CN117799863A - Compact disc type batch uplink aircraft - Google Patents
Compact disc type batch uplink aircraft Download PDFInfo
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- CN117799863A CN117799863A CN202311620362.6A CN202311620362A CN117799863A CN 117799863 A CN117799863 A CN 117799863A CN 202311620362 A CN202311620362 A CN 202311620362A CN 117799863 A CN117799863 A CN 117799863A
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- 238000003860 storage Methods 0.000 claims abstract description 42
- 238000004891 communication Methods 0.000 claims abstract description 20
- 238000005259 measurement Methods 0.000 claims abstract description 19
- 238000007639 printing Methods 0.000 claims abstract description 16
- 238000009826 distribution Methods 0.000 claims abstract description 13
- 238000000034 method Methods 0.000 claims abstract description 13
- 230000008569 process Effects 0.000 claims abstract description 11
- 238000010146 3D printing Methods 0.000 claims abstract description 5
- 238000012423 maintenance Methods 0.000 claims abstract description 5
- 239000003380 propellant Substances 0.000 claims abstract description 5
- 230000005611 electricity Effects 0.000 claims abstract description 4
- 230000006870 function Effects 0.000 claims description 28
- 230000007246 mechanism Effects 0.000 claims description 26
- 238000013461 design Methods 0.000 claims description 21
- 238000000926 separation method Methods 0.000 claims description 11
- 238000003384 imaging method Methods 0.000 claims description 10
- 238000004140 cleaning Methods 0.000 claims description 6
- 230000006835 compression Effects 0.000 claims description 5
- 238000007906 compression Methods 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 238000001514 detection method Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 230000008447 perception Effects 0.000 claims description 3
- 238000007726 management method Methods 0.000 description 10
- 230000001174 ascending effect Effects 0.000 description 6
- 230000009471 action Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000003825 pressing Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000010365 information processing Effects 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/244—Spacecraft control systems
-
- 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
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Radar, Positioning & Navigation (AREA)
- Automation & Control Theory (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Navigation (AREA)
Abstract
The invention discloses a compact disc type batch uplink aircraft, which comprises: the integrated propulsion system is used for providing thrust required by track maneuvering and track maintenance and comprises an integrated storage tank and an integrated printing thruster, and the integrated storage tank is matched with the integrated printing thruster; the integrated storage tank, the mounting plate and the sailboard form a main bearing structure of the aircraft together, strength and rigidity required in the operation process of the aircraft are provided, the basic shape of the aircraft is kept, and the 3D printing storage tank is arranged in the integrated storage tank and is used for storing the propellant of the aircraft; the integrated printing thruster is used for generating rated thrust; the electronic module is arranged on the +Y surface in the aircraft and is used for comprehensive electricity of the whole satellite, power supply and distribution and measurement and control communication; the MEMS sensitive element is arranged on the +Y plane in the aircraft and is used for providing inertial sensitive information of the aircraft; the function multiplexing star sensor is matched with the MEMS sensing element and the electronic module and is used for determining the gesture track of the aircraft.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a compact disc type batch uplink aircraft.
Background
With the continuous development of aerospace industry, various frequent aerospace activities put more demands on functions, batch rapid launching and the like of the aircraft. In the traditional aircraft design, the aircraft system is mostly divided into attitude and orbit control, measurement and control data transmission, power supply and distribution, structure, thermal control and load aliquotation systems, the design among all the subsystems is relatively independent, the interface is clear, the communication among the subsystems is reduced, but the designed aircraft deployment is globally optimal, the redundancy is too high, and the compactness is insufficient. Meanwhile, as the configuration design difference of the plurality of aircrafts is obvious, the carrying uplink mode is mostly independent uplink, and the launching space allowance of the carrier rocket is difficult to be effectively utilized. Such aircraft designs present two types of problems: on one hand, the designed aircraft has limited functional density, and the interaction among subsystems brings redundant design, so that the utilization efficiency of the whole system is low; on the other hand, the design thought of the independent ascending aircraft is difficult to meet the requirement of high emission quantity in the future.
Therefore, how to design an aircraft capable of uplink in batches with a compact structure for realizing low-cost large-scale satellite constellation development and deployment is a problem to be solved in the prior art.
Disclosure of Invention
The invention aims to provide an aircraft which is compact in structure and can ascend in batches.
The invention provides a compact disc type batch uplink aircraft, which comprises:
the integrated propulsion system is used for providing thrust required by rail maneuvering and rail maintenance and comprises an integrated storage tank and an integrated printing thruster, and the integrated storage tank is matched with the integrated printing thruster;
the integrated storage tank, the mounting plate and the sailboard form a main bearing structure of the aircraft together, strength and rigidity required in the running process of the aircraft are provided, the basic shape of the aircraft is maintained, and the 3D printing storage tank is arranged in the integrated storage tank and is used for storing propellant of the aircraft; the integrated printing thruster is used for generating rated thrust;
the electronic module is arranged on the +Y surface in the aircraft and is used for comprehensive electricity of the whole satellite, power supply and distribution and measurement and control communication;
the MEMS sensitive element is arranged on the +Y plane in the aircraft and is used for providing inertial sensitive information of the aircraft;
and the functional multiplexing star sensor is matched with the MEMS sensitive element and the electronic module and is used for determining the gesture track of the aircraft.
Preferably, the integrated compact propulsion system further comprises: the device comprises an annular buffer cavity, an electromagnetic valve, a pressure reducing valve and a pressure sensor;
the annular buffer cavity is 3D printed in the integrated storage tank and used for heating working media;
the electromagnetic valve is arranged around the integrated printing thruster and is used for controlling the thrust switch;
the pressure reducing valve is arranged on the inner side of the integrated storage tank and is used for controlling the pressure in the buffer cavity;
the pressure sensor is arranged on the inner side of the integrated storage tank and is used for collecting pressure values in the integrated storage tank and the buffer cavity.
Preferably, the integrated printing thruster is provided with 12 stations, and the 6-degree-of-freedom decoupling layout is arranged on the integrated storage box structure.
Preferably, the electronic module includes: the high-performance processor module, the power distribution management module, the measurement and control communication module and the GNSS navigation module are integrated on a PCB and mutually matched, and the PCB is fixed in the aircraft;
the high-performance processor module is used for communicating with an external single machine and collecting analog quantity information; the power distribution management module receives an instruction from the high-performance processor module and feeds back state information to the high-performance processor module at the same time; the measurement and control communication module is used for executing whole-satellite radio measurement and control communication; the GNSS navigation module is used for maintaining and track positioning.
Preferably, the function multiplexing star sensor is arranged in the aircraft and is used for multiplexing with the function of tracking and aiming load on the satellite, and accurately tracking and aiming the target object in the working process.
Preferably, the system further comprises a payload, wherein the payload is arranged in the +X direction of the aircraft and is used for realizing tasks or functions executed by the aircraft.
Preferably, the payload is also used for aircraft perception detection and space debris removal, and a generalized interface is adopted to carry imaging load and debris cleaning load;
the imaging load is used for imaging a space target; the debris cleaning load is used for space debris capture and removal.
Preferably, the device also comprises a star connection release structure, a compression mechanism and a guide rail;
the compressing mechanism comprises a separating mechanism and a spring, wherein the separating mechanism is used for providing initial separating speed and comprises a driving end and a driven end; the driving end and the driven end are respectively arranged on the separated satellite and the separated satellite, and the compression spring is positioned in the driving end and the driven end; the guide rail is used for positioning and guiding the separation initial process.
Preferably, the star connection release structure is connected through a threaded structure, and the compressing mechanism realizes limit and bearing through a boss and a groove between the aircrafts.
Preferably, after the aircraft enters the track, the star connection release structure is unlocked, a spring in the compressing mechanism acts on the star, and the aircraft realizes the multi-group batch ascending and grouping on-track release of the compact disc type design aircraft under the limit of the guide rail.
Compared with the prior art, the scheme provided by the invention at least comprises the following beneficial technical effects:
the disk type satellite realizes high functional density, high carrier-to-mass uplink of the aircraft through the compact design of the main system of the aircraft. Specifically, by structural function integrated compact propulsion system design, a propellant storage tank is used as a whole satellite main bearing structure, so that redundant structural mass in conventional satellite design is omitted; through the design of the high-integration electronic module, complex cable connection of each electronic unit in the conventional satellite design is omitted, and the functional density of the system is improved; through the high-integration MEMS sensitive element and the functional multiplexing star sensor, the whole star light-weight design is realized under the condition of meeting the measurement precision of the whole star gesture; through the batch uplink separating mechanism, the large-batch combined uplink of the aircraft is realized, the carrying allowance is efficiently utilized, and the single star average emission cost is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are only embodiments of the present invention, and other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of a compact disc type aircraft configuration;
FIG. 2 is another schematic illustration of a compact disc type aircraft configuration;
FIG. 3 is a schematic diagram of a compact disc type aircraft structural function integrated compact propulsion system;
FIG. 4 is a schematic view of a batch upstream of disc-type aircraft.
In the figure, a 1-solar cell and a solar sensor; 2-payload; 3-an integrated compact propulsion system; 4-electronics module; 5-MEMS sensitive elements; 6-star sensor; 7-a load bearing structure; 8-a thruster; 9-an annular buffer chamber; 10-3D printing of the tank; 11-valve; 12-carrying an uplink mounting surface; 13-a drive end of the separation mechanism; 14-a passive end of the separation mechanism; 15-compact disc type aircraft.
Detailed Description
A compact disc type batch uplink aircraft of the present invention will be described in more detail below with reference to the drawings, in which preferred embodiments of the present invention are shown, it being understood that one skilled in the art could modify the invention described herein while still achieving the advantageous effects of the invention. Accordingly, the following description is to be construed as broadly known to those skilled in the art and not as limiting the invention.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The invention is more particularly described by way of example in the following paragraphs with reference to the drawings. The advantages and features of the present invention will become more apparent from the following description. It should be noted that the drawings are in a very simplified form and are all to a non-precise scale, merely for convenience and clarity in aiding in the description of embodiments of the invention.
Referring to fig. 1 and 2, a compact disc type aircraft 15 according to the present embodiment includes:
the integrated propulsion system is used for providing thrust required by rail maneuvering and rail maintenance and comprises an integrated storage tank and an integrated printing thruster, and the integrated storage tank is matched with the integrated printing thruster;
the integrated storage tank, the mounting plate and the sailboard form an aircraft main bearing structure 7 together, strength and rigidity required in the operation process of the aircraft are provided, and the basic shape of the aircraft is maintained, and the integrated storage tank comprises a 3D printing storage tank 10 for storing the propellant of the aircraft; the integrated printing thruster is used for generating rated thrust;
the electronics module 4 is arranged on the +Y surface in the aircraft and is used for comprehensive electricity of the whole satellite, power supply, power distribution, measurement and control communication;
the MEMS sensitive element 5 is arranged on the +Y plane in the aircraft and is used for providing inertial sensitive information of the aircraft;
and the function multiplexing star sensor 6 is matched with the MEMS sensitive element 5 and the electronics module 4 and is used for determining the attitude orbit of the aircraft.
Specifically, the compact disc type batch uplink aircraft provided by the invention has multiple functions such as imaging, communication, attitude and orbit control and the like, the high-integration MEMS sensitive element 5 and the high-integration electronic module 4 based on the PCB design can realize the minimization of on-board power management, communication and computer modules, and the compact propulsion system 3 with integrated structure and function can realize the compact layout of the propulsion system.
Further, the integrated compact propulsion system 3 further comprises: the annular buffer cavity 9, the electromagnetic valve, the pressure reducing valve and the pressure sensor;
the annular buffer cavity 9 is 3D printed in the integrated storage tank and used for heating working media;
the electromagnetic valve is arranged around the integrated printing thruster and is used for controlling the thrust switch;
the pressure reducing valve is arranged on the inner side of the integrated storage tank and is used for controlling the pressure in the buffer cavity;
the pressure sensor is arranged on the inner side of the integrated storage tank and is used for collecting pressure values in the integrated storage tank and the buffer cavity.
Specifically, the structure and function integrated compact propulsion system adopts the design of integrating a storage tank and a whole satellite main bearing structure, and divides an annular area in an aircraft through an internal thin-wall structure to form a storage tank and a buffer cavity required by the propulsion system of the aircraft, and the storage tank and the buffer cavity are directly printed in the bearing structure 7 through a thruster and an electromagnetic valve, so that the redundant quality required by the secondary bearing structure 7 of the aircraft is saved, and the compactness of the system is improved.
Furthermore, the high-integration electronic module 4 mainly comprises a high-performance processor module, a power distribution management module, a measurement and control communication module and a GNSS navigation module, and all the functional modules are integrated on the whole printed circuit board and bear task functions such as satellite task management, GNC task management, whole-satellite power supply and distribution management, measurement and control communication and load management. The integrated electronic module 4 realizes high integration of hardware and software, and can realize functions of on-board low-power consumption processing, on-board complex information processing, on-board integrated network communication, network time synchronization and the like.
Specifically, the high-performance processor module is a core control unit of the whole satellite, and can realize the communication function with all external single machines of the whole satellite and the acquisition function of analog quantities such as external voltage, current, resistance and the like. The measurement and control communication module is a whole-satellite measurement and control communication radio execution part, performs data communication with the high-performance processor module through the synchronous RS422, can receive uplink remote control information from a satellite ground station or other satellites, can also receive telemetry information which is packaged and framed by the processor module, and outputs the telemetry information to the ground station or other satellites in a downlink manner.
The GNSS navigation module is a reference device for whole-satellite time maintenance and orbit positioning, and CAN receive navigation positioning signals from a Global Positioning System (GPS) and a Beidou satellite navigation system (BD) for data calculation to obtain time information and orbit information, and the time information and the orbit information are provided for the high-performance processor module through a CAN bus or an RS422 serial port.
The power distribution management module is not provided with a processing calculation unit, is driven by receiving instructions from the high-performance processor module in the platform, and realizes power supply and power failure control of various external equipment products, and meanwhile, the power distribution management module provides state information to the high-performance processor module in a voltage analog quantity feedback mode and mainly comprises important information such as whole-star bus voltage, storage battery voltage, whole-star bus current, storage battery charging current, storage battery discharging current, solar battery array input current and the like.
Furthermore, the function multiplexing star sensor is arranged in the aircraft and is used for multiplexing with the function of tracking and aiming load on the satellite, and accurately tracking and aiming the target object in the working process.
Further, the MEMS sensitive element comprises a Pi Naxing star sensor and a 6-axis MEMS inertial measurement unit light small-sized sun sensor, wherein the star sensor is used for accurately determining the satellite attitude of a chip, and the accuracy is 5%. The MEMS inertial measurement unit comprises an accelerometer and a gyroscope, can realize the measurement of chip star acceleration and angular velocity, and the light and small solar sensor 1 is respectively arranged on the + -Y surface of a satellite orbit system, so that the coverage of a 2 pi space view field is ensured, and can realize the functions of acquiring and determining the attitude information of the aircraft in the full mission stage.
Furthermore, the payload 2 is arranged in the +x direction of the aircraft, and adopts a generalized interface to carry imaging load, debris cleaning load and the like, so as to realize the functions of sensing and detecting the aircraft, cleaning the space debris and the like. The imaging load is used for imaging a space target, the debris cleaning load is used for capturing and removing space debris and the like, and functions of aircraft perception detection, space debris removal and the like are realized.
Referring to fig. 2, for the compact propulsion system 3 with integrated structure and function provided in this embodiment, the design of integrating the storage tank with the whole satellite main bearing structure 7 is adopted, the annular area in the aircraft is divided by the internal thin-wall structure, so as to form the storage tank and the buffer cavity required by the propulsion system of the aircraft, the thruster 8 and the electromagnetic valve are directly printed in the bearing structure 7, the redundant quality required by the secondary bearing structure 7 of the aircraft is saved, and the compactness of the system is improved.
Referring to fig. 3, the compact disc type aircraft further includes a star connection release structure, a pressing mechanism, and a guide rail. The compact disc type design of the functions of multi-group batch ascending, grouping on-orbit release and the like of the aircraft can be realized. The batch uplink separating mechanism comprises a star connection releasing structure, a pressing mechanism, a spring and a guide rail. The compression release mechanism consists of a separation mechanism driven end 14, a separation mechanism driving end 13 and a spring, wherein the separation mechanism driving end 13 and the separation mechanism driven end 14 are respectively arranged on a separation satellite and a separated satellite, and the spring is positioned in the driving end and the driven end and can play a role in providing initial separation speed. The guide rail is used for separating the initial positioning and guiding. The batch uplink separating mechanism can realize the functions of compact disc type design of multiple groups of aircrafts such as batch uplink, grouping on-orbit release and the like.
In the carrying ascending stage, the star connection release structure is connected through non-fire separation nuts among the stars, and the compressing mechanism realizes limit and bearing for bosses and grooves among the stars. After entering the track, the connection release structure is unlocked, a spring acts on the star in the pressing mechanism, and then the star realizes the functions of compact disc type design of multi-group batch ascending, grouping on-track release and the like of the aircraft under the limit action of the guide rail. The batch ascending function of the aircraft is realized, single or multiple groups of disc-type aircraft are released according to the requirement in the on-orbit release section, and the group delivery function is realized.
The foregoing description of the invention has been presented for purposes of illustration and description, and is not intended to be limiting. Several simple deductions, modifications or substitutions may also be made by a person skilled in the art to which the invention pertains, based on the idea of the invention.
Claims (10)
1. A compact disc batch uplink aircraft, comprising:
the integrated propulsion system is used for providing thrust required by rail maneuvering and rail maintenance and comprises an integrated storage tank and an integrated printing thruster, and the integrated storage tank is matched with the integrated printing thruster;
the integrated storage tank, the mounting plate and the sailboard form a main bearing structure of the aircraft together, strength and rigidity required in the running process of the aircraft are provided, the basic shape of the aircraft is maintained, and the 3D printing storage tank is arranged in the integrated storage tank and is used for storing propellant of the aircraft; the integrated printing thruster is used for generating rated thrust;
the electronic module is arranged on the +Y surface in the aircraft and is used for comprehensive electricity of the whole satellite, power supply and distribution and measurement and control communication;
the MEMS sensitive element is arranged on the +Y plane in the aircraft and is used for providing inertial sensitive information of the aircraft;
and the functional multiplexing star sensor is matched with the MEMS sensitive element and the electronic module and is used for determining the gesture track of the aircraft.
2. The compact disc batch upstream vehicle of claim 1 wherein the integrated compact propulsion system further comprises: the device comprises an annular buffer cavity, an electromagnetic valve, a pressure reducing valve and a pressure sensor;
the annular buffer cavity is 3D printed in the integrated storage tank and used for heating working media;
the electromagnetic valve is arranged around the integrated printing thruster and is used for controlling the thrust switch;
the pressure reducing valve is arranged on the inner side of the integrated storage tank and is used for controlling the pressure in the buffer cavity;
the pressure sensor is arranged on the inner side of the integrated storage tank and is used for collecting pressure values in the integrated storage tank and the buffer cavity.
3. The compact disc type batch upstream vehicle of claim 1 in which said integrated print thrusters are provided with 12, 6 degree of freedom decoupling arrangements on an integrated tank structure.
4. The compact disc batch upstream vehicle of claim 1 wherein the electronics module comprises: the high-performance processor module, the power distribution management module, the measurement and control communication module and the GNSS navigation module are integrated on a PCB and mutually matched, and the PCB is fixed in the aircraft;
the high-performance processor module is used for communicating with an external single machine and collecting analog quantity information; the power distribution management module receives an instruction from the high-performance processor module and feeds back state information to the high-performance processor module at the same time; the measurement and control communication module is used for executing whole-satellite radio measurement and control communication; the GNSS navigation module is used for maintaining and track positioning.
5. The compact disc type batch uplink aircraft according to claim 1, wherein the function multiplexing star sensor is arranged in the aircraft and is used for multiplexing with a satellite tracking load function, and accurately tracking and aiming a target object in the working process.
6. The compact disc batch upstream vehicle of claim 1 further comprising a payload disposed in the vehicle +x direction for performing a task or function performed by the vehicle.
7. The compact disc type batch uplink aircraft according to claim 6, wherein the payload is further used for aircraft perception detection and space debris removal, and a generalized interface is adopted to carry imaging load and debris removal load;
the imaging load is used for imaging a space target; the debris cleaning load is used for space debris capture and removal.
8. The compact disc type batch uplink aircraft according to claim 1, further comprising a star connection release structure, a hold down mechanism and a guide rail;
the compressing mechanism comprises a separating mechanism and a spring, wherein the separating mechanism is used for providing initial separating speed and comprises a driving end and a driven end; the driving end and the driven end are respectively arranged on the separated satellite and the separated satellite, and the compression spring is positioned in the driving end and the driven end; the guide rail is used for positioning and guiding the separation initial process.
9. The compact disc type batch uplink aircraft according to claim 8, wherein the star connection release structure is connected through a threaded structure, and the hold-down mechanism achieves limiting and bearing through a boss and a groove between the aircraft.
10. The compact disc type batch uplink aircraft according to claim 8, wherein after the aircraft enters the track, the star connection release structure is unlocked, a spring in the compression mechanism acts on the star, and the aircraft realizes multi-group batch uplink and grouping on-track release of the compact disc type design aircraft under the limit of the guide rail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311620362.6A CN117799863A (en) | 2023-11-30 | 2023-11-30 | Compact disc type batch uplink aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311620362.6A CN117799863A (en) | 2023-11-30 | 2023-11-30 | Compact disc type batch uplink aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117799863A true CN117799863A (en) | 2024-04-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311620362.6A Pending CN117799863A (en) | 2023-11-30 | 2023-11-30 | Compact disc type batch uplink aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN117799863A (en) |
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- 2023-11-30 CN CN202311620362.6A patent/CN117799863A/en active Pending
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