Patent Application
20110297783
This invention is directed to a system for controlling missiles or projectiles, where canards extend and retract at predetermined frequencies.
In the field of guided weapons there are primarily two possible aerodynamically controlled airframes, namely, a rolling airframe and a roll stabilized airframe. These two schemes cover most of the missiles and projectiles with aerodynamic controls.
A missile or projectile with a rolling airframe has an airframe that is free to roll or its rolling motion is controlled by a device (such as a rolleron) to keep the roll rate at a certain value. Aerodynamic controlled deflections can then be coordinated with the roll position, which is calculated by roll-resolvers using roll gyros. A typical example is the Sidewinder missile, which uses four steering canards.
Another embodiment of the rolling airframe uses only one pair of aerodynamic control surfaces and deflects them in a proper position to satisfy the guidance and control vector demand.
General Dynamics pioneered several new design features to create the Redeye missile, which was the first rolling airframe missile (RAM). Unlike conventional roll stabilized missiles which are steered in two axes, pitch and yaw, by two (pitch, yaw) control channels, a RAM uses a single control channel which is “phased” to introduce pitch and yaw commands subject to the missile's instantaneous orientation (roll angle) in roll. In this fashion a single pair of control surfaces can do the work of two pairs of control surfaces, reducing weight and space requirements with some penalty in maneuver performance. General Dynamics applied further new technology to the Redeye missile by designing all of the guidance and control electronics with solid state transistor and integrated circuit technology, a first in tactical missiles. Another major weight saving measure was the use of electrical control actuators to displace bulkier conventional hydraulics. Internal wiring harnesses in the missile were replaced with lighter, flexible, flat printed wiring harnesses.
Two schemes of control by a single pair of deflecting canards have been used in RAM missiles. In one of the schemes, the canards generate the lift forces by deflecting the canards by a certain angle by an actuator according to the roll position and the lift required to generate the lateral acceleration to change the trajectory angle. In the other scheme, referred to as “Dithering Canards,” the canards, once deployed, vibrate or dither at some frequency in the rolling airframe to create the appropriate lateral force to steer the missile or projectile.
Dithering canards are simpler than deflectable canards with specific angles of deflection because it is not necessary to have a complex servomechanism to deflect them. However, the dithering canard scheme needs to be packed and then deployed after launch, which usually makes the mechanical design complex.
Seeking simplicity and low cost solutions to be used in the control of guided mortar projectiles, General Dynamics found a solution with the so-called roll controlled fixed canard (RCFC) system, as set forth in U.S. Pat. No. 7,354,017 to Morris et al. The RCFC system is an integrated fuze and guidance- and flight-control system that uses global positioning system (GPS) and/or inertial navigational system (INS) navigation and that is installed by replacing current fuze hardware in existing mortars or other projectiles. A typical projectile having the RCFC system comprises:
Another concept to create trajectory correction to artillery projectiles is disclosed in PCT Published Application No. WO 2008/143707 to Pritash. Trajectory errors can be corrected in two ways: Assuming an overshoot, a deployable set of brake fins or disks is used to correct the range errors. This assumes that the target is at a range shorter than at which the weapon is aimed, because it only can waste kinetic energy by braking the projectile by the use of aerodynamic brakes.
A deflection correction is based on the fact that a very fast spinning projectile will divert (drift) to one side depending of the roll motion direction, and therefore changing the roll rate changes the amount of the lateral drift. The spin correction fins of Pristash do exactly this by extending or retracting spin fins which are at fixed incidence but in opposite directions. The spin rate, and hence the deflection, is controlled. However, the gun or weapon must be aimed in a specific direction prior to shooting so that by changing the spin rate and braking the velocity over the trajectory, the desired target can be hit.
Similar to the control system discussed above, this system is much more complex than is needed for slow rolling projectiles.
It is an object of this invention to provide a novel system for controlling missiles or projectiles, which is simpler and less expensive than the systems described above.
It is also an object of this invention to provide a rolling projectile with extending and retracting canards.
It is a further object of this invention to provide missiles or projectiles where canards extend and retract for times and at predetermined frequencies corresponding to the rate of rotation of the projectile.
It is a yet further object of this invention to provide a projectile comprising:
It is a yet further object of the invention that the projectile or missile will have a GPS or INS navigational system that will be in operative communication with the canards in the forward section.
These and other objects of the invention will become more apparent from the disclosure herein.
According to the invention, a cost-effective 2 or 3 DOF steering system, when coupled with a GPS or INS navigation system, provides course correction to improve the targeting precision of mortars, bombs, artillery projectiles and missiles. In one aspect of the invention, tail fins to produce rotation are provided, which tail fins cause the projectile to slowly roll in flight. A flight control system comprises canards that extend and retract for times and at predetermined frequencies on the forward end of the projectile.
The flight control system is attached to or incorporated within the body of the projectile. During projectile flight, the flight control system measures the projectile's position (using GPS or INS technology), and then the flight control system, which includes sensors, initiates flight control actuators that precisely extend and retract the canards.
As the projectile rotates, the relative rotational position and canard extension (from the projectile body) varies as an actuator controls the positional extension of the canards. The controlled extension and retraction of the canards varies the lift on the forward, leading edge of the projectile fuze. The resulting variation of lift on the forward point of the fuze provides for variation of the angle of attack on the nose and forward canards. This system provides a low g correction of the projectile's path.
According to the invention, the simplicity of the RCFC concept (only one signal to steer the projectile using the brake system) is maintained, but it is coupled with the fixed incidence of extending and retracting canards using only one linear actuator while the complete airframe is rolling by the use of canted tail fins. In both concepts, the rolling motion is required to obtain the lateral force vector in the desired direction due to only one pair of canards being present. Roll motion is not produced to create gyroscopic stability, nor to control the spin rate to use the gyroscopic drift as lateral force producer.
Thus, a slowly rolling projectile, when coupled with a GPS or INS navigational system, provides course correction to improve the precision of mortars, bombs, artillery projectiles, and missiles.
The steering system according to the invention includes tail fins, canards, a GPS and/or INS navigational system, a flight control computer, and an interface to the fuze and projectile or missile body. Tail fins are placed at an angle to the longitudinal axis that induces rotation and creates a slowly rolling projectile in flight. On the forward end of the projectile the steering system includes extending and retracting canards. The steering system is fixed to the projectile body. The canards are planar and preferably canted at a fixed angle to the longitudinal axis, and they are at fixed incidence.
During projectile flight the GPS and/or INS navigational system measures the projectile's position, and the flight control computer initiates flight control actuators that precisely extend and retract the canards. The controlled extension and retraction of the canards varies the lift on the nose or fuze of the projectile. The resultant variation in lift on the nose or fuze of the projectile provides a trim angle of attack of the entire projectile, which produces a lateral force that steers the projectile into a desired path to correct the errors such as variation of muzzle velocity, mortar laying errors, and meteo.
The current requirements for precision fires and minimum collateral damage for the actual battlefield requires low cost solutions for control devices to be applied in smart weapons. Mortar projectiles with correction systems based on low cost GPS/INS meet these requirements.
The current trend in the case of low cost guided or corrected mortar munitions is characterized by the following requirement matrix:
Desired features of the system could be described as follows:
The control and guidance system disclosed and claimed herein has the following advantages:
A particularly relevant aspect of the invention herein is that it is a simple way to generate control forces in mortar projectiles, using a device which can be integrated with a fuze, can be armed in a system at low cost, and is compatible with current developments in GPS/INS guidance packages of these types of smart projectiles.
Preset aiming is not necessary according to the invention, because in both cases the gun/weapon will be aimed at the intended target and the ballistic computations will determine the errors of the calculated nominal trajectory, which will be compensated by the guidance and control system extending and retracting canards in a rolling airframe.
For a full understanding of the present invention, reference should now be made to the following detailed description of the preferred embodiments of the invention as illustrated in the accompanying drawings.
The preferred embodiments of the present invention will now be described with reference to
Front section 4 comprises canards 12 that extend or retract from housing 14. Canards 12 are shown extended in
Preferably there are two canards 12. Optimally there could be from 2 to 8 canards, preferably equidistantly positioned around housing 14.
The size of the canards will depend upon several factors, including the sign of the projectile. For example, for a mortar having a length of from about 0.5 to almost 1.5 m, the canards could each be from about 10 to about 50 cm in width and about 10 to about 50 cm in length, the surface area extending radially from the outer surface of housing 14.
The control system according to the invention is shown in the block diagram set forth in
Actuator 16 or 34 is an electrical or mechanical device that causes one or both canards 12 to extend or retract as desired, preferably for times and/or at frequencies that correspond to the rate of rotation of the projectile. For example, the canards may extend from the housing once per cycle, that is, once per rotation of the projectile, for from one-third to one-half the cycle, the timing dependent upon the rotation and the correction necessary. There may be situations where the canards can extend and retract more than once a cycle, or less than every cycle, or for most or all of a cycle, dependent upon the correction required. There may be one particular frequency at which the actuator operates or, optionally, the frequency may vary according to signals from flight control system 18. It is within the scope of the invention that the frequency of the extension and retraction of the canards will be from about 2 to about 20 times/sec., more preferably from about 5 to about 10 times/sec. Optionally canards 12 may be extended partially or fully and not retracted for a set period of time.
Typically the canards will be extended once and retracted once during one rotation of a projectile. The diagram shown in
In
In a calculated example of an embodiment of the invention, a mortar with a mass of 4.40 kg was fired at an initial angle of 45° with a velocity of 300.00 m/sec. The rotational frequency was 8.00 Hz, at the maximum lateral acceleration.
The time of the flight was 36.40 sec, the range being 5506.0 m. The maximum height was 1640.30 m, at which point the velocity of the projectile was at a minimum of 147.24 m/sec. This occurred 19.50 sec after launch. The velocity at impact was 194.76 m/sec, at an angle of 54.73°. The maximum lateral correction was calculated at 233.69 m.
There has thus been shown and described a novel rolling projectile with extending and retracting canards, particularly one which fulfills all the objects and advantages sought therefore. Many changes, modifications, variations and other uses and applications of the subject invention will, however, become apparent to those skilled in the art after considering this specification and the accompanying drawings which disclose the preferred embodiments thereof. All such changes, modifications, variations and other uses and applications which do not depart from the spirit and scope of the invention are deemed to be covered by the invention, which is to be limited only by the claims which follow.
This application is based upon and claims the priority of co-pending and commonly assigned U.S. Provisional Patent Application Ser. No. 61/254,840, filed Oct. 26, 2009, incorporated herein in its entirety by reference.
| Number | Date | Country | |
|---|---|---|---|
| 61254840 | Oct 2009 | US |
