DE3014480C1 - Acceleration-resistant gyroscope for missiles - Google Patents

Description

a) an elastically suspended bearing (3, 4, 5, 6, 8) with a relatively small amount of play rotating parts as well as

b) has a rigid support bearing (21, 22; surfaces 2.2, 7.3; 7.2,10.1) with a comparatively large play (d \, ?, dz 7, di, io) of the parts moving relative to one another, whereby the elastically suspended bearing when exceeded predetermined acceleration values is relieved.

2. A position gyro according to claim 1, characterized by further frames (7) rotatable about mutually perpendicular axes (7.1) with at least one elastically suspended bearing (8), the frames (2, 7) on the respective adjacent sides defined contact surfaces (2.2 , 7.3) that have a defined distance (d% 7) from one another in the non-accelerated state of the attitude gyro.

3. Location gyro according to claim 1 or 2, characterized by a housing (10) in which the outer frame (7) is rotatably mounted in at least one elastically suspended bearing (8), the housing and the frame having defined contact surfaces (7.2, 10.1 ) which have a defined distance (dj, 10) from one another in the non-accelerated state of the position gyro.

4. Location gyro according to one of claims 1 to 3, characterized in that at least one of the Support bearing is designed as a slide bearing (21,22).

5. Position gyro according to one of claims 1 to 4, characterized in that the resiliently suspended Bearings (3, 4, 5, 6, 8) are movable in the radial and / or axial direction.

6. Location gyro according to one of claims 1 to 3, characterized in that the resiliently suspended Bearings (3,4,5,6) Brackets (16,17,18,19) made of tough elastic material.

The invention relates to an acceleration-resistant attitude gyro for missiles with a gimbal-mounted one Centrifugal rotor, which is held in bearings in a frame and the frame also has bearings for rotation has about a further axis.

In positional gyroscopes of this type, a comparatively small, heavy gyroscope is only set in rotation shortly before or with the launch of the missile, which can be done, for example, by the propellant gases of a fuel charge, which act on the turbine-like blades of the gyroscope and rotate it to a few 1000 revolutions in a short time bring per second. During this drive phase, the gimbal suspension of the rotor must be blocked. The cardanic suspension is only released when the target speed is reached and the drive phase of the rotary rotor has ended. This release often happens in a phase in which the missile is exposed to very high take-off accelerations; in special cases these can ^{exceed 10 4} g. Since the acceleration forces are only transmitted to the frame and the rotor via the bearings, the bearings must be appropriately oversized to avoid damage, which, however, affects the sensitivity of the gyroscope. Despite the corresponding oversizing of the bearings, the acceleration resistance of known position gyros is comparatively low.

It is the object of the invention to create an acceleration-resistant attitude gyro for missiles, which maintains this functionality even through the intervention of high starting accelerations. Fulfilled this task a trained according to claim 1 position gyro, which is advantageous according to the subclaims can be trained.

In the following, the invention will be explained in more detail with reference to an embodiment shown in the figures will. It shows

F i g. 1 shows a section through an acceleration-resistant position gyro along the rotor axis;

F i g. 2 a section perpendicular to the rotor axis.

In the case of the FIG. 1 and 2, a rotary rotor 1 is rotatably mounted in a first frame 2 in ball bearings 3 and 4. The frame 2 is in turn rotatably mounted about an axis 2.2 perpendicular to the rotor axis 1.1, likewise in ball bearings 5 and 6 within a second frame 7. The second frame 7 is in turn rotatably suspended in ball bearings 8 and 9 (FIG. 2) in a housing 10 and is provided with a tap 11 which indicates changes in the angle of the frame 7 with respect to the housing 10. In the frame 2 and 7 and in the housing 10, coaxial bores 12, 13 and 14 are provided through which a propellant gas from a gas generator 15 is guided in the tangential direction onto the rotary rotor 1, and there it strikes the guide vanes 1.1, which through Millings in the outer surface of the rotary rotor 1 have arisen.
The attitude gyro is installed in a missile in such a way that the take-off accelerations (arrow b) in the direction of the frame axis 7.1 act in the direction shown. A gyro installed in this way then serves, for example, to stabilize the missile's roll.

For the case in which the acceleration forces act on the position gyro in the direction shown, are the bearings of the rotary rotor 3 and 4 and the bearings 5 and 6 of the first frame 2 in rings 16, 17, 18 and 19 embedded from a tough elastic material. This allows the rigid radial bearings 3 to 6 under the Dodge the influence of acceleration forces perpendicular to the bearing axis.

The radial bearings 8 and 9 of the second frame 7 are fastened in the housing 10 or on the frame axis in such a way that an axial movement is possible in a direction opposite to the acceleration b. For this purpose, the bearing 8 is elastically supported in the axial direction by a spring 20.
The high acceleration forces occurring during take-off in the direction shown cause the following in the attitude gyro:

Under the influence of inertia, the spring 20 is compressed until the normally defined in a

ORIGINAL INSPECTED

Distance d ₇ , \ ₀ located surfaces 7.2 and 10.1 of the second frame and the housing touch. The surfaces 7.2 and 10.1 have a defined roughness and size and thus a calculable friction. The spring 20 as well as the roughness and the distance d ₇ , _{] 0 of} the surfaces 7.2 and 10.1 are matched to one another in such a way that the frame 7 is securely supported and blocked by the housing 10 when a predetermined acceleration value is exceeded.

Due to the inertia forces, the viscoplastic rings 18 and 19 will continue to deform until the surfaces 2.2 of the first frame and 7.3 of the second frame , which are normally located at a defined distance (J2,7), also touch. The elastic properties of the rings 18 and 19 and the distance ofe, 7 are coordinated so that the bearings 5 and 6 are not further loaded by a predetermined acceleration force, since the frame 2 is then directly supported by the frame 7 via the contact surfaces 2.2 and 7.3, also with a defined roughness.

Finally, under the further influence of the acceleration force, the viscoplastic rings 16 and 17 of the rotor bearings 3 and 4 are also deformed until the rotor axes 1.3 and 1.4 are laterally displaced so far that they touch concentrically arranged run-up disks 21 and 22. Since the rotor 1 is blown by the gas generator 15 during the launch phase of the missile, that is, it is set in rotation, the run-up disks 21 and 22 are designed as comparatively large sliding bearings, so that the rotor is only slightly braked during the acceleration phase. The elastic properties of the rings 16 and 17 as well as the play d \, ₂ between the run-up disks and the rotor axes in the non-accelerated state is in turn coordinated so that the bearings 3 and 4 are no longer loaded beyond predetermined acceleration forces.

At the end of the starting phase, the acceleration force decreases, so that the distances d 1, 2, ofe, 7 and d ₇ , 10 shown are set again due to the elastic properties of the rings 16 to 19 and the spring 20. Since the contact surfaces 2.2 and 7.3 as well as 7.2 and 10.1 have both a defined roughness and a defined size, the acceleration value at which the gyro frames are free can be precisely determined in advance. With the appropriate dimensioning of the elastic mountings and the contact surfaces as well as a corresponding action time of the gas generator 15, a separate device for blocking the gyro frame during the starting phase can be dispensed with.

For this purpose 2 sheets of drawings

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Claims (1)

Patent claims: 1. Acceleration-resistant attitude gyro for missiles with a gimbal-mounted rotor, which is held in a frame in bearings and the frame also bearings for rotation about a has another axis, characterized in that the bearings of the rotary rotor (1) and the frame (2,7) each at least