CN112988121A - High-adaptability spacecraft program design method, spaceborne computer and spacecraft - Google Patents
High-adaptability spacecraft program design method, spaceborne computer and spacecraft Download PDFInfo
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Abstract
The invention discloses a high-adaptability space vehicle program design method, an on-board computer and a space vehicle, wherein the method comprises the following steps: s1, the content of the flight program is not embedded in the satellite affair software, the flight program which needs the satellite to operate independently according to time is set as program control instructions which are executed in sequence according to the time sequence, and the program control instruction set is stored in a first memory of the satellite-borne computer; storing the housekeeping software program into a second memory of the on-board computer; and S2, synchronously debugging, verifying and upgrading the flight program and the housekeeping software respectively. The invention realizes the autonomous operation of the satellite according to the flight program based on the program control instruction set, and carries out the design iteration of the flight program and the whole satellite development process in parallel, thereby greatly reducing the period and the cost, fully adapting to the use requirement of the low-orbit satellite giant constellation and laying a foundation for better establishing the low-orbit satellite giant constellation.
Description
Technical Field
The invention relates to the field of satellite software design, in particular to a high-adaptability aerospace craft program design method, an on-board computer and an aerospace craft.
Background
In order to meet the increasing global satellite network access requirement, particularly to solve the internet access problem in rural areas, ocean areas and other areas, satellite internet services, especially low-orbit satellite constellations, are actively explored and developed at home and abroad, and the satellite internet services have global internet access capability. Aiming at the low-orbit satellite constellation applied in commercialization, in order to realize no dead angle coverage in the world, the low-orbit satellite constellations are all configured into giant constellations, wherein 17 batches of 1015 satellites are transmitted by the Starlink plan of the SpaceX company in 1 month and 21 days in 2021 year, 4.2 million satellites are planned in the whole system construction, and the transmission plan is far superior to that of the traditional satellites. In addition, the low-orbit satellite constellation can be served only by a certain scale, the initial investment is large, and for better construction of the low-orbit satellite constellation,
the cost reduction and the rapid design of the low-orbit satellite are the necessary routes.
The traditional satellite model development task needs to go through three stages of initial sampling, identification and sample correction, high reliability and high success rate are achieved with long period and high cost, so that the aerospace industry in China obtains remarkable achievement in the last decades and obtains sufficient technical accumulation. The construction of low-orbit satellite constellations in the new era needs to be changed from high quality to high efficiency and high benefit. At present, most of cubic satellite and small satellite projects begin to adopt a design scheme of 'one-step sampling', the development period and the cost are greatly reduced, but the development period in the sampling stage is still longer, particularly, 4 to 6 months are often required for development of a satellite-borne computer and satellite affair software, the development period is at least 1 to 2 months longer than that of other components on a satellite in the same stage, because a flight program and the satellite affair software are usually solidified together by a traditional satellite, the flight program can also be iteratively updated after a desktop combined test, the change of any one of the flight program and the satellite affair software needs to be re-burnt, and the waste of time and cost is caused. In addition, the low-orbit satellite is often short in design life, a new satellite needs to be timely sent to replace and supplement a failed satellite in the long-term operation process of the constellation, and the satellite also needs to have a short development period.
Disclosure of Invention
The invention aims to at least solve the technical problems in the prior art, and particularly provides a high-adaptability aerospace craft program design method, an on-board computer and an aerospace craft.
In order to achieve the above object of the present invention, according to a first aspect of the present invention, there is provided a high-adaptability spacecraft programming method comprising: step S1, the content of the flight program is not embedded in the satellite affair software, the flight program which needs the satellite to operate independently according to time is set as a program control instruction set which is executed in sequence according to time sequence, and the program control instruction set is stored in a first memory of the satellite-borne computer; storing the housekeeping software into a second memory of the on-board computer; and step S2, synchronously debugging, verifying and upgrading the flight program and the housekeeping software respectively.
The technical scheme is as follows: the method realizes the autonomous operation of the satellite according to the flight program based on the program control instruction set, does not need to solidify the content of the flight program to the satellite affair software any more, changes the solidification relation between the traditional satellite flight program and the satellite affair software, carries out the design iteration of the flight program and the whole satellite development process in parallel, greatly reduces the period and the cost, fully adapts to the design and use requirements of the giant constellation of the low-orbit satellite, and lays a foundation for better establishing the giant constellation of the low-orbit satellite. When the content needs to be changed and upgraded in the debugging and verifying processes of the flight program, the content of the program control instruction set only needs to be changed and uploaded to the first memory, the design state of the housekeeping software does not need to be changed, the housekeeping software code does not need to be repeatedly changed and burnt, and the method is more flexible and efficient.
In a preferred embodiment of the present invention, the program-controlled instruction set is triggered by a first event and then runs in time sequence, the house keeping software program is triggered by a second event, and the first event and the second event may be the same or different; and when the first event and the second event are the same, the first event and the second event are both an electricity-on event of the aerospace craft or a separation event of the aerospace craft and the rocket.
The technical scheme is as follows: the spacecraft (such as a satellite) can automatically run a flight program according to the time sequence after being integrally powered on or separated from a rocket, and can autonomously run the housekeeping software.
In a preferred embodiment of the present invention, in step S2, the process of designing, debugging, verifying and upgrading the flight program in the first memory includes: s21, synchronously designing and developing each single aircraft, an on-board computer, a housekeeping software program and an initial flight program of the spacecraft, wherein the initial flight program comprises an initial orbit section flight program of the spacecraft, the initial orbit section flight program is set into an initial program control instruction set which is sequentially executed according to a time sequence and is uploaded to a first memory through a measurement and control channel, and the housekeeping software program is stored into a second memory; step S22, performing a desktop joint test, wherein the desktop joint test comprises the step of performing an electrical joint test on each subsystem and load of the platform by taking a real-time simulator and a satellite-borne computer as centers; step S23, iteratively upgrading the flight program in the first memory according to the desktop joint test result; and step S24, performing aerospace craft assembly after the single machines, the subsystems and the loads are debugged, supplementing and perfecting an antenna unfolding program and/or a solar wing unfolding program (namely a sailboard unfolding program) in the flight program of the first memory, and performing a complete machine test.
The technical scheme is as follows: the design, debugging, verification and updating of the flight program are realized independently of the housekeeping software, the flight program is developed in parallel with the whole satellite development process, the period and the cost are greatly reduced, meanwhile, the program which is required to be automatically executed on the satellite according to the time in the flight program can be executed according to the requirement, and the housekeeping software is not embedded with the related flight program.
In a preferred embodiment of the invention, the initial flight procedure comprises all or part of four procedures of powering up and enabling each component in an attitude and orbit control subsystem of the aerospace craft, unfolding the sailboard, unlocking the antenna and unfolding the antenna.
The technical scheme is as follows: these procedures enable flight control of the initial orbit segment of the aerospace vehicle.
In a preferred embodiment of the present invention, the first memory is FLASH, and/or the second memory is EEPROM.
The technical scheme is as follows: the first memory is FLASH, which is convenient for fast erasing and updating of the whole block, the cost is low, the reliability of the EEPROM is high, only a single byte can be erased and modified, and the software debugging and modification are convenient.
To achieve the above object, according to a second aspect of the present invention, there is provided an on-board computer comprising a processor, a first memory and a second memory connected to the processor; the first memory stores a flight program which is set as a program control instruction set sequentially executed according to a time sequence; the second memory stores a house keeping software program.
The technical scheme is as follows: the flight program and the satellite affair software are stored in the satellite-borne computer in a separated mode, the solidification relation between the traditional satellite flight program and the satellite affair software is changed, the design iteration of the flight program and the whole satellite development process are carried out in parallel, the period and the cost are greatly reduced, meanwhile, the flight program is set to be a program control instruction set, the satellite can run autonomously according to the flight program, the flight program content does not need to be solidified to the satellite affair software any more, the use requirement of the low-orbit satellite giant constellation is fully met, and a foundation is laid for better building the low-orbit satellite giant constellation.
To achieve the above object, according to a third aspect of the present invention, there is provided an aerospace vehicle comprising the on-board computer of the present invention.
The technical scheme is as follows: the aerospace craft stores the flight program and the satellite affair software separately, changes the solidification relation between the traditional satellite flight program and the satellite affair software, carries out the design iteration of the flight program and the whole satellite development process in parallel, greatly reduces the period and the cost, simultaneously sets the flight program into a program control instruction set, realizes the autonomous operation of the satellite according to the flight program, does not need to solidify the flight program content to the satellite affair software any more, fully adapts to the use requirement of the low-orbit satellite giant constellation, and lays a foundation for better establishing the low-orbit satellite giant constellation.
In a preferred embodiment of the present invention, the spacecraft is separated from the rocket, and then autonomously operates according to a program control instruction set to establish an initial attitude and a satellite-to-ground communication link, and is controlled by a ground remote control instruction through the satellite-to-ground communication link to complete various tasks.
The technical scheme is as follows: the program control instruction set ensures that the aerospace craft can successfully establish the initial attitude.
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Fig. 1 is a schematic flow chart of a high-adaptability aerospace vehicle programming method according to an embodiment of the invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention.
In the description of the present invention, unless otherwise specified and limited, it is to be noted that the terms "mounted," "connected," and "connected" are to be interpreted broadly, and may be, for example, a mechanical connection or an electrical connection, a communication between two elements, a direct connection, or an indirect connection via an intermediate medium, and specific meanings of the terms may be understood by those skilled in the art according to specific situations.
Aiming at the characteristics of low cost, high batch production and short development period of low-orbit constellation satellites, the invention discloses a high-adaptability spacecraft programming method, which comprises the following steps in a preferred embodiment as shown in figure 1:
step S1, the content of the flight program is not embedded in the satellite affair software, the flight program which needs the satellite to operate independently according to time is set as a program control instruction set which is executed in sequence according to time sequence, and the program control instruction set is stored in a first memory of the satellite-borne computer;
storing the housekeeping software program into a second memory of the on-board computer; the house keeping software programs preferably include, but are not limited to, house keeping management programs, time management programs, attitude and orbit control management programs, and thermal control management programs.
And step S2, synchronously debugging, verifying and upgrading the flight program and the housekeeping software respectively.
In the embodiment, different from the traditional satellite affair software which can be designed only by determining the flight program of the initial orbit segment, the method does not need to control and embed the autonomous operation part program on the satellite in advance, can flexibly adjust the flight program according to the development progress and the test specific conditions of each subsystem, achieves the purpose of carrying out the development and debugging of the satellite affair computer and the software in parallel with the whole satellite test, reduces the time cost and the economic cost of iterative design, and lays a foundation for the rapid mass application of the giant low-orbit constellation satellite.
In this embodiment, preferably, the first memory is FLASH and/or the second memory is EEPROM. The program control instruction refers to an instruction executed according to a time sequence in the satellite control instruction and is uploaded to FLASH of the satellite-borne computer through a measurement and control channel. Preferably, other memories are also provided for storing logs, important data, and the like.
In a preferred embodiment, the set of program-controlled instructions is triggered by a first event and then run in a chronological order, and after the first event occurs, the instructions in the set of program-controlled instructions are executed in sequence according to a preset chronological order. The star affair software program is triggered to run through a second event, and the first event and the second event can be the same or different;
and when the first event and the second event are the same, the first event and the second event are both an electricity-on event of the aerospace craft or a separation event of the aerospace craft and the rocket.
In this embodiment, the specific process of the high-adaptability space aircraft programming method may include:
1. the on-board computer and the star affair software are designed to be universal, unnecessary logic judgment is reduced, and the storage and sequential execution of program control instructions of the program control instruction set in the FLASH are supported; the star affair software program does not embed the working sequence content of the upper assembly of the initial orbit section star in the flight program, such as the electrification and the enabling of each assembly of the attitude and orbit control subsystem, the unfolding of the sailboard, the unlocking of the antenna and the like.
2. The satellite measurement and control subsystem is designed with high adaptability and supports setting the working content related to the flight program of the initial orbit segment of the satellite and needing to be automatically executed according to time as a program control instruction set; the content of the satellite program control instruction set can be flexibly changed in each stage before transmission, including development, test and the like, and is uploaded to a satellite-borne computer FLASH through a measurement and control channel, and the whole satellite is powered on and then is executed according to the time sequence, so that the effect of autonomous operation on the satellite is achieved.
3. Determining an initial flight program according to the on-orbit task, the flight scheme and the on-satellite product development state of the satellite, setting the initial orbit section working time sequence as a program control instruction set to be uploaded to an on-board computer FLASH for desktop joint test without embedding the initial orbit section working time sequence into the satellite software; the design state of the housekeeping software does not need to be changed any more for the iterative upgrade of the flight program, namely, the housekeeping software codes are repeatedly modified and burnt, so that the method is more flexible and efficient.
4. And performing iterative upgrade on the flight program according to the conditions of the desktop joint test, the whole satellite development and the test, supplementing and perfecting the contents of antenna expansion, solar wing expansion and the like which are not tested in the desktop joint test process, and performing controlled solidification to be a program control instruction and then uploading and standby emission.
5. After the satellite and the satellite are separated, an initial attitude and a satellite-ground communication link are established according to the autonomous operation of the program control instruction set, and then the control is carried out through a ground remote control instruction to complete various tasks.
By the flight program design method, the on-satellite program autonomous operation mode based on the program control instruction set is adopted, the design iteration of the flight program and the whole satellite development process are carried out in parallel, the period and the cost are greatly reduced, the use requirement of the low-orbit satellite giant constellation is fully met, and a foundation is laid for better building the low-orbit satellite giant constellation.
The innovation points of the process are as follows: the method has the advantages that the autonomous operation of the satellite according to a flight program is realized based on a program control instruction set, the content of the flight program does not need to be solidified to the satellite affair software any more, the flight program design is carried out in parallel with the development of an on-board computer (the satellite affair software), and the development and debugging time of the on-board computer (the satellite affair software) is greatly reduced; in the process of desktop combined test, the contents of the debugging and modifying flight program only need to change the contents of the program control instruction and upload the program control instruction, and the design state of the housekeeping software does not need to be changed, namely, the housekeeping software codes are repeatedly modified and burned, so that the method is more flexible and efficient.
In a preferred embodiment, in step S2, the process of debugging, verifying and upgrading the flight program in the first memory includes:
s21, synchronously designing and developing each single aircraft, spaceborne computer, housekeeping software and primary flight program of the spaceflight vehicle, wherein the primary flight program comprises an initial orbit section flight program of the spaceflight vehicle, the initial orbit section flight program is set to be a primary program control instruction set which is sequentially executed according to time sequence and is uploaded to a first memory through a measurement and control channel, and the housekeeping software program is stored in a second memory;
step S22, performing desktop joint test, wherein the desktop joint test comprises the step of performing electrical joint test on each subsystem and load of the platform by taking a real-time simulator and a satellite-borne computer as centers;
step S23, iteratively upgrading the flight program in the first memory according to the desktop joint test result, preferably but not limited to upgrading the flight program from the aspects of program content, execution sequence, time requirement and the like;
and step S24, performing aerospace craft assembly after the single machines, the subsystems and the loads are debugged, supplementing and perfecting contents such as antenna unfolding and/or solar wing unfolding programs in the flight program of the first memory, and performing a complete machine test.
In the present embodiment, preferably, the first version of flight procedure includes, but is not limited to, all or part of the power-up and enable procedure, the sail deployment procedure, the antenna unlock procedure, and the antenna deployment procedure of each component in the attitude and orbit control subsystem of the space vehicle.
In a preferred embodiment, the on-board computer comprises a processor, a first memory and a second memory, wherein the first memory and the second memory are connected with the processor; the first memory stores a flight program which is set as a program control instruction set sequentially executed according to a time sequence; the second memory stores a star software program. The second memory may be a memory separate from the processor or may be a memory internal to the processor.
In the present embodiment, the flight procedure preferably includes, but is not limited to, all or part of the power-up and enable procedure, the sail deployment procedure, the antenna unlock procedure, and the antenna deployment procedure of each component in the satellite upper attitude and orbit control subsystem.
In an application scenario of the embodiment, taking a development process of a first satellite (initial development) of a certain type of satellite as an example, the development is performed by using the method, and the process flow is as follows:
firstly, determining a whole satellite design scheme according to the on-orbit task and the flight scheme of the satellite, and performing single-machine index decomposition and technical requirement issuing, wherein the period is 1 month.
Secondly, synchronously developing each single machine and designing an initial version flight program, wherein the on-board computer and the housekeeping software are designed in a universal mode, the flight program does not need to be designed and embedded, only 3 months are needed, and the traditional method needs to design a special on-board computer of the type and needs 5 months; the method can reduce development time by 2 months at this stage.
Thirdly, after the development of the satellite borne computer is finished, the initial flight program is set as a program control instruction set to be uploaded, the flight program is iteratively upgraded according to the situation of the desktop joint test, and the design state of the satellite borne computer (satellite affair software) does not need to be changed (namely, the code of the satellite affair software is repeatedly modified and burnt) by using the method, so that the desktop joint test is more flexible and efficient compared with the traditional method, only 3 months are needed, and 4 months are needed for changing the state of the satellite borne computer by the traditional method; the method can reduce development time by 1 month at this stage.
And fourthly, performing satellite final assembly after debugging of each single machine, each subsystem and each load is finished, performing a whole satellite test, finally modifying and controlling the flight program in the process (supplementing and perfecting the contents of tests which are not performed in the desktop joint test process, such as antenna expansion, solar wing expansion and the like), uploading the program control instruction set to a satellite-borne computer FLASH, and requiring 2 months in the stage.
Fifthly, the satellite is in butt joint with a carrier after completing the whole satellite test and is launched according to a plan, and the period of the stage is 1 month; after the satellite and the arrow are separated when the vehicle arrives at the designated position, an initial attitude and a satellite-ground communication link are established according to the program control instruction set, and then the vehicle is controlled through a ground remote control instruction to complete various tasks.
In this application scenario, the programming method provided by this patent is expected to reduce the lead satellite development cycle from 13 months to 10 months.
In another application scenario of the embodiment, a process of developing a satellite fault reissue satellite (inherited type) of the type in a low-earth constellation is taken as an example. The method is used for development, and the process flow is as follows:
firstly, determining a whole satellite design scheme according to the on-orbit task of the reissued satellite, the fault condition of the original satellite and a new flight scheme, and performing single-machine type selection and improved design, wherein the period still needs 1 month.
Secondly, synchronously developing each improved single machine, inheriting single machine matching and designing an initial flight program, wherein most of the improved single machines can be inherited due to the improved design, and the on-board computer can be directly used under the condition that the on-board computer does not break down, and the single machine development time can be reduced by 3 months only in the stage of only 2 months; if the design state does not need to be changed (the original satellite does not break down and leaves the orbit after the service life is over), the flight program is designed and then set as a program control instruction set for uploading, all the other single machines continue to use the equipment of the model for assembly, and the test can be carried out, and only 1 month is needed under the condition.
And thirdly, after the development of the satellite borne computer is completed, performing desktop joint test according to the content of the initial flight program, and performing iterative upgrade on the flight program, wherein the design state of the satellite borne computer does not need to be changed any more, and because most products such as loads, platforms, single computers and satellite borne computers are used continuously, the period of the stage is only 1 month, and the time can be saved by 2 months.
And fourthly, carrying out satellite final assembly after debugging of the single machines, the subsystems and the loads is finished, only carrying out simple whole-satellite tests because most single machines are selected to be continuously used, finally modifying and determining the flight program in the process, solidifying the program control instruction set and uploading the program control instruction set to the satellite-borne computer, wherein only 1 month is needed in the stage, and the whole-satellite test time of 1 month can be saved.
And fifthly, the satellite is in butt joint with a carrier after completing the whole satellite test, is launched according to a plan (1 month is needed), reaches a designated position to separate a satellite and an arrow, establishes an initial attitude and a satellite-ground communication link according to a program control instruction set, and is subsequently controlled through a ground remote control instruction to complete a reissue task.
In the application scenario, the programming method provided by the patent is expected to reduce the development period of the reissued satellite from 13 months to 6(5) months.
The invention also discloses an aerospace vehicle which comprises the spaceborne computer in a preferred embodiment.
In a preferred embodiment, after the aerospace craft and the rocket are separated, the aerospace craft and the rocket autonomously operate according to a program control instruction set to establish an initial attitude and a satellite-ground communication link, and are controlled by a ground remote control instruction through the satellite-ground communication link to complete various tasks.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. A high-adaptability aerospace vehicle programming method, comprising:
step S1, the content of the flight program is not embedded in the satellite affair software, the flight program which needs the satellite to operate independently according to time is set as a program control instruction set which is executed in sequence according to time sequence, and the program control instruction set is stored in a first memory of the satellite-borne computer; storing the housekeeping software program into a second memory of the on-board computer;
and step S2, synchronously debugging, verifying and upgrading the flight program and the housekeeping software respectively.
2. The high-adaptability space vehicle programming method according to claim 1, wherein the set of programmed instructions is triggered by a first event and then run in chronological order, and the star software program is triggered by a second event, and the first event and the second event may be the same or different;
and when the first event and the second event are the same, the first event and the second event are both an electricity-on event of the aerospace craft or a separation event of the aerospace craft and the rocket.
3. The high-adaptability aerospace vehicle programming method of claim 1, wherein in step S2, the process of designing, debugging, verifying and upgrading the flight program in the first memory comprises:
s21, synchronously designing and developing each single aircraft, an on-board computer, a housekeeping software program and an initial flight program of the spacecraft, wherein the initial flight program comprises an initial orbit section flight program of the spacecraft, the initial orbit section flight program is set into an initial program control instruction set which is sequentially executed according to a time sequence and is uploaded to a first memory through a measurement and control channel, and the housekeeping software program is stored into a second memory;
step S22, performing a desktop joint test, wherein the desktop joint test comprises the step of performing an electrical joint test on each subsystem and load of the platform by taking a real-time simulator and a satellite-borne computer as centers;
step S23, iteratively upgrading the flight program in the first memory according to the desktop joint test result;
and step S24, performing aerospace craft assembly after the single machines, the subsystems and the loads are debugged, supplementing and perfecting an antenna unfolding program and/or a solar wing unfolding program in the flight program of the first memory, and performing a complete machine test.
4. The high-adaptability space shuttle program design method of claim 1, wherein the initial flight program comprises all or part of four procedures of powering up and enabling each component in the attitude and orbit control subsystem of the space shuttle, sailboard unfolding procedure, antenna unlocking procedure and antenna unfolding procedure.
5. The high-adaptability space vehicle programming method according to claim 1, wherein the first memory is FLASH and/or the second memory is EEPROM.
6. An on-board computer comprising a processor, a first memory and a second memory coupled to the processor;
the first memory stores a flight program which is set as a program control instruction set sequentially executed according to a time sequence;
the second memory stores a house keeping software program.
7. The on-board computer of claim 6, wherein the flight procedure comprises all or part of the powering and enabling procedure, the sailboard unfolding procedure, the antenna unlocking procedure and the antenna unfolding procedure of each component in the satellite attitude and orbit control subsystem.
8. An on-board computer as claimed in claim 6 or claim 7 wherein the first memory is FLASH and/or the second memory is EEPROM.
9. An aerospace vehicle comprising an on-board computer as claimed in any one of claims 6 to 8.
10. An aerospace vehicle as claimed in claim 9, wherein the aerospace vehicle is configured to operate autonomously after separation from the rocket in accordance with the set of programming instructions to establish an initial attitude and a satellite-to-ground communications link, and to perform tasks under control of ground remote control instructions via the satellite-to-ground communications link.
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