Aircraft folding control surface

IPC classes for russian patent Aircraft folding control surface (RU 2446988):

F42B10/14 - using fins spread or deployed after launch, e.g. after leaving the barrel

B64C9/34 - collapsing or retracting against or within other surfaces or other members

Another patents in same IPC classes:

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Folding steering surface of pilotless flying vehicle / 2356790

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Folded aerodynamic surface / 2338663

Folding aerodynamic surface / 2349498

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Rocket projectile / 2258890

The rocket projectile has a nose fuse, warhead, self-propelled rocket engine with a nozzle junction box with a bell mouth a bladed tail unit a bell mouth, blade surface. The bell mouth of the nozzle junction is made with an outer cylindrical section with a diameter 0.6-0.7 of the projectile caliber, the tail unit blade attachments are made in the form of two rows of lugs located on the surface of the bell mouth. The tail unit blades are made in the form of two rows of lugs positioned on the bell mouth surface. The surface blades are made in the form of flat plates, in the closed position resting with its side surface on the cylindrical surface of the bell mouth. In the open position the blades are installed with a clearance of 0.15 to 0.25 of the projectile caliber between their side chord and the cylindrical surface of the bell mouth.

FIELD: transport.

SUBSTANCE: proposed control surface comprises root section and support. Root section is arranged aircraft airframe to turn thereon. Said root section accommodates support to turn about axis perpendicular to root section center surface. With support folded, part of control surface area ahead of root section turn axle is related to that behind said axle as 1:1 to 3:1. Folded control surface in unfolded position corresponds to condition of axial compensation.

EFFECT: reduced moment load in folded position.

4 cl, 7 dwg

The invention relates to aircraft control, in particular to steering surfaces.

The prior art collapsible steering the surface of the aircraft (patent # EN 2356790 from 27.05.2009, IPC VS 9/00)made tselnopovorotnogo and hinged to the hull.

The disadvantage of analogue is the increased torque load on the drive collapsible steering surface in the folded position and at the time of the start of the aircraft.

The prior art collapsible steering surface controlled projectile (patent # US 6202958 from 20.03.2001, IPC F42B 10/14), consisting of the root part, which can be rotated console is installed.

The disadvantage of analogue is the increased torque load on the drive root part at the time of launch of the projectile.

Closest to the proposed invention, the technical solution chosen as a prototype, is collapsible steering surface missiles (patent US 6578792 from 17.06.2003, IPC F42B 15/01)that contains the root element, which can be rotated console is installed.

The disadvantage of the prototype is the increased torque load on the drive collapsible steering surface in the folded position and at the time of launch.

Object of the present invention is to provide a collapsible steering p the surface with optimum overall mass by reducing the torque load, acting about the axis of rotation of the root portion of the steering surfaces on the steering actuator surface (or on the locking mechanism of the steering surface) in the folded position and at the start of the aircraft.

The problem is due to the fact that collapsible steering the surface of the aircraft contains a root part and the console is made in the form of tail surfaces, and the root part is installed on the body of the aircraft can be rotated, and the console is installed on the root portion can be rotated about an axis perpendicular to the middle surface of the root of the movable part, while in the folded position of the console, the ratio of the square folding steering the surface of the aircraft, located in front of the axis of rotation of the root part of the square folding steering the surface of the aircraft, located behind the axis of rotation of the root part is from 1:1 to 3:1; and collapsible steering the surface of the aircraft in the unfolded position matches an axial compensation.

In a particular embodiment of the invention the problem is solved due to the fact that the sweep of the leading edge of the root part is from 20° to 80°.

In a particular embodiment of the invention the problem is solved due to the fact that the sweep n the Central edge of the console in the unfolded position ranges from -20° to 80°.

In a particular embodiment of the invention the problem is solved due to the fact that the root part and the console is made with Wisconsin aerodynamic profile.

The present invention allows to optimize the overall mass characteristics by reducing the torque load on the drive steering surface. Reducing the torque load reduces the effort and locking in the folded position and to reduce the drive power.

1 shows the side view of a collapsible steering surface, while the console is in working position (the arrow shows the direction of flight).

Figure 2 is a top view of a collapsible steering surface, while the console is in working position.

Figure 3 shows the side view of a collapsible steering surface, while the console is in the folded position (the arrow shows the direction of flight).

Figure 4 shows a top view of a collapsible steering surface, while the console is in the folded position (the arrow shows the velocity vector flow).

Figure 5 shows the location of the squares of S₁and S₂for the folded collapsible steering surface, side view.

Figure 6 shows the position of the mean aerodynamic chord for the unfolded foldable steering surface, side view.

On IG depicted collapsible steering surface in isometric projection, while the console is in working position.

Consider the execution collapsible steering the surface of the aircraft (hereinafter steering surface)at which the aircraft is made in the form of missiles to be placed on an aircraft carrier. In flight on the suspension under the media and the launch on the steering surface acts incoming flow, causing increased torque load on the drive steering surface (or locking device). This can lead to such consequences as reducing the reliability of the rotation axis of the root portion, and hence the increase in the required drive power, control the rotation of the steering surface that, in turn, leads to increased size and weight of the structure. Increased torque load on the steering surface (in General) when folded position of the steering surface occurs in the form of hinge moment, the value of which is enhanced by the maximum distance between the position of the axis and the center of pressure of the steering surface hinge moment - "Aerogasdynamics of the flight control system aircraft, Vtechnology, Publishing house of Moscow state technical University n.a. Bauman, 2004, pp.17-18 and 237-240).

The steering surface consists of a root portion 1 and console 2. The root part 1 installed on the main body of the aircraft with the possibility of the of borota axis a ₁perpendicular to the hull. The root part 1 made in the form of a steering surface, the sweep of the leading edge root of χ₁=20°÷70°. The magnitude of l₁the root portion 1 is limited by the conditions of storage, transportation and operation of the aircraft. For example, in the case of complete aircraft as missiles, the magnitude of l₁the root part 1 should provide free placement of missiles in transport-launch container or under the wing of the plane. In the root portion 1 has a groove 3 located along its middle surface.

In the groove 3 can be rotated console is installed 2. Axis a₂to turn the arm 2 relative to the root portion 1 is perpendicular to the middle surface of the root part 1 (it should be noted that depicted in figure 1-7 position of the axis a₂before the axis a₁is only an example of implementation of the invention and the axis a₂can be located outside the axis a₁without affecting the essence of the invention). In the unfolded position of the console 2 sweep her front edge χ₂=-20°÷80°. The value of l scale steering surface is selected based on the objectives, which will be used by the aircraft. The value of b₂chord console 2, similar to the scale l₁the root portion 1, is limited to what conditions of storage, transportation and maintenance of aircraft. In the folded position the console 2 is located along the body of the aircraft in the direction of movement of the aircraft.

It should be noted that in the absence of the console 2 scale l₁the root portion 1 is not sufficient for effective control.

The steering surface in the unfolded position of the console 2 has a mean aerodynamic chord of the MAR length b_SAKH. The distance h from the front end of the MAR to the axis a₁0.25÷0.5 b_SAKHand is selected from considerations of axial compensation (axial - see "Aerodynamics, stability and control of a supersonic aircraft", as amended Gssrs, Moscow, Nauka Fizmatlit, 1996, str-339, the position of the axis is the same source, s-413). The range of possible δ provisions axis is depicted in Fig.6. The exact position of the axis a₁depends on the specific conditions of use of the aircraft, in particular on the velocities. Axial allows to reduce the hinge moment acting on the steering surface, due to the rational choice of the axis of rotation of the steering surface. Thus, if the root part 1 is missing and the console 2 is installed directly on the body of the aircraft can be rotated about the axis a₁when folded position the console is 2 hinge moment acting on the console 2, will have the maximum value, even if in the unfolded position, the console 2 will comply with axial compensation. Collapsible steering the surface of the aircraft, formed a core part 1 and console 2 in the unfolded position, complies with the requirements of axial compensation. Steering the surface formed by the core part 1 and console 2 in the folded position, if possible, meets the requirements of axial compensation. If the steering surface formed by the core part 1 and console 2 in the folded position, does not meet the requirements of axial compensation, the hinge moment acting on the console 2, significantly lower hinge point arising in the case of the console 2 in the folded position in the absence of a root portion 1. This is achieved by selection of the parameters m (the distance from the axis a₁to the rear edge of the root portion) and n (the distance between the axes a₁and a₂), subject to the condition h=0,25÷0.5 b_1CAX. The ratio of S₁:S₂part of the square folded steering surface S₁(i.e. including the root part and the console), located in front of the axis a₁to part of the square folded steering surface S₂located behind the axis a₁is from 1:1 to 3:1 (see Fig.7). This condition allows you to bring the folded relevo the surface to the axial compensation, while complying with the requirements to the scale of the console 2, the chord console 2, the scope of the root portion 1 and the condition for the axial compensation decomposed steering surface. There is no need to accurately observe the condition of axial compensation for steering folded surface, moreover, it may lead to non-compliance of the conditions listed above, which is unacceptable, and therefore selected this attitude of squares S₁:S₂. The root part 1 and console 2 is made with Wisconsin aerodynamic profile that is illustrated in figure 2, 4 and 5.

Collapsible steering the surface of an aircraft provided with a device enabling rotation of the root part 1, and the device providing the folding console 2, and can also be equipped with a device to allow fixation of the console in the folded position, and a device to allow fixation of the console in the unfolded position (figures not shown).

Collapsible steering the surface of the aircraft operates as follows.

Make the start of the aircraft and release the console from 2 fixation in the folded position. Using devices that provide a folding console, bring the console 2 in the working position. Fix console 2 in the working position. Using the drive control position collapsible steering surface Letatlin the machinery.

Technical solution allows to optimize the overall mass characteristics collapsible steering surface by reducing the torque load acting on the elements collapsible steering surface in the folded position, due to the structural design collapsible steering surface. Collapsible steering the surface of the aircraft is intended for use in aircraft, for example, guided missiles, in case of restrictions of space to accommodate the tail surfaces.

1. Collapsible steering the surface of the aircraft, containing the root portion mounted on the body of the aircraft can be rotated, and the console is made in the form of steering surfaces and mounted on the root portion can be rotated about an axis perpendicular to the middle surface of the root portion, wherein the root portion is made in the form of a steering surface, when the folded position of the console, the ratio of the square folding steering the surface of the aircraft, located in front of the axis of rotation of the root part of the square folding steering the surface of the aircraft, located behind the axis of rotation of the root part is from 1:1 to 3:1; collapsible steering the surface of the aircraft in the unfolded progenitive condition axial compensation.

2. Collapsible steering the surface of an aircraft according to claim 1, characterized in that the sweep of the leading edge of the root part is from 20° to 80°.

3. Collapsible steering the surface of an aircraft according to claim 1, characterized in that the sweep of the leading edge of the console in the unfolded position ranges from -20° to 80°.

4. Collapsible steering the surface of an aircraft according to claim 1, wherein the root part and the console is made with Wisconsin aerodynamic profile.