Ground real-time display method for on-orbit electric quantity of remote sensing satellite storage battery pack

Abstract

The invention relates to a ground real-time display method for on-orbit electric quantity of a remote sensing satellite storage battery pack, and belongs to the field of remote sensing satellite storage battery design. Obtaining the rated electric quantity QE of a satellite storage battery pack; the satellite obtains the charging current IC and the discharging current ID of the storage battery pack in real time in an on-orbit mode; the satellite calculates the charging electric quantity QC and the discharging electric quantity QD of the storage battery pack in real time on orbit; the satellite calculates the current electric quantity QR of the storage battery pack in real time on orbit; the satellite calculates the percentage PR of the current electric quantity of the storage battery pack relative to the rated electric quantity in real time on orbit; the charging current IC, the discharging current ID, the charging electric quantity QC, the discharging electric quantity QD, the current electric quantity QR and the percentage PR of the current electric quantity relative to the rated electric quantity are transmitted to the ground and displayed to satellite operation personnel and application personnel; transmitting the electric quantity parameter calculated each time to the ground; according to the invention, the current electric quantity of the on-orbit storage battery pack of the satellite and the percentage of the relative rated electric quantity are displayed to satellite operators and application personnel on the ground in real time.

Description

Technical Field

[0001] The invention belongs to the field of remote sensing satellite battery design, and relates to a method for real-time display of the on-orbit power of a remote sensing satellite battery pack on the ground. Background Art

[0002] The battery pack is an essential component of a remote sensing satellite. When the sunlight intensity on the satellite's solar wing is not good (set to 0 completely), the battery pack needs to provide electrical energy for all the satellite's electronic devices. The current power in the battery pack severely restricts the use of the satellite by satellite operators and application personnel on the ground. Similar to people using mobile phones, if the satellite can display the current power of the battery pack in real time and accurately, as well as the percentage of the relative rated power, it can help ground personnel make full and efficient use while ensuring sufficient and safe power supply when operating the satellite to perform remote sensing tasks. Summary of the Invention

[0003] The technical problem solved by the invention is: overcoming the deficiencies of the prior art, and proposing a method for real-time display of the on-orbit power of a remote sensing satellite battery pack on the ground, so as to realize real-time display of the current power of the satellite's on-orbit battery pack and the percentage of the relative rated power to the ground satellite operators and application personnel.

[0004] The technical solution adopted by the invention is:

[0005] A method for real-time display of the on-orbit power of a remote sensing satellite battery pack on the ground, comprising:

[0006] Step 1: Obtain the rated power Q of the satellite battery pack E ;

[0007] Step 2: The satellite on orbit obtains the charging current I of the battery pack in real time C and the discharging current I D ;

[0008] Step 3: The satellite on orbit calculates the charging power Q of the battery pack in real time C and the discharging power Q D ;

[0009] Step 4: The satellite on orbit calculates the current power Q of the battery pack in real time R ;

[0010] Step 5: The satellite on orbit calculates the percentage P of the current power of the battery pack relative to the rated power R ;

[0011] Step 6: Transmit the charging current I in Step 2 C and the discharging current I D , the charging power Q in Step 3 Cand the discharge capacity Q D , the current capacity Q in step four R , the percentage P of the current capacity to the rated capacity in step five R are transmitted to the ground and displayed to satellite operators and application personnel;

[0012] Step seven: Repeat steps two to six, and transmit the power parameters calculated each time to the ground.

[0013] In the above method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack, in step one, Q E is the design index of the battery pack. When the battery pack is produced, Q E is determined.

[0014] In the above method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack, in step two, the satellite obtains the charging current I C and the discharge current I D of the battery pack through the monitoring circuit in the power controller;

[0015] To prevent the small changes of the monitoring circuit near zero from affecting the subsequent calculation results, it is necessary to preset the effective threshold of the charging current and the effective threshold of the discharge current, denoted as I CE and I DE respectively, and the unit is ampere;

[0016] When the absolute value of the charging current obtained this time is less than the effective threshold of the charging current, the charging current this time is recorded as 0; otherwise, it is recorded as the effective charging current I C ;

[0017] When the absolute value of the discharge current obtained this time is less than the effective threshold of the discharge current, the discharge current this time is recorded as 0; otherwise, it is recorded as the effective discharge current I D .

[0018] In the above method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack, in step three, the calculation methods of the charging capacity Q C and the discharge capacity Q D are as follows:

[0019] Q C =Q C(n-1) +I C ×T÷3600

[0020] Q D =Q D(n-1) +I D ×T÷3600

[0021] In the formula, Q CThe charging power of the battery pack obtained for this calculation;

[0022] Q C(n-1) The charging power of the battery pack obtained for the previous calculation;

[0023] I C The charging current of the battery pack obtained in step 2 for this time;

[0024] Q D The discharging power of the battery pack obtained for this calculation;

[0025] Q D(n-1) The discharging power of the battery pack obtained for the previous calculation;

[0026] I D The discharging current of the battery pack obtained in step 2 for this time;

[0027] T is the measurement duration for this time.

[0028] In the above method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack, the Q C and Q D The initial values are preset and default to 0; after the satellite is in orbit, the initial values of Q C and Q D are changed through remote control commands.

[0029] In the above method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack, in step 4, the calculation method of the current power Q R is as follows:

[0030] Q R =Q R0 +K C ×Q C −Q D

[0031] In the formula, Q R0 is the initial power of the battery pack;

[0032] K C is the charging efficiency coefficient of the battery pack;

[0033] Q C is the charging power of the battery pack obtained this time;

[0034] Q D is the discharging power of the battery pack obtained this time.

[0035] In the above method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack, the values of Q R0 and K C are preset and default to Q respectivelyE and 0.98. After the satellite is in orbit, Q R0 and K C The set values are changed through remote control commands.

[0036] In the above method for real-time ground display of the on-orbit battery power of a remote sensing satellite, in step five, the percentage P R of the current power relative to the rated power is calculated as follows:

[0037] P R = Q R ÷Q E ×100%.

[0038] In the above method for real-time ground display of the on-orbit battery power of a remote sensing satellite, in step six, the charging current I C and the discharging current I D , the charging power Q C and the discharging power Q D , the current power Q R , and the percentage P R of the current power relative to the rated power are used as satellite telemetry parameters and transmitted to the ground through the telemetry downlink for display to satellite operators and application personnel.

[0039] In the above method for real-time ground display of the on-orbit battery power of a remote sensing satellite, in step seven, the conditions for terminating the power parameter calculation are:

[0040] The charging current I C and the discharging current I D are both 0; and after terminating the power parameter calculation, Q C is set to Q C0 , Q D is set to Q D0 , and wait for recalculation.

[0041] The beneficial effects of the present invention compared with the prior art are:

[0042] (1) The present invention can display in real time the current power of the on-orbit battery pack of a remote sensing satellite and the percentage relative to the rated power. The existing methods only display the historical cumulative values of the charging power and the discharging power, and the intuitive display of the current available power of the battery pack is insufficient;

[0043] (2) The calculation process of the current power of the battery pack in the present invention is all realized by the satellite independently, without the need for ground calculation and processing. Therefore, the obtained data can not only be used by ground personnel, but also can be used as the data source for the satellite's autonomous health and autonomous mission functions;

[0044] (3) The display effect of the current battery charge of the present invention is the same as that of commonly used mobile phones, making the usage experience very friendly for satellite operators and application personnel. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a flowchart for real-time ground display of the on-orbit battery charge of the remote sensing satellite battery pack of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0046] The present invention will be further described below in conjunction with embodiments.

[0047] The present invention provides a method for real-time ground display of the on-orbit battery charge of a remote sensing satellite battery pack. The power control controller equipped on the remote sensing satellite can monitor the charging current and discharging current of the battery pack in real time. On the premise that the rated battery charge of the battery pack is a determined design value, the computer equipped on the satellite can calculate the charging charge and discharging charge of the battery pack by using the above current data through software, and then calculate the current battery charge and its percentage of the relative rated battery charge, and transmit it to the ground in real time through the satellite telemetry downlink for display to satellite operators and application personnel.

[0048] The method for real-time ground display of the on-orbit battery charge of a remote sensing satellite battery pack, as Figure 1 shown, specifically includes the following steps:

[0049] Step 1: Obtain the rated battery charge Q of the satellite battery pack E . Q E is the design index of the battery pack. When the battery pack is produced, Q E is already determined.

[0050] Step 2: The satellite obtains the charging current I C and discharging current I D of the battery pack in real time on orbit. The satellite realizes obtaining the charging current I C and discharging current I D of the battery pack through the monitoring circuit in the power controller. In order to prevent the small changes of the monitoring circuit near zero from affecting the subsequent calculation results, it is necessary to preset the charging current effective threshold and discharging current effective threshold, which are respectively denoted as I CE and I DE , and the unit is ampere.

[0051] When the absolute value of the charging current obtained this time is less than the charging current effective threshold, the charging current this time is recorded as 0; otherwise, it is recorded as the effective charging current I C .

[0052] If the absolute value of the discharge current obtained this time is less than the effective threshold of the discharge current, the discharge current this time is recorded as 0; otherwise, it is recorded as the effective discharge current I D .

[0053] Step 3: The satellite calculates the charging power Q C and the discharging power Q D of the battery pack in real time during orbit. The charging power Q C and the discharging power Q D are calculated as follows:

[0054] Q C = Q C(n-1) + I C × T ÷ 3600

[0055] Q D = Q D(n-1) + I D × T ÷ 3600

[0056] In the formula, Q C is the charging power of the battery pack obtained from this calculation;

[0057] Q C(n-1) is the charging power of the battery pack obtained from the previous calculation;

[0058] I C is the charging current of the battery pack obtained in Step 2 this time;

[0059] Q D is the discharging power of the battery pack obtained from this calculation;

[0060] Q D(n-1) is the discharging power of the battery pack obtained from the previous calculation;

[0061] I D is the discharging current of the battery pack obtained in Step 2 this time;

[0062] T is the measurement duration this time.

[0063] Among them, the initial values of Q C and Q D are preset, and the default setting is 0; after the satellite is in orbit, the initial values of Q C and Q D are changed through telecommand.

[0064] Step 4: The satellite calculates the current power Q R of the battery pack in real time during orbit. The calculation method of the current power Q R is as follows:

[0065] Q R = Q R0 + KC ×Q C -Q D

[0066] where Q R0 is the initial power of the battery pack;

[0067] K C is the charging efficiency coefficient of the battery pack;

[0068] Q C is the charging power of the battery pack obtained this time;

[0069] Q D is the discharging power of the battery pack obtained this time.

[0070] Among them, the values of Q R0 and K C are preset, and are default set to Q E and 0.98 respectively. After the satellite is in orbit, the set values of Q R0 and K C are changed through telecommand.

[0071] Step Five: The satellite calculates in real time the percentage P R of the current power of the battery pack relative to the rated power. The calculation method of the percentage P R of the current power relative to the rated power is:

[0072] P R = Q R ÷ Q E × 100%.

[0073] Step Six: Transmit the charging current I C and discharging current I D in Step Two, the charging power Q C and discharging power Q D in Step Three, the current power Q R in Step Four, and the percentage P R of the current power relative to the rated power in Step Five to the ground and display them to satellite operators and application personnel.

[0074] Regard the charging current I C and discharging current I D 、charging power Q C and discharging power Q D 、current power Q R 、and the percentage P R of the current power relative to the rated power as satellite telemetry parameters and transmit them to the ground through the telemetry downlink to display to satellite operators and application personnel.

[0075] Step 7: Repeat Steps 2 to 6, and transmit the calculated power parameters to the ground each time.

[0076] The conditions for terminating the calculation of power parameters are:

[0077] Charging current I C and discharging current I D are both 0; and after terminating the calculation of power parameters, set Q C to Q C0 and set Q D to Q D0 , and wait for the next calculation.

[0078] Embodiment

[0079] A certain remote sensing satellite is currently in orbit working.

[0080] Step 1: The satellite acquires and records the rated power of the battery pack, Q E = 100 Ah.

[0081] Repeat Steps 2 to 6 at a time interval of 10 s, i.e., T = 10 s.

[0082] Step 2: The satellite acquires and records the charging current and discharging current of the battery pack in real time during orbit. For example, this is the 100th time to execute Step 2:

[0083] I C = 0

[0084] I D = 30 A

[0085] Step 3: The satellite calculates the charging power and discharging power of the battery pack in real time during orbit. For example, this is the 100th time to execute Step 3:

[0086] Q C100 = Q 99 + I C × T ÷ 3600 = 0 + 0 × 10 ÷ 3600 = 0

[0087] Q D100 = Q D99 + I D × T ÷ 3600 = 7.958 + 30 × 10 ÷ 3600 = 8.039 Ah

[0088] Step 4: The satellite calculates the current power of the battery pack in real time during orbit:

[0089] Q R = Q R0 + K C × Q C -Q D= 100 + 0.98×0 - 8.039 = 91.961 Ah

[0090] Step Five: The satellite calculates in real time the percentage of the current battery power of the battery pack relative to the rated power:

[0091] P R = Q R ÷ Q E × 100% = 91.961 ÷ 100 × 100% = 91.961%

[0092] Step Six: The charging current and discharging current (I C and I D ) of the battery pack, the charging power and discharging power (Q C and Q D ), the current power of the battery pack and the percentage relative to the rated power (Q R and P R ) obtained in Steps Two to Five are all used as telemetry parameters of the satellite and are transmitted to the ground through the telemetry downlink for display to satellite operators and application personnel.

[0093] Step Seven: Terminate the calculation, which requires simultaneously meeting the following conditions: The charging current and discharging current (I C and I D ) of the battery pack are both 0. After terminating the calculation, set Q C to Q C0 , set Q D to Q D0 , and wait for the next calculation.

[0094] The present invention can display in real time the current power of the battery pack of the remote sensing satellite in orbit and the percentage relative to the rated power. The existing methods only display the historical cumulative values of the charging power and discharging power, and there is insufficient intuitive display of the currently available power of the battery pack.

[0095] The calculation process of the current power of the battery pack in the present invention is all realized independently by the satellite without the need for ground calculation and processing. Therefore, the obtained data can not only be used by ground personnel, but also can be used as the data source for the satellite's autonomous health and autonomous mission functions.

[0096] The display effect of the current power of the battery pack in the present invention is the same as that of a commonly used mobile phone, making the usage experience of satellite operators and application personnel very friendly.

[0097] Although the present invention has been disclosed above in preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the methods and technical content disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack, characterized in that: Including: Step 1: Obtain the rated power Q of the satellite battery pack E ; Step 2: The satellite obtains the charging current I of the battery pack in real time during orbit operation C and the discharging current I D ; Step 3: The satellite calculates the charging power Q C and discharging power Q D of the battery pack in real time during orbit operation; Step 4: Calculate the current power Q of the battery pack in real time during satellite operation R ; Step 5. Calculate the percentage P of the current power of the battery pack relative to the rated power in real time during satellite operation R ; Step 6: Transmit the charging current I C and the discharging current I D , the charging quantity Q C and the discharging quantity Q D in Step 3, the current quantity Q R in Step 4, and the percentage P R of the current quantity to the rated quantity in Step 5 to the ground for display to satellite operators and application personnel; Step 7: Repeat Steps 2 to 6, and transmit the power parameter calculated each time to the ground.

2. The real-time ground display method for the on-orbit power of the remote sensing satellite battery pack according to claim 1, characterized in that: In the first step, Q E is the design index of the battery pack. When the battery pack is produced, Q E is determined.

3. The ground real-time display method for the on-orbit power of the remote sensing satellite battery pack according to claim 1, wherein: In the second step, the satellite obtains the charging current I of the battery pack through the monitoring circuit in the power controller C and the discharging current I D ; To prevent the small changes of the monitoring circuit near the zero value from affecting the subsequent calculation results, it is necessary to preset the effective charging current threshold and the effective discharging current threshold, denoted as I CE and I DE , both in amperes; When the absolute value of the charging current obtained this time is less than the effective threshold of the charging current, the charging current this time is recorded as 0. Otherwise, it is recorded as the effective charging current I C ; If the absolute value of the discharge current obtained this time is less than the effective threshold of the discharge current, the discharge current this time is recorded as 0; otherwise, it is recorded as the effective discharge current I D .

4. A method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack according to claim 3, characterized in that: In the third step, the charging quantity Q C and the discharging quantity Q D are calculated as follows: Q C = Q C(n-1) + I C × T ÷ 3600 Q D = Q D(n-1) + I D × T ÷ 3600 Where Q C is the charging power of the battery pack obtained from this calculation; Q C(n-1) The charging power of the battery pack obtained for the last calculation; I C is the charging current of the battery pack obtained in step two this time; Q D The discharge power of the battery pack obtained for this calculation; Q D(n-1) The discharged power of the battery pack obtained from the last calculation; I D is the discharge current of the battery pack obtained in step two this time; T is the measurement duration this time.

5. A method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack according to claim 4, characterized in that: The said Q C and Q D have initial values that are preset, with the default setting being 0; after the satellite is in orbit, the initial values of Q C and Q D are changed via a remote control command.

6. The method for real-time ground display of the on-orbit power of the remote sensing satellite battery pack according to claim 4, characterized in that: In the fourth step, the current power Q R is calculated as follows: Q R = Q R0 + K C × Q C − Q D Where Q R0 is the initial charge of the battery pack; K C is the charging efficiency coefficient of the battery pack; Q C The charging power of the battery pack obtained this time; Q D is the discharge power of the battery pack obtained this time.

7. A method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack according to claim 6, characterized in that: Q R0 and K C The values of are preset, and the default values are set to Q E and 0.98 respectively. After the satellite is in orbit, Q R0 and K C The set values of are changed through remote control commands.

8. A method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack according to claim 1, characterized in that: In the fifth step, the percentage P of the current power relative to the rated power R is calculated as follows: P R = Q R ÷Q E × 100%.

9. A method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack according to claim 1, characterized in that: In step six, the charging current I C and the discharging current I D , the charging power Q C and the discharging power Q D , the current power Q R , and the percentage P R of the current power relative to the rated power are used as satellite telemetry parameters and transmitted to the ground through the telemetry downlink for display to satellite operators and application personnel.

10. A method for real-time ground display of the on-orbit power of a remote sensing satellite battery pack according to claim 1, characterized in that: In the said Step 7, the condition for terminating the power parameter calculation is: Charging current I C and discharging current I D are both 0; and after the end-of-charge parameter calculation, Q C is set to Q C0 , Q D is set to Q D0 , and wait for the next calculation.

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