CN102322952A - Movable mirror locking device of space infrared Fourier transform spectrum detecting instrument - Google Patents

Abstract

The invention discloses a movable mirror locking device of a space infrared Fourier transform spectrum detecting instrument, which comprises corrugated tube type pneumatic elements, pneumatic pins, gas tubes, an gas holder, a pressure sensor, electromagnetic valves, a three-way joint and a gas releasing head. The locking device performs the function of locking and unlocking a movable mirror. When high-pressure gas is inflated into the locking device, the pneumatic pins extend out and a movable mirror moving frame is locked; and when the inflated high-pressure gas is discharged, the movable mirror moving frame is unlocked.

Description

Moving mirror locking device for space infrared Fourier transform spectrometer

technical field

The invention relates to space photoelectric instrument technology, specifically a moving mirror locking device, which is applied to a space infrared Fourier transform spectrum detector, which is used for satellite atmospheric remote sensing detection.

Background technique

For satellite atmospheric remote sensing detectors, the traditional ones are filter-type detectors, which have been gradually replaced by space infrared Fourier transform spectroscopic detectors in the polar orbit of the earth. For example, IASI in Europe and CrIS in the United States are both Fourier transform spectroscopic detectors. In the geostationary orbit, GOES-I to GOES-N in the United States are filter-type, but they will also be replaced by a new generation of Fourier transform spectroscopic detectors, such as the MTG in Europe. Fourier transform spectrometers are characterized by a much higher spectral resolution. This infrared Fourier transform spectrometer has a moving mirror as a modulating component of the optical path difference. Due to the high precision of the moving parts of the moving mirror, this part needs to be locked during launch and transportation.

At present, the locking devices for moving parts on satellites usually include explosive bolts, electromagnetic locks and memory metals. Explosive bolts contain explosives in the bolts. After the satellite is launched, the explosives in the bolts will be detonated when needed to break the bolts and release the lock. Single use. This type of lock is not suitable for locking inside the instrument, explosives can contaminate the inside of the instrument. Electromagnetic locking is to use electromagnet to attract or equivalently attract the locked object, and unlocking is completed by cutting off the power supply. Electromagnetic locking is reusable. If a larger locking stroke and locking force are required, the volumetric weight of the electromagnet increases rapidly. The locking of the moving mirror, which is a precision moving part of the spectrometer, is not very suitable. The precision part of the moving mirror is like a finely calibrated pendulum. The locking requirement for it is that it can only limit its multiple degrees of freedom, and cannot exert locking force on it. The memory metal method is to lock the moving parts by heating special metals to generate thermal deformation. IASI is using this locking method. At present, there is no memory metal with such a large stroke and high thrust in China. The locking device provided by this patent is a locking method based on yet another principle. It uses gas pressure to push the elastic element so that the column pin is inserted into the locking hole to limit the position of the movable mirror frame, so as to achieve the purpose of locking.

Contents of the invention

The object of the present invention is to provide a moving mirror locking device for a space infrared Fourier transform spectrum detector.

Technical scheme of the present invention is as follows:

The locking device scheme is shown in Figure 1: it consists of a bellows type pneumatic element 1, a pneumatic pin 2, an air pipe 3, an air reservoir 4, a pressure sensor 5, a solenoid valve 6, a three-way joint 7, an air pipe 8, Pipeline support 9, fixed flange 10, deflation head 11. The locking device has the functions of locking and unlocking the moving mirror. In the locking device, when the high-pressure gas is charged, the pneumatic pin 2 is stretched out, inserted into the hole of the locked part (see Figure 2), and locked by the locked part. The bottom of the pneumatic pin 2 is relatively large, and when the pin is pushed out to a certain stroke, the bottom is seated on the fixed frame. Through precise design and manufacture, the head of the pin is just matched with the locking hole. The thrust of the gas is borne by the fixed frame, and only acts as a limit to the moving mirror moving frame. Four locking holes are designed at different positions on the moving mirror frame. In this way, the locking device can constrain all degrees of freedom of the moving mirror moving frame. When the charged high-pressure gas is released, the locked part is unlocked.

The process of locking the moving mirror of the instrument is to unscrew the venting head 11 to expose the head of the vent pipe, connect the high-pressure gas source, power on the solenoid valve, and the high-pressure gas passes through the vent pipe 8, tee joint 7, solenoid valve 6, and gas storage cylinder 4 . The air pipe 3 reaches the pneumatic element 1. Under the action of the gas pressure, the pneumatic pin protrudes outward and is inserted into the locking hole of the moving mirror moving frame to lock the moving mirror moving frame. After the locking is completed, remove the solenoid valve first. current, the solenoid valve is closed, and then the high-pressure gas source is removed, and then the air release head 11 is screwed on. The pressure sensor 5 is used to monitor the gas pressure; the process of unlocking the moving mirror of the instrument is to power on the solenoid valve again, the solenoid valve is opened, and the high-pressure gas The pressure in the pneumatic element 1 is released through the solenoid valve 6, the three-way joint 7, the vent pipe 8, and the deflation head 11, the pneumatic pin is retracted, and the moving mirror frame is unlocked.

When the deflation head 11 deflates, it deflates symmetrically around the circle, thereby avoiding additional reaction force and affecting the attitude of the satellite.

The advantages of the present invention are:

The locking device adopts a pneumatic locking method. 1) The pneumatic components of the locking actuator of this locking device are small in size and light in weight, and can be used in places where the space around the locked object is small and light weight is required, and multiple ones can be installed at the same time, which is very suitable for space applications; 2) This locking When the device is locked, no locking force is applied to the locked object, and it only acts as a position constraint, which is very suitable for the locking of precision moving parts; 3) This locking device uses two solenoid valves in combination, which doubles the reliability of unlocking, which is very important for space. The locking mechanism used is very important; 4) This locking device uses an air storage tank to solve the slow air leakage of the system, and installs a pressure sensor to monitor the pressure, so that it can ensure that the locking system is at the required air pressure in a certain period of time. Timely detection and replenishment. This does not affect the use of space instruments, because locking the moving parts of instruments is generally required during launch.

Description of drawings

Figure 1: The locking device of the space infrared Fourier spectroscopy detector;

In the picture:

1- Pneumatic components;

2- Pneumatic pin;

3 - trachea;

4-air tank;

5 - pressure sensor;

6- Solenoid valve;

7-Tee joint;

8 - snorkel;

9-pipe support;

10 - fixed flange;

11-Deflation head.

Figure 2: Locking principle of moving mirror moving frame.

Detailed ways

The structural example of the present invention is shown in Fig. 1, and it is used for the locking of moving mirror of space Fourier transform spectrometer. The main parameters are: pneumatic component 1 direct 21mm, length 24mm, pneumatic pin 2 stroke 4mm, inflation pressure 6kg/cm ² . Share 4 pneumatic components, and share an air reservoir 4, the diameter of the air reservoir part is 52mm, and the height is 66mm. Each pneumatic element is communicated with the air reservoir through the air pipe 3 . The pressure of the gas storage tank is sensed by the sensor 5, and the pressure signal is sent to the satellite for monitoring. The inflation and deflation of the air reservoir is carried out by two electromagnetic valves 6 and a vent pipe 8 (3mm inner diameter). The control voltage of the solenoid valve is 24V, and the power is 2W. Inflate the air reservoir, and the pneumatic pin is extended to achieve locking. Deflate the air reservoir to unlock it. When it is necessary to inflate, unscrew the deflation head 11, connect the high-pressure air source, energize the solenoid valve 6 to open the solenoid valve, and carry out inflation, wait for 20 seconds, remove the control voltage of the solenoid valve, and the inflation is completed. Remove the high-pressure air source and screw on the air release head. When it is necessary to deflate, connect the 24V voltage of the solenoid valve for half a minute, and the high-pressure gas in the gas storage tank will be released through the solenoid valve, the ventilation pipe and the deflation head. Use two solenoid valves in parallel to increase reliability.

Claims (2)

1. A space infrared Fourier transform spectrum detector moving mirror locking device, it consists of a bellows type pneumatic element (1), a pneumatic pin (2), a trachea (3), an air reservoir (4), a pressure sensor ( 5), solenoid valve (6), three-way joint (7), vent pipe (8), pipeline bracket (9), fixed flange (10), and air release head (11), characterized in that: the instrument dynamic The mirror locking process is to unscrew the venting head (11), expose the head of the vent pipe, connect the high-pressure gas source, power on the solenoid valve, and the high-pressure gas passes through the vent pipe (8), tee joint (7), solenoid valve ( 6) The air storage tank (4) and the air pipe (3) reach the pneumatic element (1). Under the action of the gas pressure, the pneumatic pins protrude outwards and are inserted into the locking holes of the moving mirror moving frame to move the moving mirror. After the locking is completed, first remove the current of the solenoid valve, the solenoid valve is closed, then remove the high-pressure gas source, and then screw on the air release head (11). The pressure sensor (5) is used to monitor the gas pressure; the moving mirror of the instrument The unlocking process is to power on the solenoid valve again, the solenoid valve is opened, and the high-pressure gas is released through the solenoid valve (6), tee joint (7), vent pipe (8), and deflation head (11), and the pneumatic element (1) The pressure in the cylinder is released, the pneumatic pin is retracted, and the moving mirror movement frame is unlocked. 2. The moving mirror locking device of the space infrared Fourier transform spectrometer according to claim 1, characterized in that: said deflation head (11) deflates symmetrically around the circle, thereby avoiding additional The reaction force affects the attitude of the satellite.

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