CN201317462Y

CN201317462Y - Small hybrid power flying platform

Info

Publication number: CN201317462Y
Application number: CNU2008202183187U
Authority: CN
Inventors: 杜小林; 孙丽; 韩刚; 朱爱华
Original assignee: SHENYANG RUIYI TECHNOLOGY Co Ltd
Current assignee: Liaoning Jingwei Surveying & Mapping Co., Ltd.
Priority date: 2008-09-28
Filing date: 2008-09-28
Publication date: 2009-09-30
Anticipated expiration: 2018-09-28

Abstract

The utility model relates to a small hybrid power flying platform, which is realized by adopting an oil-electricity mixed mechanism through a single propeller or double propellers. An oil-electricity mixed power device is adopted, and an internal combustion engine and an electric motor can independently supply the power, and a front-towing and rear-pushing layout is adopted. By switching the control system, three work statuses such as independent work of the gasoline engine, independent work of the motor and simultaneous work of the gasoline engine and the motor can be realized. At the same time, the power device also can realize the propeller-sharing driving mode through a transmission mechanism. With the small hybrid power flying platform, the small flyer can work in the high altitude area.

Description

The miniature hybrid power flying platform

Technical field:

The utility model relates to a kind of actuating device of miniature self-service beam riding device, especially a kind of miniature hybrid power flying platform.

Background technology:

Known Miniature Vehicle platform almost only adopts a kind of propulsion source to fly at present.Useful oil electricity form also be to rely on solar poweredly, its limitation is arranged.Small aircraft, particularly small-sized unmanned aircraft generally adopt compact internal combustion engine.Principle by burning can be known, reach desirable burning and need satisfy certain conditions, compares as temperature, air pressure, relative humidity, fuel and density of air etc.And small-sized spark ignition engine can only be in normal operation under the specific environment.But owing to the increase of earth surface air with sea level elevation thins out, small-sized spark ignition engine does not have supercharging equipment, can not work in high height above sea level spatial domain, and make the operating range of SUAV (small unmanned aerial vehicle) limited.The fugitiveness of internal combustion engine makes the operation of unmanned plane have very big risk simultaneously, and ground object is constituted potential safety hazard.Because engine noise is bigger, at some special dimension, as low-altitude reconnaissance, gives away one's position easily.

Summary of the invention:

At above-mentioned the deficiencies in the prior art, the utility model provides a kind of compatible with environment strong, safe and reliable miniature hybrid power flying platform.

For achieving the above object, the technical solution adopted in the utility model is: the miniature hybrid power flying platform, it adopts oil, electric mixed organization, and realizes by single screw or twin-propeller structure.

The engine installation that the utility model has adopted oil, electricity to mix, combustion engine and electronic function independently provide power, take to pull in front and others push behind layout.By handover control system, the three kinds of mode of operations of can realizing that spark ignition engine works independently, motor works independently and oily mechanical, electrical machine is worked simultaneously.Engine installation also can be realized oar drive pattern altogether by transmission device simultaneously.The utility model can make small aircraft in high height above sea level regional work.

Description of drawings:

Fig. 1 is the utility model twin screw scenario-frame scheme drawing.

Fig. 2 is the structural representation of the utility model single screw scheme.

Fig. 3 is the structural representation of transmission device among Fig. 2.

Fig. 4 is the External view of SUAV (small unmanned aerial vehicle).

Fig. 5 is the left view of Fig. 4.

Fig. 6 is the birds-eye view of Fig. 4.

Fig. 7 is a principle of work block diagram of the present utility model.

The specific embodiment:

Embodiment one

By aircraft aerodynamics as can be known, the center of gravity of aircraft is relatively-stationary.Because the consumption of fuel, the weight of aircraft will alleviate, and will inevitably cause the aerodynamic variation of complete machine, and Fuel Tank is most important in the residing position of aircraft.Therefore, as shown in Figure 1, the utility model adopts twin-propeller structure to realize: Fuel Tank 4 is positioned at the center of gravity of airplane 12 places.For the trim machine gravity, the power battery pack 7 that quality is bigger is positioned over front fuselage, looks machine gravity and adjusts.Oil power pack 3 and Electronmotive Force group 8 are installed on the rear and front end of fuselage respectively.Oil power pack 3 is connected with after screw 1; Electronmotive Force group 8 is connected with front propeller 9.The rear end power pack provides thrust, and the front end power pack provides pulling force, and the front and back position of two kinds of power system configurations is interchangeable.Consider air resistance, screw propeller all adopts folded form.When taking off, look the airport condition and can take off separately with oily power pack 3, also can take off simultaneously with oily power pack 3 and Electronmotive Force group 8.After arriving safe altitude, close Electronmotive Force group 8, be that power continues to climb with oily power pack 3, after unmanned plane climbs the height of oily power pack 3 cisco unity malfunctions, the startup Electronmotive Force group 8 arrival object height that continues to climb, and do cruising flight.After finishing the work, make full use of the gravitional force of aircraft, relying on spirals glides reduction highly.For guaranteeing safety, start Electronmotive Force group 8 once more behind the arrival certain altitude, drive is landed.

As Fig. 4-shown in Figure 6, adopt the unmanned plane of double-propeller structure can use this profile feature: two shoes and flying wing type layout.When two kinds of power are worked simultaneously, before being in, draws in the wake flow of oar by the pusher oar, according to the flying speed of different aircraft and the rotating speed of screw propeller, be in long-pending should the amassing with rotating speed is of the pitch of the screw propeller in the wake flow and rotating speed greater than the pitch of the screw propeller of routine.Therefore, forward and backward screw propeller should adopt different pitches.

Embodiment two

As shown in Figure 2, the utility model can also adopt the structure of single screw to realize: oily power pack 3 is connected by transmission device 14 with Electronmotive Force group 8, and outputting power drives a screw propeller 13.This power adopts propulsion mode, considers air resistance, and screw propeller 13 adopts folded form.When taking off, look the airport condition and take off perhaps catapult-assisted take-off with oily power pack 3 separately.After unmanned plane climbs the height of oily power pack 3 cisco unity malfunctions, start the Electronmotive Force group 8 arrival object height that continues to climb, and do cruising flight.After finishing the work, make full use of the gravitional force of aircraft, relying on spirals glides reduction highly.For guaranteeing safety, start Electronmotive Force group 8 once more behind the arrival certain altitude, drive is landed.

As shown in Figure 3, transmission device 14 is by unilateral bearing A15, unilateral bearing B16, and electrical machine belt pulley 17, oily machine belt wheel 18 and synchronous belt 19 constitute.Motor output shaft 20 is connected with unilateral bearing A15.Oil machine output shaft 21 is connected with unilateral bearing B16.Screw propeller 13 is connected with oily machine belt wheel 18.Synchronous belt 19 couples together two belt wheels.Unilateral bearing B16 is in the oily machine belt wheel 18.Unilateral bearing A15 is in the electrical machine belt pulley 17.

Work as oil start, when motor quits work.Oil machine output shaft 21 rotates counterclockwise, and unilateral bearing B16 is locked, and oily machine belt wheel 18 rotates counterclockwise, and screw propeller 13 also rotates counterclockwise, and flying power is provided.Because this moment, motor did not start, under the drive of synchronous belt 19, electrical machine belt pulley 17 relative motor output shafts 20 clockwise rotate, and unilateral bearing A15 is not locked, electrical machine belt pulley 17 freedom.

Work as electric motor starting, when oily machine quits work.Motor output shaft 20 rotates counterclockwise, and unilateral bearing A15 is locked, and electrical machine belt pulley 17 rotates counterclockwise.Because this moment, oily machine did not start, the oily relatively machine belt wheel 18 of oily machine output shaft 21 clockwise rotates, and unilateral bearing B16 is not locked, oily machine belt wheel 18 freedom.Drive oily machine belt wheel 18 by synchronous belt 19 and rotate counterclockwise, the screw propeller 13 that links to each other with oily machine belt wheel 18 rotates counterclockwise, and flying power is provided.

As shown in Figure 7: mode is divided into two kinds, and the one, send instruction by ground control system, by the data radio station emission, airborne data radio station received signal passes to the self-driving instrument.Self-driving instrument processing signals also controls respectively that throttle size had both been controlled in the steering wheel position and the control electronic governor had both been controlled motor speed.Another kind is by setup program, self-driving instrument automatic guidance.

Claims

1, the miniature hybrid power flying platform is characterized in that, it adopts oil, electric mixed organization, and realizes by single screw or twin-propeller structure.

2, miniature hybrid power flying platform as claimed in claim 1 is characterized in that, adopts twin-propeller structure: Fuel Tank (4) is positioned at the center of gravity of airplane (12) and locates; For the trim machine gravity, power battery pack (7) is positioned over front fuselage, look machine gravity and adjust; Oil power pack (3) and Electronmotive Force group (8) are installed on the rear and front end of fuselage respectively; Oil power pack (3) is connected with after screw (1); Electronmotive Force group (8) is connected with front propeller (9); The rear end power pack provides thrust, and the front end power pack provides pulling force.

3, miniature hybrid power flying platform as claimed in claim 1 or 2 is characterized in that, the front and back position of oil, two kinds of actuating units of electricity is interchangeable.

4, miniature hybrid power flying platform as claimed in claim 1 or 2 is characterized in that, forward and backward screw propeller all adopts folded form, the pitch difference.

5, miniature hybrid power flying platform as claimed in claim 2 is characterized in that, adopts the unmanned plane of double-propeller structure can use two shoes and flying wing type layout.

6, miniature hybrid power flying platform as claimed in claim 1 is characterized in that, adopt the structure of single screw: oily power pack (3) is connected by transmission device (14) with Electronmotive Force group (8), and outputting power drives a screw propeller (13).

As claim 1 or 6 described miniature hybrid power flying platforms, it is characterized in that 7, described screw propeller (13) adopts folded form.