CN206278258U - A kind of control system of the rollover of aircraft, driftage and yaw stability - Google Patents
A kind of control system of the rollover of aircraft, driftage and yaw stability Download PDFInfo
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- CN206278258U CN206278258U CN201621135232.9U CN201621135232U CN206278258U CN 206278258 U CN206278258 U CN 206278258U CN 201621135232 U CN201621135232 U CN 201621135232U CN 206278258 U CN206278258 U CN 206278258U
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- rollover
- driftage
- stabilizer
- aircraft
- control system
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Abstract
A kind of control system of the rollover of aircraft, driftage and yaw stability, including the driftage rollover stabilizer being made up of upper driftage rollover stabilizer and lower driftage rollover stabilizer, the bottom of upper driftage rollover stabilizer and the top of lower driftage rollover stabilizer are rotatably connected on the upper and lower aircraft plane of symmetry of aircraft tail end respectively, and can independently be rotated around the axle of above-below direction, on the mass centre of aircraft, lower driftage rollover stabilizer is under the mass centre of aircraft for wherein upper driftage rollover stabilizer；Two driftage rollover stabilizer size and dimensions are identical or approximate.The utility model has the advantages that：It is arranged symmetrically the simple and stable control contributed to airborne vehicle.The utility model is located on the center line of the airborne vehicle with towed machine nose propeller, to ensure its slip-stream for making full use of aero propulsion device to produce, even in low-speed operations and hovering, can produce effective rollover and driftage control.
Description
Technical field
The utility model is related to the control system of a kind of rollover of aircraft, driftage and yaw stability, belongs to aircraft control
The technical field of system processed.
Background technology
From Lai Te brother's epoch, the control system by the use of rotatable chain of command as aircraft is just had started to.Earliest flies
The elevator and rudder used on machine control the pitching and driftage/rollover of aircraft respectively.The rollover and steering of these aircrafts are all
It is very slow.Warpage wing is invented by Lai Te brothers, the independent axle of aircraft three control is realized first, and increased rollover speed
Rate, reduces radius of turn.Later, Glenn Ke Disi had invented aircraft aileron aileron to control rollover, with warpage wing
Compare, being one has the significant great invention for simplifying and improveing.
And someone has invented lifting stabilizer hereafter,（stabilator）, it be the stabilization function of horizontal stabilizer and
The control system that the pitch control function of elevator is combined.Then elevon has been invented again（elevon）, it is combined
The function of elevator and aileron, is generally used in wingflying aircraft and the body design of the mixing wing.The elevon utilizes symmetric deflection difference
To realize independent pitching and rolling control.Similar, vertical slab tail is also invented, and realizes drag iron and side
To the combination of the function of rudder.
Some fixed-wing VTOL（VTOL）Aircraft is described to be X- wing machines, there is four moveable control tables thereon
Face, is substantially two adjacent V- tails.These types may have four to be hinged on built-in stabilizer, can rotate respectively
Independent control face, similar to the conventional direction rudder and elevator of original fixed-wing aircraft.
Rudder and vertical full motivation tail are traditionally controlled not as a rollover for having notable contribution, because traditionally
Than wing much shorter, too short moment arm leads to not carry out effective rollover control vertical tail.Set for newer fuselage
Meter, including low aspect ratio fixed-wing VTOL aircraft, rollover inertia and suppress rollover aerodynamic drag be it is low-down, so
Make it possible that vertical tail surfaces were never put into practice as main rollover control, but this technology.
The content of the invention
The technical problem that the utility model is solved is to provide a kind of rollover, driftage and control of yaw stability for aircraft
System processed.
The technical solution of the utility model is：A kind of control system of the rollover of aircraft, driftage and yaw stability, its
It is characterised by, including the driftage rollover stabilizer being made up of upper driftage rollover stabilizer and lower driftage rollover stabilizer, upper driftage
The bottom of rollover stabilizer and the top of lower driftage rollover stabilizer are rotatably connected on the upper and lower flight of aircraft tail end respectively
On the device plane of symmetry, and can independently be rotated around the axle of above-below direction, wherein upper driftage rollover stabilizer is in the quality of aircraft
On the heart, lower driftage rollover stabilizer is under the mass centre of aircraft；Two driftage rollover stabilizer size and dimensions are identical
Or it is approximate.
Described upper driftage rollover stabilizer and lower driftage rollover stabilizer is equipped with and can respectively drive rollover of being gone off course on this
The drive device that stabilizer and lower driftage rollover stabilizer are deflected to identical or different direction, to produce the rollover mutually supplied
Torque or opposite rollover torque.
Described upper driftage rollover stabilizer and lower driftage rollover stabilizer is connected by the axis of rotation of above-below direction respectively
It is connected on above aircraft tail end and following, the rotating shaft passes through a transmission mechanism and be located in aircraft tail end or fuselage respectively
Motor driven is connected.
The utility model has the advantages that：When pitching rudder or similar pitch control device are combined, the utility model
All three axles control of airborne vehicle can be realized.For the all-wing aircraft and the boat of the mixing wing body of low aspect ratio that take off vertically and land
Pocket, the utility model especially has value.It is of the present utility model to be arranged symmetrically the simple peace contributed to airborne vehicle
Steady control.The utility model is located on the center line of the airborne vehicle with towed machine nose propeller, to ensure its abundant profit
The slip-stream produced with aero propulsion device, even in low-speed operations and hovering, effective rollover and driftage control can be produced.
Brief description of the drawings
Fig. 1 is dimensional structure diagram of the utility model on VTOL fixed wing aircraft（It is static or fly nonstop to shape
State）；
Fig. 2 describes the symmetric deflection by rollover stabilizer of going off course（Two parts are deflected in the same direction）To control the driftage of aircraft
Angle（It is to left drift in figure）；
Fig. 3 is illustrated and deflected by the difference of rollover stabilizer of going off course（Two parts are reversely deflected）To control the rollover of aircraft
Angle（It is to turn on one's side to the right in figure）；
Fig. 4 is illustrated and is deflected 90 ° of aerial aerobrakings and right of acquisition by the top or bottom of rollover stabilizer of going off course
Assist the schematic diagram of fuselage pitching motion.
Fig. 5 is illustrated and obtained for aerobatic with transitory loss by 90 ° of the difference deflection of rollover stabilizer of going off course
Yaw stability is the quick comprehensively aerial aerobraking of cost.
Specific embodiment
Referring to Fig. 1, the control system of a kind of rollover of aircraft of the utility model, driftage and yaw stability, including it is upper
Driftage rollover stabilizer 1 and lower driftage rollover stabilizer 2, the bottom of upper driftage rollover stabilizer 1 and lower driftage rollover stabilizer 2
Top be rotatably connected on respectively on the upper and lower aircraft plane of symmetry of aircraft tail end 3, and can be around the axle of above-below direction
Independent to rotate, wherein upper driftage rollover stabilizer 1 is on the mass centre of aircraft, lower driftage rollover stabilizer 2 is in aircraft
Under mass centre；Two driftage rollover stabilizer size and dimensions are identical or approximate.
Described upper driftage rollover stabilizer 1 and lower driftage rollover stabilizer 2 can respectively to identical or different direction
Deflection, to produce the rollover torque or opposite rollover torque mutually supplied.
Described upper driftage rollover stabilizer 1 and lower driftage rollover stabilizer 2 are respectively by the axis of rotation of above-below direction
It is connected to above aircraft tail end 3 and following, the rotating shaft passes through a transmission mechanism respectively（Routine techniques, it is not shown）Be located at
Motor in aircraft tail end 3 or fuselage（It is not shown）Drive connection.
The deflection of driftage rollover stabilizer can effectively change its own angle of attack, increase or decrease and act on the air of itself
The size and Orientation of power.Produced aerodynamic force will act predominantly on vertical and horizontal direction, almost without vertical component.Cause
Hung down for the equivalent synthesis gas power that driftage rollover stabilizer is produced can be produced at its own and the mass centre of aircraft between
Nogata to longitudinal direction on moment arm, so can produce driftage, rollover and pitching torque.
The medium symmetric deflection of driftage rollover stabilizer（I.e. upper driftage rollover stabilizer 1 and lower driftage rollover stabilizer 2 are same
To deflection, as shown in Figure 2）Main will produce approximately equalised air force in horizontal direction.The moment arm of longitudinal direction is more long,
Form powerful yawing, it is ensured that effectively driftage control.Because driftage rollover stabilizer is in the upper and lower both sides in Aircraft Quality center
Near symmetrical distribution, the size similar with its, shape and deflection angle, the Control System Design is to causing driftage-rollover coupling
Possibility there's almost no.Pitching-driftage coupling can also ignore, because produced as driftage rollover stabilizer up and down
Time averaging induced drag will be roughly equal.The medium difference deflection of driftage rollover stabilizer（As shown in Figure 3）One will be produced
The individual turning moment around fuselage axis（Clockwise or counterclockwise）And cause fuselage to turn on one's side to the right or to the left.
Depth driftage rollover stabilizer deflection will cause its own advanced stall, produce a larger longitudinal time average
Air force.When two driftage rollover stabilizer stall simultaneously, a Quick air braking function will be caused, while effectively driftage
Control and stability（Accompanying drawing 5）By transitory loss.When upper driftage rollover stabilizer 1 or the lower driftage rollover advanced stall of stabilizer 2
When（Accompanying drawing 4）, a non-zero pitching moment will be caused, it can deflect enhancing or decrease by symmetrical elevon, to cause one
Individual quick pitching moment, or aerobraking in Quick air.In this case, yaw stability and control will not lose,
Can only be weakened.
As described above, the art of this patent provides a brand-new aircraft control concept, that is, gather drag iron, direction
The function of rudder and aileron is combined into a new part for being referred to as driftage rollover stabilizer, is used to increase yaw stability and offer
Independent yaw and rollover are controlled.Driftage rollover stabilizer can also be combined the whole rotation along three axis of control aircraft with elevator
Rotate and make.
Claims (3)
1. a kind of rollover of aircraft, driftage and yaw stability control system, it is characterised in that including by it is upper driftage turn on one's side
Stabilizer（1）With lower driftage rollover stabilizer（2）The driftage rollover stabilizer of composition, upper driftage rollover stabilizer（1）Bottom
With lower driftage rollover stabilizer（2）Top be rotatably connected on aircraft tail end respectively（3）The upper and lower aircraft plane of symmetry on,
And can independently be rotated around the axle of above-below direction, wherein upper driftage rollover stabilizer（1）On the mass centre of aircraft, under
Driftage rollover stabilizer（2）Under the mass centre of aircraft；Two driftage rollover stabilizer size and dimensions are identical or approximate.
2. aircraft according to claim 1 rollover, driftage and yaw stability control system, it is characterised in that
Described upper driftage rollover stabilizer（1）With lower driftage rollover stabilizer（2）Gone off course on this rollover steady equipped with that can drive respectively
Determine device（1）With lower driftage rollover stabilizer（2）To the drive device that identical or different direction deflects, to produce what is mutually supplied
Rollover torque or opposite rollover torque.
3. aircraft according to claim 1 rollover, driftage and yaw stability control system, it is characterised in that
Described upper driftage rollover stabilizer（1）With lower driftage rollover stabilizer（2）Connected by the axis of rotation of above-below direction respectively
In aircraft tail end（3）Above and it is following, the rotating shaft is respectively by a transmission mechanism and being located at aircraft tail end（3）Or fuselage
Interior motor driven connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621135232.9U CN206278258U (en) | 2016-10-19 | 2016-10-19 | A kind of control system of the rollover of aircraft, driftage and yaw stability |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621135232.9U CN206278258U (en) | 2016-10-19 | 2016-10-19 | A kind of control system of the rollover of aircraft, driftage and yaw stability |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206278258U true CN206278258U (en) | 2017-06-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621135232.9U Expired - Fee Related CN206278258U (en) | 2016-10-19 | 2016-10-19 | A kind of control system of the rollover of aircraft, driftage and yaw stability |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206278258U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314762A (en) * | 2016-10-19 | 2017-01-11 | 吴瑞霞 | Method for controlling rollover, yaw and yaw stability of aircraft |
-
2016
- 2016-10-19 CN CN201621135232.9U patent/CN206278258U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314762A (en) * | 2016-10-19 | 2017-01-11 | 吴瑞霞 | Method for controlling rollover, yaw and yaw stability of aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170627 Termination date: 20171019 |