Classifications

• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
  • G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
  • G01P3/64—Devices characterised by the determination of the time taken to traverse a fixed distance
  • G01P3/66—Devices characterised by the determination of the time taken to traverse a fixed distance using electric or magnetic means
  • G01P3/665—Devices characterised by the determination of the time taken to traverse a fixed distance using electric or magnetic means for projectile velocity measurements

Definitions

• the invention relates to a method and an apparatus for measuring a projectile or parts thereof, during flight, possibly up to the target area.
• the object of the present invention is to provide a method and a device for measuring a projectile or parts thereof, which work simply, are versatile and enable the use of simple and inexpensive sensors.
• This object is achieved by a method in which the electrical charge, which is given to the projectile or its parts by air friction and / or gas cloud generated by ignition or detonation, is detected by at least one inductively operating sensor and the zero crossing of the received signal is evaluated.
• a projectile receives an electric charge on its way to its destination as a result of air friction. This induces a voltage in the form of a signal with a zero crossing when flying past the sensor or when passing through the sensor due to a magnetic field generated by a moving charge in the induction coil is measured, its speed can be determined.
• the Sig can trigger other measuring devices, for example target X-ray devices.
• the speed of the projectile or part thereof can be predetermined by using two or more along the trajectory JL
• the fragments of explosive projectiles or the like are electrically charged by the gas cloud of the explosive and can accordingly be measured, whereby a temporal resolution of the fragment cloud can be taken before.
• the method can be carried out by means of a device which detects at least one sensor with an induction coil in the area of the flight path, which is coupled to an evaluation device which records at least zero time crossing of the signal generated by the sensor.
• Fig. 1 shows schematically a device for measuring a projectile.
• Fig. 2 shows schematically the course of a device generated by the sensor of the device, of Fig. 1.
• 3 schematically shows the use of several sensors along the trajectory of a projectile.
• the device shown in Fig. 1 comprises a sensor 1 made of egg on a frame 2, which is, for example, a simple wooden frame, ge celtic induction coil 3.
• the frame 2 can have a circumferential groove 4 for receiving a few turns of the induction coil 3 have isolated Dra.
• the frame 2 can have a stand 5, which makes it easier to set.
• the area 1 enclosed by the induction coil 3 expediently in the range from approximately 1 to 6 m 2 . It is also expedient to arrange the frame 2 as perpendicular as possible to the direction of flight 6 of a jectile 7 to be detected.
• the induction coil 3 is connected to a matching circuit 8, a preamplifier 9, a filter 10, a squelch 11 and a device driver 12, via a line 13 and a line sensor 14, the signal generated by the induction coil can be given to an evaluation direction 15 are, preferably a transiscope, ie digital memory and screen display, so that a visual evaluation can be vorgeno.
• a computer 15 and / or a timer 17 a be closed to carry out an automatic evaluation.
• a pulse that can be measured at the induction coil 3 has a maximum spa of the order of a few 100 uV when a projectile 7 flies past or through the induction coil 3.
• Fig. 2 shows voltage pulse as it is generated by the induction coil 3 depending on the t or the flight path s.
• the time or the path s Q on the zisse represent the point at which the projectile 7 passes the induction coil. At this point the signal would pass through zero, the projectile 7 would have constant electrical charge.
• the electrical La increases continuously due to air friction, the passage of the signal approximately to the right - based on the W flight direction covered - becomes t or s. postponed. If this shift is lost in the inaccuracy, it need not be taken into account.
• a corresponding correction can also be carried out, since amplitudes of the positive and negative branches of the signal do not have the same absolute maximum values U, U • for the same reason, so that the difference 'between them results in a correction value for determining time t can be calculated by the arithmetic for the flyby of the projectile 7. If two or more sensors 1 are present at predetermined intervals along the trajectory of the projectile 7, cf. Fig. 3, the amplitude can also be used to determine the charge change during flight projectile 7 and thus to correct the time difference between two passes of the signals from two sensors 1. When the projectile 7 has a large flight path, its electrical charge approaches a maximum value, so that a correction of the zero crossing only makes sense at a short distance from the launching or blasting site, up to about 60 to 80 m.
• the speed of a profile 7 can be determined in different sections of its trajectory 18.
• the measurement is independent of the weather and time of day and requires k magnetization of the projectile 7. Even if the projectile 7 " hits the inductor 3, an evaluable signal is present because the zero point signal has been reached.
• the measurements can also be carried out at a distance of a few meters
• the costs of the induction coil 3 are very low, so that it does not have to be protected from damage, and wobbling or overturning projectiles always generate pulses of the same polarity in contrast to magn 7

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• Physics & Mathematics (AREA)
• General Physics & Mathematics (AREA)
• Geophysics And Detection Of Objects (AREA)

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• 1987
  • 1987-01-28 DE DE19873702429 patent/DE3702429A1/de active Granted
  • 1987-11-26 EP EP88900017A patent/EP0299000A1/de not_active Ceased
  • 1987-11-26 US US07/252,368 patent/US4935697A/en not_active Expired - Fee Related
  • 1987-11-26 WO PCT/EP1987/000733 patent/WO1988005914A1/de not_active Application Discontinuation

Non-Patent Citations (1)

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