CN112572836B - Method for selecting net capture load emission window based on discarded satellite attitude nutation characteristic - Google Patents

Method for selecting net capture load emission window based on discarded satellite attitude nutation characteristic Download PDF

Info

Publication number
CN112572836B
CN112572836B CN202011480345.3A CN202011480345A CN112572836B CN 112572836 B CN112572836 B CN 112572836B CN 202011480345 A CN202011480345 A CN 202011480345A CN 112572836 B CN112572836 B CN 112572836B
Authority
CN
China
Prior art keywords
net
nutation
time
theta
emission
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN202011480345.3A
Other languages
Chinese (zh)
Other versions
CN112572836A (en
Inventor
张庆展
靳永强
郝晓龙
谭明朗
江晟
肖余之
朱虹
范庆玲
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shanghai Aerospace System Engineering Institute
Original Assignee
Shanghai Aerospace System Engineering Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shanghai Aerospace System Engineering Institute filed Critical Shanghai Aerospace System Engineering Institute
Priority to CN202011480345.3A priority Critical patent/CN112572836B/en
Publication of CN112572836A publication Critical patent/CN112572836A/en
Application granted granted Critical
Publication of CN112572836B publication Critical patent/CN112572836B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—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
    • B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G4/00—Tools specially adapted for use in space
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
    • Y02D30/00—Reducing energy consumption in communication networks
    • Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Sampling And Sample Adjustment (AREA)

Abstract

The invention relates to a method for selecting a net capture load emission window based on the attitude nutation characteristic of a waste satellite, belonging to the technical field of satellite net capture waste satellites; step one, extracting a maximum nutation angle thetamaxMinimum nutation angle thetaminAnd a nutation period T; step two, acquiring the launching time t of the net capture loadintWith a target time tinf(ii) a Calculating the time width Tnet＝tinf‑tint(ii) a Step three, setting a nutation angle adaptive threshold theta for directly transmitting net capture load without selecting a windownet(ii) a Fourthly, calculating to obtain a nutation angle satisfying theta not more than theta in a single periodnetTime width T ofθ＝tθs‑tθj(ii) a Step five, determining the time width delta T and the emission time T of the emission window of the net capture loadintAnd a satisfaction condition of the nutation angle theta at the time of emission; the invention provides a method for selecting a launching window according to the attitude nutation rule of the abandoned satellite, the adaptability of the nutation angle of the net-caught load and the time width from the launching moment to the capturing of the net-caught load, and realizes the reliable capturing of the large-attitude nutation abandoned satellite.

Description

Method for selecting net capture load emission window based on discarded satellite attitude nutation characteristic
Technical Field
The invention belongs to the technical field of satellite net-capture waste satellites, and relates to a net-capture load emission window selection method based on the nutation characteristic of the attitude of a waste satellite.
Background
The method for cleaning the track environment is safe and effective by capturing the abandoned satellites by using the net-capture load and dragging the abandoned satellites to the track of the grave. In-orbit attitude of a satellite rejected will generally rotate about its axis of maximum inertia and will nutate with varying degrees of attitude and the nutation angle will be periodic, with a maximum nutation angle and a minimum nutation angle. The attitude nutation of the abandoned satellite makes the large-size accessories of the body, such as the tail end position of the solar sailboard, change constantly in space.
According to published data, the current net capture load adopts a direct transmission mode, namely, after the net capture load carried by a satellite approaches to a waste satellite to reach a proper distance, the net capture load is directly transmitted to capture a target, and the problem of transmission window selection is not considered. The direct launching mode can realize reliable capture for the abandoned satellite with stable posture or small posture nutation, but when the posture nutation of the abandoned satellite is large, the nutation of the abandoned satellite can lead the net body to contact the tail end of the large-size accessory of the abandoned satellite body in advance for a period of time during capture, and the net body is wound due to nutation motion, so that the net body configuration is disordered, and the net capture fails. And in addition, due to engineering constraints, the size of the net capture load cannot be infinite, so that the net capture load adopting a direct transmission mode inevitably has a certain nutation angle capture adaptive range, and the direct transmission mode aiming at the abandoned satellite with a large attitude nutation cannot realize capture. Therefore, the emission window needs to be selected according to parameters such as the attitude nutation rule of the abandoned satellite, the nutation angle adaptive capacity of the net-caught load, the time width from the emission moment to the capture of the net-caught load and the like, and the problem that the reliable capture of the abandoned satellite with large attitude nutation cannot be realized due to the direct emission of the net-caught load is solved.
No description or report of related technologies similar to the invention is found at present, and similar data in China are not collected.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method for selecting the emission window of the net capture load overcomes the defects of the prior art, provides a method for selecting the emission window of the net capture load based on the posture nutation characteristic of the abandoned satellite, and realizes the reliable capture of the abandoned satellite in large posture nutation according to the posture nutation rule of the abandoned satellite, the adaptability of the nutation angle of the net capture load and the time width from the emission moment to the capture of the net capture load.
The technical scheme of the invention is as follows:
the method for selecting the net capture load emission window based on the attitude nutation characteristic of the abandoned satellite comprises the following steps:
step one, acquiring a historical attitude nutation rule curve of a waste satellite, and extracting nutation characteristic parameters including a maximum nutation angle thetamaxMinimum nutation angle thetaminAnd a nutation period T;
step two, acquiring the emission time t of the net capture load according to the historical data of the abandoned satelliteintWith a target time tinf(ii) a Calculating the time width T from the self-emission moment of the net-captured load to the captured targetnet＝tinf-tint；
Step three, setting a nutation angle adaptive threshold theta for directly transmitting net capture load without selecting a windownet；
Step four, nutating a rule curve according to the historical attitude of the abandoned satellite in the step one; let the nutation angle theta equal to theta in a single periodnetWill nutate the angular rate of change
Figure BDA0002837347030000021
The time less than zero is denoted as tθjWill nutate the angular rate of change
Figure BDA0002837347030000022
The time greater than zero is denoted tθs(ii) a And will tθsRecording as the end time of the single nutation period; the calculated nutation angle in the single period satisfies the condition that theta is less than or equal to thetanetTime width T ofθ＝tθs-tθj；
Step five, according to the nutation period T and the time width T from the self-emission moment of the net-captured load to the captured targetnetThe nutation angle in the sum single period satisfies that theta is less than or equal to thetanetTime width T ofθDetermining the time width delta T and the emission time T of the emission window of the net capture loadintAnd nutation angle at launchThe satisfaction condition of theta.
In the method for selecting the net capture load emission window based on the attitude nutation characteristic of the waste satellite, in the first step, a historical attitude nutation rule curve of the waste satellite is obtained through a three-dimensional reconstruction and motion characteristic identification method; as known from satellite attitude momentum theory, the nutation angle is periodically changing, with a maximum nutation angle and a minimum nutation angle.
In the third step of the method for selecting the emission window of the net capture load based on the attitude nutation characteristic of the abandoned satellite, the adaptive nutation angle threshold theta for directly emitting the net capture load without selecting the windownetThe satisfying conditions are as follows:
θmin≤θnet≤θmax
and sin (theta)net+θε)≤2×λ×V×Ts÷L
In the formula, lambda is a value safety coefficient, and lambda is 0.4-0.6;
l is the envelope size of the in-orbit abandoned satellite; l is less than or equal to 40 m;
v is the flying speed when the net-caught load contacts the waste satellite, and V is more than or equal to 6 m/s;
Tstime for completion of closing up of net mouth for net-catching load, TsLess than or equal to 1.5 s;
θεan error is identified for the nutation angle, less than or equal to 3 °.
In the fifth step of the selection method of the net capture load emission window based on the discarded satellite attitude nutation characteristic, the time width delta T and the emission time T of the net capture load emission window are determinedintAnd the nutation angle theta during emission is as follows:
s1, when Tnet≤TθWhen, i.e. 1 emission window per nutation period, the time width of the emission window, Δ T, is Tθ-Tnet(ii) a Emission time tintSatisfies the condition tθj≤tint≤tθj+Tθ-Tnet(ii) a The nutation angle theta at the time of emission satisfies the condition theta (t)θj+Tθ-Tnet)≤θ≤θnet(ii) a Wherein, theta(tθj+Tθ-Tnet) Represents tθj+Tθ-TnetA nutation angle of the obsolete satellite at time;
s2, when Tθ<Tnet<0.5×(Tθ+ T), the emission window time width Δ T ═ T-TnetTime of transmission tintSatisfies the condition 0. ltoreq. tint≤tθs-Tnet(ii) a Nutation angle theta and rate of change of nutation angle at launch
Figure BDA0002837347030000033
Satisfies the conditions
Figure BDA0002837347030000031
S3, 0.5X (T)θ+T)≤TnetWhen T is less than or equal to T, the time width Delta T of the emission window is T-TnetTime of transmission tintSatisfies the condition 0. ltoreq. tint≤tθs-Tnet(ii) a Nutation angle theta and rate of change of nutation angle at launch
Figure BDA0002837347030000034
Satisfies the conditions
Figure BDA0002837347030000032
S4, when Tnet>At T, each fix (T)netRounding the period by div T) +1, wherein each nutation period has 1 emission window; wherein, fix (T)netDiv T) represents a pair TnetRounding off T, note Δ Tnet＝Tnet-fix(TnetDiv T) x T; when Δ T is reachednet≤TθIf so, the judgment is continued by switching to the condition in S1; when T isθ<ΔTnet<0.5×(Tθ+ T) is converted into the condition in S2, and judgment is continued; when 0.5 × (T)θ+T)≤ΔTnetWhen the value is less than or equal to T, the judgment is continued under the condition of S3.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention provides a method for selecting a net capture load emission window based on the attitude nutation characteristic of a waste satellite, which is provided according to the attitude nutation rule of the waste satellite, the adaptability of the nutation angle of the net capture load and the time width from the emission moment to the capture of the net capture load;
(2) the method provided by the invention solves the problem that the reliable capture of the large-attitude nutation waste satellite cannot be realized by directly launching the net capture load, and provides a prerequisite for the aircraft to remove the space waste satellite by using the net capture load.
Drawings
FIG. 1 is a flowchart of emission window selection in accordance with the present invention;
FIG. 2 shows that T is satisfied by the present inventionnet≤TθA conditional emission window schematic;
FIG. 3 shows that T is satisfied by the present inventionθ<Tnet<0.5×(Tθ+ T) conditional emission window schematic;
FIG. 4 shows that the present invention satisfies 0.5 × (T)θ+T)≤TnetSchematic diagram of emission window under ≦ T condition.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a method for selecting a net capture load transmitting window based on the attitude nutation characteristic of a waste satellite, which is used for realizing the reliable capture of a large-attitude nutation waste satellite according to the attitude nutation rule of the waste satellite, the adaptability of the nutation angle of the net capture load and the time width from the transmitting moment to the capturing of the net capture load.
The method for selecting the net capture load emission window based on the discarded satellite attitude nutation characteristic specifically comprises the following steps as shown in fig. 1:
step one, acquiring a historical attitude nutation rule curve of a waste satellite, and extracting nutation characteristic parameters including a maximum nutation angle thetamaxMinimum nutation angle thetaminAnd a nutation period T; generally, a three-dimensional reconstruction and motion characteristic identification method is used for obtaining a historical attitude nutation rule curve of a waste satellite; as known from satellite attitude momentum theory, the nutation angle is periodically changed, and a maximum nutation angle and a minimum nutation existAnd (6) moving angle.
Step two, acquiring the emission time t of the net capture load according to the historical data of the abandoned satelliteintWith the target time of capture tinf(ii) a Calculating the time width T from the self-emission moment of the net-captured load to the captured targetnet＝tinf-tint(ii) a The time width T is generally obtained by mathematical simulation of the launch and deployment process of the net-capture loadnetThe intrinsic characteristic parameter belonging to the net capture load is a constant value.
Step three, setting a nutation angle adaptive threshold theta for directly transmitting net capture load without selecting a windownet(ii) a Adaptive nutation angle threshold theta for direct emission of net-caught loads without selecting windowsnetThe satisfying conditions are as follows:
θmin≤θnet≤θmax
and sin (theta)net+θε)≤2×λ×V×Ts÷L
In the formula, lambda is a value safety coefficient, and lambda is 0.4-0.6;
l is the envelope size of the in-orbit abandoned satellite; l is less than or equal to 40 m;
v is the flying speed when the net-caught load contacts the waste satellite, and V is more than or equal to 6 m/s;
Tstime for completion of closing up of net mouth for net-catching load, TsLess than or equal to 1.5 s;
θεan error is identified for the nutation angle, less than or equal to 3 °.
Step four, nutating a rule curve according to the historical attitude of the abandoned satellite in the step one; let the nutation angle theta equal to theta in a single periodnetWill nutate the angular rate of change
Figure BDA0002837347030000051
The time less than zero is denoted as tθjWill nutate the angular rate of change
Figure BDA0002837347030000052
The time greater than zero is denoted as tθs(ii) a And will tθsRecording as the end time of the single nutation period; the calculated nutation angle in the single period satisfies the condition that theta is less than or equal to thetanetTime width T ofθ＝tθs-tθj；
Step five, according to the nutation period T and the time width T from the self-emission moment of the net capture load to the capture targetnetThe nutation angle in the sum single period satisfies that theta is less than or equal to thetanetTime width T ofθDetermining the time width delta T and the emission time T of the emission window of the net capture loadintAnd the satisfaction condition of the nutation angle theta at the time of emission.
Determining the time width delta T and the emission time T of the emission window of the net capture loadintAnd the nutation angle theta during emission is as follows:
s1, when Tnet≤TθWhen, i.e. 1 emission window per nutation period, the time width of the emission window, Δ T, is Tθ-Tnet(ii) a Emission time tintSatisfies the condition tθj≤tint≤tθj+Tθ-Tnet(ii) a The nutation angle theta at the time of emission satisfies the condition theta (t)θj+Tθ-Tnet)≤θ≤θnet(ii) a Wherein, θ (t)θj+Tθ-Tnet) Represents tθj+Tθ-TnetA nutation angle of the obsolete satellite at time; as shown in fig. 2, the dotted line in the figure is located within the emission window (window width), and the thick solid line is the time width from the emission time of the net capture load to the capture target.
S2, when Tθ<Tnet<0.5×(Tθ+ T), the emission window time width Δ T ═ T-TnetTime of transmission tintSatisfies the condition 0. ltoreq. tint≤tθs-Tnet(ii) a Nutation angle theta and rate of change of nutation angle at launch
Figure BDA0002837347030000063
Satisfies the conditions
Figure BDA0002837347030000061
As shown in fig. 4, the dotted line in the figure is located inside the emission window, and the thick solid line is the time width from the emission time of the net capture load to the capture target.
S3、When 0.5 × (T)θ+T)≤TnetWhen T is less than or equal to T, the time width Delta T of the emission window is T-TnetTime of transmission tintSatisfies the condition 0. ltoreq. tint≤tθs-Tnet(ii) a Nutation angle theta and rate of change of nutation angle at launch
Figure BDA0002837347030000064
Satisfies the conditions
Figure BDA0002837347030000062
As shown in fig. 3, the dotted line in the figure is located inside the emission window, and the thick solid line is the time width from the emission time of the net capture load to the capture target.
S4, when Tnet>At T, each fix (T)netIntegrating the period by dividing T) +1, wherein each nutation period has 1 emission window; wherein, fix (T)netDiv T) represents a pair TnetRounding off T, note Δ Tnet＝Tnet-fix(TnetDiv T) x T; when Δ T is reachednet≤TθIf so, the judgment is continued by switching to the condition in S1; when T isθ<ΔTnet<0.5×(Tθ+ T) is converted into the condition in S2, and the judgment is continued; when 0.5 × (T)θ+T)≤ΔTnetWhen the value is less than or equal to T, the judgment is continued under the condition of S3.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.

Claims (4)

1. The method for selecting the net capture load emission window based on the attitude nutation characteristic of the abandoned satellite is characterized by comprising the following steps: the method comprises the following steps:
step one, obtaining historical attitude nutation rule and curve of abandoned satelliteLines and extracting a nutation characteristic parameter including a maximum nutation angle thetamaxMinimum nutation angle thetaminAnd a nutation period T;
step two, acquiring the emission time t of the net capture load according to the historical data of the abandoned satelliteintCapturing the target time tinf(ii) a Calculating the time width T from the self-emission moment of the net-captured load to the captured targetnet＝tinf-tint；
Step three, setting a nutation angle adaptive threshold theta for directly transmitting net capture load without selecting a windownet；
Step four, nutating a rule curve according to the historical attitude of the abandoned satellite in the step one; let the nutation angle theta equal to theta in a single periodnetWill nutate the angular rate of change
Figure FDA0003583149250000011
The time less than zero is denoted as tθjWill nutate the angular rate of change
Figure FDA0003583149250000012
The time greater than zero is denoted tθs(ii) a And will tθsRecording as the end time of the single nutation period; the calculated nutation angle in the single period satisfies the condition that theta is less than or equal to thetanetTime width of
Figure FDA0003583149250000013
Step five, according to the nutation period T and the time width T from the self-emission moment of the net capture load to the capture targetnetThe nutation angle in the sum single period satisfies that theta is less than or equal to thetanetTime width T ofθDetermining the time width delta T and the emission time T of the emission window of the net capture loadint' and the satisfaction condition of the nutation angle theta at the time of emission.
2. The method for selecting the net capture load emission window based on the attitude nutation characteristic of the abandoned satellite as claimed in claim 1, wherein: in the first step, a historical attitude nutation rule curve of the abandoned satellite is obtained through a three-dimensional reconstruction and motion characteristic identification method; as known from satellite attitude momentum theory, the nutation angle is periodically changing, with a maximum nutation angle and a minimum nutation angle.
3. The method for selecting the net capture load emission window based on the attitude nutation characteristic of the abandoned satellite as claimed in claim 2, wherein: in the third step, the net capture load is directly transmitted without selecting a window and is adaptive to the nutation angle threshold thetanetThe satisfying conditions are as follows:
θmin≤θnet≤θmax
and sin (theta)net+θε)≤2×λ×V×Ts÷L
In the formula, lambda is a value safety coefficient, and lambda is 0.4-0.6;
l is the envelope size of the in-orbit abandoned satellite; l is less than or equal to 40 m;
v is the flying speed when the net-caught load contacts the waste satellite, and V is more than or equal to 6 m/s;
Tstime for completion of closing up of net mouth for net-catching load, TsLess than or equal to 1.5 s;
θεan error is identified for the nutation angle, less than or equal to 3 °.
4. The method for selecting the net capture load emission window based on the attitude nutation characteristic of the abandoned satellite as claimed in claim 3, wherein: in the fifth step, the time width delta T and the emission time T of the emission window of the net capture load are determinedint' A specific method for satisfying the condition of the nutation angle theta during transmission is as follows:
s1, when Tnet≤TθWhen, i.e. 1 emission window per nutation period, the time width of the emission window, Δ T, is Tθ-Tnet(ii) a Moment of transmission tint' satisfying the condition tθj≤tint′≤tθj+Tθ-Tnet(ii) a The nutation angle theta at the time of emission satisfies the condition theta (t)θj+Tθ-Tnet)≤θ≤θnet(ii) a Wherein, θ (t)θj+Tθ-Tnet) Represents tθj+Tθ-TnetA nutation angle of the obsolete satellite at time;
s2, when Tθ＜Tnet＜0.5×(Tθ+ T), the emission window time width Δ T ═ T-TnetTime of transmission tint' satisfying the condition 0. ltoreq. tint′≤tθs-Tnet(ii) a Nutation angle theta and rate of change of nutation angle at launch
Figure FDA0003583149250000023
Satisfies the conditions
Figure FDA0003583149250000021
S3, 0.5X (T)θ+T)≤TnetWhen T is less than or equal to T, the time width Delta T of the emission window is T-TnetTime of transmission tint' satisfying the condition 0. ltoreq. tint′≤tθs-Tnet(ii) a Nutation angle theta and rate of change of nutation angle at launch
Figure FDA0003583149250000024
Satisfy the condition
Figure FDA0003583149250000022
S4, when TnetWhen > T, each fix (T)netIntegrating the period by dividing T) +1, wherein each nutation period has 1 emission window; wherein, fix (T)netDiv T) represents a pair TnetRounding off T, note Δ Tnet＝Tnet-fix(TnetDiv T) x T; when Δ T is reachednet≤TθIf so, converting to the condition in S1 and continuing judging; when T isθ＜ΔTnet＜0.5×(Tθ+ T) is converted into the condition in S2, and judgment is continued; when 0.5 × (T)θ+T)≤ΔTnetWhen the value is less than or equal to T, the judgment is continued under the condition of S3.
CN202011480345.3A 2020-12-15 2020-12-15 Method for selecting net capture load emission window based on discarded satellite attitude nutation characteristic Active CN112572836B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011480345.3A CN112572836B (en) 2020-12-15 2020-12-15 Method for selecting net capture load emission window based on discarded satellite attitude nutation characteristic

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011480345.3A CN112572836B (en) 2020-12-15 2020-12-15 Method for selecting net capture load emission window based on discarded satellite attitude nutation characteristic

Publications (2)

Publication Number Publication Date
CN112572836A CN112572836A (en) 2021-03-30
CN112572836B true CN112572836B (en) 2022-05-31

Family

ID=75135200

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202011480345.3A Active CN112572836B (en) 2020-12-15 2020-12-15 Method for selecting net capture load emission window based on discarded satellite attitude nutation characteristic

Country Status (1)

Country Link
CN (1) CN112572836B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116135703B (en) * 2023-04-20 2023-06-16 中国科学院沈阳自动化研究所 Passive closing-in structure of space flying net system

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109131941A (en) * 2018-07-27 2019-01-04 北京控制工程研究所 A kind of anti-nutating inert satellite contact racemization method

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4424948A (en) * 1981-01-22 1984-01-10 Rca Corporation Magnetically torqued nutation damping
US5826828A (en) * 1996-02-05 1998-10-27 Hughes Electronics Corporation Sun/earth acquisition without thrusters
US5884869A (en) * 1996-03-18 1999-03-23 Hughes Electronics Corporation Satellite spin vector control with sun sensor
CN101554926B (en) * 2009-05-20 2012-05-23 上海微小卫星工程中心 Attitude control system for space vehicle and method thereof
CN107450309B (en) * 2017-07-04 2020-06-16 上海宇航系统工程研究所 Rope combination body attitude maneuver cooperative control method
CN109573110B (en) * 2018-09-20 2021-07-20 上海宇航系统工程研究所 Non-cooperative target capturing system and method

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109131941A (en) * 2018-07-27 2019-01-04 北京控制工程研究所 A kind of anti-nutating inert satellite contact racemization method

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
Detumbling of Space Debris by a Net and Elastic Tether;William J.O’Connor,et al;《JOURNAL OF GUIDANCE,CONTROL AND DYNAMICS》;20170606;全文 *
基于周期变化惯量积的主动章动控制方法研究;吕高见等;《空间控制技术与应用》;20080831;第34卷(第4期);全文 *

Also Published As

Publication number Publication date
CN112572836A (en) 2021-03-30

Similar Documents

Publication Publication Date Title
CN112572836B (en) Method for selecting net capture load emission window based on discarded satellite attitude nutation characteristic
CN108427427B (en) Method for calculating attitude angle of spacecraft to earth surface orientation target
US20190100108A1 (en) Robotic Vehicle Renewable Resource Charging Station Management Systems and Methods
US20080272233A1 (en) Method and system for generating renewable energy
CN102424116A (en) Method for optimizing orbital transfer strategy of geostationary orbit satellite
CN105446351A (en) Robotic airship system capable of locking target area for observation based on autonomous navigation
CN113268081B (en) Small unmanned aerial vehicle prevention and control command decision method and system based on reinforcement learning
CN106772466B (en) A kind of near-earth satellite target automatic capture algorithm based on shape feature search
CN110633888A (en) Multi-star task planning method based on four-layer structure genetic algorithm
CN114793129B (en) Wireless communication relay method and system based on wave glider
CN116360474A (en) Unmanned aerial vehicle active tracking capturing system and method
Zhang et al. Multi-objective optimization for UAV-enabled wireless powered IoT networks: an LSTM-based deep reinforcement learning approach
CN117610887A (en) GEO space garbage removal task planning method based on space filling station
CN110576983B (en) Attitude determination method in track transfer process
CN108562292B (en) The interspace transfer track optimizing method of solar sail based on the adaptive pseudo- spectrometry of hp
CN109976373B (en) Differential quantization feedback controller in aircraft and control method thereof
CN112572837B (en) Net capture azimuth design method based on attitude motion characteristics of abandoned satellites
CN106131482A (en) Unmanned carrier optoelectronic aims of systems capture systems and method
CN114371730A (en) Unmanned aerial vehicle tracking moving target track planning method
CN114995481A (en) Unmanned aerial vehicle autonomous inspection system and method for hydropower station volute
Maimone et al. Autonomous rock tracking and acquisition from a mars rover
CN113835439A (en) Two-dimensional cooperative guidance method for control time and angle of initial track angle freedom
CN112985389B (en) Laser charging tracking method based on unmanned aerial vehicle motion state
CN111158020A (en) Satellite-borne real-time cloud judgment system and method for satellite
CN116634457B (en) Multi-unmanned aerial vehicle self-adaptive data collection and return method based on deep reinforcement learning

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant