CN114229040A - Separable independent propulsion cabin system - Google Patents
Separable independent propulsion cabin system Download PDFInfo
- Publication number
- CN114229040A CN114229040A CN202111552076.1A CN202111552076A CN114229040A CN 114229040 A CN114229040 A CN 114229040A CN 202111552076 A CN202111552076 A CN 202111552076A CN 114229040 A CN114229040 A CN 114229040A
- Authority
- CN
- China
- Prior art keywords
- independent propulsion
- propulsion cabin
- independent
- cabin
- propulsion
- 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.)
- Pending
Links
- 238000003860 storage Methods 0.000 claims abstract description 70
- 238000002485 combustion reaction Methods 0.000 claims abstract description 40
- 239000007800 oxidant agent Substances 0.000 claims abstract description 28
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 27
- 230000001590 oxidative effect Effects 0.000 claims abstract description 21
- 239000001307 helium Substances 0.000 claims abstract description 17
- 229910052734 helium Inorganic materials 0.000 claims abstract description 17
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims abstract description 17
- 238000000926 separation method Methods 0.000 claims abstract description 17
- 239000003380 propellant Substances 0.000 claims description 20
- 230000007246 mechanism Effects 0.000 claims description 18
- 239000000126 substance Substances 0.000 claims description 18
- 238000012546 transfer Methods 0.000 claims description 12
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 10
- 238000002161 passivation Methods 0.000 claims description 10
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 claims description 6
- 229910001257 Nb alloy Inorganic materials 0.000 claims description 3
- 239000000654 additive Substances 0.000 claims description 3
- 230000000996 additive effect Effects 0.000 claims description 3
- 230000003064 anti-oxidating effect Effects 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 238000004146 energy storage Methods 0.000 claims description 3
- 239000000446 fuel Substances 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 claims description 3
- 238000005096 rolling process Methods 0.000 claims description 3
- 229910021332 silicide Inorganic materials 0.000 claims description 3
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 7
- 230000008901 benefit Effects 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 7
- 230000001360 synchronised effect Effects 0.000 description 6
- 238000005474 detonation Methods 0.000 description 5
- 230000000977 initiatory effect Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000005259 measurement Methods 0.000 description 4
- 101100534162 Arabidopsis thaliana SPS3 gene Proteins 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000002360 explosive Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000011049 filling Methods 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 241001330002 Bambuseae Species 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 101000606504 Drosophila melanogaster Tyrosine-protein kinase-like otk Proteins 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 108010066057 cabin-1 Proteins 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention discloses a separable independent propulsion pod system, comprising: the system comprises an independent propulsion cabin structure, a combustion agent storage box, an oxidant storage box, an independent propulsion cabin storage battery, an N thruster, a Beidou short message terminal, an N engine, an integrated sun sensor, an independent propulsion cabin control unit and a helium tank; wherein, the combustion agent storage tank, the oxidant storage tank and the helium tank are arranged on the side wall of the independent propulsion cabin structure; the independent propulsion cabin storage battery is connected with the independent propulsion cabin structure; the N thruster is connected with the independent propulsion cabin structure through a bracket; the Beidou short message terminal is connected with the independent propulsion cabin structure; the N engine is arranged at the bottom of the independent propulsion cabin structure; the integrated sun sensor is structurally connected with the independent propulsion cabin; the independent propulsion cabin control unit is connected with the independent propulsion cabin structure through screws. The invention realizes the separation design of the high-orbit satellite platform propulsion system and has obvious advantages of improving the satellite bearing capacity and prolonging the service life of the satellite in orbit.
Description
Technical Field
The invention belongs to the technical field of early-stage orbit lifting tasks of satellite transfer orbit segments, and particularly relates to a separable independent propulsion cabin system.
Background
At present, a domestic high-orbit satellite platform is generally provided with a two-component propulsion cabin which is integrally designed with other subsystems of the platform. The dry weight of the chemical propulsion subsystem in this configuration and the dry weight of the platform such as the structure due to the change in the configuration of the satellites caused by the configuration of the chemical propulsion subsystem, are increased by about 30% of the dry weight of the satellite platform. Because the 490N engine and the high-pressure gas circuit part for transferring orbit orbital transfer are only used for transferring orbit lifting after the separation of the satellite and the arrow in the early stage, the part of the chemical propulsion system becomes a stiff system during the subsequent satellite synchronous orbit task, and is a key factor for restricting the satellite from further improving the bearing ratio.
The high orbit satellite two-component chemical propulsion subsystem needs to complete the task requirements of satellite orbit maneuvering, synchronous orbit fixed-point capturing, position maintaining, attitude control and adjustment of each stage, and has the following basic functions: a) helium storage function. b) Helium depressurisation supply function. c) Propellant storage function. d) The propellant manages the dispensing function. e)490N transition engine ignition function. f) And (5) controlling the 10N attitude control thruster. h) And (4) performing electronic circuit control functions of the propulsion subsystem. During the orbital transfer maneuver of the satellite between the transfer orbit and the middle orbit (from the connection of the air path system to the disconnection of the air path system), the system is in an extrusion type constant-pressure working mode, and gas required by the pressure maintenance of the storage tank is provided by a high-pressure helium bottle. After the gas circuit is cut off, the propulsion system is in a pressure-drop type working mode during the whole working period until the service life of the satellite is finished, and all or part of the functions of b), d), e), h) and the like are lost due to the change of the working mode of the system in the following whole service life period of the synchronous orbit (generally 15 years), so that the functional module matched with the system is also dead.
The two-component propulsion cabin integrally designed with other subsystems of the platform mainly has the following 3 problems: 1. after the propulsion system is converted into a pressure-drop working mode, a 490N engine and a high-pressure gas circuit part for transferring orbit orbital transfer become a stiff system, propellant consumption for maintaining the orbit is greatly wasted, and the service life of the satellite synchronous orbit is seriously influenced; 2. the integrated propulsion cabin and other subsystems of the platform are uniformly distributed, the layout of the propulsion module or the pipeline is limited by the layout positions of various devices, and the layout design of the shortest path cannot be carried out; 3. the size of the satellite body cannot be further reduced due to the constraint of the layout space of the integrated propulsion cabin.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the separable independent propulsion cabin system is provided, the separation design of the propulsion system of the high-orbit satellite platform is realized, and the system has remarkable advantages of improving the satellite bearing capacity and prolonging the in-orbit service life of the satellite.
The purpose of the invention is realized by the following technical scheme: a detachable self-contained propulsion pod system, comprising: the system comprises an independent propulsion cabin structure, a combustion agent storage box, an oxidant storage box, an independent propulsion cabin storage battery, a 10N thruster, a Beidou short message terminal, a 490N engine, an integrated sun sensor, an independent propulsion cabin control unit and a helium tank; wherein the combustion agent storage tank is disposed on a sidewall of the independent propulsion pod structure; the oxidant storage tank is arranged on the side wall of the independent propulsion cabin structure; wherein the oxidant reservoir is opposite the combustion agent reservoir; the independent propulsion cabin storage battery is connected with the independent propulsion cabin structure; the 10N thruster is connected with the independent propulsion cabin structure through a support; the Beidou short message terminal is connected with the independent propulsion cabin structure through a screw; the 490N engine is arranged at the bottom of the independent propulsion cabin structure; the integrated sun sensor is connected with the independent propulsion cabin structure through the space sensitive support; the independent propulsion cabin control unit is connected with the independent propulsion cabin structure through screws; the helium bottle is arranged on the side wall of the independent propulsion cabin structure.
In the separable independent propulsion cabin system, the independent propulsion cabin structure comprises a central bearing cylinder and a horizontal bracket; wherein, the combustion agent storage box is connected with the central bearing cylinder through a horizontal bracket; the oxidant storage tank is connected with the central bearing cylinder through another horizontal bracket.
In the separable independent propulsion cabin system, the combustion agent storage tank is used for storing green dinitrogen tetroxide of the two-component chemical propulsion system, and the outer shell and the inner propellant management device of the combustion agent storage tank are processed by titanium alloy.
In the separable independent propulsion pod system, the oxidizer storage tank is used for storing methylhydrazine of the two-component chemical propulsion system, and the outer shell and the inner propellant management device of the oxidizer storage tank are also made of titanium alloy.
In the separable independent propulsion cabin system, the independent propulsion cabin storage battery is an energy storage power supply of an independent propulsion cabin structure, and has the function of converting chemical energy into electric energy during working and supplying power for a heater and instrument equipment of the independent propulsion cabin structure for a long time.
In the separable independent propulsion cabin system, the 10N thruster comprises a solenoid valve and a thrust chamber; wherein the electromagnetic valve is connected with the thrust chamber; the thrust chamber comprises an injector and a combustion chamber nozzle; wherein, the injector is connected with the nozzle of the combustion chamber; the injector adopts a double-vortex scheme and is formed by machining a high-temperature resistant titanium alloy; the material of the combustion chamber nozzle is niobium alloy in an additive shape, and the inner surface and the outer surface of the combustion chamber nozzle are coated with silicide anti-oxidation coatings.
In the separable independent propulsion cabin system, the Beidou short message terminal receives Beidou and a global positioning navigation system (CPS) navigation positioning signal, completes positioning calculation, and sends a positioning calculation result to the independent propulsion cabin control unit through an RS serial port.
In the above separable autonomous propulsion pod system, the 490N engine includes a second thrust chamber and two propellant control valves; wherein, the two propellant control valves are arranged at the valve of the thrust chamber; the two propellant control valves are used for respectively controlling the flow of the oxidant and the fuel, and the starting and the shutdown of the engine are controlled by the opening and the closing of the propellant control valves.
In the separable independent propulsion cabin system, the integrated sun sensor measures the direction of the sun relative to the integrated sun sensor, and the output rolling and pitching attitudes of the satellite are used for establishing the ignition attitude during orbital transfer.
In the separable independent propulsion cabin system, under the combined mode, the separable independent propulsion cabin system and the main satellite are launched into orbit along with the carrier rocket through the connecting and separating mechanism; after the star and the arrow are separated, the main star serves as a main controller of the combination, and a separable independent propulsion cabin system serves as an execution mechanism to drive the 490N engine to ignite to complete a track lifting task; after separation between satellites, independently establishing an off-orbit attitude by taking an independent propulsion cabin control unit as a main controller, and autonomously determining a track and completing off-orbit operation through a GNSS receiver; after the separable independent propulsion cabin system is out of orbit and decelerated, the separable independent propulsion cabin system flies to a homeland short message return area and returns to the decelerated orbit through a short message; when the separable independent propulsion cabin system meets the preset derailment requirement, the storage battery of the independent propulsion cabin is exhausted, the passivation operation is completed, and then the separated independent propulsion cabin system enters the earth atmosphere for meteorology.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the invention, the on-orbit separation of the high-orbit satellite propulsion cabin can be realized by the separable independent propulsion cabin system, and the propulsion cabin modules in the original integrated design are optimized and combined again by optimizing the function division of the dual-component propulsion system, so that the stiffness of the satellite synchronous orbit section system is effectively reduced.
(2) According to the invention, through the configured independent propulsion cabin control circuit box, the integrated satellite-sensitive and Beidou short message terminal and other equipment, the off-orbit attitude can be automatically established after the independent propulsion cabin is separated from the main satellite, the automatic off-orbit passivation operation of the separable independent propulsion cabin is realized, and the off-orbit position is downloaded to the ground through the Beidou short message terminal.
(3) According to the invention, through the master-slave control logic design of the housekeeping, the measurement and control management unit (STMU) and the independent propulsion cabin control circuit box (SPSE), two working modes of combination control and independent propulsion cabin control can be realized, and under the combination control mode, the master satellite provides power supply and information interfaces for the independent propulsion cabin and uses the independent propulsion cabin as an actuating mechanism to carry out combination control. Under the control mode of the independent propulsion cabin, the independent propulsion cabin is supplied with power by a configured storage battery, and the independent propulsion cabin controls the circuit box SPSE to independently complete the off-orbit passivation work.
(4) According to the invention, the layout of equipment such as the helium tank, the 10N thruster, the 490N engine and the like is optimized, and the 490N engine and the high-pressure gas path part for transferring orbit orbital transfer form an independent whole, so that the stiff separation of the system is realized, and the bearing ratio of the satellite is further improved.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic structural diagram of a separable autonomous propulsion pod system provided by an embodiment of the present invention;
FIG. 2 is a diagram of the size constraints of the detachable independent propulsion pod provided by an embodiment of the present invention;
FIG. 3 is a diagram of a power supply and information interface of a detachable independent propulsion pod according to an embodiment of the present invention;
fig. 4 is an on-orbit work flow of the separable independent propulsion pod provided by the embodiment of the invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The embodiment provides a separable independent propulsion cabin system, which is used for an orbit lifting task in the early stage of a satellite orbit transfer stage, and when a propellant reaches an off-orbit warning line, the propellant is separated from a main satellite, and the off-orbit passivation operation is automatically completed. As shown in fig. 1, the detachable independent propulsion pod system of the present embodiment includes: the system comprises an independent propulsion cabin structure 1, a combustion agent storage box 2, an oxidant storage box 3, an independent propulsion cabin storage battery 4, a 10N thruster 5, a Beidou short message terminal 6, a 490N engine 7, an integrated sun sensor 8, an independent propulsion cabin control unit SPSE9 and a helium bottle 10. Wherein the content of the first and second substances,
the combustion agent storage box 2 is arranged on the side wall of the independent propulsion cabin structure 1; the oxidant storage tank 3 is arranged on the side wall of the independent propulsion cabin structure 1; wherein the oxidant storage tank 3 is opposite to the combustion agent storage tank 2; the independent propulsion cabin storage battery 4 is connected with the independent propulsion cabin structure 1; the 10N thruster 5 is connected with the independent propulsion cabin structure through a bracket; the Beidou short message terminal 6 is connected with the independent propulsion cabin structure 1 through a screw; the 490N engine 7 is arranged at the bottom of the independent propulsion pod structure 1; the integrated sun sensor 8 is connected with the independent propulsion cabin structure 1 through a space sensitive support; the independent propulsion pod control unit SPSE9 is connected to the independent propulsion pod structure 1 by screws; the helium tank 10 is arranged on the side wall of the independent propulsion pod structure 1.
The independent propulsion cabin structure 1 is mainly used for providing an installation structure of independent propulsion cabin equipment and mainly comprises 1 central bearing cylinder, 2 horizontal brackets, 2 side bearing rod systems, a combustion box pull rod, an upper inner supporting plate, a lower inner supporting plate, a connecting joint and a bearing cylinder transfer frame; the central bearing cylinder has two connecting frames, namely a carrying butt-joint frame and a bearing cylinder upper frame, the bearing cylinder upper frame is in threaded connection with the bearing cylinder adapter frame, and the bearing cylinder adapter frame provides a 1194A standard interface to realize butt joint with the main star.
As shown in fig. 2, a precisely controllable dimensional constraint relationship is formed among the central force-bearing cylinder 1, the horizontal bracket 2, the combustion agent tank 3 and the oxidizing agent tank 4, and the constraint relationship is as follows:
V1＝4/3*π*R1 3+π*R1 2*H1
V2＝4/3*π*R2 3+π*R2 2*H2
(L+R3)*V1*ρ1＝(1+x％)(M+R3)*V2*ρ2
wherein R is1Is the inner radius of the combustion agent storage box, L is the length of the bearing cylinder from the center of the combustion agent storage box to the center, H1As height of combustion agent tank, p1Is the density of the combustion agent, R2Is the inner radius of the oxidant storage tank, M is the length of the bearing cylinder from the center to the center of the oxidant storage tank, rho2Is the density of the oxidizing agent, H2For height of combustion agent storage tank, R3Radius of central bearing cylinder, x% of dimension between filling amount of storage tank and level, V1Volume of combustion agent storage tank, V2Is the volume of the oxidant reservoir.
By the formula, the dimension keeping precision between the filling amount of the storage tank and the level is good.
The combustion agent storage tank 2 is used for storing green dinitrogen tetroxide of the two-component chemical propulsion system, and the outer shell of the storage tank and the inner propellant management device are processed by titanium alloy. The combustion agent storage box 2 is connected with the bearing cylinder through a horizontal bracket
The oxidant storage tank 3 is used for storing methyl hydrazine of a two-component chemical propulsion system, and the shell of the storage tank and the inner propellant management device are also processed by titanium alloy and are connected with a bearing cylinder through a horizontal bracket.
The independent propulsion cabin storage battery 4 is an energy storage power supply of the propulsion cabin and has the function of converting chemical energy into electric energy during working so as to supply power for a heater and instrument equipment of the independent propulsion cabin 1 for a long time.
The 10N thruster 5 is a power device for satellite attitude adjustment and orbit maneuvering, and consists of an electromagnetic valve and a thrust chamber. The thrust chamber comprises an injector and a combustion chamber nozzle, wherein the injector adopts a double-vortex scheme and is formed by machining a high-temperature resistant titanium alloy. The nozzle material of the combustion chamber is niobium alloy, and is in an additive shape, and the inner surface and the outer surface of the nozzle are coated with silicide anti-oxidation coatings. The 10N thruster is connected with the independent propulsion cabin structure through a bracket.
The Beidou short message terminal 6 in the invention is a device which completes positioning calculation by receiving Beidou and a navigation positioning signal of a global positioning navigation system (CPS) and sends the positioning calculation result to an independent propulsion cabin control unit (SPSE)9 through an RS422 serial port. The Beidou short message terminal 6 is connected with the independent propulsion cabin structure 1 through a screw.
The 490N engine 7 of the invention is a satellite important orbit control actuating mechanism, it is made up of a thrust chamber and two propellant control valves, the thrust chamber is the combustion apparatus of the engine, the function of two control valves is to control the flow of oxidizing agent and fuel separately, start and shut-off of the control engine through opening, closing of the control valve. The thrust chamber consists of a direct-current mutual-impact injector head and a single-wall liquid film radiation cooling body with a large-area-ratio high-altitude spray pipe. The 490N engine 7 is connected to the independent propulsion pod structure 1 by a specially designed engine mount.
The integrated sun sensor 8 is an attitude measuring sensor for determining the attitude of the satellite by measuring the azimuth of the sun relative to the sensor, and the rolling and pitching attitudes of the satellite output by the sun sensor are used for establishing the ignition attitude during orbital transfer. The integrated sun sensor 8 is connected with the independent propulsion cabin structure 1 through the space sensitive support.
The independent propulsion cabin control unit SPSE9 has the main functions of completing the drive control of the actuating mechanism of the two-component propulsion system, the thermal control of the propulsion cabin, the detonation of initiating explosive and the detonation of the separating mechanism of the combined body connecting device, and the like, and feeding back the working state information of the propulsion cabin to the main star. The individual propulsion pod control unit SPSE9 is connected to the individual propulsion pod structure 1 by means of screws.
The independent propulsion pod of the present invention may 1 be operated in both combination control and independent propulsion pod control modes. The specific on-orbit working process comprises the following steps: under the combined mode, the independent propulsion cabin and the main star are launched into orbit along with the carrier rocket through the connecting and separating mechanism. After the star and the arrow are separated, the main star AOCU serves as a combined main controller, and the independent propulsion cabin serves as an execution mechanism to drive the 490N engine to ignite so as to finish the track lifting task. After separation between satellites, the independent propulsion cabin control unit SPSE is used as a main controller to independently establish an off-orbit attitude, and a GNSS receiver autonomously determines the orbit and completes the off-orbit operation. After the independent propulsion cabin is out of orbit and decelerated, the independent propulsion cabin flies to a homeland short message return area and returns to the decelerated orbit through a short message. When the independent propulsion cabin meets the requirement of derailment, the storage battery of the independent propulsion cabin is exhausted, the passivation operation is completed, and then the independent propulsion cabin gradually enters the earth atmosphere for meteorology.
The helium tank 10 in the invention is a helium storage device required in the satellite orbit changing process, and generally, the helium tank is made of a composite material wound around a gas tank, the inner liner is made of titanium alloy through welding, and T1000 carbon fiber is wound outside the helium tank.
The independent propulsion cabin control unit SPSE has the main functions of completing the drive control of the actuating mechanism of the double-component propulsion system, the thermal control of the propulsion cabin, the detonation of initiating explosive and the detonation of the separating mechanism of the combined body connecting device and the like, and feeding back the working state information of the propulsion cabin to the main satellite.
The specific functions realized by the SPSE are:
a. the method comprises the following steps of performing drive control on 8-way 10N electromagnetic valves, 7-way self-locking valves and 1 490N engine of the double-component propulsion system, supplying power to 3 pressure sensors and collecting telemetering output of the pressure sensors;
b. carrying out power supply and RS422 serial communication on 1 sun sensor, 3 inertia measurement units and 2 short message terminals which are arranged on an independent propulsion cabin;
c. the communication function with a main satellite attitude and orbit control unit AOCU is realized;
d. initiating control is carried out on initiating explosive devices of the double-component chemical propulsion system, and electric tripping of the inter-satellite separation plug and belt explosion bolt initiation are controlled;
e. after being separated from the main star, the SPSE realizes the off-orbit passivation operation of the independent propulsion cabin through controlling the sensors and the actuating mechanism of the separable propulsion cabin.
The independent propulsion cabin structure consists of 1 central bearing cylinder, 2 horizontal brackets, 2 side bearing rod systems, a combustion box pull rod, an upper inner supporting plate, a lower inner supporting plate, a connecting joint and a bearing cylinder adapter frame; the central bearing cylinder has two connecting frames, namely a carrying butt-joint frame and a bearing cylinder upper frame, the bearing cylinder upper frame is in threaded connection with the bearing cylinder switching frame, and the bearing cylinder switching frame provides a 1194A standard interface to realize butt joint with the main star. The connection of the oxidant storage tank and the bearing cylinder adopts a form of glue joint of the assembly parts, so that the bending moment generated by the connection of the storage tank is reduced to the maximum extent, the load in the cylinder wall surface is converted, and the connection precision of the oxidant storage tank and the bearing cylinder is favorably ensured. The 2 combustion agent storage boxes are respectively arranged on the two sides of the independent propulsion cabin, are arranged on the horizontal bracket and are connected with the bearing cylinder through side plates. The 490N engine support links to each other with a bearing section of thick bamboo inside wall through connecting the corner box, and the 490N engine is installed on support flange quotation.
As shown in fig. 3, in the present invention, the independent propulsion cabin is powered by 100V from the main satellite in the combined state, after the inter-satellite separation preparation of the combined unit is completed, the housekeeping and measurement and control management unit STMU sends out a bus instruction to make the independent propulsion cabin powered by the independent propulsion cabin storage battery SPSB, and then the STMU sends out a bus instruction to drive the power supply to control the power supply to disconnect 100V power supply from the power distribution unit PCDU; the STMU sends a program control T0 signal to the independent propulsion cabin control driving unit SPSE through the bus, the SPSE drives the X1F and the X2F to carry out electric disconnection, and a power supply required by the electric disconnection is supplied by the independent propulsion cabin storage battery SPSB group. And after the X1F and the X2F are electrically disconnected, the independent propulsion cabin is telemetrically interrupted, and the subsequent off-track operation is autonomously carried out under the support of a battery.
In the invention, fall-off signals of a satellite and rocket separation surface X1F and X2F are collected by an SPSE and then are sent to a main satellite attitude and orbit control unit AOCU through an RS422 interface; signals of the satellite and rocket separation surface separation switch are sent to the main satellite STMU, the AOCU and the PCDU through the inter-satellite X1F and the inter-satellite X2F, and are used for the satellite affair computer to start satellite and rocket separation program control, the control subsystem to judge flight stages and the like. After the control subsystem judges that the star and the arrow are separated and the stars are not separated, the independent propulsion cabin is used as an actuating mechanism to control the assembly;
in the invention, the main star and the independent propulsion cabin are connected through an inter-star separation mechanism. When the star is separated, the inter-star belting is detonated by an instruction sent by the SPSE, the SPSB provides a detonation current, and the separated belting is left on the independent propulsion cabin.
The independent propulsion pod workflow is shown in figure 4.
The independent propelling module can work in two working modes of combination control and independent propelling module control. The specific on-orbit working process comprises the following steps: under the combined mode, the independent propulsion cabin and the main star are launched into orbit along with the carrier rocket through the connecting and separating mechanism. After the star and the arrow are separated, the main star AOCU serves as a combined main controller, and the independent propulsion cabin serves as an execution mechanism to drive the 490N engine to ignite so as to finish the track lifting task. After separation between satellites, the independent propulsion cabin control unit SPSE is used as a main controller to independently establish an off-orbit attitude, and a GNSS receiver autonomously determines the orbit and completes the off-orbit operation. After the independent propulsion cabin is out of orbit and decelerated, the independent propulsion cabin flies to a homeland short message return area and returns to the decelerated orbit through a short message. When the independent propulsion cabin meets the requirement of derailment, the storage battery of the independent propulsion cabin is exhausted, the passivation operation is completed, and then the independent propulsion cabin gradually enters the earth atmosphere for meteorology.
According to the invention, the on-orbit separation of the high-orbit satellite propulsion cabin can be realized by the separable independent propulsion cabin system, and the propulsion cabin modules in the original integrated design are optimized and combined again by optimizing the function division of the dual-component propulsion system, so that the stiffness of the satellite synchronous orbit section system is effectively reduced; according to the invention, through the configured independent propulsion cabin control circuit box, the integrated satellite-sensitive and Beidou short message terminal and other equipment, the off-orbit attitude can be automatically established after the independent propulsion cabin is separated from the main satellite, the automatic off-orbit passivation operation of the separable independent propulsion cabin is realized, and the off-orbit position is downloaded to the ground through the Beidou short message terminal; according to the invention, through the master-slave control logic design of the housekeeping, the measurement and control management unit (STMU) and the independent propulsion cabin control circuit box (SPSE), two working modes of combination control and independent propulsion cabin control can be realized, and under the combination control mode, the master satellite provides power supply and information interfaces for the independent propulsion cabin and uses the independent propulsion cabin as an actuating mechanism to carry out combination control. Under the control mode of the independent propulsion cabin, the independent propulsion cabin is supplied with power by a configured storage battery, and the independent propulsion cabin controls a circuit box SPSE to independently complete the off-orbit passivation work; according to the invention, the layout of equipment such as the helium tank, the 10N thruster, the 490N engine and the like is optimized, and the 490N engine and the high-pressure gas path part for transferring orbit orbital transfer form an independent whole, so that the stiff separation of the system is realized, and the bearing ratio of the satellite is further improved.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A detachable self-contained propulsion pod system, comprising: the system comprises an independent propulsion cabin structure (1), a combustion agent storage box (2), an oxidant storage box (3), an independent propulsion cabin storage battery (4), a 10N thruster (5), a Beidou short message terminal (6), a 490N engine (7), an integrated sun sensor (8), an independent propulsion cabin control unit (9) and a helium tank (10); wherein the content of the first and second substances,
the combustion agent storage box (2) is arranged on the side wall of the independent propulsion cabin structure (1);
the oxidant storage tank (3) is arranged on the side wall of the independent propulsion cabin structure (1); wherein the oxidant tank (3) is opposite to the combustion agent tank (2);
the independent propulsion cabin storage battery (4) is connected with the independent propulsion cabin structure (1);
the 10N thruster (5) is connected with the independent propulsion cabin structure through a bracket;
the Beidou short message terminal (6) is connected with the independent propulsion cabin structure (1) through a screw;
the 490N engine (7) is arranged at the bottom of the independent propulsion cabin structure (1);
the integrated sun sensor (8) is connected with the independent propulsion cabin structure (1) through an insensitive support;
the independent propulsion cabin control unit (9) is connected with the independent propulsion cabin structure (1) through screws;
the helium bottle (10) is arranged on the side wall of the independent propulsion cabin structure (1).
2. The detachable self-contained propulsion pod system of claim 1, wherein: the independent propulsion cabin structure (1) comprises 1 central bearing cylinder and 2 horizontal brackets; wherein the content of the first and second substances,
the combustion agent storage box (2) is connected with the central bearing cylinder through a horizontal bracket;
the oxidant storage tank (3) is connected with the central bearing cylinder through another horizontal bracket.
3. The detachable self-contained propulsion pod system of claim 1, wherein: the combustion agent storage tank (2) is used for storing green dinitrogen tetroxide of the two-component chemical propulsion system, and the shell and the inner propellant management device of the combustion agent storage tank (2) are made of titanium alloy.
4. The detachable self-contained propulsion pod system of claim 1, wherein: the oxidizer storage tank (3) is used for storing methyl hydrazine of the two-component chemical propulsion system, and the outer shell and the inner propellant management device of the oxidizer storage tank (3) are also made of titanium alloy.
5. The detachable self-contained propulsion pod system of claim 1, wherein: the independent propulsion cabin storage battery (4) is an energy storage power supply of the independent propulsion cabin structure (1) and is used for converting chemical energy into electric energy during working and supplying power for the heater and the instrument equipment of the independent propulsion cabin structure (1) for a long time.
6. The detachable self-contained propulsion pod system of claim 1, wherein: the 10N thruster (5) comprises an electromagnetic valve and a thrust chamber; wherein the content of the first and second substances,
the electromagnetic valve is connected with the thrust chamber;
the thrust chamber comprises an injector and a combustion chamber nozzle; wherein, the injector is connected with the nozzle of the combustion chamber; the injector adopts a double-vortex scheme and is formed by machining a high-temperature resistant titanium alloy; the material of the combustion chamber nozzle is niobium alloy in an additive shape, and the inner surface and the outer surface of the combustion chamber nozzle are coated with silicide anti-oxidation coatings.
7. The detachable self-contained propulsion pod system of claim 1, wherein: the Beidou short message terminal (6) receives Beidou and a navigation positioning signal of a global positioning navigation system (CPS), completes positioning calculation, and sends a positioning calculation result to the independent propulsion cabin control unit (9) through an RS422 serial port.
8. The detachable self-contained propulsion pod system of claim 1, wherein: the 490N engine (7) comprises a second thrust chamber and two propellant control valves; wherein, the two propellant control valves are arranged at the valve of the thrust chamber;
the two propellant control valves are used for respectively controlling the flow of the oxidant and the fuel, and the starting and the shutdown of the engine are controlled by the opening and the closing of the propellant control valves.
9. The detachable self-contained propulsion pod system of claim 1, wherein: the integrated sun sensor (8) measures the direction of the sun relative to the integrated sun sensor, and the output rolling and pitching attitudes of the satellite are used for establishing the ignition attitude during orbital transfer.
10. The detachable self-contained propulsion pod system of claim 1, wherein: in the combined mode, the separable independent propulsion cabin system and the main satellite are launched into orbit along with the carrier rocket through the connecting and separating mechanism; after the star and the arrow are separated, the main star serves as a main controller of the combination, and a 490N engine (7) is driven to ignite by taking a separable independent propulsion cabin system as an execution mechanism to complete a track lifting task; after separation between satellites, an independent propulsion cabin control unit (9) is used as a main controller to autonomously establish a derailing attitude, and a GNSS receiver autonomously determines a track and completes the derailing operation; after the separable independent propulsion cabin system is out of orbit and decelerated, the separable independent propulsion cabin system flies to a homeland short message return area and returns to the decelerated orbit through a short message; when the separable independent propulsion cabin system meets the preset derailment requirement, the energy of the independent propulsion cabin storage battery (4) is exhausted, the passivation operation is completed, and then the separated independent propulsion cabin system enters the earth atmosphere for meteority.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111552076.1A CN114229040A (en) | 2021-12-17 | 2021-12-17 | Separable independent propulsion cabin system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111552076.1A CN114229040A (en) | 2021-12-17 | 2021-12-17 | Separable independent propulsion cabin system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114229040A true CN114229040A (en) | 2022-03-25 |
Family
ID=80757954
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111552076.1A Pending CN114229040A (en) | 2021-12-17 | 2021-12-17 | Separable independent propulsion cabin system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114229040A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116513491A (en) * | 2023-07-05 | 2023-08-01 | 北京未来宇航空间科技研究院有限公司 | Superior and space replenishment system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN112298617A (en) * | 2020-09-29 | 2021-02-02 | 北京空间飞行器总体设计部 | On-orbit separable satellite propulsion service cabin main structure |
| CN112373727A (en) * | 2020-11-24 | 2021-02-19 | 中国空间技术研究院 | Separable satellite propulsion system configuration |
| CN112937917A (en) * | 2020-08-11 | 2021-06-11 | 中国科学院微小卫星创新研究院 | Separation method of satellite propulsion module and satellite system |
| CN112977882A (en) * | 2021-03-12 | 2021-06-18 | 上海卫星工程研究所 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
-
2021
- 2021-12-17 CN CN202111552076.1A patent/CN114229040A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN112937917A (en) * | 2020-08-11 | 2021-06-11 | 中国科学院微小卫星创新研究院 | Separation method of satellite propulsion module and satellite system |
| CN112298617A (en) * | 2020-09-29 | 2021-02-02 | 北京空间飞行器总体设计部 | On-orbit separable satellite propulsion service cabin main structure |
| CN112373727A (en) * | 2020-11-24 | 2021-02-19 | 中国空间技术研究院 | Separable satellite propulsion system configuration |
| CN112977882A (en) * | 2021-03-12 | 2021-06-18 | 上海卫星工程研究所 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116513491A (en) * | 2023-07-05 | 2023-08-01 | 北京未来宇航空间科技研究院有限公司 | Superior and space replenishment system |
| CN116513491B (en) * | 2023-07-05 | 2023-09-15 | 北京未来宇航空间科技研究院有限公司 | Superior and space replenishment system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10738739B2 (en) | Rocket engines systems | |
| US8091835B2 (en) | Exchangeable propellant cartridge system | |
| CN109018444A (en) | Rocket-powered mars transporter power system | |
| US4741502A (en) | Method and apparatus for launching a spacecraft by use of a recoverable upper rocket stage | |
| US20090140101A1 (en) | Direct Flight Far Space Shuttle | |
| JP2010524780A (en) | Usage and usage of optimized collaborative spacecraft | |
| US20090230249A1 (en) | Method of Launching into Operational Orbit an Artificial Satellite and Associated Propulsion Device | |
| CN113998150A (en) | Ultra-low orbit satellite full-electric propulsion orbit maintaining system | |
| US20220315251A1 (en) | Space Mission Energy Management Architecture | |
| CN114229040A (en) | Separable independent propulsion cabin system | |
| CN110001823B (en) | Combined intelligent vehicle system | |
| CN110104222A (en) | A kind of modularization propulsion service system promoted based on mixed mode | |
| CN113044246A (en) | Propelling working medium supply method and system based on air suction type electric propulsion | |
| CN114291300B (en) | Ground-moon shuttle aircraft propulsion system | |
| CN112298606B (en) | Off-orbit method for geostationary orbit communication satellite | |
| CN111891391B (en) | Satellite propulsion module and separation method thereof | |
| CN106198033B (en) | A kind of in-orbit computational methods of satellite engine/motor specific impulse | |
| CN110925032B (en) | Lunar pneumatic power generation method based on propelling residual resource secondary utilization | |
| CN116513379A (en) | Hybrid power supply wave glider and control method thereof | |
| JPH0339188B2 (en) | ||
| US11203447B1 (en) | Propulsion system for space vehicles | |
| JPH01500531A (en) | Complex spacecraft control system | |
| CN115432207A (en) | Space ferry system and use method thereof | |
| CN213735621U (en) | High-efficient safe spacecraft attitude adjustment ware | |
| CN116929159B (en) | Carrier rocket with solid-liquid hybrid power and launching method thereof |
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 |