift, D are that resistance, K are lift-drag ratios to dynamic characteristic.Understand, under this condition
During cruising flight, unmanned plane lift-drag ratio is about 10., can be with now according to unmanned plane drag characteristic and turbojet engine oil consumption characteristic
Reckoning obtains unmanned plane cruising time for t=50min, meets design requirement.
The aerodynamic numerical simulation result of table 2.
3rd, Structural Design Requirement
Unmanned plane totality pneumatic design and structure design are closely bound up, it is considered to loading, assembling and the design of rudder face of structure,
Structure design is proposed claimed below：
3.1 electronic whirlpool spray sizes
Size is sprayed in electronic whirlpool, and fuselage interior installs 8, and position has been reserved, it is desirable to the air inlet exhaust outlet of electronic whirlpool spray
Should be unobstructed；
The requirement of 3.2 centers of gravity
It is required that aircraft center of gravity is at the cusp 723mm of head；
3.3 turbojet engine installation requirements
Turbojet engine head is positioned at the cusp 910mm of head, and afterbody carries out profile according to specific installation site
Blade local modification；
3.4 fuel tank installation requirements
Fuel tank is placed on air intake duct both sides, and its center of gravity is overlapped with the center of gravity of aircraft, i.e., positioned at apart from head cusp 723mm
Place；
3.5 electronic whirlpool spray battery installation requirements
One piece of 12s, 40AH, 25C can be used, it is also possible to two pieces of 12s, 20AH, 25C's, be installed according to structure arrangement adjustment
Position；
3.6 rudder face design requirements
Inboard is lifting rudder face, and outside is cham-shell aileron, and rudder face upper and lower surface type face should be with clean configuration during design
It is consistent, next rudder face leading edge to trailing edge distance is 120mm；
The requirement of 3.7 Landing Gear Designs
Undercarriage is without folding and unfolding, support when only being stood as unmanned aerial vehicle.
Brief description of the drawings
Fig. 1 is aerodynamic configuration view.
Fig. 2 is that size is sprayed in electronic whirlpool.
Embodiment
Step 1：Allow electronic whirlpool spray to produce lift with land to take off vertically and overcome aircraft own wt, reach VTOL
Purpose.
Step 2：Before thrust produced by sustainer overcomes the resistance in aircraft traveling process produced by aircraft to reach
Winged purpose, while going to control the posture of aircraft with torque of the chain of command produced by differential.
Claims (6)
1. the stealthy unmanned plane of electronic Wo Pen VTOL Flying-wing, it is characterised in that aircraft power is used as using ducted fan
Source, and using the spray of electronic whirlpool as unmanned plane main body, the unmanned vehicle with VTOL and hovering flight ability.
2. the stealthy unmanned plane of electronic Wo Pen VTOL Flying-wing, analyzed by structure design and pneumatic design, volume,
All there is salient feature in disguised and flying quality.
3. the stealthy unmanned plane of electronic Wo Pen VTOL Flying-wing, it is characterised in that mobility shows unique characteristics, suitable for multiple
Heterocycle performs task under border.
4. the stealthy unmanned plane of electronic Wo Pen VTOL Flying-wing, it is characterised in that compact conformation, propulsive efficiency is high.
5. the stealthy unmanned plane of the electronic Wo Pen VTOL Flying-wing according to claim 1-2, it is characterised in that make an uproar
Sound is low, good concealment.
6. the profile sign of the stealthy unmanned plane of the electronic Wo Pen VTOL Flying-wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710040757.7A CN107054668A (en) | 2017-01-20 | 2017-01-20 | A kind of stealthy unmanned plane based on electronic Wo Pen VTOL Flying-wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710040757.7A CN107054668A (en) | 2017-01-20 | 2017-01-20 | A kind of stealthy unmanned plane based on electronic Wo Pen VTOL Flying-wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107054668A true CN107054668A (en) | 2017-08-18 |
Family
ID=59597953
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710040757.7A Pending CN107054668A (en) | 2017-01-20 | 2017-01-20 | A kind of stealthy unmanned plane based on electronic Wo Pen VTOL Flying-wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107054668A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114030636A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Design method for air inlet channel configuration of front output shaft engine helicopter |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020162914A1 (en) * | 2001-02-16 | 2002-11-07 | Jose Albero | Aircraft system architecture |
| CN104290907A (en) * | 2014-10-15 | 2015-01-21 | 西南科技大学 | Novel hybrid vertical/short take-off and landing (V/STOL) unmanned aerial vehicle |
| CN105015770A (en) * | 2015-07-29 | 2015-11-04 | 张飞 | Vertical take-off and landing aircraft with wing body blended with single duct |
| CN105314111A (en) * | 2014-06-27 | 2016-02-10 | 周彦辉 | Large-size high-speed invisible flying saucer |
| CN105620739A (en) * | 2016-02-17 | 2016-06-01 | 杨海涛 | Turbojet type multiple-spindle aircraft and control method thereof |
| CN106184741A (en) * | 2016-09-30 | 2016-12-07 | 中国科学院工程热物理研究所 | A kind of flying wing type ducted fan VUAV |
-
2017
- 2017-01-20 CN CN201710040757.7A patent/CN107054668A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020162914A1 (en) * | 2001-02-16 | 2002-11-07 | Jose Albero | Aircraft system architecture |
| CN105314111A (en) * | 2014-06-27 | 2016-02-10 | 周彦辉 | Large-size high-speed invisible flying saucer |
| CN104290907A (en) * | 2014-10-15 | 2015-01-21 | 西南科技大学 | Novel hybrid vertical/short take-off and landing (V/STOL) unmanned aerial vehicle |
| CN105015770A (en) * | 2015-07-29 | 2015-11-04 | 张飞 | Vertical take-off and landing aircraft with wing body blended with single duct |
| CN105620739A (en) * | 2016-02-17 | 2016-06-01 | 杨海涛 | Turbojet type multiple-spindle aircraft and control method thereof |
| CN106184741A (en) * | 2016-09-30 | 2016-12-07 | 中国科学院工程热物理研究所 | A kind of flying wing type ducted fan VUAV |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114030636A (en) * | 2021-11-19 | 2022-02-11 | 中国直升机设计研究所 | Design method for air inlet channel configuration of front output shaft engine helicopter |
| CN114030636B (en) * | 2021-11-19 | 2023-04-28 | 中国直升机设计研究所 | Front-output-shaft engine helicopter air inlet channel configuration design method |
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| SE01 | Entry into force of request for substantive examination | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170818 |
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| WD01 | Invention patent application deemed withdrawn after publication |