CN107745808A - A kind of compound helicopter - Google Patents
A kind of compound helicopter Download PDFInfo
- Publication number
- CN107745808A CN107745808A CN201711131346.5A CN201711131346A CN107745808A CN 107745808 A CN107745808 A CN 107745808A CN 201711131346 A CN201711131346 A CN 201711131346A CN 107745808 A CN107745808 A CN 107745808A
- Authority
- CN
- China
- Prior art keywords
- speed changer
- fuselage
- engine
- propeller
- dcb specimen
- 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
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
-
- 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
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- 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
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of compound helicopter, including fuselage, contrarotation DCB Specimen, transmission system and parachute；The front end of described fuselage is provided with propeller；Wing is arranged with the middle part of fuselage；The top of waist is provided with contrarotation DCB Specimen, and the top of waist contrarotation DCB Specimen is provided with parachute storehouse, parachute is provided with parachute storehouse；Described transmission system is arranged on fuselage, and transmission system is connected with contrarotation DCB Specimen, propeller respectively, can drive contrarotation DCB Specimen, propeller rotation.The present invention organically organically combines rotor, propeller and fuselage, both there is the advantages of fixed wing aircraft voyage is remote, security is good and carrying capacity is high, can solve the defects of needing runway during fixed wing aircraft landing again, vertical lift and the hovering of the present invention can be realized by rotor so that maneuverability of the present invention.
Description
Technical field
The present invention relates to a kind of aircraft, is specifically related to a kind of compound helicopter.
Background technology
With the opening of low altitude airspace, Aircraft Market is skyrocketed through.Fixed wing aircraft has flight course safe, and flight is fast
The advantages of degree is fast, and voyage is remote and carrying capacity is high, and its landing process needs to use runway and can not hovered, and adds airport and builds
If expense.Helicopter has vertical lift, and technology is simple, the advantages of maneuverability, but its cruising time it is short and, airborne vibration
Greatly.
The content of the invention
In order to solve the above-mentioned technical problem, the present invention provides a kind of cruising time length, and maneuverability, safe is compound
Helicopter.
The technical solution adopted by the present invention is：A kind of compound helicopter, including fuselage, contrarotation DCB Specimen, power train
System and parachute；The front end of described fuselage is provided with propeller；Wing is arranged with the middle part of fuselage；Set at the top of waist
There is contrarotation DCB Specimen, the top of waist contrarotation DCB Specimen is provided with parachute storehouse, landing is provided with parachute storehouse
Umbrella；Described transmission system is arranged on fuselage, and transmission system is connected with contrarotation DCB Specimen, propeller respectively, can be driven
Dynamic contrarotation DCB Specimen, propeller rotation.
In above-mentioned compound helicopter, described afterbody is provided with auxiliary direction controlling propeller.
In above-mentioned compound helicopter, described afterbody is provided with auxiliary pitch control propeller.
In above-mentioned compound helicopter, described afterbody is provided with gyroscope.
In above-mentioned compound helicopter, floating drum is provided with described fuselage.
In above-mentioned compound helicopter, described parachute storehouse is arranged on fixing axle upper end, and fixing axle lower end passes through coaxial
The interior rotor shaft of reversion DCB Specimen is fixed on fuselage.
In above-mentioned compound helicopter, the interior rotor shaft and outer rotor shaft of contrarotation DCB Specimen are connected with speed changer B, are become
Fast device B input shaft passes through clutch A and speed changer A output axis connection, speed changer A input shaft and engine A output
Axis connection；Engine A is arranged on fuselage；Engine A output shaft and speed changer C input axis connection；Speed changer C output
Axle is connected by clutch B with propeller.
In above-mentioned compound helicopter, interior rotor shaft and outer rotor shaft and speed changer B, the speed changer of contrarotation DCB Specimen
E connections, speed changer B, speed changer E input shaft respectively by clutch A, clutch C respectively with speed changer A, speed changer D it is defeated
Go out axis connection；Speed changer A, speed changer D the input shaft output axis connection with engine A, engine B respectively, engine A, hair
Motivation B is arranged on fuselage；Engine A, engine B are connected by clutch B, clutch D with speed changer C respectively, speed changer C
Output shaft be connected with propeller.
Compared with prior art, the beneficial effects of the invention are as follows：
1. the present invention organically organically combines contrarotation DCB Specimen and propeller with fuselage, both with fixed wing aircraft
The advantages of voyage is remote, security is good and carrying capacity is high, can solve the defects of needing runway during fixed wing aircraft landing again, can
To realize vertical lift and the hovering of the present invention by rotor so that maneuverability of the present invention.
2. the middle part of fuselage of the present invention is provided with parachute, can not be hindered by rotor, parachute fell in the present invention
Opened in journey, the speed that the present invention falls when landing is greatly lowered, greatly mitigate injury to personnel and impaired journey of the invention
Degree, improve the security of the present invention.
3. floating drum is arranged with the fuselage of the present invention, when the present invention is intentional or is forced to drop on the water surface, floating drum
Enough buoyancy can just be produced, it is ensured that the present invention will not sink, and improve the security of the present invention.
4. the afterbody of fuselage of the present invention is provided with auxiliary direction controlling propeller and auxiliary pitch control propeller, can aid in
Pitch control of the present invention and steering.
Brief description of the drawings
Fig. 1 is the front view of the present invention.
Fig. 2 is the left view (parachute opening) of the present invention.
Fig. 3 is the structure chart of the embodiment 1 of the transmission system of the contrarotation DCB Specimen of the present invention.
Fig. 4 is the schematic diagram of the embodiment 1 of the transmission system of the contrarotation DCB Specimen of the present invention.
Fig. 5 is the structure chart of the embodiment 2 of the transmission system of the contrarotation DCB Specimen of the present invention.
Fig. 6 is the schematic diagram of the embodiment 2 of the transmission system of the contrarotation DCB Specimen of the present invention.
In figure：1 fuselage；11 propellers；111 speed changer C；112 clutch B；113 clutch D；12 wings；13 parachutes
Storehouse；131 fixing axles；14 parachutes；15 auxiliary pitch control propellers；16 auxiliary direction controlling propellers；17 floating drums；18 is vertical
Empennage；19 tailplanes；10 gyroscopes；2 contrarotation DCB Specimens；21 engine A；22 speed changer A；23 outer rotor shafts；In 24
Rotor shaft；25 speed changer B；26 clutch A；28 speed changer D；29 speed changer E.
Embodiment
The present invention is further illustrated below in conjunction with the accompanying drawings.
As shown in figures 1 to 6, the present invention includes fuselage 1, contrarotation DCB Specimen 2, transmission system and parachute；Described machine
The front fuselage of body 1 is provided with propeller 11；The middle part of fuselage 1 is arranged with wing 12；The top at the middle part of fuselage 1 is provided with contrarotation
DCB Specimen 2, contrarotation DCB Specimen 2 are connected by transmission device 22 with engine 21.The middle part contrarotation DCB Specimen of fuselage 1
2 top is provided with parachute storehouse 13, and parachute storehouse 13 is arranged on the upper end of fixing axle 131, and the lower end of fixing axle 131 passes through inward turning
Wing axle 24 is arranged on the fuselage of fuselage 1.Parachute 14 is provided with parachute storehouse 13, the afterbody of fuselage 1 is provided with vertical tail 18, vertically
The top of empennage is provided with tailplane 19.Parachute 14 can open in drop event of the present invention, and the present invention is greatly lowered
The speed fallen when landing, greatly mitigate injury to personnel and impaired degree of the invention.
Described fuselage drive end unit is provided with auxiliary direction controlling propeller 16, auxiliary pitch control propeller 15 and gyroscope
10；Auxiliary direction controlling propeller can aid in steering operation of the present invention, and auxiliary pitch control propeller can aid in the present invention
Complete pitching operation.Floating drum 17 is arranged with described fuselage, when the present invention is intentional or is forced to drop on the water surface, is floated
Cylinder 17 can just produce enough buoyancy, it is ensured that the present invention will not sink, and improve the security of the present invention.The machine of the present embodiment
Be provided with four floating drums 17 in body 1, four floating drums 17 are located at the lower section center of gravity front and rear sides of center of gravity of the present invention, floating drum 17 using
Compressed natural gas storage tank with large volume.
As shown in Figure 3,4, the interior rotor shaft 24 of contrarotation DCB Specimen 2 of the invention and outer rotor shaft 23 respectively with speed change
Device B 25 is connected, and speed changer B 25 input shaft passes through clutch A 26 and speed changer A22 output axis connection；Speed changer A22
Input shaft and engine A 21 output axis connection, engine A 21 installs on the fuselage 1.Engine A 21 output shaft with
Speed changer C input axis connection, speed changer C output shaft are connected by clutch B112 with propeller 11.Engine A 21 can
To drive propeller 11 and contrarotation DCB Specimen 2 to act simultaneously, propeller 11 and contrarotation bispin can also be driven respectively
The single movement of the wing 2, it operates as shown in table 1.
Table 1：Monomotor transmission system operation mode and state of flight
The transmission system of the contrarotation DCB Specimen 2 of the present invention can also use two engines to realize, such as Fig. 5,6 institutes
Show.The interior rotor shaft 24 and outer rotor shaft 23 of the contrarotation DCB Specimen 2 of the present invention are connected with speed changer B25, speed changer E29,
Speed changer B25, speed changer E29 input shaft respectively by clutch A26, clutch C201 respectively with speed changer A22, become
Fast device D 28 output axis connection；Speed changer A22, speed changer D 28 input shaft respectively with engine A21, engine B27
Axis connection is exported, engine A21, engine B27 are installed on the fuselage 1.Engine A21, engine B27 pass through clutch respectively
B112, clutch D113 output shaft are connected with speed changer C 111 respectively, and speed changer C 111 output shaft and propeller 11 connect
Connect.Two engines of configuration can cause the security performance of the present invention, flying quality to be further enhanced.The present invention can adopt
The selection of various different flight states, any one engine are carried out with the offline mode of a variety of power matchings shown in table 2
Either two engines can drive rotor and propeller individually or simultaneously, eliminate single power set or driving section
Influence of the failure of part to flight safety, reduce the extent of injury caused by multiple faults while generation.
The twin-engined drive system operation modes of table 2 and state of flight
Under extremity, two engine simultaneous faults or rotor and propeller can not all work.If also one
Fixed horizontal velocity and height, the present invention can glide to find suitable landing place.If this case also has certain height
But during horizontal velocity deficiency, the parachute for the upper end of fixing axle 131 being arranged in contrarotation DCB Specimen 2 can not be by rotor
Obstruction, be pulled up launching by rocket, opened during airplane falling, speed when airplane falling lands is greatly lowered
The impaired degree of degree, greatly mitigation injury to personnel and aircraft.
Claims (8)
1. a kind of compound helicopter, it is characterized in that：Including fuselage, contrarotation DCB Specimen, transmission system and parachute；Described
The front end of fuselage is provided with propeller；Wing is arranged with the middle part of fuselage；The top of waist is provided with contrarotation DCB Specimen,
The top of waist contrarotation DCB Specimen is provided with parachute storehouse, and parachute is provided with parachute storehouse；Described transmission system
On fuselage, transmission system is connected with contrarotation DCB Specimen, propeller respectively, can drive contrarotation DCB Specimen,
Propeller rotates.
2. compound helicopter according to claim 1, it is characterized in that：Described afterbody is provided with auxiliary direction controlling spiral shell
Revolve oar.
3. compound helicopter according to claim 1 or 2, it is characterized in that：Described afterbody is provided with auxiliary pitching control
Propeller processed.
4. compound helicopter according to claim 3, it is characterized in that：Described afterbody is provided with gyroscope.
5. compound helicopter according to claim 3, it is characterized in that：Floating drum is provided with described fuselage.
6. compound helicopter according to claim 1, it is characterized in that：Described parachute storehouse is arranged on fixing axle upper end,
Fixing axle lower end is fixed on fuselage through the interior rotor shaft of contrarotation DCB Specimen.
7. compound helicopter according to claim 1 or 2, it is characterized in that：The interior rotor shaft of contrarotation DCB Specimen and outer
Rotor shaft is connected with speed changer B, speed changer B input shaft by clutch A and speed changer A output axis connection, speed changer A's
The output axis connection of input shaft and engine A；Engine A is arranged on fuselage；Engine A output shaft is defeated with speed changer C's
Enter axis connection；Speed changer C output shaft is connected by clutch B with propeller.
8. compound helicopter according to claim 1 or 2, it is characterized in that：The interior rotor shaft of contrarotation DCB Specimen and outer
Rotor shaft is connected with speed changer B, speed changer E, and speed changer B, speed changer E input shaft are divided by clutch A, clutch C respectively
Not with speed changer A, speed changer D output axis connection；Speed changer A, speed changer D input shaft respectively with engine A, engine B
Output axis connection, engine A, engine B be arranged on fuselage on；Engine A, engine B pass through clutch B, clutch respectively
Device D is connected with speed changer C, and speed changer C output shaft is connected with propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711131346.5A CN107745808A (en) | 2017-11-15 | 2017-11-15 | A kind of compound helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711131346.5A CN107745808A (en) | 2017-11-15 | 2017-11-15 | A kind of compound helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107745808A true CN107745808A (en) | 2018-03-02 |
Family
ID=61250825
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711131346.5A Pending CN107745808A (en) | 2017-11-15 | 2017-11-15 | A kind of compound helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107745808A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110641238A (en) * | 2019-11-08 | 2020-01-03 | 孙林青 | An all-round flying car with excellent safety for land, sea and air |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08150818A (en) * | 1994-11-29 | 1996-06-11 | Rokuro Hosoda | Multifunction helicopter |
| US20090159740A1 (en) * | 2007-12-21 | 2009-06-25 | Brody David E | Coaxial rotor aircraft |
| CN101602403A (en) * | 2008-06-12 | 2009-12-16 | 张庆柳 | Vertical take-off and landing aircraft (VTOL aircraft) |
| CN104401487A (en) * | 2014-11-19 | 2015-03-11 | 中国航空工业经济技术研究院 | Logistics unmanned rotor wing aircraft capable of walking on ground |
| CN105173070A (en) * | 2015-07-30 | 2015-12-23 | 北京航空航天大学 | Combined coaxial unmanned helicopter |
| CN106314785A (en) * | 2016-08-30 | 2017-01-11 | 中航沈飞民用飞机有限责任公司 | Coaxial double-rotor aircraft |
| CN207417142U (en) * | 2017-11-15 | 2018-05-29 | 孙林青 | A kind of compound helicopter |
-
2017
- 2017-11-15 CN CN201711131346.5A patent/CN107745808A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08150818A (en) * | 1994-11-29 | 1996-06-11 | Rokuro Hosoda | Multifunction helicopter |
| US20090159740A1 (en) * | 2007-12-21 | 2009-06-25 | Brody David E | Coaxial rotor aircraft |
| CN101602403A (en) * | 2008-06-12 | 2009-12-16 | 张庆柳 | Vertical take-off and landing aircraft (VTOL aircraft) |
| CN104401487A (en) * | 2014-11-19 | 2015-03-11 | 中国航空工业经济技术研究院 | Logistics unmanned rotor wing aircraft capable of walking on ground |
| CN105173070A (en) * | 2015-07-30 | 2015-12-23 | 北京航空航天大学 | Combined coaxial unmanned helicopter |
| CN106314785A (en) * | 2016-08-30 | 2017-01-11 | 中航沈飞民用飞机有限责任公司 | Coaxial double-rotor aircraft |
| CN207417142U (en) * | 2017-11-15 | 2018-05-29 | 孙林青 | A kind of compound helicopter |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110641238A (en) * | 2019-11-08 | 2020-01-03 | 孙林青 | An all-round flying car with excellent safety for land, sea and air |
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