CN106771362A - A kind of single shaft, integral type strapdown acceleration measurement device - Google Patents
A kind of single shaft, integral type strapdown acceleration measurement device Download PDFInfo
- Publication number
- CN106771362A CN106771362A CN201611241189.9A CN201611241189A CN106771362A CN 106771362 A CN106771362 A CN 106771362A CN 201611241189 A CN201611241189 A CN 201611241189A CN 106771362 A CN106771362 A CN 106771362A
- Authority
- CN
- China
- Prior art keywords
- mounting hole
- signal
- acceleration
- shock absorber
- circuit
- 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
Classifications
-
- 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
- G01P15/125—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 capacitive pick-up
-
- 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
- G01P15/0802—Details
-
- 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
-
- 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
- G01P2015/0862—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 being provided with particular means being integrated into a MEMS accelerometer structure for providing particular additional functionalities to those of a spring mass system
- G01P2015/0882—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 being provided with particular means being integrated into a MEMS accelerometer structure for providing particular additional functionalities to those of a spring mass system for providing damping of vibrations
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Vibration Prevention Devices (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
Abstract
The invention discloses a kind of single shaft, integral type strapdown acceleration measurement device, including：Quartz flexible accelerometer, signal transacting and interface circuit, secondary power supply module and telemetric circuit and device body；Device body includes：Body construction, is arranged on the mounting flange in the middle part of body construction, and, it is arranged on the multiple mounting grooves on body construction；Quartz flexible accelerometer, signal transacting and interface circuit, secondary power supply module and telemetric circuit are connected by corresponding mounting groove with body construction；Wherein, quartz flexible accelerometer and secondary power supply module are located at the top of the mounting flange；Signal transacting and interface circuit and telemetric circuit are located at the lower section of mounting flange.The present invention solves the problems, such as to solve the complex environment for being difficult to tackle rocket flight process that the horizontal normal direction table of existing three axle is present and the effective acceleration information for effectively extracting rocket body motion.
Description
Technical field
The invention belongs to field of measuring technique, more particularly to a kind of single shaft, integral type strapdown acceleration measurement device.
Background technology
The important symbol that carrier rocket develops as high and new technology, key is played in the aerospace industry development construction of China
Effect, strapdown acceleration measurement device participates in carrier rocket gesture stability as important unit on the arrow of control system, influences appearance
The precision and performance of state control system, are to ensure that an important ring of the reliable and stable operation of carrier rocket.
Apparent acceleration information during adding table to measure rocket motion using the horizontal normal direction of three axles more than conventional carrier rocket, but by
More complicated in the horizontal normal direction table self structure of three axles, installation difficulty is high and alignment error is uncontrollable, so as to be difficult to ensure that certainty of measurement
And the accuracy of control system Control of decreasing load information；The horizontal normal direction table volume of three axles is bigger than normal simultaneously, heavier-weight, to rocket body structure
It is required that and environmental condition it is stricter, the reliability requirement to mounting bracket is also of a relatively high, installation site be limited, it is impossible to be arranged on
Rocket body inwall optimal location, be unfavorable for tackle rocket flight process complex environment and effectively extract rocket body motion it is effective plus
Velocity information.
The content of the invention
Technology solve problem of the invention：Overcome the deficiencies in the prior art, there is provided a kind of single shaft, integral type strapdown acceleration
Measurement apparatus, to solve the complex environment for being difficult to reply rocket flight process of the horizontal normal direction table presence of existing three axle and effectively carry
Take out the problem of the effective acceleration information of rocket body motion.
In order to solve the above-mentioned technical problem, the invention discloses a kind of single shaft, integral type strapdown acceleration measurement device, bag
Include：Quartz flexible accelerometer (1), signal transacting and interface circuit (2), secondary power supply module (3) and telemetric circuit (4) and dress
Put body (5)；
Device body (5) includes：Body construction (51), is arranged on the mounting flange (52) in the middle part of body construction (51), with
And, it is arranged on the multiple mounting grooves on body construction (51)；
Quartz flexible accelerometer (1), signal transacting and interface circuit (2), secondary power supply module (3) and telemetric circuit
(4) it is connected with body construction (51) by corresponding mounting groove；Wherein, quartz flexible accelerometer (1) and secondary power supply module
(3) positioned at the top of the mounting flange；Signal transacting and interface circuit (2) and telemetric circuit (4) are under mounting flange
Side；
Quartz flexible accelerometer (1), for measuring the acceleration information that rocket body motion is produced, obtains acceleration signal；
Signal transacting and interface circuit (2), for gathering acceleration signal and temperature signal, and, to acceleration signal
A/D conversions are carried out with temperature signal；
Secondary power supply module (3), voltage conversion is carried out for the output voltage to arrow last time power supply, and, to once
Power supply is filtered treatment；
Telemetric circuit (4), for the acceleration signal after treatment to be sent to control and telemetry system, is carried out surely to rocket
Fixed control, the unexpected open circuit of primary power source for preventing instantaneous overcurrent from causing.
In above-mentioned single shaft, integral type strapdown acceleration measurement device, signal transacting and interface circuit (2) are additionally operable to：It is right
Acceleration signal is compensated and completes digital filtering treatment, and, led to control system on arrow and surface telemetry system
Letter, rocket body pitching, the apparent acceleration of yaw direction in measurement flight course.
In above-mentioned single shaft, integral type strapdown acceleration measurement device, signal transacting and interface circuit (2), including：Accelerate
Degree meter signaling conversion circuit (21), temperature signal collection circuit (22) and signal processing circuit and interface circuit (23)；
Accelerometer signal change-over circuit (21), the acceleration signal for gathering quartz flexible accelerometer (1) output,
And the acceleration signal to collecting carries out A/D conversions；
Temperature signal collection circuit (22), for collecting temperature signal, and temperature signal to collecting carries out A/D and turns
Change；
Signal processing circuit (23), for decoding, for read-write EEPROM, serial ports controller and A/D operations provide piece choosing letter
Number.
In above-mentioned single shaft, integral type strapdown acceleration measurement device, the secondary power supply module (3), including：First son
Power module (31), the second sub- power module (32), the 3rd sub- power module (33) and wave filter (34)；
The first sub- power module (31), the second sub- power module (32), the 3rd sub- power module (33) and wave filter
(34) it is symmetricly set on the front, rear, left and right four direction of quartz flexible accelerometer (1).
In above-mentioned single shaft, integral type strapdown acceleration measurement device, the output voltage of the first sub- power module (31) is：
±15V；
The output voltage of the second sub- power module (32) is：±5V；
The output voltage of the 3rd sub- power module (33) is：±5V；
The output voltage of primary power source is：28V±3V.
In above-mentioned single shaft, integral type strapdown acceleration measurement device, the single shaft, integral type strapdown acceleration analysis dress
Putting also includes：Four shock absorbers and two electric connectors；
Described device body (5), also includes：Be arranged on body construction (51), at the mounting flange (52) position
First shock absorber mounting hole (53), the second shock absorber mounting hole (54), the 3rd shock absorber mounting hole (55), the 4th shock absorber are installed
Hole (56), the first electric connector mounting hole (57) and the first electric connector mounting hole (58)；Wherein, the first shock absorber mounting hole
(53), the second shock absorber mounting hole (54), the 3rd shock absorber mounting hole (55) and the 4th shock absorber mounting hole (56) are respectively provided with
At four diagonal positions of mounting flange (52)；First electric connector mounting hole (57) and the first electric connector mounting hole (58)
It is located therein between two shock absorber mounting holes；
Four shock absorbers pass through the first shock absorber mounting hole (53), the second shock absorber mounting hole (54), the 3rd vibration damping respectively
Device mounting hole (55) and the 4th shock absorber mounting hole (56) are connected with device body (5)；
Two electric connectors respectively by the first electric connector mounting hole (57) and the first electric connector mounting hole (58) and
Device body (5) is connected.
In above-mentioned single shaft, integral type strapdown acceleration measurement device, quartz flexible accelerometer (1) uses DC voltage-stabilizing
Power supply (voltage ± 15 ± 0.1V) is powered.
In above-mentioned single shaft, integral type strapdown acceleration measurement device, the single shaft, integral type strapdown acceleration analysis dress
Put, also include：Upper cover plate (81), lower cover (82), and at least two conductive seal circles；
At least two conductive seals circle is separately positioned between upper cover plate (81) and device body (5) and lower cover
Between plate (82) and device body (5).
The present invention has advantages below：
(1) single shaft of the present invention, integral type strapdown acceleration measurement device, using single shaft integrated structure design,
Each part is optimized, it is ensured that small product size is small, lightweight, can be directly mounted on rocket body interstage section inwall, to arrow
The single axial acceleration of body is measured, and can effectively solve the problems, such as that measurement apparatus are influenceed by arrow wall vibrations, reduces rocket body attached
Plus influence of the motion to certainty of measurement, reduce influence of the rocket body additional movement to certainty of measurement, it is ensured that strapdown acceleration is surveyed
Measure the precision and reliability of device.
(2) single shaft of the present invention, integral type strapdown acceleration measurement device, using anti-interference mounting means, can be with
Measurement apparatus input shaft is installed along rocket body inwall tangential direction, the vibration of rocket body thin-walled and low frequency cell breath is reduced to flying
The influence of row acceleration, so as to strengthen certainty of measurement of the measurement apparatus under rocket flight environment, improves the reliability of measurement apparatus
Property.
Brief description of the drawings
Fig. 1 is a kind of single shaft, the top view of integral type strapdown acceleration measurement device in the embodiment of the present invention；
Fig. 2 is a kind of single shaft, the upward view of integral type strapdown acceleration measurement device in the embodiment of the present invention；
Fig. 3 is the electrical block diagram of a kind of signal transacting and interface circuit in the embodiment of the present invention；
Fig. 4 is a kind of single shaft, the structural representation of integral type strapdown acceleration measurement device in the embodiment of the present invention.
Specific embodiment
It is public to the present invention below in conjunction with accompanying drawing to make the object, technical solutions and advantages of the present invention clearer
Implementation method is described in further detail.
Single shaft of the present invention, integral type strapdown acceleration measurement device are being tied as a kind of high precision measuring device
Miniaturization, unitary design, greatly reduce its installation difficulty and space requirement on arrow wall, while strapdown acceleration on structure
It is measurement apparatus small volume, lightweight, can be directly tangentially mounted on rocket body inwall, so as to can effectively be shelled from rocket body vibration effect
From rocket motion acceleration, therefore application on the launch vehicle has obvious advantage, while product may be implemented in complicated flying
High reliability application and high-acruracy survey under row environment, therefore in the spacecraft neck very high to product reliability and life requirements
Domain, can overcome the shortcomings of traditional horizontal Fa Jiabiao installation difficulty is big, measurement is complicated, temperature environment requirement is high, realize high accuracy and
High reliability is measured.
Reference picture 1, shows a kind of single shaft, the vertical view of integral type strapdown acceleration measurement device in the embodiment of the present invention
Figure；Fig. 2, shows a kind of single shaft, the upward view of integral type strapdown acceleration measurement device in the embodiment of the present invention.Such as Fig. 1 and
2, in the present embodiment, the single shaft, integral type strapdown acceleration measurement device, including：Quartz flexible accelerometer 1, signal
Treatment and interface circuit 2, secondary power supply module 3 and telemetric circuit 4 and device body 5.
Wherein, described device body 5 includes：Body construction 51, is arranged on the mounting flange 52 at the middle part of body construction 51, with
And, it is arranged on the multiple mounting grooves on body construction 51.Preferably, body construction 51 can using modulus/density than it is high,
The hard aluminium alloy bar material (e.g., LY12CZ) that yield strength/density ratio is high, thermal conductivity is good.
In the present embodiment, quartz flexible accelerometer 1, signal transacting and interface circuit 2, secondary power supply module 3 and distant
Slowdown monitoring circuit 4 is connected by corresponding mounting groove with body construction 51；Wherein, quartz flexible accelerometer 1 and secondary power supply module 3
Positioned at the top of the mounting flange；Signal transacting and interface circuit 2 and telemetric circuit 4 are located at the lower section of mounting flange.
Wherein, quartz flexible accelerometer 1, the acceleration information that rocket body motion is produced is obtained for measuring, and is accelerated
Degree signal.Preferably, the quartz flexible accelerometer 1 can use single shaft quartz accelerometer, by gauge outfit and servo circuit
Composition, small volume, high precision, technology and technical maturity are powered, to quick using D.C. regulated power supply (voltage ± 15 ± 0.1V)
Sense apparent acceleration information.
Signal transacting and interface circuit 2, for gathering acceleration signal and temperature signal, and, to acceleration signal and
Temperature signal carries out A/D conversions (Analog/Digital, analog/digital).Preferably, signal transacting and interface circuit 2 are also used
In：Digital filtering treatment is compensated and completed to acceleration signal, and, enter with control system on arrow and surface telemetry system
Row communication, rocket body pitching, the apparent acceleration of yaw direction in measurement flight course.
Reference picture 3, shows the electrical block diagram of a kind of signal transacting and interface circuit in the embodiment of the present invention.
In the present embodiment, signal transacting and interface circuit 2 are used with DSP (Digital Signal Processor, Digital Signal Processing
Device) centered on computer plate, completed accelerometer data conversion, collection by DSP and its peripheral circuit and processed, and various
The requirement of input/output interface.Preferably, as shown in figure 3, signal transacting and interface circuit 2 can include：Accelerometer signal
Change-over circuit 21, temperature signal collection circuit 22 and signal processing circuit and interface circuit 23.Wherein, accelerometer signal conversion
Circuit 21 can select the A/D converter (AD976A) of 16, the acceleration letter for gathering the output of quartz flexible accelerometer 1
Number, and acceleration signal to collecting carries out A/D conversions.Temperature signal collection circuit 22 it is main by amplifier modulate circuit and
A/D conversion chips (AD7893) are constituted, and for collecting temperature signal, and temperature signal to collecting carries out A/D conversions.Letter
Number process circuit 23 mainly realizes decoding function by decoder, and, it is read-write EEPROM (Electrically Erasable
Programmable Read-Only Memory, electrically erasable read-only memory), serial ports controller and A/D operation provide piece choosing letter
Number.
Secondary power supply module 3, voltage conversion is carried out for the output voltage to arrow last time power supply, and, to once electricity
Source is filtered treatment.
In the present embodiment, as shown in figure 1, secondary power supply module 3 can include：First the 31, second son of sub- power module
Power module 32, the 3rd sub- power module 33 and wave filter 34.The first sub- power module 31, the second sub- power module 32,
3rd sub- power module 33 and wave filter 34 are symmetricly set on the front, rear, left and right four direction of quartz flexible accelerometer 1.
Wherein, the output voltage of the first sub- power module 31 is：±15V；The output voltage of the second sub- power module 32 is：
±5V；The output voltage of the 3rd sub- power module 33 is：±5V；The output voltage of primary power source is：28V±3V.
In the present embodiment, the Main Function of secondary power supply module 3 is that arrow last time power supply (28V ± 3V) is converted to victory
± 15V, ± 5V power supplys needed for connection acceleration measurement device work, and treatment is filtered to primary power source in input, with
Primary power source is isolated.
Telemetric circuit 4, for the acceleration signal after treatment to be sent to control and telemetry system, stabilization is carried out to rocket
Control, the unexpected open circuit of primary power source for preventing instantaneous overcurrent from causing.
In the present embodiment, telemetric circuit 4 can use RS485 serial bus transmission consensus standards, and semiduplex mode will
Acceleration signal after treatment is sent to control and telemetry system through interface circuit in the form of serial ports 485, and rocket is carried out to stablize control
System, while preventing instantaneous overcurrent from causing the unexpected open circuit of primary power source.
Preferably, telemetric circuit 4 is using using RS485 serial bus transmission consensus standards, semiduplex mode, power supply
Isolate with other power sourced electrics, wherein, it is main with the interface circuit of control system on arrow and surface telemetry system by asynchronous serial port
Control chip TL16C552A, optocoupler and RS485 interface chips SN55LBC176 composition；Simultaneously using two current-limiting resistances of 1 Ω
Parallel connection, power consumption is 0.25W, and the partial pressure of protective resistance does not influence the normal work of secondary power supply module 3, prevents instantaneous overcurrent from making
Into the unexpected open circuit of primary power source, play a part of battery on protection arrow.
In the preferred embodiment of the present invention, such as Fig. 1 and 2, described device body 5 can also include：It is arranged on body
The first shock absorber mounting hole 53, the second shock absorber mounting hole 54 in structure 51, at the position of the mounting flange 52, the 3rd vibration damping
Device mounting hole 55, the 4th shock absorber mounting hole 56, the first electric connector mounting hole 57 and the first electric connector mounting hole 58.
Wherein, the first shock absorber mounting hole 53, the second shock absorber mounting hole 54, the 3rd shock absorber mounting hole 55 and the 4th subtract
The device mounting hole 56 that shakes is separately positioned at four diagonal positions of mounting flange 52.First electric connector mounting hole 57 and the first electricity
Connector mounting hole 58 is located therein between two shock absorber mounting holes.
Preferably, the single shaft, integral type strapdown acceleration measurement device also include：Four shock absorbers and two electrical connections
Device.
Wherein, four shock absorbers pass through the first shock absorber mounting hole 53, the second shock absorber mounting hole 54, the 3rd vibration damping respectively
The shock absorber mounting hole 56 of device mounting hole 55 and the 4th is connected with device body 5.
Preferably, shock absorber selects T-shaped design, and material is silica gel, and line resonant frequency is screened in 65~70Hz in 6.06g
Damping efficiency 40%~50% in vibration, damping efficiency about 70% in 13.65g acceptance tests.
In the present embodiment, it is contemplated that the reasonable installation requirement of shock absorber and the installation center and whole strapdown of shock absorber
The skew of acceleration measurement device barycenter, the general structure of strapdown acceleration measurement device is installed using central flange.Additionally, prompt
Using outside integral vibration damping mode, damper is arranged on the position of mounting flange 52 to connection acceleration measurement device, to reduce during work
The vibration and impact being subject to, shock absorber mounting surface are apart from each other, it is ensured that the stability of installation accuracy.
Two electric connectors.Pass through the first electric connector mounting hole 57 and the first electric connector mounting hole 58 and device respectively
Body 5 is connected.
Additionally, in all to setting radiating groove on lateral wall of device body 5, to ensure the single shaft, integral type strapdown
Acceleration measurement device has good heat dispersion.
In the preferred embodiment of the present invention, reference picture 4, show a kind of single shaft, integral type in the embodiment of the present invention
The structural representation of strapdown acceleration measurement device.Such as Fig. 4, the single shaft, integral type strapdown acceleration measurement device also include：
Upper cover plate 81, lower cover 82, and at least two conductive seal circles.Wherein, at least two conductive seals circle is respectively provided with
Between upper cover plate 81 and device body 5 and between lower cover 82 and device body 5.
In the present embodiment, can by the way of radial seal, between upper cover plate 81 and device body 5 and under
Conductive seal circle is provided between cover plate 82 and device body 5, additionally, being also provided between two electric connectors and device body 5
There is conductive seal circle, it is ensured that whole strapdown acceleration measurement device is internally formed an environment for closing.
Based on above-described embodiment, the application to the strapdown acceleration measurement device below is illustrated.
In the present embodiment, the strapdown acceleration measurement device can be in tangentially mounted mode installed between rocket body level
On section inwall, first, the acceleration information for producing is moved by quartz flexible accelerometer sensitivity rocket body；Again by signal transacting and
The acceleration signal of interface circuit collection quartz flexible accelerometer output, and digital quantity is converted to, it is filtered treatment and misses
Difference compensation, so as to measure the apparent acceleration of rocket body pitching, yaw direction in flight course；Finally, telemetric circuit is by after treatment
Acceleration signal is sent to control system through interface circuit in the form of serial ports 485, to carry out stability contorting to rocket.
In sum, described in the embodiment of the present invention single shaft, integral type strapdown acceleration measurement device, using single shaft integrally
Change structure design, Each part is optimized, it is ensured that small product size is small, lightweight, can be directly mounted at rocket body interstage section
On inwall, axial acceleration single to rocket body is measured, and can effectively solve the problems, such as that measurement apparatus are influenceed by arrow wall vibrations,
Reduce influence of the rocket body additional movement to certainty of measurement, reduce influence of the rocket body additional movement to certainty of measurement, it is ensured that be prompt
Join the precision and reliability of acceleration measurement device.
Secondly, single shaft, integral type strapdown acceleration measurement device described in the embodiment of the present invention, using anti-interference installation side
Formula, measurement apparatus input shaft can be installed along rocket body inwall tangential direction, reduce the vibration of rocket body thin-walled and low frequency breathing
Influence of the effect to Flight Acceleration, so as to strengthen certainty of measurement of the measurement apparatus under rocket flight environment, improves measurement dress
The reliability put.
The above, optimal specific embodiment only of the invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
Should all be included within the scope of the present invention.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (8)
1. a kind of single shaft, integral type strapdown acceleration measurement device, it is characterised in that：Including：Quartz flexible accelerometer (1),
Signal transacting and interface circuit (2), secondary power supply module (3) and telemetric circuit (4) and device body (5)；
Device body (5) includes：Body construction (51), is arranged on the mounting flange (52) in the middle part of body construction (51), and, if
Put the multiple mounting grooves on body construction (51)；
Quartz flexible accelerometer (1), signal transacting and interface circuit (2), secondary power supply module (3) and telemetric circuit (4) are led to
Corresponding mounting groove is crossed to be connected with body construction (51)；Wherein, quartz flexible accelerometer (1) and secondary power supply module (3) position
In the top of the mounting flange；Signal transacting and interface circuit (2) and telemetric circuit (4) are positioned at the lower section of mounting flange；
Quartz flexible accelerometer (1), for measuring the acceleration information that rocket body motion is produced, obtains acceleration signal；
Signal transacting and interface circuit (2), for gathering acceleration signal and temperature signal, and, to acceleration signal and temperature
Degree signal carries out A/D conversions；
Secondary power supply module (3), voltage conversion is carried out for the output voltage to arrow last time power supply, and, to primary power source
It is filtered treatment；
Telemetric circuit (4), for the acceleration signal after treatment to be sent to control and telemetry system, carries out stablizing control to rocket
System, the unexpected open circuit of primary power source for preventing instantaneous overcurrent from causing.
2. single shaft according to claim 1, integral type strapdown acceleration measurement device, it is characterised in that
Signal transacting and interface circuit (2), are additionally operable to：Digital filtering treatment is compensated and completed to acceleration signal, and,
Communicated with control system on arrow and surface telemetry system, measurement flight course in rocket body pitching, yaw direction regarding acceleration
Degree.
3. single shaft according to claim 1, integral type strapdown acceleration measurement device, it is characterised in that signal transacting and
Interface circuit (2), including：Accelerometer signal change-over circuit (21), temperature signal collection circuit (22) and signal processing circuit
And interface circuit (23)；
Accelerometer signal change-over circuit (21), the acceleration signal for gathering quartz flexible accelerometer (1) output, and it is right
The acceleration signal for collecting carries out A/D conversions；
Temperature signal collection circuit (22), for collecting temperature signal, and temperature signal to collecting carries out A/D conversions；
Signal processing circuit (23), for decoding, for read-write EEPROM, serial ports controller and A/D operations provide chip selection signal.
4. single shaft according to claim 1, integral type strapdown acceleration measurement device, it is characterised in that the secondary electricity
Source module (3), including：First sub- power module (31), the second sub- power module (32), the 3rd sub- power module (33) and filtering
Device (34)；
The first sub- power module (31), the second sub- power module (32), the 3rd sub- power module (33) and wave filter (34)
It is symmetricly set on the front, rear, left and right four direction of quartz flexible accelerometer (1).
5. single shaft according to claim 4, integral type strapdown acceleration measurement device, it is characterised in that
The output voltage of the first sub- power module (31) is：±15V；
The output voltage of the second sub- power module (32) is：±5V；
The output voltage of the 3rd sub- power module (33) is：±5V；
The output voltage of primary power source is：28V±3V.
6. a kind of single shaft according to claim 1, integral type strapdown acceleration measurement device, it is characterised in that the list
Axle, integral type strapdown acceleration measurement device also include：Four shock absorbers and two electric connectors；
Described device body (5), also includes：Be arranged on body construction (51), at the mounting flange (52) position first
Shock absorber mounting hole (53), the second shock absorber mounting hole (54), the 3rd shock absorber mounting hole (55), the 4th shock absorber mounting hole
(56), the first electric connector mounting hole (57) and the first electric connector mounting hole (58)；Wherein, the first shock absorber mounting hole
(53), the second shock absorber mounting hole (54), the 3rd shock absorber mounting hole (55) and the 4th shock absorber mounting hole (56) are respectively provided with
At four diagonal positions of mounting flange (52)；First electric connector mounting hole (57) and the first electric connector mounting hole (58)
It is located therein between two shock absorber mounting holes；
Four shock absorbers are pacified by the first shock absorber mounting hole (53), the second shock absorber mounting hole (54), the 3rd shock absorber respectively
Dress hole (55) and the 4th shock absorber mounting hole (56) are connected with device body (5)；
Two electric connectors pass through the first electric connector mounting hole (57) and the first electric connector mounting hole (58) and device respectively
Body (5) is connected.
7. single shaft according to claim 1, integral type strapdown acceleration measurement device, it is characterised in that
Quartz flexible accelerometer (1) is using D.C. regulated power supply (voltage ± 15 ± 0.1V) power supply.
8. single shaft according to claim 1, integral type strapdown acceleration measurement device, it is characterised in that the single shaft, one
Body formula strapdown acceleration measurement device, also includes：Upper cover plate (81), lower cover (82), and at least two conductive seal circles；
At least two conductive seals circle is separately positioned between upper cover plate (81) and device body (5) and lower cover
(82) and device body (5) between.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611241189.9A CN106771362B (en) | 2016-12-29 | 2016-12-29 | A kind of uniaxial, integral type strapdown acceleration measurement device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611241189.9A CN106771362B (en) | 2016-12-29 | 2016-12-29 | A kind of uniaxial, integral type strapdown acceleration measurement device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106771362A true CN106771362A (en) | 2017-05-31 |
| CN106771362B CN106771362B (en) | 2019-05-24 |
Family
ID=58924130
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611241189.9A Active CN106771362B (en) | 2016-12-29 | 2016-12-29 | A kind of uniaxial, integral type strapdown acceleration measurement device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106771362B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109682991A (en) * | 2018-12-12 | 2019-04-26 | 上海航天控制技术研究所 | A kind of carrier rocket high-altitude active off-load accelerometer device |
| CN110542432A (en) * | 2019-08-13 | 2019-12-06 | 中国航空工业集团公司西安飞行自动控制研究所 | Single-shaft frame for split design and assembly and manufacturing method thereof |
| CN110850112A (en) * | 2019-11-22 | 2020-02-28 | 上海航天控制技术研究所 | Carrier rocket carries with miniaturized high accuracy acceleration measuring device that subtracts |
| CN111103438A (en) * | 2018-10-25 | 2020-05-05 | 航天科工惯性技术有限公司 | Device and method for testing accelerometer core |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB791827A (en) * | 1948-03-22 | 1958-03-12 | Mini Of Supply | Improvements in or relating to accelerometers |
| WO2006096741A1 (en) * | 2005-03-07 | 2006-09-14 | Stewart Robert E | High accuracy strapdown digital accelerometer |
| CN101413835A (en) * | 2008-11-26 | 2009-04-22 | 上海神开石油化工装备股份有限公司 | Apparatus for testing load and acceleration |
| CN101487709A (en) * | 2009-02-27 | 2009-07-22 | 哈尔滨工程大学 | Micro-miniature inertial measuring unit |
| CN101975872A (en) * | 2010-10-28 | 2011-02-16 | 哈尔滨工程大学 | Method for calibrating zero offset of quartz flexible accelerometer component |
| CN201777393U (en) * | 2010-08-02 | 2011-03-30 | 浙江大学 | Multi-parameter composite environmental test device |
| CN202676172U (en) * | 2012-06-26 | 2013-01-16 | 西安金源电气股份有限公司 | Conductor galloping sensor |
| CN202929500U (en) * | 2012-07-04 | 2013-05-08 | 航天科工惯性技术有限公司 | Accelerometer and its temperature control circuit |
| CN103604431A (en) * | 2013-11-21 | 2014-02-26 | 北京航空航天大学 | Strapdown compass system based on triaxial integrated high-precision optic fiber gyroscope |
| CN203704917U (en) * | 2014-04-08 | 2014-07-09 | 北京全信科工科技发展有限公司 | Double-axis digital tilt sensor |
| CN104802697A (en) * | 2015-03-30 | 2015-07-29 | 西北工业大学 | Micro inertial measurement unit and measurement unit based adaptive headlamp control method |
| CN205373720U (en) * | 2016-01-27 | 2016-07-06 | 中联天通科技（北京）有限公司 | A add table module for on -vehicle portable positioning orientation appearance |
-
2016
- 2016-12-29 CN CN201611241189.9A patent/CN106771362B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB791827A (en) * | 1948-03-22 | 1958-03-12 | Mini Of Supply | Improvements in or relating to accelerometers |
| WO2006096741A1 (en) * | 2005-03-07 | 2006-09-14 | Stewart Robert E | High accuracy strapdown digital accelerometer |
| CN101413835A (en) * | 2008-11-26 | 2009-04-22 | 上海神开石油化工装备股份有限公司 | Apparatus for testing load and acceleration |
| CN101487709A (en) * | 2009-02-27 | 2009-07-22 | 哈尔滨工程大学 | Micro-miniature inertial measuring unit |
| CN201777393U (en) * | 2010-08-02 | 2011-03-30 | 浙江大学 | Multi-parameter composite environmental test device |
| CN101975872A (en) * | 2010-10-28 | 2011-02-16 | 哈尔滨工程大学 | Method for calibrating zero offset of quartz flexible accelerometer component |
| CN202676172U (en) * | 2012-06-26 | 2013-01-16 | 西安金源电气股份有限公司 | Conductor galloping sensor |
| CN202929500U (en) * | 2012-07-04 | 2013-05-08 | 航天科工惯性技术有限公司 | Accelerometer and its temperature control circuit |
| CN103604431A (en) * | 2013-11-21 | 2014-02-26 | 北京航空航天大学 | Strapdown compass system based on triaxial integrated high-precision optic fiber gyroscope |
| CN203704917U (en) * | 2014-04-08 | 2014-07-09 | 北京全信科工科技发展有限公司 | Double-axis digital tilt sensor |
| CN104802697A (en) * | 2015-03-30 | 2015-07-29 | 西北工业大学 | Micro inertial measurement unit and measurement unit based adaptive headlamp control method |
| CN205373720U (en) * | 2016-01-27 | 2016-07-06 | 中联天通科技（北京）有限公司 | A add table module for on -vehicle portable positioning orientation appearance |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111103438A (en) * | 2018-10-25 | 2020-05-05 | 航天科工惯性技术有限公司 | Device and method for testing accelerometer core |
| CN109682991A (en) * | 2018-12-12 | 2019-04-26 | 上海航天控制技术研究所 | A kind of carrier rocket high-altitude active off-load accelerometer device |
| CN109682991B (en) * | 2018-12-12 | 2021-12-07 | 上海航天控制技术研究所 | Accelerometer device for high-altitude active load shedding of carrier rocket |
| CN110542432A (en) * | 2019-08-13 | 2019-12-06 | 中国航空工业集团公司西安飞行自动控制研究所 | Single-shaft frame for split design and assembly and manufacturing method thereof |
| CN110850112A (en) * | 2019-11-22 | 2020-02-28 | 上海航天控制技术研究所 | Carrier rocket carries with miniaturized high accuracy acceleration measuring device that subtracts |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106771362B (en) | 2019-05-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106771362A (en) | A kind of single shaft, integral type strapdown acceleration measurement device | |
| CN101670886B (en) | Method and device for diagnosing information fusion fault of underwater robot propeller | |
| CN102032900A (en) | Digital dip-angle sensor | |
| CN205066776U (en) | Nine attitude sensor based on data fusion | |
| CN206514864U (en) | A kind of unmanned plane inertial measuring unit and the unmanned plane containing it | |
| CN206459751U (en) | A kind of infrared temperature monitor | |
| CN108528492A (en) | A kind of inertial navigation system transfer car(buggy) | |
| CN111577152A (en) | Mining drilling rod based on central cable and data acquisition and transmission system | |
| WO2016101921A1 (en) | Battery information collection system of bus micro-power consumption group | |
| CN107153372A (en) | A kind of miniature data collecting system of the expansible stack of passage | |
| CN102548312B (en) | The method of a kind of high overload recorder local segmentation embedding | |
| CN201897473U (en) | Digital inclination sensor | |
| CN110146212A (en) | Joint of mechanical arm torque posture wireless sensor | |
| CN104501836B (en) | A kind of wireless device for flight data calibration | |
| CN102215602A (en) | Wireless sensor network monitoring node in high-temperature coalfield fire area at 130-1000 DEG C and monitoring method thereof | |
| CN206174952U (en) | Drilling deviational survey device | |
| CN210037233U (en) | Portable vehicle operation stationarity measurement analyzer | |
| CN208751879U (en) | One kind being used for new energy vehicle Brake energy recovery test device | |
| CN104807580B (en) | integrated wireless indicator diagram sensor | |
| CN203349854U (en) | High precision digital sensor calibration test system based on PC machine | |
| CN206740163U (en) | Sensor detection circuit plate | |
| CN103645708A (en) | Mining vehicle running state signal collection device | |
| CN209673278U (en) | A kind of IEPE free-field blast pressure "pencil" sensor | |
| CN204945710U (en) | A kind of driver control circuit | |
| CN205981233U (en) | High speedtransmitter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |