CN112705920B - Satellite assembling method - Google Patents
Satellite assembling method Download PDFInfo
- Publication number
- CN112705920B CN112705920B CN202011487584.1A CN202011487584A CN112705920B CN 112705920 B CN112705920 B CN 112705920B CN 202011487584 A CN202011487584 A CN 202011487584A CN 112705920 B CN112705920 B CN 112705920B
- Authority
- CN
- China
- Prior art keywords
- satellite
- test
- plate
- cabin
- load
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 68
- 238000012360 testing method Methods 0.000 claims abstract description 256
- 238000012986 modification Methods 0.000 claims abstract description 52
- 230000004048 modification Effects 0.000 claims abstract description 52
- 230000007613 environmental effect Effects 0.000 claims abstract description 36
- 230000008569 process Effects 0.000 claims abstract description 28
- 238000004519 manufacturing process Methods 0.000 claims abstract description 11
- 238000013461 design Methods 0.000 claims abstract description 10
- 238000005259 measurement Methods 0.000 claims description 21
- 238000009434 installation Methods 0.000 claims description 20
- 238000004088 simulation Methods 0.000 claims description 10
- 238000001514 detection method Methods 0.000 claims description 7
- 239000003292 glue Substances 0.000 claims description 7
- 238000002360 preparation method Methods 0.000 claims description 7
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 238000009413 insulation Methods 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 238000007689 inspection Methods 0.000 claims description 5
- 238000005286 illumination Methods 0.000 claims description 4
- 230000010354 integration Effects 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 3
- 229910052757 nitrogen Inorganic materials 0.000 claims description 3
- 239000003973 paint Substances 0.000 claims description 3
- 238000005253 cladding Methods 0.000 claims 2
- 238000007726 management method Methods 0.000 claims 1
- 238000012552 review Methods 0.000 claims 1
- 239000007921 spray Substances 0.000 claims 1
- 238000011161 development Methods 0.000 description 4
- 238000005192 partition Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000011056 performance test Methods 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 238000003860 storage Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- JJWKPURADFRFRB-UHFFFAOYSA-N carbonyl sulfide Chemical compound O=C=S JJWKPURADFRFRB-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000005670 electromagnetic radiation Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 230000005358 geomagnetic field Effects 0.000 description 1
- 230000005486 microgravity Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
本发明提供了一种卫星装配方法，包括：完成卫星初样设计、结构图纸的绘制、卫星投产、卫星生产和卫星验收工作后，进行以下卫星装配流程，包括：进行集成测试装配，形成集成测试整星，进行多个状态下的测试；在集成测试整星的基础上，进行热试验改装，形成热试验整星；在热试验整星的基础上，进行环境试验改装，形成环境试验整星；在环境试验整星的基础上，进行出厂前测试改装和出厂改装，形成最终的待发射整星。
The invention provides a satellite assembling method, which includes: after completing the initial design of the satellite, the drawing of the structural drawing, the satellite production, the satellite production and the satellite acceptance, the following satellite assembling process is performed, including: performing an integrated test assembly to form an integrated test The whole star is tested in multiple states; on the basis of the integrated test of the whole star, thermal test modification is carried out to form a thermal test whole star; on the basis of the thermal test whole star, environmental test modification is carried out to form an environmental test whole star ; On the basis of the environmental test of the whole satellite, the factory test modification and factory modification are carried out to form the final complete satellite to be launched.
Description
Technical Field
The invention relates to the technical field of satellite assembly, in particular to a satellite assembly method.
Background
The assembly of the satellite is a series of final assembly work which is required to be carried out after the satellite completes pre-research, development and design, simulation analysis and processing production, and any satellite can be successfully delivered and successfully launched after the satellite passes through the stage;
the general assembly of the satellite is to reliably fix the equipment used by each subsystem to the required star body position according to the general requirements, and connect the equipment through cables and pipes to form the whole star with the quality characteristics, precision and air tightness meeting the general requirements; ensure that the device can work normally under the action of various environments such as a ground stage, a launching stage, a flying stage and the like.
The rationality of the final assembly design flow will directly affect the overall scheme, the development period, the development cost and the quality of the product of the satellite. The final assembly designer needs to balance the configuration and the overall layout of the satellite and the advantages and disadvantages of various final assembly schemes, and strives to find the optimal scheme under the condition of meeting the task requirement so as to achieve the optimal design of the satellite final assembly. But instead. For an excellent final assembly design, besides meeting the technical index requirements, good quality indexes and economic indexes should be obtained at the same time.
In the satellite final assembly process, besides the assembly of the satellite, various environment tests of the satellite, such as satellite precision measurement, quality characteristic test, vibration test, noise test, seal leakage detection, electrical performance test, EMC test and the like, are also completed in each stage of the assembly.
The satellite is subjected to various environmental influences and actions after being shipped from a factory and through the processes of transportation, launching, orbit entering, orbital operation and the like, and the complexity and diversity of the environments are difficult to overcome by common industrial products. For example, in the process of ground transportation, the satellite is subjected to vibration and impact, in the process of launching, the satellite is subjected to mechanical environment effects such as acceleration, noise, vibration and impact, in the process of orbital motion, the satellite is in a vacuum and cryogenic environment, and is also subjected to the effects of cosmic rays, solar radiation, electromagnetic radiation, high-energy particles and the like, and in addition, the satellite is influenced by various environments such as plasma, a geomagnetic field, microgravity and the like. In order to verify the rationality of satellite design, the influence of various severe environments which the satellite may experience is required to be completed before the satellite leaves a factory, namely the examination of an environment test, in order to reasonably and efficiently complete the environment test, the general assembly process is required to be optimized during the general assembly of the satellite, and the repeated disassembly and assembly of the satellite and the ineffective transportation caused by the repeated replacement of test sites due to an unreasonable test sequence are avoided.
With the vigorous development of the satellite industry, the function of the satellite is more and more emphasized by people, more constellations are built in the future, the satellite can be produced in batch like an automobile, the production period is greatly shortened by reasonably formulating an assembly flow, the efficiency is improved, the cost can be saved, the market demand is quickly responded, and better economic benefit is generated.
Disclosure of Invention
The invention aims to provide a satellite assembly method, which aims to solve the problems that repeated disassembly and assembly and invalid transportation frequently occur in the existing satellite assembly process, and unnecessary damage is caused to a satellite by the possible repeated tests and other conditions.
In order to solve the above technical problem, the present invention provides a satellite assembly method, including:
after completing the drawing of satellite prototype design, structure drawing, satellite commissioning, satellite production and satellite acceptance work, the following satellite assembly processes are carried out, including:
carrying out integrated test assembly to form an integrated test whole star, and carrying out tests under a plurality of states;
performing thermal test modification on the basis of the integrated test of the whole satellite to form a thermal test whole satellite;
on the basis of the whole satellite of the thermal test, carrying out environmental test modification to form the whole satellite of the environmental test;
and carrying out pre-factory test modification and factory modification on the basis of the environment test whole star to form the final whole star to be launched.
Optionally, in the satellite assembling method, performing integrated test assembly to form an integrated test whole satellite, and performing tests in multiple states includes:
preparing before assembling the star, including preparing a star file, preparing required tooling equipment, and completing the preassembly of the main frame;
carrying out first-state whole-star assembly to form a first-state whole star, and carrying out whole-star desktop joint test;
carrying out second-state whole-satellite assembly to form a second-state whole satellite, and carrying out whole-satellite airborne fine measurement;
carrying out whole satellite assembly in a third state to form a whole satellite in the third state, and carrying out satellite loading electrical measurement, satellite function module electrical measurement, satellite information flow test and model flying satellite loading test under the satellite wired condition;
and carrying out fourth-state whole-satellite assembly to form a fourth-state whole satellite, and carrying out whole-satellite single-machine on-off machine inspection under the satellite wired condition.
Optionally, in the satellite assembling method,
the whole-star desktop joint test comprises the following steps: the aluminum sheet metal is used as a test desktop and a ground, the grounding parts of all satellite equipment or cables are connected to the aluminum sheet metal and connected to a satellite grounding pile between tests, and the cables are connected for electrical measurement of the following contents: the method comprises the following steps of satellite testing minimum configuration system electrical interface testing, power supply and overall circuit single electrical interface testing, measurement and control subsystem single electrical interface testing, attitude and orbit control subsystem single electrical interface testing, structure and mechanism subsystem single electrical interface testing and load subsystem electrical interface testing;
carrying out whole star desktop joint test still includes carrying out whole star comprehensive test, include: respectively testing the functions of the branch system, the information flow and the closed-loop model flight;
the precise measurement under the whole-satellite space load comprises the following steps: and measuring the precision of a thruster single machine, a gyroscope single machine, a sun sensor single machine and a star sensor single machine.
Optionally, in the satellite assembling method, performing the first-state whole satellite assembling includes:
spraying paint, punching air holes and sticking a reflecting lens on a structure plate of a single machine;
carrying out propulsion system assembly and thermal control coating on a structural slab bottom plate of the propulsion system, and carrying out propulsion system leakage detection;
checking whether a single machine shell formed by each structural plate meets the precision requirement;
the single machine and the structural plate are preassembled, and all the connecting screws are screwed in and out according to the standard;
installing a bottom plate and a top plate of the platform cabin and the main frame by adopting a positive fastening piece, smearing anti-loosening glue and screwing the anti-loosening glue according to standard torque;
installing a bottom plate and a partition plate of the load cabin and the main frame by adopting a positive fastening piece, smearing anti-loosening glue and screwing the anti-loosening glue according to standard torque;
a heating plate, a thermocouple and a thermistor are adhered to the satellite mounting single machine and the bracket;
splitting the main frame into a platform cabin main frame and a load cabin main frame;
the tightening torque of all fasteners was reviewed.
Optionally, in the satellite assembling method, performing second-state whole satellite assembling includes:
installing a thruster single machine, a gyroscope single machine, a sun sensor single machine and a star sensor single machine;
performing a third state whole star assembly comprising:
installing each load on a cabin plate of a satellite, flatly placing the cabin plate on an installation vehicle, finishing initial cable arrangement of the cable when each cabin plate of the satellite is in an open cabin state, integrally assembling each mounting plate of the platform cabin to a main frame of the platform cabin, and integrally assembling each mounting plate of the load cabin to a main frame of the load cabin;
performing a fourth state whole star assembly comprises:
the platform cabin and the load cabin are superposed, a cabin plate is reserved in each of the platform cabin and the load cabin and is not matched with the cabin, faults are checked through the cabin plate during startup and shutdown inspection, and a positioning block between the platform cabin and the load cabin is detached according to the field condition.
Optionally, in the satellite assembling method, the step of integrally assembling each mounting plate of the platform cabin to the platform cabin main frame is as follows:
adjusting a main frame of the platform cabin, placing the main frame of the platform cabin on a special assembly platform of the platform cabin, adjusting the special assembly platform of the platform cabin by a level gauge, wherein the parallelism degree of the special assembly platform of the platform cabin and a horizontal plane is better than 1mm/1000mm, and a process frame is arranged on the main frame of the platform cabin to keep the stability of the main frame of the platform cabin;
installing a prism on the precision measurement tool and a prism of the platform cabin bottom plate, and adjusting the prism of the bottom plate to enable the error between the prism of the bottom plate and the prism of the precision measurement tool to be within a range of +/-15';
mounting the platform cabin bottom plate on a satellite tool, mounting each single machine and each cable, mounting a thermistor and a thermocouple of the platform cabin bottom plate, and checking redundancy;
mounting the platform cabin-Y plate on a satellite tool, mounting each single machine and cables, mounting a platform cabin-Y plate thermistor and a thermocouple, and checking redundancy;
mounting the platform cabin-Z plate on a satellite tool, mounting each single machine and each cable, mounting a platform cabin-Z plate thermistor and a thermocouple, and checking redundancy;
mounting the platform cabin and the Z plate on a satellite tool, mounting each single machine and each cable, mounting the platform cabin and the Z plate thermistor and the thermocouple, and checking redundancy;
mounting the platform cabin and the Y plate on a satellite tool, mounting each single machine and each cable, mounting the platform cabin and the Y plate on a thermistor and a thermocouple, and checking redundancy;
after the mounting plates of the platform cabin are assembled, closing the platform cabin-Y plate, connecting the-Y plate with the-Z plate, connecting cables between the-Y plate and the + Y plate, closing the platform cabin-Z plate, placing the platform cabin-Z plate and the XY surface of the main frame in a parallel and separated mode, connecting and arranging the-Z plate and the + Y plate cables, and enabling the platform cabin + Y and + Z plates to be in a flat lying state so as to have a cabin-dividing test function.
Optionally, in the satellite assembling method, the step of integrally assembling each mounting plate of the load compartment to the main frame of the load compartment is as follows:
adjusting a main frame of the load cabin, placing the main frame of the load cabin on a special assembly platform for the load cabin, and adjusting the special assembly platform for the load cabin by using a level meter, wherein the parallelism of the special assembly platform for the load cabin and a horizontal plane is better than 1mm/1000 mm; firstly, mounting a load cabin bottom plate, a partition plate and a top plate, and mounting a process frame on the rest surfaces;
installing the load cabin-Y plate on a tooling vehicle, connecting each single machine on the installation plate with a relevant cable, mounting a thermistor and a thermocouple of the load cabin-Y plate, and checking redundancy;
the load cabin and the Z plate are installed on a tooling vehicle, each single machine on the installation plate is connected with a related cable, a thermistor and a thermocouple of the load cabin and the Z plate are pasted, and redundant materials are checked;
the load cabin and the Y plate are installed on a tooling vehicle, each single machine on the installation plate is connected with a related cable, a thermistor and a thermocouple of the load cabin and the Y plate are pasted, and the redundancy is checked;
the load cabin-Z plate is arranged on a tooling vehicle, each single machine on the mounting plate is connected with a related cable, a thermistor and a thermocouple of the load cabin-Z plate are pasted, and redundant materials are checked;
after the load cabin roof is installed with a single machine and connected with related cables, supporting the load cabin roof to a proper height, and checking redundancy;
after the mounting plates of the load compartment are assembled, closing the Y plate of the load compartment, connecting cables between the-Y plate and the + Z-Y plate and the + Y plate of the load compartment, closing the Z plate of the load compartment, connecting cables between the + Y plate and the-Z plate, closing the load compartment and the Y plate, arranging the cables, enabling the load + Y plate to lie at 90 degrees, enabling the-Z plate of the load compartment to be in a 45-degree open state, and enabling the top plate to be supported to be at a proper height.
Optionally, in the satellite assembling method, on the basis of the integrated testing whole satellite, a thermal test modification is performed, and the forming of the thermal test whole satellite includes:
the whole satellite is completely assembled, the intra-satellite cable is connected well, all cabin plates are closed, the thermal control simulation piece is used for replacing an extra-satellite single machine and antenna load, an extra-satellite heat pipe is installed, a thermocouple for a thermal test is installed, and a plurality of layers of heat insulation components are coated outside the satellite;
the storage tank is pushed to be in a nitrogen filling state;
the other parts except the thermal control simulation part on the satellite are in a normal state.
Optionally, in the satellite assembling method, on the basis of the thermal test of the whole satellite, the environmental test is modified to form the environmental test whole satellite, including:
removing a thermal control simulation piece for replacing an extra-satellite single machine and an antenna load, installing a normal sample piece of the extra-satellite single machine and the antenna load, and removing a thermocouple and an extra-satellite multilayer heat insulation assembly for a thermal test;
mounting a mechanical sensor for testing;
the other parts except the mechanical sensors for the test on the satellite are in a sample state;
the environmental test process sequentially comprises quality characteristic test, solar array installation, sine vibration test, noise test, EMC test, array expansion test, illumination test and full-system leakage test.
Optionally, in the satellite assembly method, on the basis of the environmental test of the whole satellite, pre-factory test modification and factory modification are performed to form a final whole satellite to be launched, where the method includes:
the test modification before delivery comprises the following steps: dismantling all the sensors on the satellite without any operation on the satellite equipment; the satellite external heat pipe is disassembled, and the load cabin top plate is opened, so that the satellite can better radiate internal heat in a test state;
the pre-factory test comprises the following steps: whether all indexes of the whole star are changed through all the environmental tests and whether the whole star still meets the factory requirements is checked;
factory modification is performed when the test before the final factory dispatch is finished, and comprises the following steps: combining the load cabin top plate, installing the satellite externally-attached heat pipe, and assembling the satellite to a final delivery state.
In the satellite assembling method provided by the invention, the integrated test whole satellite is formed by carrying out integrated test assembly, the tests under multiple states are carried out, the thermal test refitting is carried out on the basis of the integrated test whole satellite to form the thermal test whole satellite, the environmental test refitting is carried out on the basis of the thermal test whole satellite to form the environmental test whole satellite, the test refitting before leaving factory and the factory refitting are carried out on the basis of the environmental test whole satellite to form the final whole satellite to be launched, the working sequence of each satellite loading stage can be reasonably arranged, the labor cost can be saved, the satellite loading time can be saved, meanwhile, the repeated disassembly and assembly of the satellite and the invalid transportation caused by the repeated replacement of the test sites due to the unreasonable test sequence can be avoided, the risk of damage to the satellite can be reduced, and the mass production of the satellite can be guaranteed.
Drawings
FIG. 1 is a schematic flow chart of a satellite assembly method according to an embodiment of the invention;
FIG. 2 is a schematic view of a third embodiment of the present invention;
FIG. 3 is a schematic view of a third condition load compartment closure according to an embodiment of the present invention;
FIG. 4 is a fourth state assembly diagram according to an embodiment of the present invention.
Detailed Description
The satellite assembling method proposed by the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become more apparent from the following description. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
The core idea of the invention is to provide a satellite assembly method to solve the problems of repeated disassembly and assembly, invalid transportation, repeated tests and the like which often occur in the existing satellite assembly process and cause unnecessary damage to the satellite.
In order to realize the idea, the invention provides a satellite assembly method, which comprises the following steps: after completing the drawing of satellite prototype design, structure drawing, satellite commissioning, satellite production and satellite acceptance work, the following satellite assembly processes are carried out, including: carrying out integrated test assembly to form an integrated test whole star, and carrying out tests under a plurality of states; performing thermal test modification on the basis of the integrated test of the whole satellite to form a thermal test whole satellite; on the basis of the whole satellite of the thermal test, carrying out environmental test modification to form the whole satellite of the environmental test; and carrying out pre-factory test modification and factory modification on the basis of the environment test whole star to form the final whole star to be launched.
The invention discloses a satellite assembly process, wherein the satellite assembly is the assembly work of final assembly integration (including A state, B state and C state), thermal test modification, environmental test modification, test modification before delivery and the like of a satellite before delivery; the method aims to integrate and assemble a complete satellite and provide a foundation for the test of the whole satellite; the whole satellite assembly process comprises the assembly of a structure and a single machine, the modification of a thermal test, an environmental test, an electrical property test before delivery and the like; the whole process is finished before the satellite leaves the factory.
The invention relates to a satellite assembly technology in the technical field of spaceflight, in particular to a technical process comprising the assembly of a structure and a single machine, thermal test, environmental test and modification of electrical property test before delivery.
The invention aims to provide an assembly process of a satellite, wherein when the satellite completes the initial design, the drawing, production and acceptance of a structure drawing are firstly carried out; secondly, the assembly work of the satellite, the assembly of the satellite not only comprises the assembly of a satellite main frame, but also comprises the installation of a satellite platform and load equipment, the connection of an on-satellite cable and the treatment of on-satellite thermal control measures; the satellite can also perform the work of electrical property test, whole satellite quality characteristic test, sine vibration test, noise test, EMC test and the like in the assembling process;
the assembly process of the invention mainly comprises the following steps: the method comprises the following steps of (1) integrating test satellite loading (A state test, B state test and C state test), thermal test modification, environmental test modification, pre-factory test modification and factory modification;
the satellite A state satellite mainly comprises an A0 state (corresponding to a first state) and an A1 state (corresponding to a second state); the A0 state is a whole satellite desktop joint test state, and the A1 state is a precise test state under a whole satellite empty load state;
in the state B (corresponding to the third state), all loads are installed on the cabin plates of the satellite, the cabin plates are flatly placed on an installation vehicle, and each cabin plate of the satellite is in an open cabin state, so that initial cable arrangement is completed; the state can meet the requirement of satellite loading comprehensive tests such as satellite loading electric test, satellite function module electric test, satellite information flow test, model flight and the like of the satellite under the wired condition.
And C state (corresponding to a fourth state) satellite loading is to assemble all the cabin plates of the satellite on a satellite main frame in an integrated mode, the platform cabin and the load cabin are overlapped, and the platform cabin and the load cabin are respectively reserved with one cabin plate not-fit cabin, so that faults can be conveniently checked in the electrical performance test, and a positioning block between the two cabins can be removed through negotiation with a designer according to the field condition. The state can meet the requirement of on-off inspection of the whole satellite single machine under the satellite wired condition.
The vacuum thermal test modification is whole-satellite thermal control modification, the whole satellite needs to be completely assembled, the intra-satellite cable connection is complete, all cabin plates are closed, some off-satellite single machines and antenna loads are replaced by thermal control simulation parts, on-satellite and off-satellite heat pipes are installed, thermocouples for thermal tests are installed, and a multi-layer heat insulation assembly is coated. The storage tank is pushed to be in a nitrogen filling state without installing a solar sailboard. The other products except the thermal control simulation part on the satellite are in a normal state. This state is mainly for the next vacuum heat test.
The environmental test modification is carried out after the vacuum thermal test is finished, and the main modification work is as follows: and (3) removing the extraterrestrial thermal control simulation single machine and the antenna in the thermal vacuum state, installing a sample piece, removing the thermocouple for the thermal test and removing the extraterrestrial multilayer thermal insulation assembly. And (4) mounting a mechanical sensor for the test. Other products on the satellite are in a normal state. The next work that can be done after this state is completed includes quality characteristic test, installation of solar windsurfing boards, sinusoidal vibration test, noise test, EMC test, windsurfing board deployment and illumination test, and subsequent leak detection test (full system), etc.
The test modification before leaving factory is the modification for the last time before the satellite leaves factory to test the electrical performance of the satellite, and aims to check whether the satellite can normally work after undergoing all the environmental tests, whether the performance is reduced and whether the satellite meets the factory requirement; the content of the modification mainly comprises the steps of disassembling the extraterrestrial heat pipe and opening the load cabin top plate so that the satellite can better radiate the internal heat in the test state;
the satellite factory modification is the last modification performed when the last test is completed, and the modification operation mainly comprises the steps of combining a load cabin top plate, installing an extraterrestrial heat pipe and assembling the satellite to a final factory state.
In the satellite assembling method provided by the invention, the integrated test whole satellite is formed by carrying out integrated test assembly, the tests under multiple states are carried out, the thermal test refitting is carried out on the basis of the integrated test whole satellite to form the thermal test whole satellite, the environmental test refitting is carried out on the basis of the thermal test whole satellite to form the environmental test whole satellite, the test refitting before leaving factory and the factory refitting are carried out on the basis of the environmental test whole satellite to form the final whole satellite to be launched, the working sequence of each satellite loading stage can be reasonably arranged, the labor cost can be saved, the satellite loading time can be saved, meanwhile, the repeated disassembly and assembly of the satellite and the invalid transportation caused by the repeated replacement of the test sites due to the unreasonable test sequence can be avoided, the risk of damage to the satellite can be reduced, and the mass production of the satellite can be guaranteed.
The following describes in detail a specific embodiment of the satellite assembly process provided by the present invention with reference to the accompanying drawings. Referring to fig. 1, the assembly process of the present invention includes: M1-M24;
the satellite final assembly work is started after the preassembly of the main frame is completed, the preparation of the M1 before the satellite comprises the preparation of a satellite loading file, the preparation of required tooling equipment and the preassembly of the main frame is completed;
after the main frame is assembled, other preparation work further comprises: the structural plate finishes spraying paint, drilling air holes and sticking OSR sheets; the platform cabin bottom plate completes the assembly and thermal control coating of the propulsion system and completes the leakage detection of the system; the precision of the structural plate shell meets the requirement; the single machine and the structural plate are preassembled, and all the connecting screws can be screwed in and out according to the standard; the platform cabin bottom plate, the top plate, the load cabin bottom plate and the partition plate are installed with the main frame, and a positive fastening piece is adopted, anti-loosening glue is coated on the positive fastening piece and the positive fastening piece is screwed down according to standard torque; and a satellite single machine, a bracket and the like are arranged to complete the pasting of the heating plate, the thermocouple and the thermistor.
The M2 main frame splitting comprises: splitting the main frame into a platform cabin main frame and a load cabin main frame; the tightening torque of all fasteners was reviewed.
The electrical test of the state A0 in the M3 is the electrical test of the whole satellite desktop in a combined test state, the test desktop uses a metal aluminum thin plate as a unified 'satellite ground', the grounding parts (points, lines and surfaces) of all on-satellite equipment or cables are connected to the plate as required and then connected to a satellite grounding pile between tests, and the cables are connected for the electrical test of the following contents: the method comprises the following steps of satellite test minimum configuration system electrical interface test, power supply and overall circuit single electrical interface test, measurement and control subsystem single electrical interface test, attitude and orbit control subsystem single electrical interface test, structure and mechanism subsystem single electrical interface test, load subsystem electrical interface test and the like;
the whole satellite comprehensive test in the M4 is to test the function test, the information flow test and the closed-loop model flight of a branch system respectively under the A0 state.
The method comprises the steps that star loading and accurate measurement are carried out in the state A1 of M5, and the main contents comprise installation and accuracy measurement of accuracy single machines such as a thruster, a gyroscope, a sun sensor and a star sensor;
the B state final assembly in M6 is the main assembly step of the satellite, comprising M6A platform cabin assembly and M6B load cabin assembly, and the contained work accounts for more than 70 percent of the total assembly task;
M6A: the steps of platform cabin assembly are as follows:
and adjusting the main frame of the platform cabin, namely placing the main frame of the platform cabin on a special assembly platform of the platform cabin, and adjusting the assembly platform by using a level meter, wherein the parallelism between the main frame of the platform cabin and a horizontal plane is superior to 1mm/1000 mm. A process frame is arranged on the frame, so that the stability of the frame is ensured;
installing a prism on the precision measurement tool and a prism of the bottom plate, and adjusting the prism of the bottom plate to enable the error between the prism of the bottom plate and the prism of the precision measurement tool to be within a range of +/-15';
mounting the platform cabin bottom plate on a satellite tool, mounting each single machine, cables and the like, mounting a thermistor and a thermocouple of the platform cabin bottom plate, and checking redundant materials;
mounting the platform cabin-Y plate on a satellite tool, mounting each single machine, cables and the like, mounting a platform cabin-Y plate thermistor and a thermocouple, and checking redundancy;
mounting the platform cabin-Z plate on a satellite tool, mounting each single machine, cables and the like, mounting a platform cabin-Z plate thermistor and a thermocouple, and checking redundancy;
the platform cabin and the Z plate are installed on a satellite tool, and are provided with single machines, cables and the like, the platform cabin and the Z plate are pasted with thermistors and thermocouples, and redundancy is checked;
the platform cabin and the Y plate are installed on a satellite tool, and are provided with single machines, cables and the like, the platform cabin and the Y plate are pasted with thermistors and thermocouples, and redundancy is checked;
after the mounting plates of the platform cabin are assembled, the whole cabin needs to be further assembled to the state shown in figure 2: and the platform cabin-Y plate is connected with cables between the-Y plate and the-Z plate and between the-Y plate and the + Y plate, the platform cabin-Z plate is combined, the platform cabin-Z plate and the XY surface of the main frame are parallelly and separately placed, and the cables of the-Z plate and the + Y plate are connected and arranged, and the platform cabin + Y plate and the + Z plate are in a flat lying state, so that the platform cabin-Y plate and the platform cabin-Z plate have a cabin-dividing testing function.
M6B: the steps of the load compartment assembly are as follows:
and adjusting the main frame of the load cabin, namely placing the main frame of the load cabin on a special assembly platform for the load cabin, and adjusting the assembly platform by using a level meter, wherein the parallelism between the main frame of the load cabin and a horizontal plane is better than 1mm/1000 mm. Firstly, mounting a load cabin bottom plate, a partition plate and a top plate, and mounting a process frame on the rest surfaces;
the load cabin-Y plate is arranged on the tooling vehicle, each single machine on the mounting plate is connected with a related cable, a thermistor and a thermocouple of the load cabin-Y plate are mounted, and redundancy is checked;
the load cabin and the Z plate are installed on a tooling vehicle, each single machine on the installation plate is connected with a related cable, a thermistor and a thermocouple of the load cabin and the Z plate are mounted, and redundancy is checked;
the load cabin and the Y plate are installed on a tooling vehicle, each single machine on the installation plate is connected with a related cable, a thermistor and a thermocouple of the load cabin and the Y plate are mounted, and redundancy is checked;
the load cabin-Z plate is arranged on a tooling vehicle, each single machine on the mounting plate is connected with a related cable, a thermistor and a thermocouple of the load cabin-Z plate are mounted, and redundancy is checked;
after the load cabin roof is installed with a single machine and connected with related cables, supporting the load cabin roof to a proper height, and checking redundancy;
after the mounting plates of the load compartment are assembled, the whole load compartment needs to be further assembled to the state shown in FIG. 3: the combined load cabin-Y board is connected with cables between the load cabin-Y board and the + Z board, + Y board and the like, the combined load cabin + Z board is connected with cables between the + Y board and the-Z board and the like, the combined load cabin + Y board is used for arranging the cables, the load + Y board is in a 90-degree horizontal lying state, the load cabin-Z board is in a 45-degree open state, and the top board is propped up to a proper height;
m7: after the assembly of the M6A platform cabin and the assembly of the M6B load cabin are completed, the assembly of the B state is finished, and the electrical measurement of the B state can be carried out;
M8-M9: the C state assembly is carried out on the basis of the B state, and mainly comprises the following operations: installing a normal multilayer assembly between the platform cabin and the load cabin, butting the two cabins, completely closing the load cabin before butting, opening the platform cabin and a Y plate at 90 degrees after butting, opening a Z plate at 45 degrees after the load cabin, supporting a top plate of the load cabin to a proper height, closing all other cabin plates, connecting cabin-penetrating cables, and inspecting redundancy as shown in figure 4; wired electric measurement can be carried out after the assembly in the C state is finished;
m10: the whole satellite heat test modification is carried out on the basis of the C state, and the specific operation is as follows: the whole satellite thermal control is modified, an in-satellite thermocouple is installed, a fixed cable in the satellite is bound and reinforced, a platform cabin + Y plate, a load cabin-Z plate and a load cabin top plate are combined, and a plurality of layers of extra-satellite positive samples are arranged;
M11-M12: after the whole satellite thermal test is modified, electrical measurement is carried out, the modification operation of the thermal test is checked to be normal, the whole satellite is not damaged, and the next thermal vacuum test can be developed;
m13: after the whole satellite heat test is finished, the environmental test is modified, and the specific operation steps are as follows: removing the extra-satellite multilayer, removing the extra-satellite thermal control simulation single machine and the antenna, installing a sample piece, opening the platform cabin + Y plate and the load cabin-Z plate, supporting the load cabin top plate to a proper height, removing the intra-satellite thermocouples, pasting a mechanical sensor, binding and reinforcing the intra-satellite cables, and closing the platform cabin + Y plate, the load cabin-Z plate and the load cabin top plate; installing a solar panel, and simultaneously carrying out unfolding and illumination tests on the solar panel;
M14-M20: after the environmental test is modified, all parts except the mechanical sensor on the satellite are normal parts, the satellite is basically in a transmitting state, and the state can be used for carrying out whole satellite precision measurement, single-point leak detection test, quality characteristic test, sinusoidal vibration test, noise test, EMC test and the like in sequence;
M21-M24: the test and modification before delivery of the whole satellite are carried out based on the whole satellite environment test modification, and the specific operation steps are as follows: all the sensors on the satellite can be dismounted without carrying out any operation on the equipment on the satellite; in the state, the whole satellite can be tested before leaving the factory, and the main purpose is to check whether all indexes of the whole satellite are changed through all the environmental tests and whether the whole satellite still meets the factory requirements, and if no problem exists, the satellite can be subjected to factory evaluation and leaves the factory.
In summary, the above embodiments describe the satellite assembly method in detail, but it goes without saying that the present invention includes but is not limited to the configurations listed in the above embodiments, and any modifications based on the configurations provided by the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (10)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011487584.1A CN112705920B (en) | 2020-12-16 | 2020-12-16 | Satellite assembling method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011487584.1A CN112705920B (en) | 2020-12-16 | 2020-12-16 | Satellite assembling method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112705920A CN112705920A (en) | 2021-04-27 |
| CN112705920B true CN112705920B (en) | 2021-08-10 |
Family
ID=75543912
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011487584.1A Active CN112705920B (en) | 2020-12-16 | 2020-12-16 | Satellite assembling method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112705920B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114966209A (en) * | 2022-05-17 | 2022-08-30 | 浙江时空道宇科技有限公司 | Method and device for detecting satellite to ground cabin plate, test equipment and storage medium |
Family Cites Families (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1020198A1 (en) * | 1981-09-16 | 1983-05-30 | Всесоюзный научно-исследовательский и проектно-технологический институт угольного машиностроения | Satellite type automated line |
| US6031486A (en) * | 1998-12-03 | 2000-02-29 | Trw Inc. | Method and apparatus for integration and testing of satellites |
| US8214993B1 (en) * | 2009-11-11 | 2012-07-10 | Coastal Cargo Company, Inc. | Method and apparatus for removing or reinstalling riser pipes of a riser bundle |
| CN102717900B (en) * | 2012-06-26 | 2014-10-15 | 上海卫星工程研究所 | Micro satellite platform suitable for low orbit satellite constellation networking application |
| CN103482082B (en) * | 2013-08-12 | 2016-11-23 | 上海卫星工程研究所 | A kind of Modular micro-satellite platform configuration |
| CN104354874B (en) * | 2014-08-05 | 2017-01-18 | 北京卫星制造厂 | Unitization structure assembling method for disassembly and reassembly through flexible traction |
| US20160288931A1 (en) * | 2015-03-31 | 2016-10-06 | Worldvu Satellites Limited | Satellite frame and method of making a satellite |
| US9908643B2 (en) * | 2015-08-05 | 2018-03-06 | Worldvu Satellites Limited | Passive thermal system providing an embedded interface for heat pipes |
| CN105928542B (en) * | 2016-04-15 | 2019-07-19 | 上海微小卫星工程中心 | A method of manufacturing a satellite |
| CN106542114B (en) * | 2016-11-03 | 2019-05-03 | 上海卫星工程研究所 | Lateral mass center high-precision ensuring method of the parallel connection tiling tank satellite in the AIT stage |
| CN109050977B (en) * | 2018-07-02 | 2020-07-14 | 上海卫星工程研究所 | High-orbit satellite final assembly method based on double-component unified propulsion system |
| CN109229422A (en) * | 2018-11-14 | 2019-01-18 | 长光卫星技术有限公司 | A kind of deck board formula satellite configuration and its assembly method |
| CN109484673B (en) * | 2018-12-24 | 2022-04-22 | 深圳航天东方红海特卫星有限公司 | Load platform separated remote sensing micro satellite configuration and assembly method thereof |
| CN110450981A (en) * | 2019-08-14 | 2019-11-15 | 上海卫星工程研究所 | Deployable separate type satellite platform and its assembly application method |
| CN110675718B (en) * | 2019-09-29 | 2021-05-07 | 南京理工大学 | Ground education satellite kit that can realize standard CubeSat function and its demonstration method |
| CN111230474B (en) * | 2020-01-10 | 2021-03-02 | 哈尔滨工业大学 | Microsatellite assembly device, parallel assembly equipment and assembly method |
| CN111274686B (en) * | 2020-01-15 | 2022-08-19 | 哈尔滨工业大学 | Batch microsatellite test method and device |
| CN111651837B (en) * | 2020-06-03 | 2023-03-24 | 中国科学院微小卫星创新研究院 | Satellite thermal control management system and method |
-
2020
- 2020-12-16 CN CN202011487584.1A patent/CN112705920B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN112705920A (en) | 2021-04-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112705920B (en) | Satellite assembling method | |
| Qi et al. | Vibration of a satellite structure with composite lattice truss core sandwich panels | |
| CN113919048B (en) | A modular configuration layout method to adapt to satellite incremental payload changes | |
| Perl et al. | Test requirements for launch, upper-stage, and space vehicles | |
| Command | Test Requirements for Launch, Upper-stage and Space Vehicles | |
| CN110146319B (en) | A structural health monitoring experimental device and method for CubeSat mounting | |
| Engberg et al. | Modal survey test of the SOTV 2x3 meter off-axis inflatable concentrator | |
| Zuckermandel et al. | Design, build, and testing of TacSat thin film solar arrays | |
| Gwozdecky | Wiring harness design methodologies and assembly integration and test for a modular microsatellite platform | |
| Loghry et al. | Path to the First Flight of the SL-OMV | |
| Demenko et al. | Evaluation of spacecraft composite structure load-carrying capability by shock test | |
| Qin et al. | Frequency Design and Test Verification of CAST2000 Small Satellite Platform | |
| Skullney et al. | Structural design of the MSX spacecraft | |
| Kim et al. | Structural Soundness Verification of a Composite Oxidant Propulsion Tank for Space Launch Vehicles Through a Structural Static Test | |
| DiSebastian III | RIGEX: Preliminary design of a rigidized inflatable get-away-special experiment | |
| Stephens | A2100 commercial satellites integrated mechanical analysis | |
| Jiaguo et al. | Design of Spacecraft Configuration and Assembly | |
| Baghal | Assembly, integration, and test methods for operationally responsive space satellites | |
| Quan et al. | Unified Longeron-Stringer Design for Cost-Effective and Efficient Structural Airframes for Collegiate Liquid Sounding Rockets | |
| Kuo et al. | Coupled load analysis application on FORMOSAT-2 development | |
| GEORGE et al. | NUCLEAR SHUTTLE SYSTEMS DEFINITION STUDY | |
| Cottingham et al. | Lessons Learned during Thermal Hardware Integration on the Global Precipitation Measurement Satellite | |
| Sadkin | Spacecraft quasi-static test performed on a shaker | |
| Eppler | An Optimized Small Satellite Bus and Structure for the THEMIS Mission | |
| Ampatzoglou et al. | Research Article Design, Analysis, Optimization, Manufacturing, and Testing of a 2U Cubesat |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |