DE4134469C1 - Radial centre-of-gravity registering appts. for aircraft or missile - has receiving roller rings rotating on running rollers of point of concn. scales spring supported against foundation - Google Patents

Abstract

A rotatable holder for the test piece (FK) is rotational symmetrical at its external region. Its i.d. is greater than the largest sample external dia. It has a bearing arrangement and a device for detecting the centre of gravity data. The rotatable holder consists of two roller rings (10a) at a distance apart along the length of the sample each consisting of two halves. Each ring has devices for measuring the distance (M1,M2) between the inside of the ring and the exterior of the sample in a coordiante system. The radial centre of gravity is derived using the distance to the vertical body axis (14). ADVANTAGE - Avoids damage to sample exterior, easy to assemble and gives accurate results.

Description

The invention relates to a device for radial determination of the center of gravity for missiles according to the preamble of pantent claim 1.

Such a device is known from US-PS 33 20 794.

To determine the radial center of gravity of a missile FK, is at the known devices of the prior art so far at least one full revolution of the FK missile with at least four measurements each 90 ° required. Because the outer contours of a missile are caused by rolling loads can be easily damaged and also mostly cable ducts and other protruding parts roll the missile from so-called rolling rings are used for this, which take up the missile and on castors and guide rollers one rotate the spring-loaded balance scale against a foundation.

The US-PS 27 22 827 is a device for radial determination of the center of gravity disclosed in which the recording of the body to be measured divided and from DE-PS 3 87 093 such a device is known the inclusion of which is rotatable and mounted on rollers. The calculation a focus due to conditions and location data of the Test object is known from DE 34 19 546 A1.

A bearing stand for balancing machines is known from DE 28 54 838 A1 which has a rotating body to be examined in one partially bearing ball bearing, consisting of two halves, embraces and clamps him. Apart from the complex overall concept This balancing machine is its use for missiles not possible because the diameter tolerances that occur in every case must be compensated for by elastic inserts in the rolling ring and thereby but not to get a perfectly defined position of the missile and the measurements are therefore incorrect. There is also tension given the missile structure.  

The applicant has also made tolerance known between the rolling ring and the missile using tape. The disadvantage this measure is that such a tolerance compensation is not easy in the required precision can be carried out and repeated placement the rolling rings required, moreover the missile is in its Contour braced in alignment with the rolling ring.

The present invention has for its object a device of the type mentioned in such a way that no tension of the Contour of the missile to be measured occur, the rolling rings easy to assemble and the radial center of gravity can be determined precisely without any problems can.

This object is achieved by the measures indicated in the characterizing part of patent claim 1. Claim 2 discloses a further embodiment.

In the following An exemplary embodiment is explained and in the description Figures of the drawing outlined. Show it:

Fig. 1 is a view of a roll mounted on two rings, each having a center of gravity balance missile in a schematic representation;

Fig. 2 shows a section along the line AA of Fig. 1,

Fig. 3 is an enlarged view of a section along the line AA of FIG. 1.

As illustrated in FIG. 1, a missile FK is mounted in two roller rings 10 a and 10 b, which can rotate on front rollers 11 a and rear on track rollers 11 b. Each of these rollers 11 a, 11 b is part of a so-called center of gravity SW, which is provided with a damping 13 and one or more measuring cells 12 .

Fig. 2 shows in section how the missile FK is mounted in the rolling ring 10 b. The inner diameter of the rolling rings 10 a and 10 b is slightly larger than the outer diameter of the missile FK. In the radial determination of the center of gravity, the missile FK lies with its cable duct 15 in a correspondingly large groove 15 a and with a part of its outer surface on the inner surface of the rolling ring 10 b. Parallel to the vertical axis 14 of the missile FK, the distances M 1 and M 2 are now formed in the form of two columns, which are measured and whose values are used in the calculation of the radial center of gravity.

The values of the distances M₁, M₂ are the values a and b (see Fig. 3) by means of a known and therefore not shown measuring device, such as. B. a probe. The sensor is either attached to the outside of the rolling rings 10 a, 10 b radially to the missile FK and guided past it or for better guidance by the z. B. performed an approach in bores rolling rings 10 a, 10 b. According to Fig. 3, the measured values a and b each contain the values of the distances M₁ and M₂, since the thickness of the rolling rings 10 a, 10 b is known.

According to Fig. 3 will now be X than the distance from the center M _F of the missile FK to the actual center of gravity with

X = Y ± W

calculated, where Y is the distance from the center M _{R of} the respective rolling ring 10 a, 10 b to the actual center of gravity determined by the center of gravity SW and

represents the calculated distance from the center M _{R of} the respective rolling ring 10 a, 10 b to the center M _{F of} the missile FK.

The rolling rings 10 a, 10 b are manufactured with the smallest possible tolerances, so that this enables a very precise determination of the radial center of gravity of the missile.

Claims (2)

1.Device for determining the radial center of gravity of missiles with rotatable, rotationally symmetrical receptacles for the missile, the inside diameter of which is greater than the maximum outside diameter of the missile and which are provided on the inside diameter with a device for preventing mutual rotation of the receptacle and missile, bearing means for the rotatable mounting of the receiving means and a measuring device for obtaining measurement data which are dependent on the center of gravity, characterized in that

• - That the rotatable receiving means of two in the longitudinal direction of the missile (FK) arranged at a distance from each other and each consisting of two halves which can be connected together are rolling rings ( 10 a, 10 b), each rolling ring ( 10 a, 10 b) spacing means for measurement of the distance between the inside of the respective rolling ring and the outside of the missile (FK) in the axis cross and
• - That the measuring device for calculating the radial center of gravity of the missile (FK) is designed taking into account the distance (M₁, M₂) in the axis cross to the given vertical missile axis ( 14 ).

2. Device according to claim 1, characterized in that the measuring device on the rolling rings ( 10 a, 10 b) can be applied radially and / or through the rolling rings ( 10 a, 10 b) can be carried out.