U.S. patent number 3,759,466 [Application Number 05/216,555] was granted by the patent office on 1973-09-18 for cruise control for non-ballistic missiles by a special arrangement of spoilers.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Army. Invention is credited to Ernst T. Evers-Euterneck.
United States Patent |
3,759,466 |
Evers-Euterneck |
September 18, 1973 |
CRUISE CONTROL FOR NON-BALLISTIC MISSILES BY A SPECIAL ARRANGEMENT
OF SPOILERS
Abstract
A missile control system for a guided missile wherein spoilers
are used for making small corrections in the trajectory of the
guided missile during the launch and cruise phase and conventional
control surfaces are employed to make large trajectory corrections
in the final homing phase of its trajectory. The spoilers are
mounted in the extremities of a missile's wing members and tail
fins; those mounted in the wing members accomplishing pitch and yaw
corrections and those in the tail fins roll corrections. The
spoilers are extended and retracted by solenoid devices.
Inventors: |
Evers-Euterneck; Ernst T.
(Huntsville, AL) |
Assignee: |
The United States of America as
represented by the Secretary of the Army (Washington,
DC)
|
Family
ID: |
22807508 |
Appl.
No.: |
05/216,555 |
Filed: |
January 10, 1972 |
Current U.S.
Class: |
244/3.21;
244/3.27 |
Current CPC
Class: |
F42B
10/64 (20130101) |
Current International
Class: |
F42B
10/00 (20060101); F42B 10/64 (20060101); F42b
013/32 (); F42b 015/02 () |
Field of
Search: |
;244/3.21,3.22,3.24-3.3,1R,1SS,90,89,113 |
References Cited
[Referenced By]
U.S. Patent Documents
Other References
more about the X-15. In Flight 73(2559): p. 196,197. Feb 14,
1958..
|
Primary Examiner: Borchelt; Benjamin A.
Assistant Examiner: Hanley; James M.
Claims
I claim:
1. A trajectory control system for a guided missile that includes
spoiler control means and control surface means employed in
combination for suitably altering the trajectory of the missile at
any point in its flight,
said control surface means being adapted for making large pitch and
yaw trajectory changes during the homing phase of the missile's
trajectory and stabilizing the missile, said control surface means
comprising:
a first pair of diametrically opposed moveable wing members,
arranged to generate large trajectory changes in pitch,
a second pair of diametrically opposed moveable wing members
disposed for making large trajectory changes in yaw, and
two pairs of diametricayly opposed tail fins for stabilizing the
missile,
said spoiler control means being adapted for making small pitch and
yaw corrections in the launch and cruise phases of the trajectory
of the missile and controlling the roll of the missile, said
spoiler control means comprising:
a cylindrical spoiler mounted in the tip of each moveable wing
member,
a spoiler mounted in the tip of each tail fin that includes control
surfaces shaped so as to provide lift surfaces that are pitched at
a desired angle with respect to the longitudinal axis of the
missile so as to roll the missile when selectively extended in
diametrically opposed pairs,
actuator means mounted in each wing member and tail fin for
selectively and fully extending and retracting the spoilers mounted
therein to accomplish small trajectory changes in pitch and yaw and
control the roll of the missile,
pitch and yaw control means mounted in said missile and connected
to the actuator means mounted in the wing members for selectively
and individually actuating the cylindrical spoilers in the wing
members for making trajectory changes in pitch and yaw, and
roll control means mounted in said missile and connected to the
actuator means mounted in the tail fins for selectively extending
diametrically opposed pairs of spoilers mounted in the tail fins so
as to roll the missile.
Description
BACKGROUND OF THE INVENTION
The invention relates to control systems for indirectly deployed
homing guided missiles. In particular the invention is a guidance
control system in which minor trajectory changes are made with a
special arrangement of spoilers during those portions of a
missile's trajectory wherein such corrections are all that is
needed before the missile acquires its target.
In certain missile applications, for example in a missile having a
semi-active homing guidance system, it is necessary to provide a
control system capable of making drastic changes in the trajectory
of the missile during its final homing stages. In such a missile it
is desirable at times to make mild trajectory changes during the
early launch and cruise phases of the missile's flight. The reason
for this is that in a semi-active homing system the missile's
homing guidance system becomes effective only after the missile
arrives in the vicinity of the target. Just how close the missile
must approach its target before acquisition can take place is of
course dependent upon the homing system installed in the missile.
It is normally the case that very severe alterations in the
missile's trajectory will be required during the final homing phase
in order to achieve intercept with a target.
A missile to be effective must be simple and reliable and it has
been found that the ultimate in simplicity and reliability in
control systems is bang-bang controls wherein the control is either
full on or full off with no intermediate degree of control
possible. Since large trajectory corrections are sometimes required
the missile must be capable of severe trajectory changes. Thus,
full control means that a considerable trajectory change is caused
each time a change is indicated by the guidance system of the
missile. Often this will be an over control which requires a
counter control movement, also a full control movement, made to off
set this over control. As is apparent this can result in many more
control movements than would be necessary if a more sophisticated
control system were employed capable of a variable degree of
control. However this over control situation is tolerated in order
to achieve the simplicity and reliability that is necessary to an
effective missile system.
The range at which a semi-active homing system in a guided missile
can acquire a target is limited and there are instances where it
would be desirable to correct the trajectory of a guided missile
during its early phases so as to assure that the missile approaches
its target at a close enough range to permit acquisition of the
target by the missile's homing system. If the bang-bang control
system used for trajectory correction during terminal homing is
also used to make corrections in the launch and cruise portion of
the trajectory then many trajectory changes will be required due to
over control. This mode of operation while providing effective
missile control significantly increases the amount of fuel and
power required to achieve intercept with the target, thus adding to
the weight, cost and handling difficulties of the system.
SUMMARY OF THE INVENTION
An object of the invention is to provide a supplementary control
system that can be used in conjunction with conventional control
systems used in guided missiles to provide effective control
throughout all of their trajectory without any significant change
in cost, weight or complexity of the missiles.
Another object of the invention is to provide a missile control
system that is capable of bang-bang operation and yet retains the
capability of making either large or small changes in the
trajectory of the missile.
A missile system constructed in accordance with this invention will
accomplish the objectives mentioned above. The missile includes
moveable wings used as control members for making severe trajectory
changes in the pitch and yaw direction, tail fins for
stabilization, and a system of spoilers wherein each of the
moveable wing members and each of the tail fins are provided with a
retractable spoiler that exerts control over the trajectory of the
missile when extended. Placing the spoilers in the tips of the
wings and tail fins insures effective lever arms for the spoilers.
Thus the drag forces that result when the spoilers are extended are
effective control forces, but these forces are small and fuel
economy, especially during the cruise mode, is enhanced. The
spoilers mounted in the moveable wing members can be individually
extended and retracted to generate up and down pitch corrections
and right and left yaw corrections. The spoilers mounted in the
tail fins achieve roll control. Roll forces are generated by
simultaneously extending, in pairs, the spoilers mounted in
diametrically opposed tail fins. The spoilers mounted in the tail
fins are provided with pitched lift surfaces to prevent or cause,
as desired, roll of the missile about its longitudinal axis when a
pair of spoilers are extended.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a simplified pictorial illustration of a deployed missile
system that shows the various portions of a guided missile's
trajectory from launch to point of intercept with a target.
FIG. 2 is a pictorial illustration of a guided missile with a
spoiler control system mounted in the ends of its wing members and
tail fins.
FIG. 3 is a view of the missile partially in cross-section with the
middle portion thereof broken away.
FIG. 4 is a view partially in cross-section and partially broken
away, from the aft end of the missile that illustrates the spoilers
mounted in the wing tips and tail fins.
FIG. 5 is a schematic showing of the spoiler control system that
illustrates how the tail fin spoilers are electrically connected to
operate in pairs whereas the wing tip spoilers operate singly.
DETAILED DESCRIPTION OF THE INVENTION
The trajectory of a guided missile and that of its target is shown
in FIG. 1. A target is usually detected by means of a radar 10 or
other suitable surveilance means and notice of the target is
forwarded to a battery 12 of guided missiles. The missiles in this
instance are of the surface to air type. Missile 14 is launched and
that portion of its trajectory from the launcher to point A is
termed the launch and cruise control mode of the missile's flight.
That part of the trajectory between point A and point B, the
intercept point, can be called the homing mode or terminal homing
phase of the missile's flight.
The spoiler control system disclosed herein has particular
application to a missile having a semi-active homing guidance
system for terminal guidance or final homing. With this type of
control system it is necessary that the missile be launched and
directed to the general vicinity of the target which is being
tracked so as to place the missile close enough to its target so
that the homing guidance system in the missile can acquire and
track the target. The acquisition range of semi-active homing
systems is usually somewhat limited and should the launch and
cruise phase of the missile's trajectory be misdirected to a
considerable extent it is possible that the missile will not close
sufficiently with the target to allow its semi-active homing
guidance system to acquire and track the target. Thus, it is
desirable, in order to assure proper target acquisition and
tracking, to make corrections in the missile's trajectory during
the launch and cruise phases thereof.
An effective missile system must have a simple and reliable control
system for making changes in its trajectory. Experience has shown
that the best control system, so far as simplicity, reliability and
weight is concerned, is a bang-bang control system; that is, a
control system wherein either the system is on and making a maximum
control effort or it is off and exerting no control.
A bang-bang type control system having a capability of making the
severe trajectory changes required while the missile is homing on a
target is not well suited for making the small trajectory
corrections required during the launch and cruise phase because
such a system tends to over control the missile each time a change
is made and this results in many changes being made during the
cruise part of the trajectory. The missile described herein has two
separate control systems, both capable of bang-bang operation; one
for the terminal homing phase and one for the launch and cruise
phase of the missile's trajectory.
FIG. 2 illustrates how this is accomplished. Missile 14 has four
wing members 16, 18, 20 and 22 that are moveably mounted on the
body of the missile. Wings 18 and 22 are moved to either pitch the
missile up or down whereas wing members 16 and 20 are moved to yaw
the missile to the right or left. Tail fins 24, 26, 28 and 30
mounted in a fixed position on the aft end of the missile stabilize
the missile.
In FIGS. 3 and 4 the manner in which the spoilers are mounted in
the tips of the wing members and tail fins is illustrated. Each of
the spoilers mounted in the wing members, spoiler 32 for example,
is mounted and controlled so as to be individually extended and
retracted. Spoiler 34 (see FIG. 4) mounted in the tip of tail fin
24 is paired with spoiler 36 mounted in tail fin 28 and the two are
connected and simultaneously controlled, see FIG. 5, so as to roll
the missile about its longitudinal axis. All of the spoilers are
extended and retracted in a similar manner so only one will be
described herein. Spoiler 32 is mounted on one end of a lever 38
whose other end is pivotally mounted to the structure of wing
member 16. Lever 38 is attached to moveable core 40 of a solenoid
41. When the current flows through coil 42 the solenoid is
energized and core 40 is moved which in turn moves lever 38,
compresses a spring 43, and extends spoiler 32. Spring 43 retracts
the spoiler when the solenoid is deenergized. The spoilers mounted
in the wing tips are small cylinders that slide within a small bore
or well 44 formed in the extremities of the wing tips.
The spoilers mounted in the tail fins are similar to those mounted
in the wings, differing only in that they are provided with pitched
lift surfaces, as illustrated in the blown up portion of FIG. 2. In
FIG. 2 for example, spoiler 36 is shown having a rectangular shaped
tab 31 formed on the outer end thereof, but it could have any other
configuration desired so long as when canted at an angle to the
longitudinal axis of the missile it forms a lift surface that rolls
the missile about its longitudinal axis. The spoilers are shaped
and arranged in diametrically opposed pairs so that spoilers 39 and
41 roll the missile in a clockwise direction and spoilers 34 and 36
roll the missile in a counter clockwise direction.
In contrast to this the spoilers mounted in the wing tips are
extended and retracted individually to make corrections in pitch
and yaw. For example, extending spoiler 32 mounted in wing member
16 will cause the missile to change its trajectory in an upward
direction, or as more commonly termed, will cause the missile to
pitch up. Likewise, extending spoiler 35 in wing member 20 will
cause the missile to pitch down. The spoilers are constructed so
that they are fully extended or fully retracted to give bang-bang
operation. The spoilers mounted in the tail fins for roll control
are connected to and actuated by a suitable roll control device 44
and the spoilers mounted in the wing tips are actuated by a pitch
and yaw control device 46 of a suitable type.
The roll, pitch and yaw control devices are not disclosed in detail
herein as there are many state of the art devices which could be
used and the one selected would depend to a large extent on the
design of the missile. The spoiler system disclosed herein is used
in conjunction with a semi-active homing guidance system, but it
should be understood that it could be used in combination with
other types of guidance systems.
* * * * *