CN211696099U - Self-triggering missile-borne data recorder - Google Patents
Self-triggering missile-borne data recorder Download PDFInfo
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- CN211696099U CN211696099U CN202020161398.8U CN202020161398U CN211696099U CN 211696099 U CN211696099 U CN 211696099U CN 202020161398 U CN202020161398 U CN 202020161398U CN 211696099 U CN211696099 U CN 211696099U
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- 230000004913 activation Effects 0.000 claims abstract description 50
- 230000007246 mechanism Effects 0.000 claims abstract description 32
- 238000012360 testing method Methods 0.000 claims abstract description 26
- 238000012545 processing Methods 0.000 claims description 28
- 238000007726 management method Methods 0.000 claims description 27
- 229910000831 Steel Inorganic materials 0.000 claims description 19
- 239000010959 steel Substances 0.000 claims description 19
- 238000013500 data storage Methods 0.000 claims description 16
- 230000009471 action Effects 0.000 claims description 10
- 238000005096 rolling process Methods 0.000 claims description 10
- 238000004891 communication Methods 0.000 claims description 6
- 230000001960 triggered effect Effects 0.000 claims description 6
- 238000013461 design Methods 0.000 claims description 4
- 230000001133 acceleration Effects 0.000 abstract description 4
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
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- 238000009434 installation Methods 0.000 description 2
- 238000012935 Averaging Methods 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 229910052987 metal hydride Inorganic materials 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 1
- -1 nickel metal hydride Chemical class 0.000 description 1
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Abstract
The utility model discloses a self-triggering missile-borne data recorder, which comprises a power module, a test recording module and an inertia triggering activation module; four low-cost triaxial acceleration sensors are adopted to test overload signals of a specific position, and triaxial overload data or overload and rotating speed data of any other position of the center of mass of the projectile body can be obtained after interpolation conversion; a double-stroke inertia trigger activation mechanism is adopted to sense the overload of the long pulse width emitted by the rocket projectile, and simultaneously, the triggering and activation of the double-stroke inertia trigger activation mechanism by the impact overload of the small pulse width in the environment are avoided; and the ultra-low power consumption power management module is adopted to uninterruptedly detect two sets of micro switches on the double-stroke inertia trigger activation mechanism, and after the two sets of micro switches on the double-stroke inertia trigger mechanism are detected to act simultaneously, the activation condition is considered to be met, and the test recording module is powered on.
Description
Technical Field
The utility model belongs to the technical field of data record appearance, concretely relates to self-triggering missile-borne data record appearance.
Background
The flight test of the rocket projectile is an essential link in the development process of the rocket projectile, and overload and rotating speed parameters of the rocket projectile in the flight process are tested through the flight test, so that the technical indexes and ballistic performance of the rocket projectile can be evaluated.
The missile-borne flight data recorder is the most common test recording means, is low in cost and simple in structure compared with ballistic telemetry recording, does not need auxiliary equipment, and is most suitable for being used as the flight data recording of rocket projectiles.
Meanwhile, the rocket projectile has the characteristics of relatively small flying overload, long overload continuous pulse width, small rotating speed and long ballistic time. Therefore, there is a need to develop a missile-borne data recorder suitable for low overload, long pulse width, small rotating speed, low cost, automatic triggering, long standby and long recording.
Disclosure of Invention
An object of the utility model is to provide a from triggering missile-borne data record appearance just in order to solve above-mentioned problem.
The utility model discloses a following technical scheme realizes above-mentioned purpose:
the utility model provides a from triggering missile-borne data record appearance installs in the rocket projectile, and from triggering missile-borne data record appearance includes:
a power supply module; the power module comprises a battery pack and a power management board; the battery pack is electrically connected with the power management board and the test recording module respectively; the power management board is used for controlling the battery pack to supply power to the test recording module after detecting an activation signal from the double-stroke inertia trigger activation mechanism;
a test recording module;
an inertia trigger activation module; the inertia trigger activation module comprises a double-stroke inertia trigger activation mechanism, and the signal output end of the double-stroke inertia trigger activation mechanism is connected with the signal input end of the power management board; the double-stroke inertia triggering activation mechanism is used for sending an activation signal to the power management board after receiving the rocket projectile and emitting overload.
Specifically, the test recording module comprises a data storage board, a signal processing board and a sensor board; the battery pack is respectively electrically connected with the data storage board, the signal processing board and the sensor board, the sensor board is used for collecting the flight data of the rocket projectile, the signal output end of the sensor board is connected with the signal input end of the signal processing board, and the signal output end of the signal processing board is connected with the signal input end of the data storage board.
Specifically, the self-triggering missile-borne data recorder further comprises:
a charging interface; the charging interface is electrically connected with the battery pack;
a data interface; one end of the data interface is in communication connection with the data storage board, and the other end of the data interface is in communication connection with the computer;
an upper cover;
a shell I; the upper cover is covered on the shell I and forms a closed structure; the charging interface and the data interface are both arranged on the upper cover;
a sensor I;
a sensor II;
a sensor PCB I; the sensor I and the sensor II are arranged on the sensor PCB I; the sensor I and the sensor II are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder;
the data storage board and the signal processing board are combined to form a signal processing and storage board; the signal processing and storing board is respectively electrically connected with the sensor PCB I and the power management board;
a sensor III;
a sensor IV;
a sensor PCB II; the sensor III and the sensor IV are arranged on the sensor PCB II; the sensor III and the sensor IV are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder; sensor I, sensor II, sensor PCB I, sensor III, sensor IV, sensor PCB II, signal processing and memory board, group battery, two-stroke inertia trigger activation mechanism all arrange in the enclosure space that upper cover and casing I formed.
Preferably, the sensor PCB I and the sensor PCB II are both arranged perpendicular to the vertical axis of the self-triggering missile-borne data recorder; the self-triggering missile-borne data recorder and the rocket projectile are coaxially installed.
Preferably, the sensor I and the sensor II are arranged on the inner side of the sensor PCB I; and the sensor III and the sensor IV are arranged on the inner side of the sensor PCB II.
Specifically, the two-stroke inertia-activated activation mechanism includes:
a shell II; two mutually parallel sliding channels are formed in the shell II; the arrangement direction of the sliding channel is parallel to the vertical axis of the self-triggering missile-borne data recorder;
a pre-quality block; an inward inclined plane is formed on one side of the upper end of the front mass block;
a rear mass block; the front mass block and the rear mass block are respectively arranged in the two sliding channels in a sliding manner; one side of the lower end of the rear mass block is provided with an arc-shaped groove for clamping the steel ball;
a steel ball; the steel ball is arranged in the rolling channel, under the overload action smaller than the designed threshold value, one part of the steel ball is contacted with one side of the front mass block, the other part of the steel ball is arranged in the groove of the rear mass block, and the rear mass block is blocked;
a spring; the two sliding channels are communicated through a rolling channel; the lower end of the front mass block and the lower end of the rear mass block are both contacted with the bottom of the sliding channel through a spring; a microswitch I is arranged in one sliding channel, a microswitch II is arranged in the other sliding channel, under the continuous overload action larger than a design threshold value, a front mass block moves downwards, the front mass block pushes the microswitch I to be closed, meanwhile, the inclined plane of the front mass block moves downwards to the position of a rolling channel, a steel ball moves leftwards, a rear mass block is free of restraint, the rear mass block moves downwards under the overload action, the microswitch II is closed, the two microswitches are all closed, and an activation instruction is triggered and sent to a power management board.
Preferably, the battery pack is a rechargeable battery.
The beneficial effects of the utility model reside in that:
the overload signals of specific positions are tested by adopting four low-cost triaxial acceleration sensors, and triaxial overload data or overload and rotating speed data of any other positions of the center of mass of the projectile body can be obtained after interpolation conversion.
The double-stroke inertia trigger activation mechanism is adopted to sense the overload of the long pulse width emitted by the rocket projectile, and simultaneously avoid the triggering and activation by the impact overload of the small pulse width in the environment.
And the ultra-low power consumption power management module is adopted to uninterruptedly detect two sets of micro switches on the double-stroke inertia trigger activation mechanism, and after the two sets of micro switches on the double-stroke inertia trigger mechanism are detected to act simultaneously, the activation condition is considered to be met, and the test recording module is powered on.
Drawings
FIG. 1 is a view of the installation of a missile-borne data recorder in a full missile;
FIG. 2 is a diagram showing a system configuration of the missile-borne data recorder;
FIG. 3 is a cross-sectional view of a configuration of a missile-borne data recorder;
FIG. 4 is a cross-sectional view of the inertia activated mechanism of the missile-borne data recorder (in an unmoved state);
FIG. 5 is a schematic diagram of the operation of the inertia activated mechanism of the missile-borne data recorder (transition state);
FIG. 6 is a schematic diagram of the operation of the inertia activated mechanism of the missile-borne data recorder (triggered state);
FIG. 7 is a schematic diagram of a missile-borne data recorder system;
in the figure: 1-a charging interface, 2-a sensor I, 3-a data interface, 4-an upper cover, 5-a sensor II, 6-a sensor PCB I, 7-a signal processing and storage board, 8-a double-stroke inertia triggering activation mechanism, 9-a battery pack, 10-a sensor III, 11-a shell I, 12-a sensor PCB II, 13-a sensor IV, 14-a power management board, 15-a shell II, 16-a front mass block, 17-a steel ball, 18-a rear mass block, 19-a spring, 20-a microswitch I, 21-a microswitch II, 22-a self-triggering missile-loading data recorder.
Detailed Description
The present invention will be further explained with reference to the accompanying drawings:
as shown in fig. 2, a self-triggering missile-borne data recorder is installed in a rocket projectile, and the self-triggering missile-borne data recorder 22 includes:
a power supply module; the power module comprises a battery pack 9 and a power management board 14; the battery pack 9 is electrically connected with the power management board 14 and the test recording module respectively; the power management board 14 is used for controlling the battery pack 9 to supply power to the test recording module after detecting an activation signal from the double-stroke inertia trigger activation mechanism 8;
a test recording module;
an inertia trigger activation module; the inertia trigger activation module comprises a double-stroke inertia trigger activation mechanism 8, and the signal output end of the double-stroke inertia trigger activation mechanism 8 is connected with the signal input end of the power management board 14; the double-stroke inertia trigger activation mechanism 8 is used for sending an activation signal to the power management board 14 after receiving the rocket projectile and emitting overload.
In this embodiment, the power supply module is controlled by the ultra-low power consumption power management module, and power is not supplied to the test recording module before the trigger activation signal is received.
As shown in fig. 2, the test recording module includes a data storage board, a signal processing board, and a sensor board; the battery pack 9 is respectively electrically connected with the data storage board, the signal processing board and the sensor board, the sensor board is used for collecting the flight data of the rocket projectile, the signal output end of the sensor board is connected with the signal input end of the signal processing board, and the signal output end of the signal processing board is connected with the signal input end of the data storage board.
As shown in fig. 3, the self-triggering missile-borne data recorder 22 further includes:
a charging interface 1; the charging interface 1 is electrically connected with the battery pack 9;
a data interface 3; one end of the data interface 3 is in communication connection with the data storage board, and the other end of the data interface 3 is in communication connection with the computer;
an upper cover 4;
a shell I11; the upper cover 4 is covered on the shell I11 and forms a closed structure; the charging interface 1 and the data interface 3 are both arranged on the upper cover 4;
a sensor I2;
a sensor II 5;
a sensor PCB I6; the sensor I2 and the sensor II 5 are arranged on the sensor PCB I6; the sensor I2 and the sensor II 5 are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder 22;
the data storage board and the signal processing board are combined to form a signal processing and storage board 7; the signal processing and storage board 7 is electrically connected with the sensor PCB I6 and the power management board 14 respectively;
a sensor III 10;
a sensor IV 13;
a sensor PCB II 12; the sensor III 10 and the sensor IV 13 are arranged on the sensor PCB II 12; the sensor III 10 and the sensor IV 13 are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder 22; the sensor I2, the sensor II 5, the sensor PCB I6, the sensor III 10, the sensor IV 13, the sensor PCB II 12, the signal processing and storing plate 7, the battery pack 9 and the double-stroke inertia trigger activation mechanism 8 are all arranged in a closed space formed by the upper cover 4 and the shell I11.
As shown in fig. 1 and 3, the sensor PCB i 6 and the sensor PCB ii 12 are both arranged perpendicular to the vertical axis of the self-triggered missile-borne data recorder 22; the self-triggering missile-borne data recorder 22 is coaxially mounted with the rocket projectile, and the axial mounting position is not limited.
As shown in fig. 3, the sensor i 2 and the sensor ii 5 are mounted on the inner side of the sensor PCB i 6; sensor III 10 and sensor IV 13 are mounted on the inside of sensor PCB II 12.
As shown in fig. 4-6, the two-stroke inertia-activated activation mechanism 8 includes:
a shell II 15; two parallel sliding channels are formed in the shell II 15; the slide channel is arranged in a direction parallel to the vertical axis of the self-triggering missile-borne data recorder 22;
a front mass block 16; an inward inclined surface is formed on one side of the upper end of the front mass block 16;
a rear mass block 18; the front mass block 16 and the rear mass block 18 are respectively slidably arranged in the two sliding channels; one side of the lower end of the rear mass block 18 is provided with an arc-shaped groove for clamping the steel ball 17;
a steel ball 17; the steel ball 17 is arranged in the rolling channel, under the overload action smaller than the designed threshold value, one part of the steel ball 17 is contacted with one side of the front mass block 16, and the other part of the steel ball 17 is arranged in the groove of the rear mass block 18 and blocks the rear mass block 18;
a spring 19; the two sliding channels are communicated through a rolling channel; the lower end of the front mass block 16 and the lower end of the rear mass block 18 are both contacted with the bottom of the sliding channel through a spring 19; a microswitch I20 is arranged in one sliding channel, and a microswitch II 21 is arranged in the other sliding channel;
as shown in fig. 4, under the continuous overload action larger than the design threshold, the front mass block 16 moves downwards, the front mass block 16 pushes the closing microswitch i 20, and meanwhile, the inclined surface of the front mass block 16 moves downwards to the position of the rolling channel;
as shown in fig. 5, the steel ball 17 moves to the left, the rear mass block 18 is free from constraint, the rear mass block 18 moves downwards under the action of overload, and the microswitch II 21 is closed;
as shown in fig. 6, both microswitches are closed, triggering an activation command and sent to the power management board 14.
In the embodiment, the double-stroke inertia trigger activation mechanism 8 adopts a mass block structure with two sets of springs 19, and only under the overload action of the long pulse width, the mechanism can close two sets of micro switches simultaneously to give a trigger activation signal, so that the false triggering of the overload of the small pulse width under other environments is avoided.
In some embodiments, the battery pack 9 is a rechargeable battery. The battery 9 is preferably a nickel metal hydride battery.
In some embodiments, the inside of the payload recorder is designed to be impact resistant and epoxy potted to withstand a hard recovery overload of 1 × 104 g.
The data recorder can test triaxial overload (+ -300 g) at different positions (point A and point B, shown in figure 1) of the data recorder based on a low-cost triaxial acceleration sensor design, convert triaxial overload at a rocket projectile centroid position through interpolation of a distance X between the point A and the point B and a distance H between the point B and the centroid position, and test a rolling speed (0-50 revolutions per second) of the rocket projectile; the missile-borne data recorder is activated by means of rocket projectile launching overload, the required pulse width is greater than 20ms, and the overload is greater than 50g and is reliably triggered and activated; the missile-borne data recorder can be standby for about 1 month before being activated, namely, after the missile is loaded and installed in a fully charged state, the missile can be selected to carry out a launching test within one month; and after the missile-borne data recorder is triggered and activated, the rocket projectile flight data are recorded, the sampling frequency is 10KHz, and the recording time is longer than 30 min.
In the application, the double-stroke inertia triggering activation mechanism 8 senses rocket projectile launching overload and gives an activation signal to a power management module in the power module; the power supply module consists of a battery pack 9 and a power supply management board 14, and when the power supply management board 14 detects an activation signal, power supply is started to the test recording module; the test recording module is a core component, consists of a sensor board, a signal processing board and a data storage board and is responsible for acquiring, processing, recording and subsequent reading of rocket projectile flight data.
In the application, the charging interface 1 can charge the data recorder; the data interface 3 is a data interface 3 of the data recorder; the distance between the sensor I2 and the sensor II 5 is R; the signal processing and storage board 7 processes and stores the sensor signals;
fig. 7 is a schematic diagram of a missile-borne data recorder system. And the four sensors respectively test three-way overload at corresponding positions, wherein the overload perpendicular to the installation of the PCB is axial overload, and the overload at the corresponding positions of the PCB can be obtained after weighted average. Interpolation is carried out according to the distance X between the point A and the point B in the figure 1 and the distance H between the centroid and the missile-borne data recorder, and the three-way overload of the centroid can be obtained; and carrying out vector addition on the radial acceleration components of the sensors to obtain centrifugal force at the corresponding position, calculating the rotating speeds of the point A and the point B according to the distance R between the mounting position and the circle center, and obtaining the average rotating speed of the projectile body after addition and averaging.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. The utility model provides a from triggering missile-borne data record appearance installs in the rocket projectile, its characterized in that, from triggering missile-borne data record appearance includes:
a power supply module; the power module comprises a battery pack and a power management board; the battery pack is electrically connected with the power management board and the test recording module respectively; the power management board is used for controlling the battery pack to supply power to the test recording module after detecting an activation signal from the double-stroke inertia trigger activation mechanism;
a test recording module;
an inertia trigger activation module; the inertia trigger activation module comprises a double-stroke inertia trigger activation mechanism, and the signal output end of the double-stroke inertia trigger activation mechanism is connected with the signal input end of the power management board; the double-stroke inertia triggering activation mechanism is used for sending an activation signal to the power management board after receiving the rocket projectile and emitting overload.
2. The self-triggering missile-borne data recorder according to claim 1, wherein: the test recording module comprises a data storage board, a signal processing board and a sensor board; the battery pack is respectively electrically connected with the data storage board, the signal processing board and the sensor board, the sensor board is used for collecting the flight data of the rocket projectile, the signal output end of the sensor board is connected with the signal input end of the signal processing board, and the signal output end of the signal processing board is connected with the signal input end of the data storage board.
3. The self-triggering missile-borne data recorder according to claim 2, further comprising:
a charging interface; the charging interface is electrically connected with the battery pack;
a data interface; one end of the data interface is in communication connection with the data storage board, and the other end of the data interface is in communication connection with the computer;
an upper cover;
a shell I; the upper cover is covered on the shell I and forms a closed structure; the charging interface and the data interface are both arranged on the upper cover;
a sensor I;
a sensor II;
a sensor PCB I; the sensor I and the sensor II are arranged on the sensor PCB I; the sensor I and the sensor II are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder;
the data storage board and the signal processing board are combined to form a signal processing and storage board; the signal processing and storing board is respectively electrically connected with the sensor PCB I and the power management board;
a sensor III;
a sensor IV;
a sensor PCB II; the sensor III and the sensor IV are arranged on the sensor PCB II; the sensor III and the sensor IV are symmetrically distributed on the vertical axis of the self-triggering missile-borne data recorder; sensor I, sensor II, sensor PCB I, sensor III, sensor IV, sensor PCB II, signal processing and memory board, group battery, two-stroke inertia trigger activation mechanism all arrange in the enclosure space that upper cover and casing I formed.
4. The self-triggering missile-borne data recorder of claim 3, wherein the sensor PCB I and the sensor PCB II are both arranged perpendicular to a vertical axis of the self-triggering missile-borne data recorder; the self-triggering missile-borne data recorder and the rocket projectile are coaxially installed.
5. The self-triggering missile-borne data recorder according to claim 3, wherein the sensor I and the sensor II are mounted on the inner side of the sensor PCB I; and the sensor III and the sensor IV are arranged on the inner side of the sensor PCB II.
6. The self-triggering missile-borne data recorder according to claim 1, wherein the two-stroke inertia-activated activation mechanism comprises:
a shell II; two mutually parallel sliding channels are formed in the shell II; the arrangement direction of the sliding channel is parallel to the vertical axis of the self-triggering missile-borne data recorder;
a pre-quality block; an inward inclined plane is formed on one side of the upper end of the front mass block;
a rear mass block; the front mass block and the rear mass block are respectively arranged in the two sliding channels in a sliding manner; one side of the lower end of the rear mass block is provided with an arc-shaped groove for clamping the steel ball;
a steel ball; the steel ball is arranged in the rolling channel, under the overload action smaller than the designed threshold value, one part of the steel ball is contacted with one side of the front mass block, the other part of the steel ball is arranged in the groove of the rear mass block, and the rear mass block is blocked;
a spring; the two sliding channels are communicated through a rolling channel; the lower end of the front mass block and the lower end of the rear mass block are both contacted with the bottom of the sliding channel through a spring; a microswitch I is arranged in one sliding channel, a microswitch II is arranged in the other sliding channel, under the continuous overload action larger than a design threshold value, a front mass block moves downwards, the front mass block pushes the microswitch I to be closed, meanwhile, the inclined plane of the front mass block moves downwards to the position of a rolling channel, a steel ball moves leftwards, a rear mass block is free of restraint, the rear mass block moves downwards under the overload action, the microswitch II is closed, the two microswitches are all closed, and an activation instruction is triggered and sent to a power management board.
7. A self-triggering missile-borne data recorder according to claim 3, wherein the battery pack is a rechargeable battery.
8. The self-triggering missile-borne data recorder according to claim 3, wherein the sensor I, the sensor II, the sensor III and the sensor IV are all three-axis sensors.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020161398.8U CN211696099U (en) | 2020-02-11 | 2020-02-11 | Self-triggering missile-borne data recorder |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020161398.8U CN211696099U (en) | 2020-02-11 | 2020-02-11 | Self-triggering missile-borne data recorder |
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| CN211696099U true CN211696099U (en) | 2020-10-16 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111174650A (en) * | 2020-02-11 | 2020-05-19 | 中国工程物理研究院总体工程研究所 | Self-triggering missile-borne data recorder |
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2020
- 2020-02-11 CN CN202020161398.8U patent/CN211696099U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111174650A (en) * | 2020-02-11 | 2020-05-19 | 中国工程物理研究院总体工程研究所 | Self-triggering missile-borne data recorder |
| CN111174650B (en) * | 2020-02-11 | 2024-06-04 | 中国工程物理研究院总体工程研究所 | Self-triggering missile-borne data recorder |
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