CN113899265A - Folding rudder wing opening time measuring device based on photoelectric element - Google Patents
Folding rudder wing opening time measuring device based on photoelectric element Download PDFInfo
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- CN113899265A CN113899265A CN202111186627.7A CN202111186627A CN113899265A CN 113899265 A CN113899265 A CN 113899265A CN 202111186627 A CN202111186627 A CN 202111186627A CN 113899265 A CN113899265 A CN 113899265A
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- emitting diode
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
- F42B35/02—Gauging, sorting, trimming or shortening cartridges or missiles
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- G—PHYSICS
- G04—HOROLOGY
- G04F—TIME-INTERVAL MEASURING
- G04F10/00—Apparatus for measuring unknown time intervals by electric means
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Abstract
The invention belongs to the technical field of missile folding rudder wing opening time measurement, and particularly relates to a folding rudder wing opening time measuring device based on a photoelectric element, wherein a first support and a second support are fixed on a base; the seat ring is fixed on the base; the measured object is placed in an inner hole of a seat ring on the base and is tightly fixed with the seat ring through a jackscrew; the first light-emitting diode component and the second light-emitting diode component are fixed on the first bracket; the first photosensitive transistor component and the second photosensitive transistor component are fixed on the second bracket; the connecting sheet connects the first bracket with the second bracket; the rudder sheet baffle ring is arranged on the object to be measured, and the rudder wing in a folded state is clamped, so that the opening is avoided. The invention provides a miniaturized non-contact measurement device for the opening time of a folding rudder wing, which has the advantages of low cost, high efficiency and high measurement precision and is suitable for the field of aircrafts requiring precise measurement of the opening time (dozens of milliseconds) of the rudder wing.
Description
Technical Field
The invention belongs to the technical field of missile folding rudder wing opening time measurement, and particularly relates to a folding rudder wing opening time measuring device based on a photoelectric element.
Background
In order to realize the miniaturization of the missile and make the transportation and storage of the missile simple and convenient, a large number of tactical missiles are launched in a box type or a cylinder type. In order to adapt to the situation, the missile adopts a folding rudder wing or a folding missile wing design. The folding rudder wing has the following functions: at the beginning, the rudder wing is in a folded state, a general launching box (barrel) is used as restraint to avoid the rudder wing from opening, and after the missile is launched out of the box (barrel), the rudder wing completes unfolding action under the action of unfolding force (generally various springs) and is locked after being in place. The unfolding in-place time of the rudder wings, namely the unfolding time, must meet the indexes specified by the general technical requirements, and if the unfolding time is too long or too short, the missile body is greatly disturbed, the aerodynamic stability of the missile is influenced, and if the unfolding time is serious, the missile is unstable, and the hit rate is reduced. The rudder wing opening time must be accurately measured. At present, the technology for measuring the opening time of the rudder wing mainly comprises high-speed shooting measurement, and has the defects of high cost, long preparation and measurement time, low efficiency due to the need of video playback and frame reading after shooting.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: aiming at the problems in the prior art, how to provide a device for measuring the opening time of a folding rudder wing.
(II) technical scheme
In order to solve the above technical problem, the present invention provides a folded rudder wing opening time measuring device based on an optoelectronic device, where the opening time measuring device includes: the device comprises a base 1, a first bracket 2, a seat ring 3, a second light emitting diode component 4, a second photosensitive transistor component 5, a first light emitting diode component 6, a first photosensitive transistor component 7, a connecting sheet 8, a rudder piece baffle ring 9, a measured object 12, a jackscrew 13 and a second bracket 15;
the base 1 is a mounting carrier of the opening time measuring device, and the first support 2, the second support 15 and the seat ring 3 are fixed on the base 1;
the object 12 to be measured is placed in the inner hole of the seat ring 3 and tightly fixed with the seat ring 3 through a jackscrew 13;
the first support 2 and the second support 15 are both vertically arranged and are positioned on the side wall of the object 12 to be measured in parallel and positioned on two sides of the rotation direction of the rudder wing of the object 12 to be measured;
the first bracket 2 is a mounting carrier for the second light-emitting diode assembly 4 and the first light-emitting diode assembly 6; wherein, the first LED assembly 6 is positioned at the upper part of the first bracket 2, and the second LED assembly 4 is positioned at the lower part of the first bracket 2;
the second support 15 is a mounting carrier for the first phototransistor component 7 and the second phototransistor component 5; wherein the first phototransistor component 7 is located at the upper part of the second support 15, and the second phototransistor component 5 is located at the lower part of the second support 15;
in the horizontal direction, the first phototransistor component 7 is located in correspondence with the first light emitting diode component 6 and the second phototransistor component 5 is located in correspondence with the second light emitting diode component 4.
The tops of the first bracket 2 and the second bracket 15 are stably connected through a horizontally arranged connecting sheet 8 matched with a first connecting screw 10;
the bottoms of the first support 2 and the second support 15 are fixedly arranged on the base 1.
The rudder sheet baffle ring 9 is arranged on the upper part of the folded rudder wing of the tested object and the mounting component 12 thereof, and the rudder wing in the initial folding state is clamped to avoid opening.
The object 12 is a folded rudder wing and a mounting component thereof.
Wherein, the first bracket 2, the second bracket 15 and the seat 3 are fixed on the base 1 through a second connecting screw 14.
The second led assembly 4 and the first led assembly 6 are fixed on the first bracket 2 by nuts 11.
The first phototransistor component 7 and the second phototransistor component 5 are fixed on the second bracket 15 through nuts 11.
In the working process, an external direct current power supply respectively supplies power to the first light-emitting diode component, the first photosensitive transistor component, the second light-emitting diode component and the second photosensitive transistor component, an external oscilloscope is used for recording output voltage signals of the first photosensitive transistor component and the second photosensitive transistor component, and at the moment, the first photosensitive transistor component and the second photosensitive transistor component respectively and normally receive optical signals of the first light-emitting diode component and the second light-emitting diode component.
When the rudder sheet retaining ring is manually lifted, namely, the simulated missile rudder wing flies out of the barrel, the rudder wing in a folded state starts to unfold under the action of torsional spring force, meanwhile, due to the rotary unfolding of the rudder wing, the first phototransistor component at the upper end is blocked from normally receiving light emitted by the first light-emitting diode component at the upper end, the output voltage level of the first phototransistor component jumps at the moment, and the moment point is the unfolding starting point of the rudder wing; when the rudder wing is unfolded to the limit position under the action of the torsional spring force, the lower end second photosensitive transistor component can be blocked to normally receive light emitted by the lower end second light emitting diode component, the output voltage level of the lower end second photosensitive transistor component jumps, and the moment point is the opening end point of the rudder wing.
And measuring the time difference of the initial level jump points of the first photosensitive transistor component and the second photosensitive transistor component recorded on the external oscilloscope to obtain the opening time of the rudder wing.
(III) advantageous effects
According to the invention, two pairs of light-emitting diodes and phototransistors are respectively arranged on the upper side and the lower side of the bracket, the light-emitting diode and the phototransistor on the upper end can determine the starting time point of the movement of the folded rudder wing, the light-emitting diode and the phototransistor on the lower end can determine the in-place time point of the movement of the folded rudder wing, and the time difference between the two is the opening time of the rudder wing. The invention has the advantages of simple structure, low cost, high measurement efficiency and high precision.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention adopts two pairs of light emitting diodes and phototransistors which are respectively arranged at the upper end and the lower end of a bracket, the light emitting diode and the phototransistor at the upper end can determine the starting time point of the movement of the folded rudder wing, the light emitting diode and the phototransistor at the lower end can determine the in-place time point of the movement of the folded rudder wing, and the time difference between the light emitting diode and the phototransistor is the opening time of the rudder wing. The working principle is simple, the volume is small, the cost is low, the efficiency is high, and the measuring precision is high.
(2) The invention can be well suitable for the fields of missile folding rudder wings, folding missile wings and the like which need to accurately measure the opening time, and has small occupied space and high measurement efficiency.
Drawings
FIG. 1 is a schematic structural diagram of an initial folded state of a rudder wing, which is a folded rudder wing opening time measuring device technology based on photoelectric elements.
FIG. 2 is a schematic diagram of the folded rudder wing opening time measuring device technology based on photoelectric elements, wherein the rudder wing is in a fully unfolded state.
FIG. 3 is a schematic diagram of the circuit operating principle of the folded rudder wing opening time measuring device technology based on the photoelectric element.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
In order to solve the above technical problem, the present invention provides a folded rudder wing opening time measuring device based on an optoelectronic device, as shown in fig. 1 to 3, the opening time measuring device includes: the device comprises a base 1, a first bracket 2, a seat ring 3, a second light emitting diode component 4, a second photosensitive transistor component 5, a first light emitting diode component 6, a first photosensitive transistor component 7, a connecting sheet 8, a rudder piece baffle ring 9, a measured object 12, a jackscrew 13 and a second bracket 15;
the base 1 is a mounting carrier of the opening time measuring device, and the first support 2, the second support 15 and the seat ring 3 are fixed on the base 1 through second connecting screws 14;
the object 12 to be measured is placed in the inner hole of the seat ring 3 and tightly fixed with the seat ring 3 through a jackscrew 13;
the first support 2 and the second support 15 are both vertically arranged and are positioned on the side wall of the object 12 to be measured in parallel and positioned on two sides of the rotation direction of the rudder wing of the object 12 to be measured;
the first bracket 2 is a mounting carrier for the second light-emitting diode assembly 4 and the first light-emitting diode assembly 6, and the second light-emitting diode assembly 4 and the first light-emitting diode assembly 6 are fixed on the first bracket through nuts 11; wherein, the first LED assembly 6 is positioned at the upper part of the first bracket 2, and the second LED assembly 4 is positioned at the lower part of the first bracket 2;
the second bracket 15 is a mounting carrier for the first phototransistor component 7 and the second phototransistor component 5, and the first phototransistor component 7 and the second phototransistor component 5 are fixed on the second bracket through nuts 11; wherein the first phototransistor component 7 is located at the upper part of the second support 15, and the second phototransistor component 5 is located at the lower part of the second support 15;
in the horizontal direction, the first phototransistor component 7 is located in correspondence with the first light emitting diode component 6 and the second phototransistor component 5 is located in correspondence with the second light emitting diode component 4.
The tops of the first bracket 2 and the second bracket 15 are stably connected through a horizontally arranged connecting sheet 8 matched with a first connecting screw 10;
the bottoms of the first support 2 and the second support 15 are fixedly arranged on the base 1.
The rudder sheet baffle ring 9 is arranged on the upper part of the folded rudder wing of the tested object and the mounting component 12 thereof, and the rudder wing in the initial folding state is clamped to avoid opening.
The object 12 is a folded rudder wing and a mounting component thereof.
In the working process, an external direct current power supply respectively supplies power to the first light-emitting diode component, the first photosensitive transistor component, the second light-emitting diode component and the second photosensitive transistor component, an external oscilloscope is used for recording output voltage signals of the first photosensitive transistor component and the second photosensitive transistor component, and at the moment, the first photosensitive transistor component and the second photosensitive transistor component respectively and normally receive optical signals of the first light-emitting diode component and the second light-emitting diode component.
When the rudder sheet retaining ring is manually lifted, namely, the simulated missile rudder wing flies out of the barrel, the rudder wing in a folded state starts to unfold under the action of torsional spring force, meanwhile, due to the rotary unfolding of the rudder wing, the first phototransistor component at the upper end is blocked from normally receiving light emitted by the first light-emitting diode component at the upper end, the output voltage level of the first phototransistor component jumps at the moment, and the moment point is the unfolding starting point of the rudder wing; when the rudder wing is unfolded to the limit position under the action of the torsional spring force, the lower end second photosensitive transistor component can be blocked to normally receive light emitted by the lower end second light emitting diode component, the output voltage level of the lower end second photosensitive transistor component jumps, and the moment point is the opening end point of the rudder wing.
And measuring the time difference of the initial level jump points of the first photosensitive transistor component and the second photosensitive transistor component recorded on the external oscilloscope to obtain the opening time of the rudder wing.
Example 1
The present embodiment provides a folded rudder wing opening time measuring device technology based on a photoelectric element, and as shown in fig. 1, the folded rudder wing opening time measuring device based on a photoelectric element includes: the device comprises a base, a first support, a seat ring, a second light emitting diode component, a second photosensitive transistor component, a first light emitting diode component, a first photosensitive transistor component, a connecting sheet, a rudder piece baffle ring, a first connecting screw, a nut, a measured object (a folding rudder wing and an installation component thereof), a jackscrew, a second connecting screw and a second support. The working principle is shown in fig. 2, an external power supply respectively supplies power to a first light-emitting diode component, a first photosensitive transistor component, a second light-emitting diode component and a second photosensitive transistor component, and an external oscilloscope is used for recording voltage signals output by the first photosensitive transistor component A and output by the second photosensitive transistor component B; after a power supply is powered on, the rudder wing is in a folding constraint state, when the rudder wing does not rotate, the first light emitting diode component and the second light emitting diode component emit light, the first photosensitive transistor component and the second photosensitive transistor component respectively and normally receive the light emitted by the first light emitting diode component and the second light emitting diode component, the test point A, B outputs low level, after the rudder wing is relieved of constraint, the rudder wing blocks a light receiving loop of the first photosensitive transistor component, the output A of the first photosensitive transistor component jumps to high level, when the rudder wing rotates further, the rudder wing does not block the light receiving loop of the first photosensitive transistor component, the output A of the first photosensitive transistor component jumps to low level, finally, when the rudder wing rotates in place, the rudder wing blocks the light receiving loop of the second photosensitive transistor component, the output B of the second photosensitive transistor component jumps to high level, the time difference between the output A, B of the first phototransistor component and the output A, B of the second phototransistor component jumping to high level is the opening time of the rudder wing.
According to fig. 1, the folded rudder wing opening time measuring device based on the photoelectric element of the embodiment comprises: the device comprises a base 1, a first support 2, a seat ring 3, a second light emitting diode component 4, a second photosensitive transistor component 5, a first light emitting diode component 6, a first photosensitive transistor component 7, a connecting sheet 8, a rudder piece baffle ring 9, a first connecting screw 10, a nut 11, a measured object (a folded rudder wing and a mounting component thereof) 12, a jackscrew 13, a second connecting screw 14 and a second support 15. The base 1 is an installation carrier of the opening time measuring device, and the first support 2, the second support 15 and the seat ring 3 are fixed through a second connecting screw 14; the tested object (the folding rudder wing and the installation component thereof) 12 is placed on the base 1, and is tightly fixed with the seat ring through a jackscrew 13 in the inner hole of the seat ring 3; the first LED assembly 6 and the second LED assembly 4 are fixed on the first bracket 2 through nuts 11; the first phototransistor component 7 and the second phototransistor component 5 are fixed on the second bracket 15 through nuts 11; the connecting piece is connected with the second bracket through a first connecting screw piece and a first bracket; the rudder sheet baffle ring 9 is arranged on a measured object (a folding rudder wing and a mounting component thereof) 12, and the rudder wing in an initial folding state is clamped to avoid opening.
According to the folding rudder wing opening time measuring device technology based on the photoelectric element, the actuating mechanism can work reliably and efficiently under the working condition, and is small in size, low in cost, convenient to install and debug and high in efficiency.
Example 2
In order to solve the above problem, the foldable rudder wing opening time measuring device technology based on a photoelectric element provided in this embodiment includes a base, a first support, a seat ring, a second light emitting diode assembly, a second photosensitive transistor assembly, a first light emitting diode assembly, a first photosensitive transistor assembly, a connecting sheet, a rudder piece retaining ring, a first connecting screw, a nut, a measured object (a foldable rudder wing and an installation assembly thereof), a jackscrew, a second connecting screw, and a second support. The first support and the second support are fixed on the base through second connecting screws; the seat ring is fixed on the base through a second connecting screw; the tested object (the folding rudder wing and the installation component thereof) is placed on the base, and the seat ring is tightly fixed with the seat ring through a jackscrew in an inner hole of the seat ring; the first light-emitting diode assembly and the second light-emitting diode assembly are fixed on the first bracket through a first nut and a second nut respectively; the first photosensitive transistor component and the second photosensitive transistor component are fixed on the second bracket through a first nut and a second nut respectively; the connecting piece is connected with the second bracket through a first connecting screw piece and a first bracket; the rudder sheet baffle ring is arranged on a measured object (a folding rudder wing and an installation component thereof), and the rudder wing in a folding state is clamped to avoid opening.
The working principle of the embodiment is as follows: an external direct current power supply respectively supplies power to the first light emitting diode component, the first photosensitive transistor component, the second light emitting diode component and the second photosensitive transistor component, an external oscilloscope is adopted to record output voltage signals of the first photosensitive transistor component and the second photosensitive transistor component, and at the moment, the first photosensitive transistor component and the second photosensitive transistor component respectively and normally receive light signals of the first light emitting diode component and the second light emitting diode component; when the rudder sheet baffle ring (simulating a missile rudder wing flying out of a cylinder) is lifted manually, the rudder wing in a folded state starts to unfold under the action of torsional spring force, meanwhile, due to the rotary unfolding of the rudder wing, the upper end first phototransistor component is blocked from normally receiving light emitted by the upper end first light emitting diode component, the output voltage level of the first phototransistor component jumps at the moment, and the moment point is the unfolding starting point of the rudder wing; when the rudder wing is unfolded to the extreme position under the action of the torsional spring force, the lower second photosensitive transistor component can be prevented from normally receiving light emitted by the lower second light-emitting diode component, the output voltage level of the lower second photosensitive transistor component jumps at the moment, and the moment point is the opening end point of the rudder wing; and measuring the time difference of the initial level jump points of the first photosensitive transistor component and the second photosensitive transistor component recorded on the external oscilloscope to obtain the opening time of the rudder wing.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111186627.7A CN113899265A (en) | 2021-10-12 | 2021-10-12 | Folding rudder wing opening time measuring device based on photoelectric element |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111186627.7A CN113899265A (en) | 2021-10-12 | 2021-10-12 | Folding rudder wing opening time measuring device based on photoelectric element |
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| CN202111186627.7A Pending CN113899265A (en) | 2021-10-12 | 2021-10-12 | Folding rudder wing opening time measuring device based on photoelectric element |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115655025A (en) * | 2022-10-25 | 2023-01-31 | 湖北三江航天红阳机电有限公司 | System and method for detecting unfolding time of folded rudder |
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| US4659037A (en) * | 1984-09-05 | 1987-04-21 | Rheinmetall Gmbh | Wing deploying system comprising an airbag |
| CN102062679A (en) * | 2010-11-11 | 2011-05-18 | 中北大学 | Measurement method of movement locus and inverting time of spherical rotor |
| CN105547060A (en) * | 2015-12-02 | 2016-05-04 | 吉林市江机民科实业有限公司 | Missile wing spreading time tester |
| CN113267096A (en) * | 2021-06-09 | 2021-08-17 | 山西华洋吉禄科技股份有限公司 | Method and device for testing wing unfolding time of missile wing or rudder wing assembly |
-
2021
- 2021-10-12 CN CN202111186627.7A patent/CN113899265A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4659037A (en) * | 1984-09-05 | 1987-04-21 | Rheinmetall Gmbh | Wing deploying system comprising an airbag |
| CN102062679A (en) * | 2010-11-11 | 2011-05-18 | 中北大学 | Measurement method of movement locus and inverting time of spherical rotor |
| CN105547060A (en) * | 2015-12-02 | 2016-05-04 | 吉林市江机民科实业有限公司 | Missile wing spreading time tester |
| CN113267096A (en) * | 2021-06-09 | 2021-08-17 | 山西华洋吉禄科技股份有限公司 | Method and device for testing wing unfolding time of missile wing or rudder wing assembly |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115655025A (en) * | 2022-10-25 | 2023-01-31 | 湖北三江航天红阳机电有限公司 | System and method for detecting unfolding time of folded rudder |
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Application publication date: 20220107 |