CN202974530U - Micro solid chemical thruster thrust measuring device - Google Patents
Micro solid chemical thruster thrust measuring device Download PDFInfo
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- CN202974530U CN202974530U CN201220542615.3U CN201220542615U CN202974530U CN 202974530 U CN202974530 U CN 202974530U CN 201220542615 U CN201220542615 U CN 201220542615U CN 202974530 U CN202974530 U CN 202974530U
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- vertical beam
- solid chemical
- balance
- crossbeam
- thrust
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Abstract
The utility model discloses a micro solid chemical thruster thrust measuring device. The micro solid chemical thruster thrust measuring device mainly comprises a support component, a force balance scale, an MEMS inertial measurement combination 7, a capacitance sensor 13, a micro solid chemical thruster 10, and a signal processing system. The micro solid chemical thruster thrust measuring device is characterized in that: the effect of the self weight of the thruster and the sensor on the measurement result is eliminated by the force balance scale; the multiple sensor measurement combination is used to avoid the measurement uncertainty due to the measurement error caused by single sensor, and the measurement accuracy and reliability are improved; the MEMS inertial measurement combination is combined with the capacitance sensor to measure the maximum thrust of the micro chemical thruster, and because of a high precision MEMS accelerometer, an MEMS gyroscope of MEMS and a signal processing circuit with high sampling frequency, the variance in size of the thrust is monitored on the real time.
Description
Technical field:
The present invention relates to a kind of thrust-measuring device of miniature solid chemical propeller
Background technology:
Propulsion system is the key subsystem of most of spacecrafts, is mainly used in position maintenance, attitude control, gravitation compensation and the orbit adjusting etc. of spacecraft.Along with minitype spacecraft, as little satellite, the continuous maturation of satellite, skin satellite technology of receiving, if need minitype spacecraft to complete some special duty, as satellite formation flying, need to be equipped with propulsion system to these minitype spacecrafts.Due to traditional propulsion system volume and quality all larger, can not be applicable to minitype spacecraft, so active demand is suitable for high reliability, low-power consumption, the microthrust of micro-satellite, the miniature propulsion system of little momentum.
Thrust how to measure miniature propulsion system is study hotspot always, can provide for the research of micro-satellite push system necessary reference by the measurement to miniature propulsion system thrust.Liu Minghou has provided the measuring method of several micro-thruster thrusts and has pointed out and relatively has been fit at present domestic thrust testing research with the only method of displacement transducer side in " Thrust Measurement For Micro Thrusters " [1], structure is generally rocked in thrust measurement for the uN level, double pendulum structure or wall counter weight construction etc.Xiong Jijun is " realizing method and the experimental study of little ox level dynamic thrust test "
[2]In provided a kind of method of utilizing displacement to measure dynamic thrust.But utilize displacement transducer to measure the measuring accuracy that micro thrust can be subject to displacement transducer, have larger measuring error (in document 2, measuring error is 10%).Along with improving constantly of mems accelerometer and MEMS gyroscope precision, make angular acceleration and the angular velocity measured in balance beam transient motion process become possibility, angular velocity, angular acceleration and displacement binding analysis calculate can enrich measurement means, and reduces the error that causes because of the single-sensor measurement.
Summary of the invention:
The object of the invention is to provide a kind of thrust-measuring device of miniature solid chemical propeller, conducts oneself with dignity on the impact of measurement result by dynamic balance balance elimination propulsion system and sensor; Adopt multisensor to measure combination, reduce the measuring error that causes because of single-sensor measurements, raising measuring accuracy; The thrust that data by the Real-Time Monitoring sensor can draw little chemical propeller over time, for the design improvement of μ N level miniature solid chemical propeller and the design of micro-satellite power system provide important references.Solution of the present invention is:
Miniature solid chemical propeller thrust-measuring device mainly comprises support component, dynamic balance balance, MEMS IMU 7, capacitive transducer 13, miniature solid chemical propeller 10, the signal processing system;
Described support component is used for holding remaining part, is included in the crash roll 11 of vacuum chamber 1 interior placement, and is fixed in the base for supporting 17 on crash roll 11;
Described capacitive transducer 13 is connected by support and described support component;
Described dynamic balance balance is equal-arm balance, comprises crossbeam 2, vertical beam 12 and fine adjustment balancing device; Described crossbeam 2 and vertical beam 12 are fixed into symmetrical cross structure, and prop up on cutter 5 by the balance that crossbeam 2 centers are positioned on base for supporting 17; Described fine adjustment balancing device makes crossbeam 2 be in horizontal direction;
Described MEMS IMU 7 is fixed on vertical beam 12, comprises a single shaft mems accelerometer and a single shaft MEMS gyroscope;
Described miniature solid chemical propeller 10 is fixed on vertical beam 12; And it is not parallel with vertical beam 12 that miniature solid chemical propeller 10 produces thrust direction;
Described signal processing system comprises that one has the signal processing circuit 15 that simulating signal amplification filtering and digital-to-analogue transform and is fixed in signal bus 14 on vertical beam 12; Described signal bus 14 comprises capacitive transducer output signal line 18, MEMS IMU output signal line 19 and little chemical propeller ignition control signal line; Signal bus 14 use card line seats 8 are fixed on balance base for supporting 17, prop up cutter 5 by balance and are connected to MEMS IMU 7 and little chemical propeller 10 and are fixed on vertical beam 12 with card line seat 8; The part that is connected with crossbeam 2 at vertical beam 12 has the signal wire redundancy.
during measurement, at first make crossbeam 2 substantially be in horizontal direction by the counterweight counterweight 6 of adjusting fine adjustment balancing device, then carefully regulate by leveling nut 3 crossbeam 2 levels that make, light a fire to miniature solid chemical propeller 10 by the signal wire that is fixed on balance vertical beam 12, producing thrust after igniting makes balance vertical beam 12 produce swing, MEMS IMU 7 is measured acceleration and the angular acceleration of vertical beam 12 in motion process, capacitive transducer 13 is measured the electric capacity between itself and vertical beam 12, the signal of MEMS IMU and capacitive transducer all is transferred to the signal processing circuit of vacuum chamber 1 outside by being fixed in signal wire on balance vertical beam 12, signal processing circuit is carried out being transferred to computing machine after the processing such as amplification filtering digital-to-analog conversion and is processed the thrust variation curve that calculates miniature solid chemical propeller 10 to signal.
Beneficial effect of the present invention: realized eliminating propulsion system and sensor deadweight to the impact of measurement result by the dynamic balance balance; Adopt multisensor to measure combination, reduce the measuring error that causes because of single-sensor measurements, raising measuring accuracy; Combine with capacitive transducer by the MEMS IMU and can measure the maximum thrust of little chemical propeller, size variation that simultaneously can Real-Time Monitoring thrust.
Description of drawings:
Fig. 1 is structure drawing of device of the present invention
Fig. 2 is the assembling side elevation of dynamic balance balance of the present invention
In figure: the 1-vacuum chamber; The 2-crossbeam; 3-leveling nut; The 4-fastening bolt; The 5-balance props up cutter; 6-counterweight counterweight; The 7-MEMS IMU; 8-card line seat; The little chemical propeller control signal wire of 9-; The little chemical propeller of 10-; The 11-crash roll; The 12-vertical beam; The 13-capacitive transducer; The 14-signal bus; The 15-signal processing circuit; 16-processes and displays computing machine; The 17-base for supporting; 18-capacitive transducer output signal line; 19-MEMS IMU output signal line.
Embodiment:
Embodiment 1:
Miniature solid chemical propeller thrust-measuring device, this device comprise dynamic balance balance, MEMS IMU 7, capacitive transducer 13, miniature solid chemical propeller 10, signal processing system;
Consult Fig. 1, the miniature solid chemical propeller thrust-measuring device in the present embodiment mainly comprises support component, dynamic balance balance, MEMS IMU 7, capacitive transducer 13, miniature solid chemical propeller 10, the signal processing system;
Described support component is used for holding remaining part, is included in the crash roll 11 of vacuum chamber 1 interior placement, and is fixed in the base for supporting 17 on crash roll 11; Crash roll 11 is used for isolated extraneous vibration to the impact of balance;
Described capacitive transducer 13 is connected by support and described support component; Capacitive transducer 13 is used for measuring the displacement of balance vertical beam 12;
Described dynamic balance balance is equal-arm balance, comprises crossbeam 2, vertical beam 12 and fine adjustment balancing device; Described crossbeam 2 and vertical beam 12 materials are density less than 400kg/m
3Thickness to alleviate quality, increases vertical beam 12 acceleration, angular velocity and displacement signal at the volley less than the fiberboard of 5mm, crossbeam 2 and vertical beam 12 are fixed into symmetrical cross structure, and prop up on cutter 5 by the balance that crossbeam 2 centers are positioned on base for supporting 17; Described fine adjustment balancing device makes crossbeam 2 be in horizontal direction; Fine adjustment balancing device in the present embodiment comprises two counterweight counterweights 6 that lay respectively at crossbeam 2 two ends and the leveling nut 3 that is fixed in the crossbeam center;
Described MEMS IMU 7 is fixed on vertical beam 12, comprises a single shaft mems accelerometer and a single shaft MEMS gyroscope; Mems accelerometer is used for measuring the acceleration of balance vertical beam 12 in motion process, and the MEMS gyroscope is used for measuring the angular acceleration of balance vertical beam 12 in motion process;
Described miniature solid chemical propeller 10 is fixed on vertical beam 12; And it is vertical with vertical beam 12 that miniature solid chemical propeller 10 produces thrust direction;
Described signal processing system comprises that one has the signal processing circuit 15 that simulating signal amplification filtering and digital-to-analogue transform and is fixed in signal bus 14 on vertical beam 12; Described signal bus 14 comprises capacitive transducer output signal line 18, MEMS IMU output signal line 19 and little chemical propeller ignition control signal line; For the impact of measuring, adopt outer insulation diameter less than the flexible signal line of 0.5mm for the motion that reduces signal wire in the present embodiment; Signal bus 14 is used for gathering the voltage signal of described capacitive transducer and the generation of MEMS IMU; Signal bus 14 use card line seats 8 are fixed on balance base for supporting 17, prop up cutter 5 by balance and are connected to MEMS IMU 7 and little chemical propeller 10 and are fixed on vertical beam 12 with card line seat 8; The part that is connected with crossbeam 2 at vertical beam 12 has the signal wire redundancy.
Mode as an alternative, the crossbeam 2 in the present embodiment and the material of vertical beam 12 can be also the sheet materials such as scale board, LDPE plastic plate;
The course of work of the present embodiment: at first according to shown in Figure 1, device is assembled up, the quality of adjusting two counterweight counterweights 6 after assembling makes the direction of balance vertical beam 12 be similar to the acceleration of gravity direction, and then trickle adjustment leveling nut 3 makes balance vertical beam 12 directions identical with the acceleration of gravity direction; Open control computing machine 16 and signal processing circuit 15 in running order, computing machine sends ignition signal and is delivered to little chemical propeller 10 by signal wire 14, makes little chemical propeller 10 igniting produce thrusts, vertical beam 12 motions of expulsive force balance balance; Signal processing circuit 15 gathers the processing such as the conversion of line number mould and amplification filtering of going forward side by side of data that MEMS IMUs 7 and capacitive transducer 13 spread out of, signal is transferred to computing machine 16 calculates and show thrust size curve, realized the variation of Real-Time Monitoring thrust size.
Claims (4)
1. miniature solid chemical propeller thrust-measuring device is characterized in that: mainly comprise support component, dynamic balance balance, MEMS IMU (7), capacitive transducer (13), miniature solid chemical propeller (10), the signal processing system;
Described support component is used for holding remaining part, is included in the crash roll (11) of placing in vacuum chamber (1), and is fixed in the base for supporting (17) on crash roll (11);
Described capacitive transducer (13) is connected by support and described support component;
Described dynamic balance balance is equal-arm balance, comprises crossbeam (2), vertical beam (12) and fine adjustment balancing device; Described crossbeam (2) and vertical beam (12) are fixed into symmetrical cross structure, and prop up on cutter (5) by the balance that crossbeam (2) center is positioned on base for supporting (17); Described fine adjustment balancing device makes crossbeam (2) be in horizontal direction;
Described MEMS IMU (7) is fixed on vertical beam (12), comprises a single shaft mems accelerometer and a single shaft MEMS gyroscope;
Described miniature solid chemical propeller (10) is fixed on vertical beam (12); And it is not parallel with vertical beam (12) that miniature solid chemical propeller (10) produces thrust direction;
Described signal processing system comprises that one has the signal processing circuit (15) that simulating signal amplification filtering and digital-to-analogue transform and is fixed in signal bus (14) on vertical beam (12); Described signal bus (14) comprises capacitive transducer output signal line (18), MEMS IMU output signal line (19) and little chemical propeller ignition control signal line; Signal bus (14) is fixed on balance base for supporting (17) with card line seat (8), props up cutter (5) by balance and is connected to MEMS IMU (7) and little chemical propeller (10) and is fixed on vertical beam (12) with card line seat (8); With the part that crossbeam (2) is connected, the signal wire redundancy is arranged at vertical beam (12).
2. miniature solid chemical propeller thrust-measuring device as claimed in claim 1, it is characterized in that: described crossbeam (2) and vertical beam (12) material are that density is less than 400kg/m
3, thickness is less than the fiberboard of 5mm.
3. miniature solid chemical propeller thrust-measuring device as claimed in claim 1, it is characterized in that: described crossbeam (2) and vertical beam (12) material are scale board.
4. miniature solid chemical propeller thrust-measuring device as claimed in claim 1, it is characterized in that: described crossbeam (2) and vertical beam (12) material are the LDPE plastic plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201220542615.3U CN202974530U (en) | 2012-10-22 | 2012-10-22 | Micro solid chemical thruster thrust measuring device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201220542615.3U CN202974530U (en) | 2012-10-22 | 2012-10-22 | Micro solid chemical thruster thrust measuring device |
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| CN202974530U true CN202974530U (en) | 2013-06-05 |
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| CN201220542615.3U Expired - Fee Related CN202974530U (en) | 2012-10-22 | 2012-10-22 | Micro solid chemical thruster thrust measuring device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102937496A (en) * | 2012-10-22 | 2013-02-20 | 西北工业大学 | Thrust measuring device of mini-type solid chemical thruster |
| CN109827704A (en) * | 2019-02-28 | 2019-05-31 | 西北工业大学 | Minute yardstick pinking thrust-measuring device based on the method for dangling |
| CN109870260A (en) * | 2019-02-27 | 2019-06-11 | 北京航空航天大学 | A kind of method of on-line measurement MEMS solid micro-thruster array thrust output |
-
2012
- 2012-10-22 CN CN201220542615.3U patent/CN202974530U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102937496A (en) * | 2012-10-22 | 2013-02-20 | 西北工业大学 | Thrust measuring device of mini-type solid chemical thruster |
| CN109870260A (en) * | 2019-02-27 | 2019-06-11 | 北京航空航天大学 | A kind of method of on-line measurement MEMS solid micro-thruster array thrust output |
| CN109827704A (en) * | 2019-02-28 | 2019-05-31 | 西北工业大学 | Minute yardstick pinking thrust-measuring device based on the method for dangling |
| CN109827704B (en) * | 2019-02-28 | 2020-08-25 | 西北工业大学 | Microscale detonation thrust measuring device based on suspension oscillation method |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130605 Termination date: 20211022 |