CN218806628U - Structure of air conditioning track maneuvering system suitable for microsatellite - Google Patents

Abstract

The utility model discloses a structure of air conditioning track mobile system suitable for microsatellite, a liquid ammonia chamber side end fixedly connected with is used for the vaporization chamber of liquid ammonia vaporization, the limit end of vaporization chamber is connected with metal collapsible tube, the utility model discloses an annular vaporization chamber structure can be fine utilize the corner space of liquid ammonia chamber sphere position, and on the basis that does not increase radial dimension, the envelope of minimize axial space uses withstand voltage metal collapsible tube to carry out the connection of thruster and vaporization chamber simultaneously, use the basin overall arrangement that can be very nimble to be in the star with the pot overall arrangement, improved the flexibility of overall arrangement, reduce the restraint to the overall arrangement, can adapt to complicated overall arrangement of buckling, used integral type thrust subassembly, integrated near the pressure biography of having integrated near the thruster, near monitoring thruster export that can be better to thruster subassembly and metal collapsible tube's installation angle is adjustable, can accomplish a structure and be suitable for multiple satellite overall arrangement.

Description

Structure of air conditioning track maneuvering system suitable for microsatellite

Technical Field

The utility model relates to an air conditioning track mobile system technical field specifically is a structure of air conditioning track mobile system suitable for microsatellite.

Background

The orbital maneuver system is an important execution component for controlling the satellite orbit, and the orbital maneuver is mainly a process of actively changing the number of orbits by a spacecraft, is divided into orbital plane maneuver and orbital plane out-of-plane maneuver and mainly has the main functions of orbit keeping, orbit transferring and orbit intersection;

and present common air conditioning track mobile device is that two ellipsoid cavitys are directly connected or the form of piling up is constituteed, the corner space of cavity can not be fully utilized to this kind of form, can occupy more under-deck space, use rigid conduit to connect between current thruster and the cavity simultaneously, this kind of form can increase a lot of difficulties to product delivery and assembly, and every set of product all need redesign processing, pressure passes to near vaporization chamber cavity, the pressure that detects thruster exit position that can not be fine to the system that the pipeline is slightly long.

SUMMERY OF THE UTILITY MODEL

The utility model provides a structure of air conditioning track mobile system suitable for microsatellite, can effectively solve and propose among the above-mentioned background art that present common air conditioning track mobile device is that two ellipsoid cavitys directly link or the form that piles up is constituteed, the corner space of the utilization cavity that this kind of form can not be abundant, can occupy more under-deck space, use the rigidity pipe to be connected between current thrustor and the cavity simultaneously, this kind of form can increase a lot of difficulties to product delivery and assembly, and each set of product all need redesign processing, pressure passes to near vaporization chamber cavity, the problem of the pressure that detects thrustor exit position that can not be fine to the system that the pipeline is long slightly comes.

In order to achieve the above object, the utility model provides a following technical scheme: a structure of a cold air rail mobile system suitable for a microsatellite comprises a liquid ammonia cavity, wherein a vaporization cavity for vaporizing liquid ammonia is fixedly connected to the end part of one side of the liquid ammonia cavity, a control plate is fixedly installed at the side position of the liquid ammonia cavity, and the side end of the vaporization cavity is connected with a metal hose;

the device comprises a vaporization cavity, a clamp, a liquid ammonia cavity pressure sensor, a filling valve, a liquid ammonia cavity pressure sensor and a control valve, wherein the clamp is sleeved on the outer side edge of the vaporization cavity at an equal angle, the inner side of the clamp and the outer side of the vaporization cavity are separated by a mica sheet, the solenoid valve is fixedly installed at the position, located at the edge end of the liquid ammonia cavity, of the inner side of the vaporization cavity, the liquid ammonia cavity pressure sensor is installed at the center of the inner side of the vaporization cavity, and the filling valve is connected to one side of the liquid ammonia cavity pressure sensor;

the two ends of the metal hose are connected with connectors, the two ends of the metal hose are connected with the vaporization cavity and the vaporization cavity pressure sensor through the connectors respectively, one end of the vaporization cavity pressure sensor is connected with a thruster support, and the center position of one side of the thruster support is connected with a thruster.

Preferably, the side in liquid ammonia chamber is provided with the mounting bracket, the equal fixed mounting in each corner position of control panel is in the inboard of mounting bracket.

Preferably, the liquid ammonia chamber is used for storing liquid ammonia, uses cylinder section to add the hemisphere structure, can increase the volume through extension cylinder section length, the vaporization chamber uses the ring shape structure, utilizes the space of liquid ammonia chamber hemisphere off-plate to install.

Preferably, the vaporization chamber mainly heats through the vaporization chamber heating plate, and the vaporization chamber heating plate is provided with two, and two vaporization chamber heating plates all closely twine the vaporization chamber round, and the vaporization chamber heating plate mainly provides the heat of vaporization for liquid ammonia vaporization.

Preferably, both sides of the vaporization chamber are connected with the vaporization chamber thermistors, and the two vaporization chamber thermistors are symmetrically arranged and are mainly used for collecting temperature data of the vaporization chamber.

Preferably, the metal hose is used for connecting the vaporization chamber and the thruster, the metal hose is mainly heated by arranging a metal hose heating sheet on the outer side of the metal hose, and the metal hose heating sheet is used for providing vaporization heat for vaporizing the liquid ammonia.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model has the advantages of being scientific and reasonable in structure, convenience safe in utilization:

the annular vaporization cavity structure used by the invention can well utilize the corner space of the spherical surface position of the liquid ammonia cavity, and reduce the envelope of the axial space as much as possible on the basis of not increasing the radial dimension, and simultaneously, the pressure-resistant metal hose is used for connecting the thruster and the vaporization cavity, the metal hose can be used for flexibly arranging the storage tank in a satellite, thereby improving the flexibility of the arrangement, reducing the restriction on the arrangement, being suitable for complex bending arrangement, using an integrated thrust assembly, integrating pressure transmission near the thruster, better monitoring the pressure near the outlet of the thruster, and adjusting the installation angle of the thruster assembly and the metal hose, so that one structure is suitable for various satellite arrangements, innovatively integrating the thruster and the pressure sensor on one assembly, reducing the volume, accurately measuring the pressure near the thruster, ensuring the stability of the pressure, and conveniently installing the thruster assembly on a satellite board.

Drawings

The accompanying drawings are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and together with the description serve to explain the invention and not to limit the invention.

In the drawings:

FIG. 1 is a schematic view of the present invention;

fig. 2 is a schematic view of the installation structure of the vaporization chamber of the present invention;

FIG. 3 is a schematic structural view of the mica sheet of the present invention;

fig. 4 is a schematic view of the mounting structure of the thruster of the present invention;

reference numbers in the figures: 1. a liquid ammonia chamber; 2. a vaporization chamber; 3. a control panel; 4. a metal hose; 5. clamping a hoop; 6. mica sheets; 7. an electromagnetic valve; 8. a liquid ammonia cavity pressure sensor; 9. a filling valve; 10. a connector; 11. a vaporization chamber pressure sensor; 12. a thruster support; 13. a thruster.

Detailed Description

The preferred embodiments of the present invention will be described hereinafter with reference to the accompanying drawings, and it should be understood that the preferred embodiments described herein are merely for purposes of illustration and explanation, and are not intended to limit the present invention.

Example (b): as shown in fig. 1-4, the utility model provides a technical scheme, a structure of air conditioning track mobile system suitable for microsatellite, including liquid ammonia chamber 1, liquid ammonia chamber 1 one side tip fixedly connected with is used for vaporization chamber 2 of liquid ammonia vaporization, vaporization chamber 2 mainly heats through vaporization chamber heating plate, vaporization chamber heating plate is provided with two, two vaporization chamber heating plates all closely twine vaporization chamber 2 round, and vaporization chamber heating plate mainly provides the vaporization heat for liquid ammonia vaporization, liquid ammonia chamber 1 is used for storing liquid ammonia, use cylinder section plus hemisphere face structure, can increase the volume through lengthening cylinder section length, vaporization chamber 2 uses ring shape structure, utilize the space outside the hemisphere face of liquid ammonia chamber 1 to install, on the basis that does not increase radial dimension, minimize the envelope of axial space, liquid ammonia chamber 1's side position fixed mounting has control panel 3, liquid ammonia chamber 1's side is provided with the side, each corner position of control panel 3 all fixed mounting in the inboard of mounting bracket, conveniently carry out firm installation with control panel 3, guarantee its stability of working process, the end of vaporization chamber 2 is connected with metal collapsible tube 4;

the clamp 5 is sleeved on the outer side edge of the vaporization chamber 2 at an equal angle, the position between the inner side of the clamp 5 and the outer side of the vaporization chamber 2 is separated by a mica sheet 6, heat exchange between the vaporization chamber 2 and the liquid ammonia chamber 1 can be reduced by the mica sheet 6, an electromagnetic valve 7 is fixedly installed at the position of the inner side of the vaporization chamber 2, which is positioned at the edge end of the liquid ammonia chamber 1, vaporization chamber thermistors are connected to two sides of the vaporization chamber 2, the two vaporization chamber thermistors are symmetrically installed and are mainly used for collecting temperature data of the vaporization chamber 2 to accurately measure the temperature condition of the vaporization chamber 2, a liquid ammonia chamber pressure sensor 8 is installed at the center position of the inner side of the vaporization chamber 2, and a filling valve 9 is connected to one side of the liquid ammonia chamber pressure sensor 8;

the two ends of the metal hose 4 are connected with connectors 10, the two ends of the metal hose 4 are connected with the vaporization cavity 2 and the vaporization cavity pressure sensor 11 through the connectors 10 respectively, the vaporization cavity pressure sensor 11 is used for measuring pressure data of the vaporization cavity 2, one end of the vaporization cavity pressure sensor 11 is connected with a thruster support 12, a thruster 13 is connected to the center of one side of the thruster support 12, the metal hose 4 is used for connecting the vaporization cavity 2 and the thruster 13, the storage tank can be flexibly arranged in a star by using the metal hose 4, constraint on arrangement is reduced, the metal hose 4 is mainly heated by arranging a metal hose heating sheet on the outer side of the metal hose 4, and vaporization heat is provided for liquid ammonia vaporization by using the metal hose heating sheet.

The utility model discloses a theory of operation and use flow: the structure of the air conditioning orbit maneuvering system suitable for the microsatellite is in the practical specific application process, the liquid ammonia cavity 1 is mainly used for storing liquid ammonia, the liquid ammonia cavity 1 adopts a cylindrical section and hemispherical surface structure, the volume can be increased by lengthening the length of the cylindrical section under different volume requirements, the expansion is flexible, working media can be contained in a smaller volume as much as possible, the vaporization cavity 2 is used for vaporizing the liquid ammonia, a circular structure is used, the space outside the hemispherical surface of the liquid ammonia cavity 1 is fully utilized, the envelope of the axial space is reduced as much as possible on the basis of not increasing the radial dimension, a hoop 5 and a mica sheet 6 are used between the vaporization cavity 2 and the liquid ammonia cavity 1 for heat insulation installation, the heat exchange between the vaporization cavity 2 and the liquid ammonia cavity 1 is reduced, and a vaporization cavity heating sheet is wound outside the vaporization cavity 2, so as to provide vaporization heat for the vaporization process of the liquid ammonia;

secondly, a liquid ammonia cavity pressure sensor 8 is used for collecting pressure data of a liquid ammonia cavity 1, is positioned at the circle center position of a vaporization cavity 2, fully utilizes the circular inner space of the vaporization cavity 2, a solenoid valve 7 is used for controlling liquid ammonia entering the vaporization cavity 2 from the liquid ammonia cavity 1, the solenoid valve 7 is also positioned inside the circular vaporization cavity 2, can fully utilize the vacant space, and is used for collecting temperature data of the vaporization cavity 2, and the two vaporization cavity thermistors are respectively arranged at two symmetrical positions to measure the temperature condition of the vaporization cavity 2 as accurately as possible;

when the vaporization chamber 2 needs to be heated, the vaporization chamber 2 is mainly heated through the vaporization chamber heating sheet to provide vaporization heat for vaporizing liquid ammonia, and the vaporization chamber heating sheet is wound around the vaporization chamber 2 for one circle and is in full contact with the vaporization chamber 2;

in the normal vaporization process of the vaporization chamber 2, the pressure sensor 11 of the vaporization chamber is used for measuring the pressure data of the vaporization chamber 2, the thruster 13 is used for controlling ammonia gas to enter the space, and after the thruster 13 is opened, the ammonia gas is sprayed out from the thruster 13 to form thrust;

when the metal hose 4 needs to be heated, the metal hose heating sheet is arranged on the outer side of the metal hose to heat the metal hose, and the metal hose heating sheet is used for providing vaporization heat for vaporizing the liquid ammonia.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (6)

1. The utility model provides a structure of cold air orbit maneuvering system suitable for microsatellite, includes liquid ammonia chamber (1), its characterized in that: a vaporization chamber (2) for vaporizing liquid ammonia is fixedly connected to the end part of one side of the liquid ammonia chamber (1), a control panel (3) is fixedly installed at the side edge position of the liquid ammonia chamber (1), and a metal hose (4) is connected to the side end of the vaporization chamber (2);

the device is characterized in that a hoop (5) is sleeved on the outer side edge of the vaporization cavity (2) at an equal angle, the position between the inner side of the hoop (5) and the outer side of the vaporization cavity (2) is separated through a mica sheet (6), an electromagnetic valve (7) is fixedly installed at the position, located at the edge end of the liquid ammonia cavity (1), of the inner side of the vaporization cavity (2), a liquid ammonia cavity pressure sensor (8) is installed at the center position of the inner side of the vaporization cavity (2), and one side of the liquid ammonia cavity pressure sensor (8) is connected with a filling valve (9);

both ends of metal collapsible tube (4) all are connected with connector (10), and the both ends of metal collapsible tube (4) link to each other with vaporization chamber (2) and vaporization chamber pressure sensor (11) through connector (10) respectively, vaporization chamber pressure sensor (11) one end is connected with thruster support (12), and one side central point of thruster support (12) puts and is connected with thruster (13).

2. A structure of a cold air rail maneuvering system for a microsatellite according to claim 1, characterized in that: the side in liquid ammonia chamber (1) is provided with the mounting bracket, the equal fixed mounting in the inboard of mounting bracket in each corner position of control panel (3).

3. A structure of a cold air rail maneuvering system for a microsatellite according to claim 1, characterized in that: liquid ammonia chamber (1) is used for storing liquid ammonia, uses the cylinder section to add the hemisphere face structure, can increase the volume through extension cylinder section length, annular structure is used in vaporization chamber (2), utilizes liquid ammonia chamber (1) hemisphere off-plate space to install.

4. A structure of a cold air orbit maneuvering system for micro-satellites as recited in claim 1, characterized in that: vaporization chamber (2) mainly heat through vaporization chamber heating plate, and vaporization chamber heating plate is provided with two, and two vaporization chamber heating plates are all closely twined vaporization chamber (2) round, and vaporization chamber heating plate mainly provides the heat of vaporization for the liquid ammonia vaporization.

5. A structure of a cold air rail maneuvering system for a microsatellite according to claim 1, characterized in that: vaporization cavity thermistors are connected to two sides of the vaporization cavity (2) and are symmetrically arranged for collecting temperature data of the vaporization cavity.

6. A structure of a cold air orbit maneuvering system for micro-satellites as recited in claim 1, characterized in that: the metal hose (4) is used for connecting the vaporization cavity (2) and the thruster (13), the metal hose (4) is mainly heated by arranging a metal hose heating sheet on the outer side of the metal hose, and the metal hose heating sheet is used for providing vaporization heat for vaporizing liquid ammonia.

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