GB2039056A - Rolling- or rotational-position measuring means for spin-stabilised flying bodies and projectiles - Google Patents
Rolling- or rotational-position measuring means for spin-stabilised flying bodies and projectiles Download PDFInfo
- Publication number
- GB2039056A GB2039056A GB7941101A GB7941101A GB2039056A GB 2039056 A GB2039056 A GB 2039056A GB 7941101 A GB7941101 A GB 7941101A GB 7941101 A GB7941101 A GB 7941101A GB 2039056 A GB2039056 A GB 2039056A
- Authority
- GB
- United Kingdom
- Prior art keywords
- projectile
- rolling
- rotational
- flying body
- measuring means
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000005096 rolling process Methods 0.000 claims abstract description 21
- 239000007787 solid Substances 0.000 claims description 20
- 238000011156 evaluation Methods 0.000 claims description 14
- 230000001419 dependent effect Effects 0.000 claims description 8
- 238000012545 processing Methods 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 238000012937 correction Methods 0.000 description 7
- 230000001133 acceleration Effects 0.000 description 5
- 230000005484 gravity Effects 0.000 description 5
- 239000003990 capacitor Substances 0.000 description 4
- 230000003321 amplification Effects 0.000 description 2
- 230000002596 correlated effect Effects 0.000 description 2
- 238000003199 nucleic acid amplification method Methods 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005474 detonation Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C9/00—Measuring inclination, e.g. by clinometers, by levels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/24—Beam riding guidance systems
- F41G7/26—Optical guidance systems
- F41G7/266—Optical guidance systems for spin-stabilized missiles
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P15/00—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration
- G01P15/02—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses
- G01P15/08—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values
- G01P15/09—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values by piezoelectric pick-up
- G01P15/0907—Measuring acceleration; Measuring deceleration; Measuring shock, i.e. sudden change of acceleration by making use of inertia forces using solid seismic masses with conversion into electric or magnetic values by piezoelectric pick-up of the compression mode type
Abstract
Rolling- or rotational-position measuring means 2, for a flying body or projectile 1, comprises a sensor, arranged eccentrically to the axis of the flying body or projectile 1 for generating a signal, and an electronic circuit 3 for evaluating this signal, the sensor comprising a piezoceramic cell 4 and a mass 5 able to act upon said cell, said mass 5 being arranged on that side of the piezoceramic cell 4 which faces the axis of the flying body or projectile 1, and being movable to some extent in the radial direction. The arrangement enables information regarding the rolling or rotational position to be acquired without requiring transmission of additional data from the outside. All the components of the measuring means 2 can be combined into one subassembly. Instead of a piezoceramic cell, a piezoresistive element co-operating with a voltage source may be provided. <IMAGE>
Description
SPECIFICATION
Rolling- or rotational-position measuring means for spin-stabilised flying bodies and projectiles
The invention relates to rolling- or rotationalposition measuring means for a spin-stabilised flying body or projectile. There is described herein rolling- or rotational-position measuring means having a sensor, arranged eccentrically to the axis of the flying body or projectile, for producing a signal which is dependent upon the instaneous rolling or rotational position, and an electronic evaluation circuit, arranged subsequent to said sensor, for further processing of this signal.
If, in the case of a spin-stabilised flying body or projectile, a correction of its flight path is to be performed after firing, then for this purpose information regarding its instantaneous rolling or rotational position is needed. To carry out such a flight-path correction it is for example known from
German Offenlegungsschrift 22 64 243 to exert on a projectile, as a result of detonation of small additional charges situated at discrete points on the periphery of the projectile, a brief correction impulse directed perpendicularly to the direction of motion of the projectile.
The instantaneous rolling or rotational position is ascertained, in the case of this known projectile, by way of a Helmholtz coil in which, by virtue of its motion, brought about as a result of the rotation of the projectile, in the terrestrial magnetic field there is induced a signal in the form of a voltage the value of which is dependent on the respective position of the coil with regard to the terrestrial field. This signal is further processed, in an electronic evaluation circuit connected subsequent to said coil, to ascertain the desired information regarding the rolling or rotational position.
The known arrangement has, in this respect, the disadvantage that, to ascertain the angle of roll or rotation from the sensor signal, there has to be present in addition a stationary measuring unit similarly containing a Helmholtz coil customarily in the launching device, to produce a comparison signal. However, this requires not only increased technical expenditure, but at the same time it presupposes an appropriate co-ordination of both measuring units.Furthermore, it is disadvantageous that, in the case of this known arrangement, the information regarding the rolling or rotational position cannot be acquired without transmission of additional data from the outside, in this instance from the stationary second measuring unit, exclusive of the projectile;
It is in addition known inter alia from German
Offenlegungsschrift No. 26 58 167, to ascertain the rolling or rotational position of a projectile from a launching device with the aid of a laser beam which is reflected as a linearly-polarised beam from a combination, arranged on the tail or rear of the projectile, consisting of a reflector and a polariser. However, what is disadvantageous about this known arrangement is the ambiguity of the achievable signal with respect to a rotation of the projectile by 1800 about its longitudinal
axis.This ambiguity can be eliminated only by additional measures, such as for instance an additional horizontal sensor or a sequence of correction impulses. In the case of this known arrangement, too, it is not possible to undertake the ascertainment and evaluation of the rolling- or rotational-position signal exclusively by the projectile.
A problem underlying the invention is to design - rolling- or rotational-position measuring means which is such as to allow solely by virtue of the information attainable in the flying body or projectile a clear statement regarding the instantaneous rolling or rotational position and which is at the same time able to be constructed as simply as possible.
According to the invention, there is provided rolling or rotational-position measuring means for a spin-stabilised flying body or projectile, said means having a sensor, arranged eccentrically to the axis of the flying body or projectile, for producing a signal which is dependent upon the instantaneous rolling or rotational position, and an electronic evaluation circuit, arranged subsequent to said sensor, for further processing this signal, and said sensor comprising a piezoceramic cell or piezoresistive element and a solid or massive body which is arranged, on that side of the piezoceramic cell or piezoresistive element facing the axis of the flying body or projectile so as to be movable to some extent in the radial direction and by whcih the piezoceramic cell or piezoresistive element can be acted upon.
Said piezoceramic cell or piezoresistive element is acted upon by the solid or massive body with differing intensities, dependent on the instantaneous rolling or rotational position of the flying body or projectile and the component, of the force of gravity, thereupon acting on the solid or massive body in its direction of motion.
In the case where the sensor includes a piezoceramic cell the variation of the voltage induced in the piezoceramic cell by virtue of its being acted upon by the solid or massive body is thereby correlated in a clear manner with the rolling or rotational motion of the flying body or projectile. The sensor supplies an approximately sinusoidal signal, in which respect the maximum of the signal curve corresponds to an instantaneous rolling or rotational position of the flying body or projectile in which the sensor is turned to the surface of the earth, whilst the minimum corresponds to a rolling or rotational position turned through 1800 as compared therewith.
The fact that a signal produced in the rolling- or rotational-positiori measuring means depends upon the acceleration components acting on the solid or massive body which acts upon the piezoceramic cell, not only makes possible a clear indication of the respective instantaneous rolling or rotational position as well as of the frequency of rotation of the flying body or projectile, but also makes it possible, in the case of self-propelled flying bodies, at the same time to determine the propellant cut-off or burnout, and therewith the end of the acceleration phase, without additional aids being necessary for this purpose. Such additional information is of importance insofar as possible flight-path corrections are customarily initiated only after cut-off or burnout of the acceleration propellant charge or charges.
Instead of a piezoceramic cell, within the scope of the invention there may be used in the same way and with the same arrangement a piezoresistive structural element co-operating with a voltage source, e.g. a battery. In this case, too, a sensor signal similar to the one described above may be obtained.
Advantageously, the piezoceramic cell or piezoresistive element and the solid or massive body may be combined into one structural element insertable as a whole into the flying body or the projectile. In this way, the rolling- or rotational-position measuring means can not only be produced in a particularly simple and pricefavourable manner, but can in addition be extremely insensitive to disturbing influences from outside.
These advantages are additionally supplemented, in the case of a preferred embodiment of the invention, in that the sensor and an electronic evaluation circuit are combined into one subassembly. In this way, the rolling- or rotational-position measuring means can be incorporated by way of addition in a particularly simple manner in flying bodies and projectiles or be exchanged at any time.
Also, according to the invention, there is provided a spin-stabilised flying body or projectile having rolling- or rotational-position measuring means comprising (a) a pressure-responsive device for generating in a circuit of the measuring means a voltage the magnitude of which is a function of the pressure, or a pressure-responsive device for causing the magnitude of a voltage in a circuit of the measuring means to be a function of the pressure, and (b) a mass mounted so as to be able to exert pressure on the pressure-responsive device in a direction radially of the axis of the flying body or projectile whereby the pressure, and thereby the said voltage magnitude, has a dependent relationship to the instantaneous rolling or rotational position of the flying body or projectile.
In the accompanying drawings, which show by way of example, one embodiment constructed in accordance with the invention:
Figure 1 shows a schematic representation of an arrangement of rolling- or rotational-position measuring means constructed in accordance with the invention, in a flying body;
Figure 2 shows an example of an electronic evaluation circuit or rolling- or rotational position measuring means constructed in accordance with the invention; and
Figures 3ad show graphically the signal variation at various points of the electronic evaluation circuit in accordance with Figure 2.
Referring to the drawings, incorporated in the interior of a spin-stabilised flying body 1 , and disposed eccentrically to its longitudinal axis, is rolling- or rotational-position measuring means 2 which contains a sensor and an electronic evaluation circuit 3 and which forms an encapsulated subsassembly. The sensor shown consists of a disc-shaped piezoceramic cell 4, and a solid or massive body 5 which is movable in the radial direction and which is opposed to the piezoceramic cell and is separated from this by an insulating layer 6. The piezoceramic cell 4 is provided with connecting lugs or contacts 7, of which one is connected directly to the wall of the flying body 1, whilst the other is conducted in insulated manner to the electronic evaluation circuit 3.
An example of the construction of the electronic evaluation circuit 3 is shown in Figure 2. In this example the circuit has, in an input part connected to the piezoceramic cell 4 by way of the appropriate contact 7, a first resistor R1, a first capacitor C1 and a first operational amplifier OP1.
Connected subsequent to this are a second operational amplifier OP2, differentiating means consisting of a second capacitor C2 and a second resistor R2, having a diode D in parallel with the second resistor R2.
By virtue of the spinning motion of the flying body 1, there acts on the solid or massive body 5, which is movable in the radial direction, a centrifugal force which is dependent upon the rotational speed of the flying body 1 and which presses this towards the piezoceramic cell 4. The pressure with which the solid or massive body 5 is, in this respect, pressed towards the piezoceramic cell 4 is, over one complete revolution of the flying body 1, approximately constant. At the same time the force of gravity acts on the solid or massive body 5, in which respect, however, only that component of the force of gravity which extends in the direction of motion of the solid or massive body 5 is effective with regard to the signal generation. The remaining component is absorbed by a lateral enclosure of the solid body 5.
If now the flying body 1 is in such a rolling or rotational position that the rolling- or rotationalposition measuring means 2 lies exactly underneath the longitudinal axis of the flying body 1, then the solid or massive body 5 is forced towards the piezoceramic cell 4 not only by the centrifugal force, but also by its weight. In this way the voltage produced in the cell reaches its maximum value. When the flying body has rotated by a further 90 about its longitudinal axis,. then the weight of the solid or massive body 5 is absorbed completely by the side walls of the rolling- or rotational-position measuring means 2 and the impingement on the piezoceramic cell 4 is effected solely by the centrifugal force acting on the solid or massive body 5.After a further 900, i.e. when the rolling- or rotational-position measuring means is disposed exactly above the
axis of the flying body, the weight of the solid or
massive body 5 acts against the centrifugal force
acting on it. Thus the pressure on the
piezoceramic cell 4, and thus the voltage
produced in it, i-eaches its minimum value.
There thus results at the output of the sensor a signal whose variation in time corresponds to the
curve shown in Figure 3a. The signal voltage is composed of a voltage component which can be
regarded for a brief period as constant and which
is produced by the centrifugal force - and which decreases with the slowing-down of the rotation of the projectile-and of an oscillating component. The frequency of this latter component corresponds to the frequency with which the flying body 1 rotates about its longitudinal axis, whereby a direct measurement of this frequency is possible. At the same time, each point of the signal curve corresponds to a specific angle of roll or rotation, whereby a clear determination of the rolling or rotational position is possible.
Further processing of the signal can be effected with the aid of the aforesaid electronic evaluation circuit 3 shown, as an example, in Figure 2. In this circuit, intitiallythe resistor R1 serves to reduce the D.C. voltage signal caused by the centrifugal force, the capacitor C1 keeping residual portions of this signal away from the input of the first operational amplifier OP 1. This first operational amplifier OP 1 serves on the one hand as an impedance transformer, on the other hand a powerful amplification of the A.C. voltage signal lying at the input is here achieved (Figure 3b).After a further amplification as far as within the limitation by the second operational amplifier OP2 (Figure 3c) there are produced, by the subsequent differentiating means consisting of the resistor R2 and the capacitor C2, respective position and negative pulses (Figure 3con. The negative pulse is filtered out by the diode D in parallel with the output so that a positive pulse is available as output signal of the electronic evaluation circuit.
This is unequivocally correlated with a fixed or particular rolling or rotational position of the flying body 1 and can -- possibly together with the information regarding the frequency of rotation be used to trigger a correction impulse by detonating a booster charge.
During the acceleration phase of the flying body 1, i.e. up to cut-off or burnout, there acts on the solid'or massive body 5, in addition to the force of gravity and to the centrifugal force, the projectile acceleration;which similarly has a component in the direction of motion of the solid or massive body 5 and is in this respect directed contrary to the force of gravity. The course of the signal variation in this flight phase thus deviates from the course of the signal variation after cut-off or burnout. This difference can additionally be made use of for information regarding the onset of the cut-off or burnout in order to determine the earliest point in time for triggering a correction impulse.
Claims (7)
1. Rolling- or rotational-position measuring means for a spin-stabilised flying object or projectile, said means having a sensor, arranged eccentrically to the axis of the flying body or projectile, for producing a signal which is dependent upon the instantaneous rolling or rotational position, and an electronic evaluation circuit, arranged subsequent to said sensor, for further processing this signal, and said sensor comprising a piezoceramic cell or piezoresistive element and a solid or massive body which is arranged, on that side of the piezoceramic cell or piezoresistive element facing the axis of the flying body or projectile, so as to be movable to some extent in the radial direction and by which the piezoceramic cell or piezoresistive element can be acted upon.
2. A spin-stabilised flying body or projectile having rolling- or rotational-position measuring means comprising (a) a pressure-responsive device for generating in a circuit of the measuring means a voltage the magnitude of which is a function of the pressure, or a pressure-responsive device for causing the magnitude of a voltage in a circuit of the measuring means to be a function of the pressure, and (b) a mass mounted so as to be able to exert pressure on the pressure-responsive device in a direction radially of the axis of the flying body or projectile whereby the pressure, and thereby the said voltage magnitude, has a dependent relationship to the instantaneous rolling- or rotational position of the flying body or projectile.
3. Rolling- or rotational-position measuring means as claimed in Claim 1, wherein the piezoceramic cell or piezoresistive element and the solid or massive body are combined into one structural element which is insertable as a whole into the flying body or projectile.
4. Rolling or rotational-position measure means as claimed in Claim 1 or 3, wherein the sensor and the electronic evaluation circuit are combined into one subassembly.
5. A spin-stabilised flying body or projectile as claimed in Claim 2, wherein the pressureresponsive device is a piezoceramic cell.
6. A spin-stabilised flying body or projectile as claimed in Claim 2, wherein the pressureresponsive device is a piezoresistive element.
7. A spin-stabilised flying body or projectile having rolling- or rotational-position measuring means, substantially as herein described with reference to the accompanying drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19782853779 DE2853779B2 (en) | 1978-12-13 | 1978-12-13 | Rolling knife for spin-stabilized missiles and projectiles |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB2039056A true GB2039056A (en) | 1980-07-30 |
| GB2039056B GB2039056B (en) | 1983-04-13 |
Family
ID=6057040
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB7941101A Expired GB2039056B (en) | 1978-12-13 | 1979-11-28 | Rolling or rotational-position measuring means for spin-stabilised flying bodies and projectiles |
Country Status (3)
| Country | Link |
|---|---|
| DE (1) | DE2853779B2 (en) |
| FR (1) | FR2444254A1 (en) |
| GB (1) | GB2039056B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4325218A1 (en) * | 1993-07-28 | 1995-02-02 | Diehl Gmbh & Co | Artillery missile |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0208544B1 (en) * | 1985-07-10 | 1989-09-06 | British Aerospace Public Limited Company | Ballistic projectiles |
| EP0371007A3 (en) | 1985-11-22 | 1991-04-17 | Ship Systems, Inc. | Spin-stabilized projectile with pulse receiver and method of use |
| DE4443134C2 (en) * | 1994-12-03 | 2001-07-05 | Diehl Stiftung & Co | Sensor device for a missile |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1009370A (en) * | 1972-01-03 | 1977-04-26 | Ship Systems | Laser guided projectile |
| US3924824A (en) * | 1973-10-17 | 1975-12-09 | Singer Co | Cross track strapdown inertial quidance system |
| US4054254A (en) * | 1975-12-04 | 1977-10-18 | General Dynamics Corporation | Rolling airframe autopilot |
| DE2658167C2 (en) * | 1976-10-30 | 1983-01-20 | Eltro GmbH, Gesellschaft für Strahlungstechnik, 6900 Heidelberg | Method and device for correcting the trajectory of a projectile |
-
1978
- 1978-12-13 DE DE19782853779 patent/DE2853779B2/en active Granted
-
1979
- 1979-11-28 GB GB7941101A patent/GB2039056B/en not_active Expired
- 1979-12-05 FR FR7929858A patent/FR2444254A1/en active Granted
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4325218A1 (en) * | 1993-07-28 | 1995-02-02 | Diehl Gmbh & Co | Artillery missile |
| US5467940A (en) * | 1993-07-28 | 1995-11-21 | Diehl Gmbh & Co. | Artillery rocket |
| DE4325218C2 (en) * | 1993-07-28 | 1998-10-22 | Diehl Stiftung & Co | Artillery missile and method for increasing the performance of an artillery missile |
Also Published As
| Publication number | Publication date |
|---|---|
| DE2853779A1 (en) | 1980-06-26 |
| DE2853779B2 (en) | 1981-07-16 |
| DE2853779C3 (en) | 1988-02-11 |
| FR2444254B3 (en) | 1981-09-11 |
| GB2039056B (en) | 1983-04-13 |
| FR2444254A1 (en) | 1980-07-11 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |