阅读说明：本技术 一种充气天线 (Inflatable antenna ) 是由 杜志贵 杨峰 任维佳 向晓霞 于 2019-11-29 设计创作，主要内容包括：本发明涉及一种体积可控的充气天线,至少包括卫星推进器、至少一个获取模块以及至少一个调整模块,第一调整模块被配置为：基于变轨环境监测信息确定第一天线调整控制信息；确定卫星推进器用于执行该特定事件的所需预估消耗量；基于第一天线调整控制信息和预估消耗量确定卫星推进器和充气天线分别对应的变轨需求混合比例系数以及与之对应的第一控制指令和第二控制指令,以使得充气天线的第一调整模块按照对接收第二控制指令的卫星推进器的第二调整模块进行气动力补偿的方式接收第一控制指令,并基于由第二获取模块于第二时刻获取的与该点火变轨位置所涉及区域相关联的第二气动力信息进行至少一次调整修正以执行至少一个相关的特定事件。(The invention relates to a volume-controllable gas-filled antenna comprising at least a satellite thruster, at least one acquisition module and at least one adjustment module, the first adjustment module being configured to: determining first antenna adjustment control information based on the orbital transfer environment monitoring information; determining a desired projected consumption of the satellite propulsor for performing the particular event; and determining a track-transfer demand mixing proportion coefficient corresponding to the satellite thruster and the inflation antenna respectively and a first control instruction and a second control instruction corresponding to the track-transfer demand mixing proportion coefficient based on the first antenna adjustment control information and the estimated consumption, so that a first adjustment module of the inflation antenna receives the first control instruction in a mode of performing aerodynamic compensation on a second adjustment module of the satellite thruster receiving the second control instruction, and performing at least one adjustment correction based on second aerodynamic information, acquired by a second acquisition module at a second moment, associated with an area related to the ignition track-transfer position to execute at least one related specific event.)

An inflatable antenna, in particular to an inflatable antenna with controllable volume, which is characterized by at least comprising an inflatable antenna and a volume control module,

the inflatable antenna comprises a flexible antenna folding surface and an unfolding component, the unfolding component is composed of at least two stages of unfolding components which can be sequentially driven by taking inflation pressure as driving force and are respectively connected to different heights on the flexible antenna folding surface,

the volume control module comprises at least a satellite thruster, at least one acquisition module and at least one adjustment module, wherein,

a first adjusting module for adjusting the position and the attitude of the inflating antenna determines a first antenna adjusting control information determined by the obtaining module based on the orbital transfer environment monitoring information and the estimated consumption of the satellite thruster determined based on the initial orbit and the target orbit for executing the specific event, and determines orbital transfer demand mixing proportionality coefficients corresponding to the satellite thruster and the inflating antenna respectively and a first control instruction and a second control instruction corresponding to the orbital transfer demand mixing proportionality coefficients, receiving the first control command in a manner such that the first adjustment module of the inflation antenna aerodynamically compensates a second adjustment module of the satellite thruster that receives the second control command, and performing at least one adjustment correction to perform at least one associated specific event based on second aerodynamic information associated with the area involved in the ignition derailment position acquired by the second acquisition module at a second time.

The inflated antenna of claim 1, wherein the configuration of the first adjustment module for adjusting the position attitude of the inflated antenna further comprises:

determining at least one ignition track-changing position based on the initial track and the target track acquired by the first acquisition module, generating track-changing environment monitoring information based on first aerodynamic information which is acquired by the second acquisition module at a first moment and is associated with an area related to the ignition track-changing position, and determining first antenna adjustment control information based on the track-changing environment monitoring information;

at least one instruction to perform a particular event of interest is determined based on the initial orbit and the target orbit, and upon receiving the at least one instruction to perform the particular event of interest, a required pre-estimated consumption of the satellite propulsor to perform the particular event is determined.

The gas filled antenna of claim 2, wherein the first antenna adjustment control information determined by the first adjustment module based on the tracking environment monitoring information includes at least a first pointing adjustment duration for antenna pointing adjustment and a first deployment adjustment duration for antenna specific surface area adjustment, and the first movement duration is determined based on the one of the first pointing adjustment duration and the first deployment adjustment duration that is greater in value, wherein,

the first adjusting module determines an antenna initial adjusting position corresponding to the first moving duration by combining the ignition track-changing position and the initial track when the first moving duration does not exceed a preset duration threshold, so that the position, where the antenna starts to be adjusted, on the initial track can be determined based on the antenna initial adjusting position.

The gas filled antenna of any one of the preceding claims, wherein the first adjustment module is further configured for performing the steps of:

s1: determining at least one preset allocation specific gravity for establishing a dynamic association relationship between the first pointing adjustment duration and the first deployment adjustment duration in response to the first movement duration exceeding the preset duration threshold;

s2: the preset distribution proportion is updated in a mode of gradually reducing the first unfolding adjustment time length and correspondingly gradually increasing the first direction adjustment time length so as to determine a second direction adjustment time length which corresponds to the preset distribution proportion and is used for updating the first direction adjustment time length and a second unfolding adjustment time length which corresponds to the preset distribution proportion and is used for updating the first unfolding adjustment time length;

s3: therefore, the second moving duration for updating the first moving duration is determined based on the larger value of the updated first pointing adjustment duration and the updated first unfolding adjustment duration, and the updated first moving duration is compared with the preset duration threshold again;

s4: and repeating the steps S1 to S3 in sequence until the first moving time length does not exceed the preset time length threshold value, stopping and outputting the first pointing adjustment time length, the first unfolding adjustment time length and the initial antenna adjustment position corresponding to the first moving time length so as to realize an optimized solution between the estimated loss minimization and the maximum track change efficiency.

An inflatable antenna according to any of the preceding claims, wherein said second adjustment module comprises at least an environment monitoring unit configured to:

acquiring current aerodynamic force information which is acquired in real time at a first moment when a satellite is located at the initial adjustment position of the satellite, is related to an area related to the initial adjustment position of the satellite and is used for providing a parameter set required by atmosphere prediction, and performing prediction calculation based on a position relation between the area related to the ignition orbital transfer position and the initial adjustment position of the satellite to generate first aerodynamic force information located in the area related to the ignition orbital transfer position;

and acquiring second aerodynamic information which is acquired in real time and is related to the area related to the ignition orbital transfer position and used for adjusting and correcting the ignition orbital transfer position of the satellite at a second moment when the satellite is positioned at the ignition orbital transfer position.

Inflatable antenna according to one of the preceding claims, wherein said second adjustment module is adapted to determine, upon receiving at least one instruction to perform a specific event of interest, a required estimated consumption of said satellite thrusters for performing said specific event, said second adjustment module being configured to:

when the first adjusting module determines at least one ignition track-changing position based on the initial track and the target track acquired by the first acquiring module, a track-changing prediction planning process of successfully transferring the ignition track-changing position from the initial track to the target track from the ignition track-changing position in a mode of neglecting the track-changing environment monitoring information is completed by combining the initial track, the target track and the ignition track-changing position, and the corresponding expected consumption amount required to be consumed for completing the track-changing prediction planning process is generated.

An inflatable antenna as claimed in any preceding claim, wherein the second adjustment module is configured to determine the orbital transfer demand mixing scaling factor for the satellite thruster and the inflatable antenna respectively based on the first antenna adjustment control information and the estimated consumption amount under the condition that the aerodynamic assistance factor of the orbital transfer environment monitoring information is determined at a first time, wherein:

when the aerodynamic assistance coefficient is smaller than 1, the second adjusting module determines that the aerodynamic information influences the execution process of the related specific event in a resistance mode, determines an orbital transfer demand mixing scaling coefficient corresponding to the inflation antenna in a mode of reducing the influence of the aerodynamic information to the maximum extent by means of the inflation antenna, and then determines an orbital transfer demand mixing scaling coefficient corresponding to the satellite thruster in a mode of increasing the estimated consumption to the minimum extent on the basis of the orbital transfer demand mixing scaling coefficient corresponding to the inflation antenna;

when the aerodynamic assistance coefficient is larger than 1, the second adjusting module judges that the aerodynamic information influences the execution process of a related specific event in an assistance mode, determines an orbital transfer demand mixing scaling coefficient corresponding to the air-filled antenna in a mode of utilizing the aerodynamic information to the maximum extent by means of the air-filled antenna, and then determines the orbital transfer demand mixing scaling coefficient corresponding to the satellite thruster in a mode of reducing the estimated consumption to the maximum extent on the basis of the orbital transfer demand mixing scaling coefficient corresponding to the air-filled antenna;

and the sum of the orbit-transfer requirement mixing proportion coefficients respectively corresponding to the satellite propeller and the inflatable antenna is equal to 1.

Gas filled antenna according to one of the preceding claims, wherein the second adjustment module further comprises an adjustment correction unit configured to:

and acquiring an error correction coefficient of first antenna adjustment control information corresponding to the first aerodynamic information at a second moment according to the deviation between the second aerodynamic information and the first aerodynamic information, performing adjustment correction within a small adjustment range on satellite pointing information corresponding to the second moment and corresponding satellite deployment information respectively based on the error correction coefficient so that the satellite can accurately correspond to the actually measured second aerodynamic information during the execution of the related specific event, and updating the orbital transfer demand mixing proportion coefficient correspondingly based on the corrected first antenna adjustment control information so that the consumption provided by the satellite propeller during the execution of the related specific event can be further accurately controlled.

An inflatable antenna according to any preceding claim, wherein the first stage deployment element (11) is capable of expanding outwardly under the action of an applied inflation pressure as a driving force to deploy at least a portion of the folded flexible antenna surface, and when the first stage deployment element (11) is expanded to the first stage fully deployed position, the second stage deployment element (12) is expanded in stages by the applied driving force in a manner that releases the shape memory effect of the plate (7) of shape memory material on the folded flexible antenna surface, so that the folded flexible antenna surface is controllably deployed in stages from bottom to top in a manner that increases the effective deployment area and reduces the deployment impact overload, and thus the folded flexible antenna surface is not fully or fully deployed in space.

Gas filled antenna according to one of the preceding claims, wherein the flexible antenna fold has at least two antenna folds that are folded/unfolded differently from each other, wherein,

the first antenna folding surface (5) can be gradually unfolded or folded along a preset path through the expansion and contraction of the first-stage unfolding component (11), the first-stage unfolding component (11) is configured to release the locking of the first-stage unfolding component (11) in the expansion/contraction direction and drive the first-stage unfolding component (11) to expand outwards/contract inwards by controllably adjusting the mode that the airflow entering the interior of the first-stage unfolding component (11) through at least one first opening flows back and forth in the interior along the height direction and the longitudinal extension direction of the interior, and therefore the first antenna folding surface (5) is driven to be gradually unfolded/folded along the preset path and is automatically locked by the first-stage unfolding component (11) after being unfolded/folded in place so as to be kept at the current unfolding position.

An inflatable antenna according to any of the preceding claims, wherein the second antenna folding surface (6) can be gradually unfolded or folded along a predetermined path by telescoping of the second stage unfolding assembly (12), wherein,

the second stage unfolding component (12) is configured to drive the second stage unfolding component (12) to be elongated in a grading manner until the second stage unfolding component (12) is abutted to the second antenna folding surface (6) by controllably adjusting the flow of the airflow entering the interior of the second stage unfolding component (12) through at least one second opening along the longitudinal extension direction of the interior, so that the second stage unfolding component (12) can release the shape memory effect of at least one shape memory material plate (7) on the second antenna folding surface (6) in a grading manner in an electrically heating manner, and the second stage unfolding component (6) is driven to be gradually unfolded along a preset path and is automatically locked by the shape memory material plate (7) to be kept at the current unfolding position after being unfolded and unfolded to the position.

A method for controlling the deployment volume of an inflatable antenna, comprising at least the steps of:

determining at least one ignition track transfer position based on the obtained initial track and the target track, generating track transfer environment monitoring information based on first aerodynamic information which is obtained at a first moment and is associated with an area related to the ignition track transfer position, and determining first antenna adjustment control information based on the track transfer environment monitoring information;

determining at least one instruction for executing a specific event of interest based on the initial orbit and the target orbit, and upon receiving at least one instruction for executing a specific event of interest, determining a required pre-estimated consumption of the satellite propulsor for executing the specific event;

and determining the orbital transfer demand mixing proportionality coefficient corresponding to the satellite thruster and the inflation antenna respectively and a first control instruction and a second control instruction corresponding to the orbital transfer demand mixing proportionality coefficient based on the first antenna adjustment control information and the estimated consumption, so that the inflation antenna receives the first control instruction in a mode of performing aerodynamic compensation on the satellite thruster receiving the second control instruction, and performing at least one adjustment correction based on second aerodynamic information acquired at a second moment and associated with the area related to the ignition orbital transfer position to execute at least one related specific event.

Deployment volume control method according to one of the preceding claims, characterized in that it comprises at least the following steps:

the first antenna adjustment control information determined based on the tracking environment monitoring information includes at least a first pointing adjustment duration for antenna pointing adjustment and a first deployment adjustment duration for antenna specific surface area adjustment, and the first movement duration is determined based on one of the first pointing adjustment duration and the first deployment adjustment duration, which is larger in value, wherein,

and determining an antenna initial adjustment position corresponding to the first movement duration by combining the ignition track-changing position and the initial track when the first movement duration does not exceed a preset duration threshold, so that the position where the antenna starts to be adjusted and is located on the initial track can be determined based on the antenna initial adjustment position.

An inflatable antenna with expandable space, which at least comprises a flexible antenna folding surface and an expansion assembly, is characterized in that the expansion assembly is composed of at least two stages of expansion assemblies which can be driven successively by taking inflation pressure as driving force and are respectively connected to different heights on the flexible antenna folding surface, wherein,

the first-stage unfolding component (11) can be outwards expanded under the driving action of inflation pressure applied to the first-stage unfolding component to drive at least part of the folding surface of the flexible antenna to unfold, and when the first-stage unfolding component (11) is expanded to a first-stage fully unfolded position, the second-stage unfolding component (12) is expanded in a grading mode in a mode of releasing the shape memory effect of the shape memory material plate (7) located on the folding surface of the flexible antenna due to the application of the driving force applied to the second-stage unfolding component, so that the folding surface of the flexible antenna can be unfolded in a grading and controllable mode from bottom to top in a grading mode to increase the effective unfolding area and reduce unfolding impact overload to be incompletely or fully unfolded.

The gas filled antenna of claim 14, wherein the flexible antenna folded surface has at least two antenna folded surfaces folded/unfolded differently from each other, wherein,

the first antenna folding surface (5) can be gradually unfolded or folded along a preset path through the expansion and contraction of the first-stage unfolding component (11), the first-stage unfolding component (11) is configured to release the locking of the first-stage unfolding component (11) in the expansion/contraction direction and drive the first-stage unfolding component (11) to expand outwards/contract inwards by controllably adjusting the mode that the airflow entering the interior of the first-stage unfolding component (11) through at least one first opening flows back and forth in the interior along the height direction and the longitudinal extension direction of the interior, and therefore the first antenna folding surface (5) is driven to be gradually unfolded/folded along the preset path and is automatically locked by the first-stage unfolding component (11) after being unfolded/folded in place so as to be kept at the current unfolding position.