Apparatus for correcting the flight path of a missile

BACKGROUND OF THE INVENTION
The invention is directed to an apparatus for correcting or adjusting the flight path of a missile, such as a high-speed shell or projectile. The missile includes a missile body containing a distributor of a flow means rotatably mounted in the missile body. The distributor has at least one outlet opening for the flow means for effecting a transverse force on the missile body. At least one blow-out opening in the circumferential surface of the missile body is alignable with the outlet opening. A braking means acts between the distributor and the missile body.
In the applicant's German patent document No. P 33 17583.7-15, not previously published, a thrust nozzle system is disclosed which can be used to control a high-speed shell or projectile. The thrust nozzle system includes a rotary nozzle member acted upon by a gas generator or producer so that it is driven by the gas flow from the gas generator. The housing of the shell has a plurality of blow-out openings distributed around its circumference so that the gas flow from the rotary nozzle member can be directed in a controlled manner. A braking arrangement, which can be actuated electromagnetically, controls the rotary nozzle member. The high speed rotary nozzle member which could also be driven by a separate rotary drive, can be stopped with the aid of the braking arrangement to direct the gas jet in a determined direction. The direction of the gas jet in space can be varied by alternating between releasing and applying the braking arrangement.
Due to the arrangement of the rotary nozzle member and the blow-out opening on the circumference of the shell housing, with this system only substantially full commands or zero commands can be achieved. Such a procedure is sufficient, as a rule, since the changeover from a full command to a zero command or from a full command in one direction to a full command in the other direction is only slight because of the high-speed rotary nozzle member. If the flight path of the shell is to be corrected only slightly, that is, if a low pulse is to be introduced in a determined normal direction, a correspondingly high-speed control must be provided for the rotary nozzle member.
SUMMARY OF THE INVENTION
Therefore, the primary object of the invention is to provide an apparatus for the sensitive adjustment or correction of the missile flight path with a metered thrust.
In accordance with the present invention, a blow-out opening in the missile body is formed in a missile part which can rotate independently of the distributor. Means are provided for rotating the distributor and the outlet opening and the blow-out opening are at least partially alignable in a controlled manner by the means for rotating the distributor and by the braking arrangement.
In an apparatus embodying the present invention, the blow-out openings are provided, in a rotating missile tip on the missile body or in another rotating part, for instance, a cylindrical region at the trailing end of the missile. The missile tip is driven independently from the flow means distributor, that is, by small obliquely angled fins, by a spring means or by explosive charges. The distance travelled by the flow means distributor in switching from a full command to a zero command, or from a command of a predetermined strength to a command altered in a dosed manner, are substantially reduced in accordance with the invention. The commands can be very sensitively adjusted by the degree of overlap or partial alignment of the blow-out opening in the missile body and the corresponding outlet opening in the distributor. The extent of the overlap of the openings is adjustable in a controlled manner.
A very simple embodiment of the apparatus, in accordance with the present invention, is provided when the flow means distributor is constructed as a propelling nozzle member driven rotatably by gas flow and including two propelling nozzles arranged off-center and acting in opposite directions and corresponding to two opposite radially directed blow-out openings in the missile tip. During a zero command, the overlap of the nozzles is 50% and can be varied in a determined direction by accelerating or braking the propelling nozzle member to achieve a dosed thrust command. As long as the braking arrangement is not effective, the propelling nozzle member rotates at a higher speed than the nozzle tip so that, proceeding from the state of zero command, when releasing the brake the rotary nozzle member runs ahead of the missile tip and, accordingly, one nozzle receives a greater overlap while the overlap of the other nozzle is reduced. If, starting from the same initial state, the brake is applied, the overlap changes in the opposite direction. In this way by correspondingly controlling the propelling nozzle member, for instance by a pulse duration modulation, a very accurately dosed command can act in a desired direction.
As mentioned above, the rotary drive for the propelling nozzle can be effected by a gas flow, such as from a gas generator. It is also possible to provide the rotary drive by ram air with the ram air also used as control air. Other combinations are possible, for instance, separation of the rotary drive and the production of the control air.
In the independent drive of the missile tip, the moment of inertia of the rotating missile tip should be substantially greater than that of the elements providing the feed of the flow means and its distribution, so that a stable movement of the missile tip is achieved.
A zero command can be produced in a number of ways. If the flow means distributor has only one outlet opening, that is, one propelling nozzle, and the missile tip has only one corresponding blow-out opening, it is possible to attain the zero command by continuously circulating a thrust jet of uniform strength. Hardly any disturbance will occur for the missile if the rotational speed of the missile tip is sufficiently high.
If two corresponding openings are provided in the flow means distributor and in the missile tip, which are aligned as indicated above, then two oppositely directed circulating thrust jets act during a zero command with an overlap of 50% of the corresponding openings, so that practically no disturbances occur on the missile.
Moreover, it is also possible to provide a single opening in the flow distributor means with a plurality of blowout openings distributed over the outer circumference of the missile tip. Between the blow-out openings in the missile tip, impact or deflecting surfaces are provided so that--in the case of ram air as control gas--the opening in the flow means distributor is blocked or--when a gas generator is used--the gas jet from the flow means distributor impacts without reaching the outside atmosphere. The gas jet can be guided away through a collecting duct. In addition, spring stops can be used for the flow means distributor with the distributor running up against the spring stops and thus being held in a position where the gas jet is directed against the impact of the deflecting surfaces. The braking arrangement is released when this occurs and the position between the missile tip and the flow means distributor is maintained to afford zero command. By braking the flow means distributor, the angular position between the distributor and the missile tip is altered so that the gas jet can flow out from the adjacent blow-out opening of the missile tip, specifically with more or less strength according to the amount of overlap. The spring stops can be overrun when the flow means distributor and the missile tip are rotated in opposite directions.
In a preferred embodiment of the invention, the rotary drive for the flow means distributor can be provided by a spring drive connected between the missile tip and the distributor. In the simplest case, the spring drive is a simple pretensioned coil spring. When the flow means distributor is braked, that is, from the position assigned to a zero command, the spring is tensioned. When the brake is subsequently released, the distributor is accelerated in the same direction as the rotating missile tip due to the stored spring energy and thus runs ahead of the tip. By a corresponding control, such as by a pulse with modulation, the thrust vector can be determined in strength and spatial direction.
The construction of the rotary drive for the flow means distributor with the aid of a spring drive has the advantage that the energy necessary for the operation of the drive is applied directly from the independently driven missile tip. The outlet nozzle of the flow means distributor can be arranged so that it is symmetrical relative to the rotational axis in the flow means distributor and affords a simple and safe construction.
To establish the direction and strength of the thrust, a control circuit is provided for establishing the relative angular positions of the openings from the flow means distributor and the missile tip with regard to the rest of the missile body. The information on this angular position can be obtained in a simple manner by angle transmitters, such as potentiometers, located on one hand between the missile body and the rotating missile tip and, on the other hand, between the flow means distributor and the missile body. The output signals of these angle transmitters are processed in a differentiator circuit.
The advantages attained with an apparatus embodying the present invention can be summarized as follows:
A very fast pulse change, that is, a very fast change in the strength and direction of the thrust, is obtained by the rotating missile tip. Moreover, the thrust is adjustable in a very sensitive manner.
The required spatial direction for a thrust pulse is quickly achieved by the independent rotation of the missile tip, that is, the missile tip determines the basic direction for the control thrust, and the modulation of the thrust is effected through the control mechanism. Basically, with this arrangement, there is an abbreviated dead time for the realization of the command.
In the arrangement of the apparatus, according to the present invention, with two openings in the flow means distributor and in the missile tip when a gas generator is used for producing the thrust jet, the bearing load of the parts involved with the flow means feed is also reduced.
Command pulses, that is, the product of the transverse force or thrust multiplied by time, are obtainable with reduced transverse force, since the thrust can be sensitively adjusted. As a result, unnecessarily high transverse forces which might negatively influence the missile flow path, are not produced.
Considerable miniaturization of the entire flow means feed is provided especially in the construction with a spring drive or friction drive for the flow means distributor.
The rate of rotation of the missile around its elongated central axis can vary widely in all of the different embodiments of the invention, accordingly, the apparatus can be used for rotating as well as non-rotating missiles.
In every embodiment of the apparatus, according to the invention, the gas flow rate through the flow distributor means is identical in all types of command to the extent possible, that is, the gas generator operates in a constant manner. During zero command, in each instance, 50% of the mass flow rate passes through two oppositely disposed locations and a stepless transition can be effected from zero command to full command. A zero command can also be achieved by a neutral exhaust of the gas without exercising any externally acting forces.
When a spring drive is used for the flow means distributor, the spring is constructed as a stop and a full command can be given practically continuously in a determined spatial direction.
The various features of novelty which characterize the invention are pointed out with particularity in the claims annexed to and forming a part of this disclosure. For a better understanding of the invention, its operating advantages and specific objects attained by its use, reference should be had to the accompanying drawings and descriptive matter in which there are illustrated and described preferred embodiments of the invention.

BRIEF DESCRIPTION OF THE DRAWING
In the drawing:
FIG. 1 is an axially extending section through the front part of a high speed missile incorporating apparatus, embodying the present invention, for correcting the flight path of the missile with the apparatus including a rotating missile tip and a driven brakeable flow means distributor;
FIG. 2 is a sectional view taken along the line II--II in FIG. 1;
FIG. 3 is an axially extending sectional view through a front part of a missile illustrating another embodiment of the apparatus for corecting the missile flight path;
FIG. 4 is an axially extending section through a front part of the missile with still another embodiment of the present invention used for correcting the flight path;
FIGS. 5a, 5b and 5c are transverse, sectional views taken along the lines V--V in FIGS. 3 and 4 for the purpose of explaining the operation of the apparatus embodying the invention;
FIG. 6 is a transverse cross-sectional view of yet another embodiment of an apparatus incorporating the present invention;
FIG. 7 is a partial transverse view through a modified embodiment with regard to the arrangement illustrated in FIG. 6;
FIG. 8 is a transverse cross-sectional view through still another embodiment of apparatus incorporating the present invention for correcting the flight path of the missile;
FIG. 9 is a transverse cross-sectional view through a missile tip and a flow means distributor connected with the missile tip by a spring drive;
FIG. 10 is a transverse cross-sectional view through an apparatus embodying the present invention for correcting the flight path of the missile corresponding to FIG. 9 at the height of the outlet openings of the flow means distributor;
FIG. 11 is an axially extending sectional view through part of a missile tip showing another modified embodiment of the apparatus incorporating the present invention; and
FIG. 12 is a partial transverse sectional view taken along the line XII--XII in FIG. 11.

DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 displays the front part of a missile 1, such as a high speed shell or projectile with a rotating missile tip 2. As viewed in FIG. 1 the left-hand end is the leading end of the missile and the missile tip and the right-hand end is the trailing end of the missile tip. Missile tip 2 is rotatably supported with a round flange or sleeve 3 in a recess 4 of the missile housing 1 extending rearwardly from the missile tip 2. The missile tip 2 has a plurality of fins 7 distributed around its outer circumference adjacent the leading end with the fins extending obliquely relative to the central axis 8 of the missile 1. During flight of the missile, the fins 7 pass through the atmosphere and provide fast rotation of the missile tip 2 around the central axis 8. In a centrally arranged borehole 9 within the missile body 1 a cylindrically shaped flow means distributor 10 is rotatably supported in the borehole 9 by radial guide bearings 11 and support bearings 12 at a trailing end flange 13 on the distributor. The flow means distributor 10 has an axially extending centrally arranged gas duct 15 open at the trailing end in the region of the flange 13 where it opens into a gas generator 16. At the opposite or leading end of the flow means distributor 10 located within the missile tip 2, the centrally arranged gas duct 15 opens into two off-center propelling or thrust nozzle 17-1, 17-2, note FIG. 2, arranged to direct flow in opposite directions in a radial plane with the openings disposed symmetrically relative to the central axis 8. Two blow-out openings 19-1, 19-2 are located in the missile tip 2 and are also positioned in a radial plane and are arranged relative to the nozzle 17-1, 17-2 through the nozzle openings 18-1, 18-2.
A braking arrangement 24 as disclosed in the German patent document No. P 33 17 583.7 is arranged about the flow means distributor 10 in the region of a recess 20 in the missile body 1. The braking arrangement 24 is actuated by a control circuit, not illustrated. The apparatus as shown in FIGS. 1 and 2 operates as follows:
Initially, the operation will be considered without the control circuit. During missile flight, the gas generator 16 is ignited and its gas jet flows through the central gas duct 15 in the flow means distributor 10 and then radially outwardly through the two propelling nozzles 17-1, 17-2. The gas jet drives the flow means distributor 10 in rapid rotation around the central axis 8 of the missile in the direction of the arrow P-1 in FIG. 2 (such rotation is effected only if the gas jet exits freely from the propelling nozzle 17-1, 17-2). At the same time, the missile tip 2 rotates in the same direction with the flow means distributor 10 as indicated by the arrow P-2, note FIG. 2.
In FIG. 2 the relative angular position of the flow means distributor 10 and missile tip 2 during a zero command is displayed, that is, the period during which no transverse forces act on the missile 1 for correcting its flight path. In this position, the extent of the overlap or alignment between the nozzle openings 18-1, 18-2 and the corresponding blow-out openings 19-1, 19-2 is 50%, that is, in this position 50% of the gas jet exits into the atmosphere through each of the blow-out openings 19-1, 19-2. The oppositely directed and equal transverse forces provided in this condition are indicated by the vectors S-1 and S-2, respectively. This relative angular position between the flow means distributor 10 and the missile tip 2 is maintained by the control circuit during the rotation of the missile tip with the flow means distributor 10, in a control manner, being braked or released from braking by the braking arrangement 24 relative to the missile body. In such operation it is ensured that the possible rate of rotation of the flow distributor means 10 is higher than the rate of rotation of the missile tip 2. The control circuit receives information from two angle transmitters 25, 26, with one transmitter 25 arranged between the missile tip 2 and the missile body 1 and the other transmitter 26 positioned between the flow means distributor 10 and the missile body 1. If a correcting thrust for adjusting the missile flight path in a determined spatial position is given, then the relative angular position between the flow means distributor 10 and the missile tip 2 is changed, with the aid of the control circuit, based on the angular relationship information received from the angle transmitters 25, 26 so that the overlapping or aligning relation of the nozzle openings 18-1, 18-2 and the blow-out openings 19-1 and 19-2 changes accordingly. If, for example, a correcting thrust is effected in a determined spatial relation through the blow-out opening 19-1, the braking arrangement is briefly applied, and proceeding from the state of the zero command illustrated in FIG. 2, as when the blow-out opening 19-1 is directed as desired. Accordingly, the flow means distributor is braked and the overlapping or partial alignment between the nozzle opening 18-1 and the blow-out opening 19-1 is increased. Simultaneously, the partial alignment between the nozzle opening 18-2 and the blow-out opening 19-2 is reduced when the correcting thrust is executed, the braking arrangement 24 is released and the flow means distributor accelerates again in the direction of the arrow P-1. When the position corresponding to a zero command in FIG. 2 is reached, this position is maintained via the control circuit by alternating between the release and the application of the braking arrangement 24. In the same manner a correcting thrust can be adjusted by the blow-out opening 19-2. The control for correcting thrust is effected with the aid of a pulse duration modulation.
Accordingly, if the braking device 24 is applied for a longer period than it is released, then the flow means distributor 10 lags behind the rotating missile tip, out of the position corresponding to zero command, with the blow-out opening conducting a larger amount of gas outwardly than the blow-out opening 19-2. Here, a correcting thrust acts in the direction of the arrow S-1 shown in FIG. 2. If, conversely, during the pulse duration modulation, the time of applying the braked arrangement is shorter than the release time, the flow means distributor 10 runs ahead of the rotating missile tip 2 so that a greater quantity of gas flow out through the blow-out opening 19-2 than through the blow-out opening 19-1. Under such a condition, a correcting thrust in the direction of arrow S-2 in FIG. 2 is achieved. The dosing of the correcting thrust is possible, in both angular directions from a position corresponding to zero command up to full command where the entire gas quantity flows out through only one blow-out opening and there is no gas exits in the other oppositely directed blow-out opening.
Additional embodiments of apparatus embodying the present invention for correcting the path of a missile are provided in FIGS. 3-12. In the various embodiments, which are identical or act identically to the embodiment shown in FIGS. 1 and 2 similar parts are designated with the same reference numerals but with the addition of a suffix letter, such as a, b, and the like.
FIG. 3 shows the leading end of a missile 1a with a rotating missile tip 2a similar to the embodiment shown in FIG. 1. The missile tip 2a is supported in the missile body 1a in the same manner as in the previous embodiment and the missile tip rotates by the action of the flow of air over the fins 7a independently from the rotation of the flow means distributor 10a and of the missile 1a, respectively. The missile tip has two blow-out openings 19a-1 and 19a-2 which communicate with the nozzle openings 18a-1, 18a-2 of the flow means distributor 10a. The thrust jet for correcting the missile flight path is produced by ram air flowing through a central ram air duct 31 in the missile tip 2a into the gas duct 15a of the flow means distributor 10a, with the gas duct 15a being open at the leading end of the missile or missile tip. From the gas duct 15a the ram air flows out through two oppositely directed radial nozzle openings 18a-1, 18a-2. The flow means distributor could, it is true, be driven by a propelling nozzle arrangement corresponding to the embodiment in FIG. 1 by means of ram air, but another construction, explained later, is used.
A bearing shaft 32 rotatably supported in the missile body 1a by means of radial guide bearings 11a and a supporting bearing 12a in the form of a conical bearing, adjoins the propelling nozzle arrangement of the flow means distributor 10a. A braking arrangement 24a similar to the embodiment in FIG. 1, is used for the flow means distributor 10a. In this arrangement, it is generally assumed that the missile tip 2a rotates in the direction P-2, the missile body 1a rotates in the direction P-3 and the flow means distributor 10a rotates in the direction P-1 so that the relative rotational direction of the flow means 10a is adjustable in the opposite direction with respect to the missile tip 2a in a controlled manner by means of the braking arrangement 24a.
The "drive" of the flow means distributor 10a is afforded by a coil spring 33a made up of a plurality of windings tensioned or gripped in between the rotating missile tip 2a and the bearing shaft 32 of the flow means distributor 10a in the region of the round flange sleeve 3a of the missile tip 2a. During rotation of the missile tip 2a, the flow means distributor 10a is carried along in the following manner. When the braking arrangement 24a is applied, the coil spring 33a is tensioned. When the braking arrangement 24a is subsequently released, the flow means distributor 10a is accelerated in the same direction as the rotation of the missile tip 2a by the stored spring energy and runs ahead of the tip until the braking arrangement 24a is again applied. By alternating between applying and releasing the braking arrangement 24a, the relative angular position of the nozzle openings 18a-1, 18a-2 can be adjusted relative to the blow-out openings 19a-1, 19a-2 in the missile tip. The relative angular position between the flow means distributor 10a and the missile tip 2a is determined by the spring 33a. One position is defined with the tensioned spring acting against the flow means distributor 10a and the other position is defined when the expanded spring bears against the round flange 3a of the missile tip 2a. Two oppositely wound coil springs could also be used as a spring drive.
The operation of the embodiment shown in FIG. 3 is explained, along with the embodiment illustrated in FIG. 4, below with the aid of FIGS. 5a-5c.
FIG. 4 also shows the leading end of a missile 1b with a rotating missile tip 2b which is rotated by the fins 7b. The support of the missile tip 2b and the missile body 1b is the same as described for the above embodiments. The cylindrical flow means distributor 10b is supported in the missile body 1b in the same manner as in the embodiment in FIG. 1. A gas generator 16b, corresponding to FIG. 1, is provided for the flow means distributor 10b. The gas flows through a central gas duct 15b of the flow distributor means and flows outwardly through the radially arranged nozzle openings 18b-1, 18-b2. The gas jet can then exit through the corresponding blow-out openings 19b-1, 19b-2 in the missile tip 2b to produce a transverse force.
For the "drive" of the flow means distributor 10b relative to the rotating missile tip 2b, a wound leaf spring 33b is located under tension between the leading end of the flow means distributor 10b and the missile tip 2b.
A braking arrangement 24b constructed in the same manner as in the previously described embodiments, is provided for the flow distributor means 10b.
In the embodiment shown in FIG. 4, the gas flow from the gas generator 16b is not used for the drive of the flow means distributor 10b, or if so then only in an insubstantial manner.
FIGS. 5a-5c illustrate cross-sections through a missile in the region of the blow-out opening 19a, 19b, respectively, based on the embodiments set forth in FIGS. 3 and 4. It can be seen in FIGS. 5a-5c that the blow-out openings 19a-1, 19b-1 and 19a-2, 19b-2 are oppositely directed and extend approximately radially. During a zero command, the amount of overlap or alignment between the blow-out openings 19 and the nozzle openings 18 (18a-1, 18b-1, 18a-2, 18a-2) of the flow means distributor 10a, 10b is 50% so that oppositely directed transverse forces S-1 and S-2 of identical size are produced. These transverse forces S-1, S-2 are maintained by corresponding control of the flow means distributor during the rotation of the missile tip, the flow means distributor and the missile body. The missile body and the flow means distributor rotate in the same direction at the same rotational speed. When starting from zero command, the braking arrangement 24a, 24b is applied, and the flow means distributor lags in its rotation relative to the missile tip. This lagging action takes place, for example, until the nozzle opening 18a-1 (18b-1) corresponds with the cooperating blow-out opening 19a-1 (19b-1), according to FIG. 5a with the nozzle opening 18a-2 (18b-2) being blocked. Accordingly, a transverse force S'1 is produced for correcting the missile flow path. On the other hand, preceding from a zero command according to FIG. 5b, if the braking arrangements 24a (24b) is released, the flow means distributor 10a (10b) is accelerated in the same direction as the rotation of the missile tip by the energy stored in the spring drive. This can take place to the extent shown in FIG. 5c. In this angular position between the flow means distributor and the missile, the nozzle opening 18a-2 (18b-2) communicates fully with the blow-out opening 19a-2 (19b-2), while the respective radially opposite nozzle opening is completely closed. Under this condition, a radially acting transverse force S'2 is achieved for correcting the missile flight path.
Of course, all possible intermediate positions between the zero command and the indicated full command are possible. The arrangement of the individual openings in the flow means distributor and in the missile tip are set forth in FIGS. 5a-5c only by way of example. Other configurations are possible in addition to the laterally offset arrangement of the individual openings with respect to the central axis of the missile shown in FIGS. 5a-5c, as long as it is ensured that, during a zero command, the overlap extent is approximately 50% and the possibility exists of changing the overlapping arrangement up to a full command.
FIG. 6 shows a cross-section through a missile 1c in the region of the blow-out openings of the missile tip 2c which rotates independently due to the action afforded by the fins 7c. The flow means distributor 10c is driven either by a gas generator as shown in FIG. 1 or by ram air as shown in FIG. 3. The flow means distributor 10c includes a single propelling nozzle 17c arranged off-center and branched off from a central gas duct 15c with a nozzle opening 18c from the duct. The flow means distributor 10c can be rotated by alternating between applying and releasing a braking arrangement, not shown, in its angular position relative to the missile tip rotating in direction P-2, in both directions corresponding to the double arrow P-1.
The rotating missile tip 2c has three blow-out openings 19c equiangularly distributed over the circumference of the tip and, in each instance, the openings extend over an angle of approximately 90.degree. and are spaced form one another by separating webs 34c.
A relatively wide open space 35c is located between the flow means distributor 10c and the shell tip 2c. The separating webs 34c serve as impact and deflecting surfaces and, in each instance, comprise a concave recess 36c facing the flow means distributor 10c. For a zero command, the flow means distributor 10c is held, by the control circuit, not shown, in the position illustrated in FIG. 6, relative to the rotating missile tip 2c, in which position the gas jet exiting from the propelling nozzle 17c impacts against the concave recess 36c of the oppositely located separating web 34c. The gas flowing out of the propelling nozzle 17c is deflected by the concave recess 36c and is distributed uniformly into the open space 35c and flows into the atmosphere in equal portions through the three blow-out openings 19c. The sum of the transverse forces is zero, accordingly, the flight path of the missile 1c is not influenced. As is possible in the embodiments described above, the angular position of the flow means distributor 10c relative to the rotating missile tip 2c is held for a zero command in the position illustrated in FIG. 6 with the movement of the flow means distributor 10c being controlled, that is, by a pulse width modulation, or with the braking force applied by the braking arrangement being changed more or less continuously. In both cases, there is a bearing control of the rotating flow means distributor relative to the missile tip.
If, in the embodiment displayed in FIG. 6, a transverse force is produced in direction B, the braking arrangement is actuated and the propelling nozzle 17c is stopped in a position where the thrust direction points in the direction B. Since the missile tip 2c continues to rotate, a transverse force is produced in the direction B as soon as the separating web 34c releases the thrust jet of the propelling nozzle 17c. When the braking arrangement is again released, a partial command or a full command is brought about so that the full command acts during the time in which the missile tip rotates past the propelling nozzle 17c over the angular region of the subsequent blow-out opening 19c. If the partial or full command is interrupted, then either the braking arrangement for the flow means distributor 10c is released with the distributor being accelerated, as soon as the thrust jet impacts on the separating shoulder 34c which runs in advance, then the movements of the missile tip and the flow means distributor are coordinated so that a zero command is established, or, particularly in the long acting full command, the rotating means distributor 10c is braked until the gas jet from the propelling nozzle 18c impacts on the following separating web 34c so that a zero command is present. From this moment the rotational movements of the flow means distributor and the missile tip are again coordinated.
This embodiment has the advantage that a quasi-continuous full command can be set in a predetermined direction, for instance the direction B as shown. In addition, the rotating flow means distributor 10c is always held so that its gas jets act in the direction B. The transverse force produced is interrupted only when the separating webs 34c of the missile tip run past the propelling nozzle 17c. If the flow means distributor is fed by a gas generator, a higher utilization coefficient of the gas generator is effected.
The embodiment of the apparatus for correcting a missile flight path, shown only partially in FIG. 7, operates according to the same principle as the embodiment in FIG. 6. Instead of providing an open space between the flow means distributor 10d and the rotating missile tip 2d, a collecting duct 37d is provided in the region of the concave recesses 36d so that the gas flowing from the propelling nozzle 17d enters the collecting duct 37d and is conducted away in a directionally neutral manner. The collecting duct 37d, including the diverse ducts, not shown, extending to the gas exhaust from the missile, has a clearly lower resistance than the gas discharge nozzle at the flow means distributor for ensuring a virtually constant mass throughput for the total command functioning period. Only a slight gap remains between the flow means distributor 10d and the missile tip 2d. The gas generator is better utilized in this arrangement. The outlet opening 19d separated from one another by webs 34d, are divided by the webs 38d for better flow guidance of the thrust jet from the propelling nozzle.
In the embodiment of FIG. 6, the rotating flow means distributor can be accommodated opposite the separating web so that it either leads or lags with respect to the rotating missile tip for producing a zero command. In the embodiment of FIG. 8, it is only possible to switch from a zero command with leading action of the rotating flow means distributor 10e. The flow means distributor 10e comprises a single propelling nozzle 17earranged off-center and separated from the rotating nozzle tip 2e by an open space 35e. In this arrangement a construction corresponding to FIG. 7 would be possible. The flow means distributor 10e is driven in the direction of the arrow P-1 by the gas generator or by ram air.
The missile tip rotating in the direction P-2 is provided with fins 7e and, as in the embodiment of FIG. 6, includes three wide blow-out openings 19e separated from one another by webs 34e.
At the flow means distributor 10e,a stop 39e is positioned for cooperating with spring stops 40e mounted on the rotating missile tip 2e. Three spring stops 40e are provided and, in each instance, they are arranged so that when releasing the braking arrangement, not shown, the high-speed flow means distributor 10e runs up against a corresponding spring stop 40e with its stop 39e and secures the propelling nozzle 17e in a position so that the gas jet flowing from the propelling nozzle 17e impacts against a separating web 34e. The relative angle between the flow means distributor 10e and the rotating missile tip 2e is maintained as long as the braking arrangement is released. The resulting command is a zero command. In contrast to the above embodiment, a control of the rotation of the flow means distributor 10e for maintaining zero command is not necessary. If a partial or full command is given in the direction B, the flow means distributor 10e is held by the braking arrangement so that the thrust jet acts in the direction B. If the command is cancelled by releasing the braking arrangement, the flow means distributor 10e accelerates until it runs up against the spring stop 40e in the leading direction and a zero command is again established. If a full command in direction B is to be maintained for a longer period of time, it can be effected in the same manner as in the embodiment shown in FIG. 6. The spring stops 40e are constructed so that they can override the stop 39e on the flow means distributor 10e during the rotation of the missile tip in the direction P-2.
FIGS. 9 and 10 display another embodiment of an apparatus for correcting a missile flight path with a modified spring drive for the flow means distributor 10f.
It is assumed that the flow means distributor 10f is supplied by a gas generator corresponding approximately to the embodiment shown in FIG. 4. The cylindrical flow means distributor 10f has only one nozzle 17f which opens into a radial nozzle opening 18f. In the region of the leading end of the cylindrical flow means distributor 10f, a spring drive is provided, similar to the one in FIG. 4, and it consists of a coil spring 33f clamped between the rotating missile tip 2f and the flow means distributor 10f. This clamping action is, however, not fixed on the missile tip 2f but rather, three stops 41f for one end 42f of the coil spring 33f with the spring end 42f bent outwardly toward the missile tip, are provided within the missile tip. The stops 41f are formed so that with the release of the braking arrangement, the flow means distributor 10f is carried along by the bent spring end 42f and rotates along with the missile tip in the direction P2 at the same rate of rotation.
FIG. 10 portrays the angular position between the flow means distributor 10f and the missile tip 2f during common rotation. The missile tip 2f has three circumferentially spaced blow-out openings 19f separated by webs 34f. The missile is constructed in the region of the blow-out openings 19f in correspondence with FIGS. 6 or 7. In FIG. 10 a construction corresponding to FIG. 6 is used. Accordingly, as long as the braking arrangement is released and the flow distributor 10f is carried along in the rotation of the missile tip 2f, the gas jet from the propellent nozzles 17f runs against a web 34f so that a zero command is present. If a command is given in the direction B the flow means distributor 10f is then braked and stopped when the gas jet points in the direction B. The gas jet from the nozzle opening 18f still runs up against the web 34f during this time. Next, however, the missile tip 2f continues to rotate and the gas jet flowing out of the blow-out opening 19f trailing the separating web 34f flows out in direction B so that an opposite transverse force is produced for correcting the missile flow path.
During continued rotation of the missile tip 2f, coil spring 33f is tensioned and stores energy. If, for example, only a short partial command is given in the direction B extending only a small angular rotation of the missile tip 2f, then the braking arrangement is released at the end of the partial command. The flow means distributor 10f is rotated by the stored spring energy in the direction of rotation P-2 of the missile tip 2f until the nozzle opening 18f again is aligned opposite a web 34f which is running ahead. Again the zero command is present, and the flow means distributor 10f is carried along in rotation by the missile tip, as described above.
If the command is to act over a longer period of time, the braking arrangement is applied for a corresondingly longer time. During braking of the flow flow means distributor 10f, coil spring 33f is tensioned, as described above until the bent end 42f of the spring overrides the stop 41f on the side of the missile tip 2f during the continued rotation of the missile tip 2f. The coil spring 33f relaxes until the next stop 41f on the side of the missile tip 2f runs against the bent end 42f of the coil spring. The full command can be maintained either by the continued braking of the flow means distributor in the fixed spatial position B, where the coil spring 33f alternately is under tension and relaxes, or the full command can be terminated by releasing the braking arrangement. The coil spring which, as a rule, is tensioned up until this time, accelerates the flow means distributor 10f in the direction P-2 until the nozzle opening 18f again trails behind a web 34f. If the coil spring is already relaxed precisely when the full command is interrupted, because the bent end 42f has contacted a stop 41f, then the end is carried along with the stop 41f and the zero command again results. The dead time between full command and zero command is increased, however, though only slightly, by means of this second possibility. Such dead time can be shortened in a transition, via the control circuit, from full command to partial command when the coil spring 33f is tensioned. The control circuit is operated by information on the changeover criterion by corresponding angle transmitters between the missile tip, the flow means distributor and the missile body, as explained in the description of the embodiment in FIG. 1.
In principle, the rotational directions of the missile tip, the flow means distributor and the missile itself can be independent of one another in all of the embodiments, since the rotary drive for the full means distributor can be adjusted in all of these embodiments. A regulation of the angular position of the flow means distributor in the embodiments shown in FIGS. 8-12 is desirable, but is not absolutely necessary, since the flow means distributor always runs automatically into a position corresponding to a zero command when the braking arrangement is released.
FIG. 11 illustrates the leading end of a missile 1g with a rotatable missile tip 2g. The missile tip rotates due to the obliquely oriented fins 7g. In a manner similar to that of the embodiment in FIG. 1, a cylindrical flow means distributor 10g with a braking arrangement 24g is supported in the missile body. The flow means distributor 10g cooperates with a gas generator 16g with the gas flowing through a central gas duct 15g to a single radial nozzle 17g. A plurality of blow-out openings 19g separated from one another by webs 34g, are distributed on the circumference of the rotating missile tip in the region of the nozzle opening 17g. Each of the webs 34g has a concave recess 36g facing toward the flow means distributor 10g and a collecting duct 37g extend from the recess 36g. In this embodiment, similar to the embodiment in FIG. 7, a zero command is achieved when the nozzle 17g faces a web 34g and the exiting gas flow is guided through the collecting duct 37g and is conducted away in a directionally neutral manner.
The drive for the flow means distributor 10g is effected by the rotating missile tip itself. In addition, a friction lining 45g is provided in the base of the borehole 14g in the missile tip 2g and the friction lining 45g is located in contact with the leading end face 46g of the flow distributor means 10g. The friction between the friction lining 45g and the leading end face 46g is dimensioned so that the flow means distributor 10g is carried along by the missile tip 2g when the braking arrangement 24g is released. Accordingly, when the flow means distributor 10g is located in the position shown in FIG. 12, a zero command exists and this zero command is maintained during the continued rotation of the missile tip 2g. As soon as the braking arrangement 24g is applied, the flow means distributor remains stationary relative to the missile body or it is at least braked while the missile continues to rotate. The gas jet flowing from the nozzle 17 g is then conducted through the adjacent blow-out opening 19g of the missile tip 2g. Here, as well, a fine dosing of the transverse force can be achieved with the overlap extent correspondingly adjusted between the nozzle opening 17g and the blow-out opening 19g. As soon as the desired overlapping is achieved, the braking arrangement 24g is released so that the flow means distributor 10g is carried along by the missile tip 2g. The extent of the overlapping is preferably adjusted in front of the next web 34g so that the maximum transverse force has already been exceeded. If a zero command is subsequently produced, the braking arrangement 24g is again applied and is released only when the nozzle opening 17g disappears behind the next web 34g of the missile tip.
In these embodiments an independently rotating missile tip, stable with respect to loading, is provided with blow-out openings in each instance. It is also possible, however, to permit another part of the missile to rotate instead of the missile tip, that is, a cylindrical part of the missile in the region of its trailing end is provided with the blow-out openings.
It is also possible to align the blow-out openings in the rotating part so that the transverse force, in addition to the radial component for correcting the flight path, also includes axial components for propelling the missile in the forward direction.
If the transverse force is produced by ram air, the outlet openings of the flow means distributor can be closed for a zero command. In contrast to the embodiments using the gas generator, an exhaust of the ram air is unnecessary.
It is also possible to install the described apparatus in other than a missile, such as in a self-propelled flying body for the purpose of correcting its flight path.
While specific embodiments of the invention have been shown and described in detail to illustrate the application of the inventive principles, it will be understood that the invention may be embodied otherwise without departing from such principles.

Number	Name	Date
4463921	Metz	Aug 1984
4522357	Bains et al.	Jun 1985
4573648	Morenus et al.	Mar 1986
4589594	Kranz	May 1986

Apparatus for correcting the flight path of a missile

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