阅读说明：本技术 微机械电场传感器测量航天器局部表面带电电压的方法 (The method of micromechanics electric-field sensor measurement spacecraft local surfaces electrified voltage ) 是由 李�昊 彭忠 刘庆海 彭毓川 李涛 徐焱林 王俊峰 郑慧奇 丁亮 唐振宇 葛丽丽 于 2019-08-14 设计创作，主要内容包括：本发明公开一种微机械电场传感器测量航天器局部结构表面带电电压的方法,包括建立描述航天器结构表面附近的电场强度与航天器结构表面带电电压之间的关系的电场模型；根据电场模型,选择电场强度与航天器带电电压关系最密切的位置作为测试点,固定设置微机械电场传感器；航天器在轨运行期间,微机械电场传感器测量测试点位置的电场强度,根据测试点的电场强度,按照电场模型描述的电场强度和带电电压之间的关系,确定航天器局部结构表面带电电压。本发明可获得航天器不同部位的结构表面带电电压数据,微机械传感器体积小、质量小、功耗低、抗冲击能力强,更符合航天设备对资源的限制和可靠性的要求。(A kind of method that the present invention discloses micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrified voltage, including the electric field model for the relationship established between the electric field strength and spacecraft structure surface electrified voltage near description spacecraft structure surface；According to electric field model, selects electric field strength and the most close position of spacecraft charging voltage relationship as test point, micromechanics electric-field sensor is fixedly installed；Period, micromechanics electric-field sensor measure the electric field strength of test point position to spacecraft in orbit, determine spacecraft partial structurtes surface electrified voltage according to the relationship between the electric field strength and electrified voltage of electric field model description according to the electric field strength of test point.The present invention can get the body structure surface electrified voltage data of spacecraft different parts, and micro mechanical sensor is small in size, quality is small, low in energy consumption, strong shock resistance, more meets space equipment to the limitation of resource and the requirement of reliability.)

1. the method for micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrified voltage, comprising the following steps:

The electric field near description spacecraft structure surface is established by theoretical calculation, Finite Element Numerical Simulation or experimental measurement method The electric field model of relationship between intensity and spacecraft structure surface electrified voltage；

According to electric field model, electric field strength and the most close position of spacecraft charging voltage relationship are selected, the position is being navigated Its device electrified voltage increases in maximum range from the minimum value of model value range, the electric field near spacecraft structure surface Electric field strength is monotonically changed and changes the maximum position of numerical value during intensity changes correspondingly, using selected position as test Micromechanics electric-field sensor is fixedly installed in point；

Spacecraft in orbit during, micromechanics electric-field sensor measure test point position electric field strength, according to test point Electric field strength determines spacecraft partial structurtes table according to the relationship between the electric field strength and electrified voltage of electric field model description Face electrified voltage.

2. the method for claim 1, wherein closing on area using micromechanics electric-field sensor measurement spacecraft structure surface The electric field strength of each measurement point in domain, according to the electric field strength and spacecraft structure of each measurement point of spacecraft structure surface close region Relationship between the electrified voltage of surface determines spacecraft partial structurtes surface electrified voltage, realizes to spacecraft partial structurtes table The measurement of face electrification.

3. the method for claim 1, wherein electric field model is numerical model, including data sheet form or curve image Form.

Technical field

The present invention relates to spacecraft secondary environment effect measurement technical fields, and in particular to a kind of spacecraft partial structurtes table The measurement method of face charged effect, more particularly to micromechanics electric-field sensor is used locally to tie as Sensitive Apparatus measurement spacecraft The method of structure surface electrified voltage.

Background technique

Spacecraft in orbit during, by the effect of the environment such as space plasma, high energy particle and solar radiation, space flight The accumulation of electrostatic charge and process of releasing, i.e. spacecraft surface charged effect occur for device body structure surface.Electrostatic caused by the effect is put Electrical phenomena safe operation in-orbit to spacecraft generates important threat: static discharge punctures spacecraft surfacing, solar battery array Etc. make its performance decline；The electromagnetic pulse interference that electric discharge generates makes sensitive electronic equipment on star, system maloperation or damage occur It is bad.According to incompletely statistics, at least existing 46 spacecraft on-orbit faults are identified as being due to spacecraft static discharge both at home and abroad Cause.Measurement spacecraft surface charged effect is prevention and the premise for eliminating the static discharge danger side of body, has the engineering significance of reality.

Method currently used for measuring spacecraft charging can be divided into contact measurement method and contactless measurement.It connects Tested electrical body is directly connected with measuring electrode by touch measurement method needs, and measurement result is vulnerable to output capacitance, the shadow of impedance It rings, measurement accuracy is low, and reading presses exponential damping at any time, may be only available for the electrostatic potential of measurement metallic object.When tested electrostatic When voltage exceeds measuring instrument maximum range, it is also possible to instrument with contacts be caused to damage.Contactless measurement is surveyed Amount electrode is not required to contact with electrical body, is not only capable of measuring the electrostatic potential of metallic object, is also capable of measuring insulator, conductor and semiconductor Electrostatic potential, and on measured body influence it is small.Therefore, the survey that contactless measurement carries out electrostatic potential is generallyd use at present Amount.

Non-contact measurement is divided into induction type and two kinds of capacitance-type vibration formula again.Induction type is i.e. using between probe and electrical body Capacitor directly incude, the induced current of generation is amplified and data processing.When using the measurement method, the palpus before detection Instrument being zeroed out far from electrical body, and with the variation of electric current in induction electrode in detecting, output result will level off to zero, It cannot achieve detection steady in a long-term.And this method actual measurement is the electrification of own material under vacuum conditions of popping one's head in, It not can accurately reflect the truth of satellite surface electrification, thus be not suitable for applied to the electrostatic potential measurement in space environment. External Electrostatic Potential Measure System mostly uses capacitance-type vibration formula, i.e., causes induction electrode and tested table using the method for mechanical oscillation Capacitance variations between face generate induced current, then the electrostatic potential by obtaining measured surface to faradic survey calculation. When using this method, without contacting with tested electrical body, functional reliability improves measuring instrument.But such detection method, excitation The driving voltage of vibration is applied on entire vibrating electrode, and additional induced current can be generated on induction electrode, influences measurement knot Fruit.In addition, this method is easy to be influenced by capacitance variations between detector and satellite structure, and vibration-type method structure Complexity, the room for improvement in terms of volume and weight is limited, and service life and performance are related to vibrating electrode material, can not be in space flight Popularization and application on device.

Summary of the invention

Based on the above issues, present invention proposition uses micromechanics electric-field sensor as Sensitive Apparatus, realizes to spacecraft The measurement of partial structurtes surface charged effect voltage.

Object of the present invention is to what is be achieved through the following technical solutions:

The method of micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrified voltage, comprising the following steps:

It is established near description spacecraft structure surface by theoretical calculation, Finite Element Numerical Simulation or experimental measurement method The electric field model of relationship between electric field strength and spacecraft structure surface electrified voltage；

According to electric field model, electric field strength and the most close position of spacecraft charging voltage relationship are selected, the position is Increase in maximum range in spacecraft charging voltage from the minimum value of model value range, near spacecraft structure surface Electric field strength is monotonically changed and the variation maximum position of numerical value during electric field strength changes correspondingly, using selected position as Micromechanics electric-field sensor is fixedly installed in test point；

Spacecraft in orbit during, micromechanics electric-field sensor measure test point position electric field strength, according to test The electric field strength of point determines that spacecraft is locally tied according to the relationship between the electric field strength and electrified voltage of electric field model description Structure surface electrified voltage.

Further, the electric field of micromechanics electric-field sensor measurement each measurement point of spacecraft structure surface close region is utilized Intensity, according between the electric field strength and spacecraft structure surface electrified voltage of each measurement point of spacecraft structure surface close region Relationship, determine spacecraft partial structurtes surface electrified voltage, realize the measurement charged to spacecraft partial structurtes surface.

Wherein, electric field model is numerical model, including data sheet form or curve image form.

Present invention uses the electric fields of micromechanics electric-field sensor measurement spacecraft structure surface close region, determine space flight General ability portion body structure surface electrified voltage avoids interference and the reference point of potential of probe material itself electrification of inductive measuring method The interference of voltage change, the spatial resolution of electric field measurement is high, and convenient for the realization multimetering of multiple sensors, thus can be with Obtain the body structure surface electrified voltage data of spacecraft different parts.Micro mechanical sensor is small in size, quality is small, low in energy consumption, anti- Impact capacity is strong, more meets space equipment to the limitation of resource and the requirement of reliability.

Detailed description of the invention:

Fig. 1 is the survey of the method for micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrified voltage of the invention Measure principal diagram.

In figure, 1- is located at the micromechanics electric-field sensor of test point；2- spacecraft；Electric field model around 3- spacecraft.

Fig. 2 be micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrified voltage of the invention method in pass The Local map of sensor.

In figure, 1- micromechanics electric-field sensor；4- spacecraft structure；The electric field of 5- spacecraft structure surface close region.

Fig. 3 is the reality of the method for micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrified voltage of the invention Apply flow chart.

Fig. 4 is that the method for micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrified voltage of the invention is implemented The flow chart of example.

Specific embodiment

Spacecraft partial structurtes surface electrified voltage is measured to micromechanics electric-field sensor of the invention referring to the drawings Method be described in detail, but this describe it is merely illustrative, it is no intended to any limit is carried out to protection scope of the present invention System.

Show it is micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrification of the invention referring to Fig. 1, Fig. 1 The measuring principle of the method for voltage illustrates.Micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrification electricity of the invention The method of pressure, including two parts, as shown in fig. 1, comprising: 1 is micromechanics electric-field sensor；3 be spacecraft structure surface Neighbouring electric field model.Electric field model 3 near spacecraft structure surface, can be by theoretical calculation, Finite Element Numerical Simulation or reality The methods of test amount is established, for describing electric field strength and spacecraft structure surface electrified voltage near spacecraft structure surface Relationship.According to electric field model 3, electric field strength and the most close position of spacecraft charging voltage relationship are selected, as test point. In selected test point, micromechanics electric-field sensor 1 is fixedly mounted.Spacecraft in orbit during, micromechanics electric field sensing The electric field strength of the measurement of device 1 test point position.According to the electric field strength of test point, the electric field strength described according to electric field model 3 Relationship between electrified voltage, it may be determined that spacecraft partial structurtes surface electrified voltage.

Sensor Local map shown in Fig. 2, description should with the micromechanics electric-field sensor measurement for being fixed on spacecraft surface The situation of point internal field.After the electrification of 4 surface of spacecraft structure, electric field 5 is generated in its surface close region.With micromechanics electric field Sensor 1 measures the test point electric field strength of spacecraft structure surface close region, can be according to test point electric field strength, electric field The relationship between electric field strength and electrified voltage that model 3 describes, determines spacecraft partial structurtes surface electrified voltage.

The implementation stream of the method for micromechanics electric-field sensor measurement spacecraft partial structurtes surface electrified voltage of the invention Journey such as Fig. 3.In the spacecraft development stage, according to the planform of spacecraft and material etc., using theoretical calculation, numerical simulation or The electric field strength and spacecraft partial structurtes surface band of description spacecraft structure surface close region are established in the methods of experiment measurement The model of relationship between piezoelectric voltage.According to model, electric field strength and the most close position of spacecraft surface electrified voltage relationship are selected It sets, as test point.Micromechanics electric-field sensor is fixedly mounted in test point.

Spacecraft in orbit during, with micromechanics electric-field sensor, measure the electric field strength of test point position.According to survey The electric field strength of pilot is locally tied according to the electric field strength and spacecraft of spacecraft structure surface close region electric field model description Relationship between the electrified voltage of structure surface can get the voltage of spacecraft partial structurtes surface charged effect.