CN103507947A - Device for balancing torque for rotor craft - Google Patents
Device for balancing torque for rotor craft Download PDFInfo
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- CN103507947A CN103507947A CN201210226739.5A CN201210226739A CN103507947A CN 103507947 A CN103507947 A CN 103507947A CN 201210226739 A CN201210226739 A CN 201210226739A CN 103507947 A CN103507947 A CN 103507947A
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- spoiler
- balancing
- rotary
- rotor
- wing aircraft
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Abstract
The invention discloses a device for balancing the torque of a rotor craft. The device comprises fixed spoilers, movable spoilers, a self-balancing device base body and a rotor. According to the invention, the fixed spoilers are configured so as to generate fixed balancing torque; moreover, variable balancing torque is generated according to the added movable spoilers. Because the angle between the movable spoilers and the rotor is 10-170 degrees, the movable spoilers not only can increase the balancing torque, but also can reduce the balancing torque as required, which can not be realized by the traditional fixed spoilers. According to the invention, the balancing torque of the rotor craft can be adjusted in real time simply and conveniently by utilizing the fixed spoilers and the movable spoilers, and the flight quality and the stability of the rotor craft can be improved.
Description
Technical field
What the present invention relates to is the moment of torsion self balancing device in a kind of rotor craft field, specifically a kind of device of realizing a kind of rotary-wing aircraft torque self-balancing.
Background technology
In recent years, along with the problem of rotary-wing flight quality and stability is more and more paid attention to, the equilibrium of torques problem of rotor craft particularly.But rely on traditional solution, such as the fixing spoiler of equilibrium of torques rotor of configuration or configuration, inefficiency, and moment of torsion fixes, safety is poor, so a kind of balancing torque capable of regulating of needs and device that can self-balancing.
China application number CN 201110110471.4, application publication number CN 102219051A, a kind of quadrotor system control method based on human-computer interaction technology is disclosed in this patent, this technology is to realize flight attitude and control by being distributed in the collaborative work of four rotors on its how much summits, comprises rotary torque balance.But this technology does not propose the solution of innovation with regard to equilibrium of torques.
China application number CN 201110035206.4, application publication number CN 102092473A, discloses a kind of multi-rotor aerocraft and method in this patent.The secondary aircraft of this technology utilization is realized hovering, flight, acceleration, deceleration, lifting, is turned to, and secondary aircraft has also been born the work of rotary torque balance.But this technology can not realize reducing of balancing torque as required.
To sum up, although the problem of rotary-wing flight quality and stability has obtained certain research, in document, have no report fixedly spoiler coordinate the means for equalising of movable spoiler.
Summary of the invention
The present invention is directed to prior art above shortcomings, a kind of device of rotary-wing aircraft torque self-balancing is provided, utilize fixedly spoiler and movable spoiler can realize simply and easily the real-time adjustment of rotor craft balancing torque, flight quality and the degree of stability of raising rotor craft.
The present invention is achieved by the following technical solutions, the present invention includes: fixedly spoiler, movable spoiler, self balancing device matrix, rotor.
Described fixedly spoiler refers to for upsetting the air-flow of rotor below, the device of balance portion rotary torque.
Described fixedly spoiler and rotor angulation are 90 degree.
The quantity of described fixedly spoiler is 4-40 sheet.
Described fixedly spoiler angle is each other 9-90 degree.
The length of described fixedly spoiler is 0.1-20 centimetre.
Described movable spoiler refers to for adjusting the air-flow of rotor below, is fixed the device of spoiler balance rotating moment of torsion.
The length of described movable spoiler is scalable, and flexible scope is 0.1-3 times of fixedly spoiler length.
Described movable spoiler and rotor angle be 10-170 degree.
The quantity of described movable spoiler is 4-40 sheet.
Described movable spoiler angle is each other 9-90 degree.
Described self balancing device matrix is for fixedly spoiler and the movably carrier of spoiler are installed.
Described rotor is the device that rotor craft is used for producing power.
Rotor craft utilizes rotor to produce power, but also can produce rotary torque, affects the flight quality of rotor craft.Traditional solution is to configure an equilibrium of torques rotor or configure fixedly spoiler to improve flight quality, but equilibrium of torques rotor device is complicated, and expends the energy of rotor craft.The balancing torque that fixedly spoiler produces is also fixed, and can not adapt to the equilibrium of torques situation of rotor craft complexity in practical flight, can not guarantee the flight quality of rotor craft.Therefore, in order to adapt to the balancing torque changing in practical flight, the balancing torque that the movable spoiler of length, adjustable angle changes has been proposed.
When the balancing torque needing when rotor craft increases, the length of movable spoiler is elongated, and it is large that angle becomes; When the balancing torque of rotor craft needs diminishes, the length of movable spoiler shortens, and angle diminishes.The telescopic scope of length of movable spoiler is 0.1-3 times of fixedly spoiler length, and angle is 10-90 degree.
To sum up, the present invention is simple in structure, can meet with the balancing torque that movable spoiler changes the balancing torque changing in rotor craft practical flight, realizes the rotary-wing flight of better quality.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
The specific embodiment
Below embodiments of the invention are elaborated, the present embodiment is implemented take technical solution of the present invention under prerequisite, provided detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
As shown in Figure 1, the device of the rotary-wing aircraft torque self-balancing described in the present embodiment comprises: fixedly spoiler 1, movable spoiler 2, self balancing device matrix 3, rotor 4.
In the present embodiment, described fixedly spoiler 1 refers to for upsetting the air-flow of rotor below, the device of balance portion rotary torque.
In the present embodiment, described fixedly spoiler 1 is 90 degree with rotor angulation.
In the present embodiment, the quantity of described fixedly spoiler 1 is 4-40 sheet.
In the present embodiment, described fixedly spoiler 1 angle is each other 9-90 degree.
In the present embodiment, the length of described fixedly spoiler 1 is 0.1-20 centimetre.
In the present embodiment, described movable spoiler 2 refers to for adjusting the air-flow of rotor below, is fixed the device of spoiler balance rotating moment of torsion.
In the present embodiment, the length of described movable spoiler 2 is scalable, and flexible scope is 0.1-3 times of fixedly spoiler length.
In the present embodiment, described movable spoiler 2 and rotor angle be 10-170 degree.
In the present embodiment, the quantity of described movable spoiler 2 is 4-40 sheet.
In the present embodiment, described movable spoiler 2 angle is each other 9-90 degree.
In the present embodiment, described self balancing device matrix 3 is for fixedly spoiler and the movably carrier of spoiler are installed.
In the present embodiment,, described rotor 4 is devices that rotor craft is used for producing power.
The principle of work of the present embodiment is: in practical flight, when the balancing torque of rotor craft needs increases, the length of movable spoiler is elongated, and it is large that angle becomes, and movable spoiler produces at fixing spoiler the difference of adjusting generation target balancing torque on the basis of moment of torsion; When the balancing torque needing when rotor craft reduces, the length of movable spoiler shortens, and angle diminishes, and movable spoiler produces at fixing spoiler the difference of adjusting generation target balancing torque on the basis of moment of torsion.Because the variation along with rotor craft balancing torque of the adjustment process of movable spoiler occurs in real time, guaranteed the equilibrium of torques of rotor craft, realized the moment of torsion self-balancing in flight course.
This device disposes fixedly spoiler and produces fixing balancing torque, and according to having added movable spoiler.Due to movable spoiler and rotor angle be 10-170 degree, therefore movable spoiler not only can increase balancing torque, and can reduce as required balancing torque, this be traditional fixedly spoiler can not.
As shown in table 1, it is as shown in the table for the application request of the present embodiment.
One group of modular design parameter of the device of table 1 rotary-wing aircraft torque self-balancing
| Fixedly spoiler and rotor angulation (degree) | 90 |
| The fixing quantity of spoiler (sheet) | 4 |
| Fixing spoiler angle (degree) each other | 90 |
| Fixedly the length of spoiler (centimetre) | 5 |
| The quantity (sheet) of |
4 |
| Movable spoiler angle (degree) each other | 90 |
To sum up, utilize fixedly spoiler and movable spoiler can realize simply and easily the real-time adjustment of rotor craft balancing torque, flight quality and the degree of stability of raising rotor craft.
Although content of the present invention has been done detailed introduction by above preferred embodiment, will be appreciated that above-mentioned description should not be considered to limitation of the present invention.Those skilled in the art, read after foregoing, for multiple modification of the present invention with to substitute will be all apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (11)
1. can realize a device for rotary-wing aircraft torque self-balancing, described device comprises: fixedly spoiler, movable spoiler, self balancing device matrix, rotor.
2. the device of rotary-wing aircraft torque self-balancing according to claim 1, is characterized in that, described fixedly spoiler refers to for upsetting the air-flow of rotor below, the device of balance portion rotary torque.
3. according to the device of the rotary-wing aircraft torque self-balancing described in claim 1,2, it is characterized in that, described fixedly spoiler and rotor angulation are 90 degree.
4. according to the device of the rotary-wing aircraft torque self-balancing described in claim 1,2, it is characterized in that, the quantity of described fixedly spoiler is 4-40 sheet.
5. according to the device of the rotary-wing aircraft torque self-balancing described in claim 1,2, it is characterized in that, described fixedly spoiler angle is each other 9-90 degree.
6. the device of rotary-wing aircraft torque self-balancing according to claim 1, is characterized in that, the length of described fixedly spoiler is 0.1-20 centimetre.
7. the device of rotary-wing aircraft torque self-balancing according to claim 1, is characterized in that, described movable spoiler refers to for adjusting the air-flow of rotor below, is fixed the device of spoiler balance rotating moment of torsion.
8. the device of rotary-wing aircraft torque self-balancing according to claim 1, is characterized in that, the length of described movable spoiler is scalable, and flexible scope is 0.1-3 times of fixedly spoiler length.
9. the device of rotary-wing aircraft torque self-balancing according to claim 1, is characterized in that, described movable spoiler and rotor angle be 10-170 degree.
10. the device of rotary-wing aircraft torque self-balancing according to claim 1, is characterized in that, the quantity of described movable spoiler is 4-40 sheet.
The device of 11. rotary-wing aircraft torque self-balancings according to claim 1, is characterized in that, described movable spoiler angle is each other 9-90 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210226739.5A CN103507947A (en) | 2012-06-29 | 2012-06-29 | Device for balancing torque for rotor craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210226739.5A CN103507947A (en) | 2012-06-29 | 2012-06-29 | Device for balancing torque for rotor craft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103507947A true CN103507947A (en) | 2014-01-15 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210226739.5A Pending CN103507947A (en) | 2012-06-29 | 2012-06-29 | Device for balancing torque for rotor craft |
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| Country | Link |
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| CN (1) | CN103507947A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103847960A (en) * | 2014-03-20 | 2014-06-11 | 西北工业大学 | Composite rotation driving vertical take-off and landing aircraft |
| CN110733638A (en) * | 2019-10-31 | 2020-01-31 | 杨小松 | rotor counter-torque propeller-jacking helicopter |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4200252A (en) * | 1977-12-21 | 1980-04-29 | Summa Corporation | Helicopter antitorque system using circulation control |
| US4708305A (en) * | 1987-01-30 | 1987-11-24 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Helicopter anti-torque system using fuselage strakes |
| CN1312205A (en) * | 2000-12-29 | 2001-09-12 | 武汉大学 | Spherical crown helicopter with single rotary wing and no tail paddle |
| CN201023654Y (en) * | 2007-04-25 | 2008-02-20 | 谭清斌 | Wing wingspan augmentation device |
-
2012
- 2012-06-29 CN CN201210226739.5A patent/CN103507947A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4200252A (en) * | 1977-12-21 | 1980-04-29 | Summa Corporation | Helicopter antitorque system using circulation control |
| US4708305A (en) * | 1987-01-30 | 1987-11-24 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Helicopter anti-torque system using fuselage strakes |
| CN1312205A (en) * | 2000-12-29 | 2001-09-12 | 武汉大学 | Spherical crown helicopter with single rotary wing and no tail paddle |
| CN201023654Y (en) * | 2007-04-25 | 2008-02-20 | 谭清斌 | Wing wingspan augmentation device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103847960A (en) * | 2014-03-20 | 2014-06-11 | 西北工业大学 | Composite rotation driving vertical take-off and landing aircraft |
| CN103847960B (en) * | 2014-03-20 | 2015-08-05 | 西北工业大学 | A kind of composite rotating drives vertically taking off and landing flyer |
| CN110733638A (en) * | 2019-10-31 | 2020-01-31 | 杨小松 | rotor counter-torque propeller-jacking helicopter |
| CN110733638B (en) * | 2019-10-31 | 2021-08-17 | 杨小松 | Rotor wing reaction torque propeller-jacking helicopter |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140115 |
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| RJ01 | Rejection of invention patent application after publication |