CN105346716A - Unmanned aerial vehicle power system and vertical take-off and landing unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle power system and vertical take-off and landing unmanned aerial vehicle Download PDFInfo
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- CN105346716A CN105346716A CN201510644573.2A CN201510644573A CN105346716A CN 105346716 A CN105346716 A CN 105346716A CN 201510644573 A CN201510644573 A CN 201510644573A CN 105346716 A CN105346716 A CN 105346716A
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Abstract
An unmanned aerial vehicle power system includes a crossbar, a vertical bar, a first motor and a first propeller, the crossbar includes a first end and a second end; the first end of the vertical bar is connected with the first end or the second end of the crossbar; the second end of the vertical bar is connected with the first motor, the first motor includes a first motor bearing; and the first propeller is connected with the first motor bearing. The unmanned aerial vehicle power system comprises the crossbar and the vertical bar, installation of the motor and the propeller in the unmanned aerial vehicle power system can be facilitated, connection and location setting of the unmanned aerial vehicle power system and a vertical take-off and landing unmanned aerial vehicle can also be facilitated.
Description
Technical field
The present invention relates to a kind of unmanned plane, be related specifically to a kind of unmanned plane power system and VUAV.
Background technology
Because unmanned plane has the advantages such as small, cost is low, and along with the fast development of flight control technique, the communication technology and Eltec, the performance of unmanned plane constantly strengthens, type is on the increase, and its application demand in military domain and civil area is constantly increased.
Unmanned plane is divided into fixed-wing unmanned plane and rotary wings unmanned plane usually.
Wherein fixed-wing unmanned plane relies on engine propels, and engine drives to produce and is parallel to the horizontal thrust of fuselage axis, makes unmanned plane can high-speed flight aloft.But because engine can not produce the lift perpendicular to fuselage axis, so fixed-wing unmanned plane can only obtain lift by the relative motion between fixed-wing and air, to overcome the gravity of fixed-wing unmanned plane, there is positive correlation in the size of lift and the speed of relative movement between fixed-wing and air, speed of relative movement is larger, and the lift that fixed-wing unmanned plane obtains is also larger.In prior art, fixed-wing unmanned plane also exists two shortcomings: the first, needs longer runway that fixed-wing unmanned plane just can be made to obtain enough horizontal velocities, obtain enough lift take off to make fixed-wing unmanned plane when taking off; The second, fixed-wing unmanned plane needs to keep enough flying speeds could obtain enough lift to overcome the gravity of self after take off.
Rotary wings unmanned plane relies on engine to make rotary wings around own axes rotation, and rotary wings time rotational and air produce relative motion and obtain lift.Because the lift of rotary wings unmanned plane generation directly drives rotary wings from transferring to produce by engine, therefore rotary wings unmanned plane takes off without the need to having horizontal flight speed, namely no longer relies on runway, overcomes the shortcoming of fixed-wing unmanned plane dependence compared with long runway.Meanwhile, rotary wings unmanned plane also overcomes the shortcoming of the flying speed needing to keep enough after fixed-wing unmanned plane takes off, rotary wings unmanned plane can vertical lift, hovering, left and right flight forwards, backwards, there is the diversified advantage of flight attitude.But due to the mainly lift that rotary wings provides, the horizontal thrust being parallel to fuselage axis that rotary wings unmanned plane obtains is less, so horizontal flight speed is slower.
In sum, in prior art, unmanned plane or need to rely on long runway, and need after taking off to keep enough flying speed; Horizontal flight speed is slower.
Summary of the invention
The problem that the present invention solves is unmanned plane or need to rely on long runway in prior art, and needs after taking off to keep enough flying speed; Horizontal flight speed is slower.
For solving the problem, the invention provides a kind of unmanned plane power system, comprising:
Cross bar, described cross bar comprises first end and the second end;
Vertical pole, the first end of described vertical pole is connected with the first end of cross bar or the second end;
First motor, the first motor is connected with the second end of vertical pole, and the first motor comprises the first motor bearings;
First screw propeller, the first screw propeller is connected with the first motor bearings.
Further, the quantity of vertical pole is two, and a vertical pole is connected with the first end of cross bar, and another vertical pole is connected with the second end of cross bar.
Further, the axes normal of described vertical pole is in the axis of cross bar.
Further, described vertical pole is fixedly connected with cross bar or is structure as a whole.
Further, also comprise: autopilot, autopilot can control the rotating speed of motor.
Compared with prior art, technical scheme of the present invention has the following advantages:
Described unmanned plane power system has cross bar and vertical pole, facilitates the installation of motor and screw propeller in unmanned plane power system, also facilitates the connection between unmanned plane power system and VUAV and position to set.
The present invention also provides a kind of VUAV, comprising: above-mentioned unmanned plane power system, fuselage and wing; Described cross bar is connected with wing, and cross bar axis being parallel is in fuselage axis; Or described cross bar is connected with fuselage, cross bar axes normal is in the fuselage plane of symmetry.
Further, described unmanned plane power system comprises autopilot, and described autopilot is arranged in fuselage.
Further, also comprise:
Second motor, the second motor is connected with afterbody; Or the second motor is connected with fuselage head;
Second motor comprises the second motor bearings, and the angle of the second motor bearings and fuselage axis is 0 °;
Second screw propeller, the second screw propeller is connected with the second motor bearings.
Further, the quantity of described cross bar is two, and the quantity of described first motor and the first screw propeller is four; Described four the first motors along the distribution of fuselage plane of symmetry Mirror Symmetry, and indulge face Mirror Symmetry distribution along fuselage.
Further, the second end of described vertical pole is on the upside of fuselage.
Compared with prior art, technical scheme of the present invention has the following advantages:
In technical scheme of the present invention, VUAV can provide lift that VUAV zero level is flown by unmanned plane power system and takes off and land, or aloft hovers.
Further, also comprise the second motor, because the angle of the second motor bearings axis and fuselage axis is 0 °, so the first motor can drive the second screw propeller to produce the power being parallel to fuselage axis around own axes rotation, VUAV high-speed horizontal flight can be made.To overcome in prior art unmanned plane or need to rely on long runway, and needing after taking off to keep enough flying speeds; Horizontal flight speed is slower.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of a kind of unmanned plane power system of first embodiment of the invention;
Fig. 2 is the schematic diagram of a kind of VUAV of second embodiment of the invention;
Fig. 3 is the schematic diagram of the another kind of VUAV of second embodiment of the invention.
Detailed description of the invention
Unmanned plane or need to rely on long runway in prior art, and need after taking off to keep enough horizontal flight speed; Horizontal flight speed is slower.
For enabling above-mentioned purpose of the present invention, feature and advantage more become apparent, and are described in detail specific embodiments of the invention below in conjunction with accompanying drawing.
Compared with fixed-wing unmanned plane, VUAV with zero velocity takeoff and anding, can possess hover capabilities, and can with the mode horizontal flight of fixed-wing flight.VUAV without dependence, and has the advantage that can hover to runway.
Compared with rotary wings unmanned plane, VUAV has much higher forward flight speed, and has larger voyage.
Just based on these advantages, VUAV is particularly useful for needs hovering or landing site is had to the occasion of particular/special requirement.
First embodiment
Present embodiments provide a kind of unmanned plane power system.
With reference to figure 1, described unmanned plane power system comprises cross bar 1, and described cross bar 1 comprises first end and the second end.Vertical pole 2, the first end of described vertical pole 2 is connected with the first end of cross bar 1 or the second end.
In the present embodiment, the first end of described cross bar 1 and the second end are all connected with vertical pole 2.The axes normal of described vertical pole 2 is in the axis of cross bar 1, and described vertical pole 2 is fixedly connected with cross bar 1 or is structure as a whole.
Second end of described vertical pole 2 is connected with the first motor 3, first motor 3 and comprises the first motor bearings, and described first motor bearings connects the first screw propeller 4.
In the present embodiment, the first motor 3 is connected with vertical pole 2 by the second end embedding vertical pole 2, and the first motor bearings passes the second end of vertical pole 2, and is connected with the first screw propeller 4.
In the present embodiment, the quantity of described cross bar 1 is two, and the quantity of described first motor 3 and the first screw propeller 4 is four, and this power system is conducive to provide pulsation-free lift, and effectively can control the flight attitude of unmanned plane.
In the present embodiment, unmanned plane power system also comprises autopilot 5, and autopilot 5 can control the rotating speed of motor.
Compared with prior art, the technical scheme of the present embodiment has the following advantages:
Described unmanned plane power system has cross bar 1 and vertical pole 2, facilitates the installation of motor and screw propeller in unmanned plane power system, also facilitates the connection between unmanned plane power system and VUAV and position to set.
Second embodiment
Present embodiments provide a kind of VUAV.
With reference to figure 2, VUAV provided by the invention, comprising:
Fuselage 6 and wing 7.
Described fuselage 6 is that Mirror Symmetry is arranged along the plane of symmetry, and the described plane of symmetry is called the fuselage plane of symmetry.Through VUAV center of gravity, and be that fuselage indulges face perpendicular to the plane of fuselage axis.
In the present embodiment, described fuselage 6 is provided with slot, described wing 7 is connected with fuselage 6 by embedding described slot, and this design makes described wing 7 detachable.
Described fuselage 6 afterbody is provided with vertical fin 8, and described vertical fin 8 is symmetrical arranged along the fuselage plane of symmetry.
In an embodiment, described VUAV also comprises the unmanned plane power system described in the first embodiment.Cross bar 1 is connected with wing 7, and cross bar 1 axis being parallel is in fuselage axis.
Second end of described vertical pole 2, on the upside of fuselage, makes the first motor 3 drive the first screw propeller 4 to produce lift around own axes.In the present embodiment, cross bar 1 axes normal is in vertical pole 2 axis, and this design, the power that the first screw propeller 4 time rotational produces is lift, and the power on other directions is zero.
The quantity of described cross bar 1 is two, and the quantity of described first motor 3 and the first screw propeller 4 is four; Described four the first motors 3 along the distribution of fuselage plane of symmetry Mirror Symmetry, and indulge face Mirror Symmetry distribution along fuselage.
First motor 3 drives the first screw propeller 4 when own axes rotation produces lift, and the center of described lift, on the center of gravity line of VUAV, can make VUAV keep balance.
Described unmanned plane power system also comprises autopilot, and described autopilot is arranged in fuselage 6.
In other embodiments, described VUAV also comprises: the common components such as elevating rudder, aileron and yaw rudder.Controlled the first motor 3 by autopilot, elevating rudder, aileron are also connected with autopilot with yaw rudder simultaneously, are coordinated by the control output of autopilot unification to VUAV.
In the present embodiment, fuselage 6 afterbody or head are connected with the second motor 9, second motor 9 and comprise the second motor bearings, and the angle of the second motor bearings and fuselage axis is 0 °, namely the second motor bearings be parallel to fuselage axis or with fuselage dead in line.The direction that this design can ensure the power that the second motor 9 drives screw propeller rotation to produce also with fuselage axis line parallel or overlap, and then makes VUAV keep balance when flying.
In the present embodiment, the second electrical axis and fuselage dead in line, and the second motor 9 is connected with fuselage 6 afterbody, connection mode can be that the second motor 9 is embedded fuselage 6 afterbody, and the second motor bearings is positioned at fuselage 6 tail section exterior, and is connected with screw propeller.
Described second motor bearings and second revolves oar and is connected, and described second motor 9 drives the second screw propeller rotation to produce thrust.When second motor 9 starts, described VUAV can high-speed horizontal flight, overcomes the shortcoming that in prior art, rotary wings unmanned plane forward flight speed is low.
In other embodiments, the second motor 9 is connected with fuselage head, and the second motor 9 drives the second screw propeller rotation to produce pulling force, and when the second motor 9 starts, pulling force also can make described VUAV high-speed horizontal flight.
With reference to figure 3, in other embodiments, cross bar 1 is connected with fuselage, and cross bar 1 axes normal is in the fuselage plane of symmetry, and cross bar 1 axes normal is in vertical pole 2 axis.This design, the power that the first motor 3 drives the first screw propeller 4 time rotational to produce is lift, and the power on other directions is zero.
Introduce the method for operation of the VUAV in the present embodiment below:
When taking off, the second motor 9 does not start, and the first motor 3 starts, and makes the first screw propeller 4 around own axes rotation, for VUAV provides lift; When the lift that the first screw propeller 4 produces is greater than the gravity of VUAV, the starting of VUAV takes off.
After VUAV takes off, the second motor 9 keeps cutting out, and flies before VUAV can be made to keep hovering or low speed.By the various combination of the first motor 3, the pitching of differentiating control VUAV, rolling and driftage can also be adopted.
Second motor 9 does not start, and reduce the rotating speed of the first screw propeller 4 gradually, lift reduces gradually, when lift is less than the gravity of VUAV, VUAV start landing.
After VUAV rises and flies to certain altitude, first screw propeller 4 keeps rotating speed constant, make VUAV held stationary, start the second motor 9, the second screw propeller rotation is made to produce thrust, the horizontal flight speed of VUAV starts to accelerate, and VUAV enters the transition stage of takeoff condition to level flight condition.When VUAV reach certain horizontal flight speed after, the first motor 3 quits work, and VUAV enters level flight condition.
When VUAV needs hovering, the second motor 9 quits work, and the thrust that the second screw propeller produces is kept to zero; First motor 3 starts, and drives the first screw propeller 4 rotation to produce lift, and make VUAV keep present level flight, when horizontal flight speed reduces to zero, VUAV is in floating state.
Although the present invention discloses as above, the present invention is not defined in this.Any those skilled in the art, without departing from the spirit and scope of the present invention, all can make various changes or modifications, and therefore protection scope of the present invention should be as the criterion with claim limited range.
Claims (10)
1. a unmanned plane power system, is characterized in that, comprising:
Cross bar, described cross bar comprises first end and the second end;
Vertical pole, the first end of described vertical pole is connected with the first end of cross bar or the second end;
First motor, the first motor is connected with the second end of vertical pole, and the first motor comprises the first motor bearings;
First screw propeller, the first screw propeller is connected with the first motor bearings.
2. unmanned plane power system as claimed in claim 1, it is characterized in that, the quantity of vertical pole is two, and a vertical pole is connected with the first end of cross bar, and another vertical pole is connected with the second end of cross bar.
3. unmanned plane power system as claimed in claim 1, it is characterized in that, the axes normal of described vertical pole is in the axis of cross bar.
4. the unmanned plane power system as described in claim 1 or 3, is characterized in that, described vertical pole is fixedly connected with cross bar or is structure as a whole.
5. unmanned plane power system as claimed in claim 1, is characterized in that, also comprise:
Autopilot, autopilot can control the rotating speed of motor.
6. a VUAV, is characterized in that, comprises by the arbitrary described unmanned plane power system of claim 1-5, fuselage and wing; Described cross bar is connected with wing, and cross bar axis being parallel is in fuselage axis; Or,
Described cross bar is connected with fuselage, and cross bar axes normal is in the fuselage plane of symmetry.
7. VUAV as claimed in claim 6, it is characterized in that, described unmanned plane power system comprises autopilot, and described autopilot is arranged in fuselage.
8. VUAV as claimed in claim 6, is characterized in that, also comprise:
Second motor, the second motor is connected with afterbody; Or the second motor is connected with fuselage head;
Second motor comprises the second motor bearings, and the angle of the second motor bearings and fuselage axis is 0 °;
Second screw propeller, the second screw propeller is connected with the second motor bearings.
9. VUAV as claimed in claim 6, it is characterized in that, the quantity of described cross bar is two, and the quantity of described first motor and the first screw propeller is four; Described four the first motors along the distribution of fuselage plane of symmetry Mirror Symmetry, and indulge face Mirror Symmetry distribution along fuselage.
10. VUAV as claimed in claim 6, it is characterized in that, the second end of described vertical pole is on the upside of fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510644573.2A CN105346716A (en) | 2015-09-30 | 2015-09-30 | Unmanned aerial vehicle power system and vertical take-off and landing unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510644573.2A CN105346716A (en) | 2015-09-30 | 2015-09-30 | Unmanned aerial vehicle power system and vertical take-off and landing unmanned aerial vehicle |
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| CN105346716A true CN105346716A (en) | 2016-02-24 |
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| CN201510644573.2A Pending CN105346716A (en) | 2015-09-30 | 2015-09-30 | Unmanned aerial vehicle power system and vertical take-off and landing unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005401A (en) * | 2016-08-08 | 2016-10-12 | 北京奇正数元科技股份有限公司 | Unmanned aerial vehicle tail tilting pair power mechanism |
| CN107352029A (en) * | 2016-05-09 | 2017-11-17 | 中国科学院沈阳自动化研究所 | A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4784351A (en) * | 1978-03-22 | 1988-11-15 | Karl Eickmann | Aircraft with a plurality of propellers, a pipe structure for thereon holdable wings for vertical take off and landing |
| CN101857086A (en) * | 2010-06-03 | 2010-10-13 | 哈尔滨盛世特种飞行器有限公司 | Dual-culvert vertical take-off and landing unmanned aerial vehicle |
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| US20120261523A1 (en) * | 2010-10-06 | 2012-10-18 | Donald Orval Shaw | Aircraft with Wings and Movable Propellers |
| KR20130005501A (en) * | 2011-07-06 | 2013-01-16 | 부산대학교 산학협력단 | Unmanned air vehicle |
| CN202953167U (en) * | 2012-09-26 | 2013-05-29 | 北京观典航空设备公司 | Unmanned aerial vehicle with wing inserted fixing device |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
-
2015
- 2015-09-30 CN CN201510644573.2A patent/CN105346716A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4784351A (en) * | 1978-03-22 | 1988-11-15 | Karl Eickmann | Aircraft with a plurality of propellers, a pipe structure for thereon holdable wings for vertical take off and landing |
| CN101857086A (en) * | 2010-06-03 | 2010-10-13 | 哈尔滨盛世特种飞行器有限公司 | Dual-culvert vertical take-off and landing unmanned aerial vehicle |
| US20120261523A1 (en) * | 2010-10-06 | 2012-10-18 | Donald Orval Shaw | Aircraft with Wings and Movable Propellers |
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| KR20130005501A (en) * | 2011-07-06 | 2013-01-16 | 부산대학교 산학협력단 | Unmanned air vehicle |
| CN202953167U (en) * | 2012-09-26 | 2013-05-29 | 北京观典航空设备公司 | Unmanned aerial vehicle with wing inserted fixing device |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107352029A (en) * | 2016-05-09 | 2017-11-17 | 中国科学院沈阳自动化研究所 | A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system |
| CN106005401A (en) * | 2016-08-08 | 2016-10-12 | 北京奇正数元科技股份有限公司 | Unmanned aerial vehicle tail tilting pair power mechanism |
| CN106005401B (en) * | 2016-08-08 | 2018-08-21 | 北京奇正数元科技股份有限公司 | A kind of unmanned plane tail verts secondary dynamic structure |
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Application publication date: 20160224 |