GB2043562A - Control surfaces of aircraft - Google Patents
Control surfaces of aircraft Download PDFInfo
- Publication number
- GB2043562A GB2043562A GB8005928A GB8005928A GB2043562A GB 2043562 A GB2043562 A GB 2043562A GB 8005928 A GB8005928 A GB 8005928A GB 8005928 A GB8005928 A GB 8005928A GB 2043562 A GB2043562 A GB 2043562A
- Authority
- GB
- United Kingdom
- Prior art keywords
- control
- aircraft
- valve
- control signal
- auxiliary
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Pressure Circuits (AREA)
- Servomotors (AREA)
- Toys (AREA)
Abstract
An aircraft has an auxiliary control surface/or canard 2 which normally moves freely in the surrounding flow, but upon the application of a control signal at 14, the surface is coupled to a servo device 11 which drives surface 2 to a desired position. The lever 8 which actuates, surface 2 is coupled to the piston 6 of a hydraulic servo cylinder 5. Cylinder 5 is normally by-passed by a pipeline 12, thus permitting free movement of surface 2. A by-pass valve 13 is provided in pipeline 12 and upon application of control signal 14, valve 13 closes and piston 6 is driven to a desired position by servo device 11 via a control valve 9. <IMAGE>
Description
SPECIFICATION
Control surfaces of aircraft
The invention relates to an aircraft with auxiliary control surfaces which may be controlled by servomotors.
In modern aircraft there is a trend towards using auxiliary control surfaces. These auxiliary control surfaces make it possible to carry out rapid corrections in the course and to neutralize the effects of movements during flight by means of direct control of buoyancy or lift or direct lateral force control. The use of these auxiliary devices producing driving control force has special advantages for target and landing approach runs and is therefbre particularly valuable in fighter aircraft.
It is known to use the already existing devices for producing driving control force in aircraft for such purposes e.g. landing flaps or transverse rudder controls for controlling elevation and external load carrying devices (py lons) for lateral control. As already mentioned however additional control surfaces namely so-called canards are also used for lateral control which have a stabilizing or destablizing effect on the aircraft---depending on their position with respect to the centre of gravity of the aircraft. A stablizing action is produced for an aircraft if an auxiliary control surface is arranged behind its centre of gravity while an auxiliary control surface has a destablizing effect if arranged in front of the centre of gravity of the aircraft.When setting an auxiliary control surface the balance of moments is disturbed and must be compensated by setting the conventional controls so that the desired flight path is maintained. The resultant driving force or torque of the conventional controls either increases or decreases the effectiveness of the auxiliary control surface depending on whether this surface is in its destablizing or its stabilizing position.
Thus, this stability effect constitutes a disadvantage in an aircraft having auxiliary control surfaces which may be set by servomotors.
According to the present invention there is provided an aircraft having at least one auxiliary control surface, drive means which may be coupled to said surface to position it, and control means responsive to a control signal and connected to said drive means, wherein, in one condition of the control signal, the surface is decoupled from said drive means so that the surface may move with the surrounding flow and, in another condition of said control signal, said drive means is coupled to said surface.
The drive means is preferably a hydraulic servo-cylinder which is bridged by a pipeline including a by-pass valve which constitutes said control means, the valve being open in response to said first-mentioned condition of the control signal and closed in response to said other condition of the control signal.
A preferred embodiment of the present invention will now be described in greater detail by way of example only with reference to the accompanying drawings, in which:
Figure 1 shows a general view of a portion of an aircraft in accordance with the present invention; and
Figure 2 shows a plan view of the aircraft of
Fig. 1.
As Figs. 1 and 2 show, a control surface 2 is arranged on the fuselage of an aircraft 1.
The aircraft may have control surfaces in front of and/or behind its centre of gravity. The control surface 2 is mounted pivotally on the aircraft 1 with a shaft 4. In order to set the control surface 2 there is an hydraulic servo cylinder 5 the piston 6 which actuates servo lever 8 of the control surface 2 via a piston rod 7. The servo cylinder 5 is, as is usual, supplied with hydraulic fluid through a control valve 9, the control piston 10 of which may be set by means of an electrical servo setting device 11. The electrical servo device 11 is settable. The operating spaces of the servo cylinder (5) produced by the piston 6 are bridged by means of a pipeline 1 2 with a normally-open valve 1 3 which is connected therein.Thus under normal conditions the bypass valve 1 3 permits the control surface 2 to move about in dependence on the flow. Thus valve 1 3 provides a free running arrangement. The electric servo device 11 and the valve 1 3 may be triggered by means of an electric control signal 1 4.
When the aircraft 1 is on a mission then for certain manoeuvres especially when fighter aircraft are in air combat, the control action may be applied to the control surface 2. The control signal 1 4 produced or given in this case therefore controls the normally open valve 1 3 and ensures that it is closed. As a result the bypass is removed so that a desired setting of the control surface may be undertaken by adjusting the control valve 9 via the electrical servo device 11.
Thus, the present invention has the advantage that the stability effect of the auxiliary control surface is avoided and that if necessary, especially in fighter aircraft, there are excellent control and steering facilities.
When required, the device provides exceptional control properties as a result of an additional or auxiliary control surface. The stability effect due to the by-pass which would occur at other times is avoided by means of the by-pass valve permitting the control surface 2 to be slowly moved about in dependence on the flow.
1. An aircraft having at least one auxiliary control surface, drive means which may be coupled to said surface to position it, and control means responsive to a control signal
**WARNING** end of DESC field may overlap start of CLMS **.
Claims (4)
1. An aircraft having at least one auxiliary control surface, drive means which may be coupled to said surface to position it, and control means responsive to a control signal and connected to said drive means, wherein, in one condition of the control signal, the surface is decoupled from said drive means so that the surface may move with the surrounding flow and, in another condition of said control signal, said drive means is coupled to said surface.
2. An aircraft according to Claim 1, wherein said drive means is a hydraulic servo cylinder.
3. An aircraft according to Claim 2, wherein said cylinder is bridged by a pipeline including a by-pass valve which constitutes said control means, the valve being open in response to said first-mentioned condition of the control signal and closed in response to said other condition of the control signal.
4. An aircraft having at least one auxiliary control surface substantially as herein described with reference to the accompanying drawings.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19792906889 DE2906889C2 (en) | 1979-02-22 | 1979-02-22 | Airplane with control surfaces in front of and behind the center of gravity |
Publications (2)
Publication Number | Publication Date |
---|---|
GB2043562A true GB2043562A (en) | 1980-10-08 |
GB2043562B GB2043562B (en) | 1983-03-09 |
Family
ID=6063635
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB8005928A Expired GB2043562B (en) | 1979-02-22 | 1980-02-21 | Control surfaces of aircraft |
Country Status (3)
Country | Link |
---|---|
DE (1) | DE2906889C2 (en) |
FR (1) | FR2449592A1 (en) |
GB (1) | GB2043562B (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2719548B1 (en) * | 1994-05-03 | 1996-07-05 | Aerospatiale | Transport plane with front tail. |
FR2778163B1 (en) | 1998-04-29 | 2000-06-23 | Aerospatiale | AIRCRAFT WITH LOWER SAIL EFFORTS |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2112757A (en) * | 1935-03-03 | 1938-03-29 | Billioque Elie Jean Henri | Stabilizing device for aeroplanes |
DE2355979B2 (en) * | 1973-11-09 | 1976-12-02 | Dornier Gmbh, 7990 Friedrichshafen | ADDITIONAL CONTROL DEVICE FOR AIRCRAFT |
FR2405869A1 (en) * | 1977-10-17 | 1979-05-11 | Onera (Off Nat Aerospatiale) | Canard for supersonic aircraft - has stabiliser disconnected from flying controls to facilitate transition to supersonic speed |
-
1979
- 1979-02-22 DE DE19792906889 patent/DE2906889C2/en not_active Expired
-
1980
- 1980-01-22 FR FR8001343A patent/FR2449592A1/en active Granted
- 1980-02-21 GB GB8005928A patent/GB2043562B/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
DE2906889A1 (en) | 1980-09-04 |
FR2449592B1 (en) | 1984-11-23 |
GB2043562B (en) | 1983-03-09 |
FR2449592A1 (en) | 1980-09-19 |
DE2906889C2 (en) | 1986-06-26 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |