CN107545108B - Method for enhancing size from dragging area to dragging mass ratio of fragment clearing task - Google Patents
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Abstract
The invention relates to a method for enhancing size from a dragging area to a mass ratio dragging of a debris clearing task, and belongs to the field of space debris clearing. The core idea of the method is as follows: the relationship between the natural decay time of the debris and its initial mass is linked to the surface of the sail required for the final desired off-track time, and based on current debris clearance criteria, the towed sail designed by the method has been considered to drive the final equation; and the method does not generally affect the sail type, it can limit the design parameters of any towed sail to further optimize the design cycle; international standards for similar tasks of the world's prime space agency have been used so that tasks defined by any country can be calculated in this way.
Description
Technical Field
The invention relates to an Ahmadglo inequality, in particular to a method for enhancing the size of a dragging area to a mass ratio dragging of a debris removal task, belonging to the field of space debris removal.
Background
The useful life of all spacecraft launched into space is limited. After their life cycle, spacecraft and satellites are useless, accumulating in space, increasing the amount of debris. The spacecraft and satellite remain in orbit unless removed or burned in the atmosphere, and as the number of debris increases, collisions between them become possible leading to the production of more debris, a phenomenon that has become normal.
Today, there are several methods to off-track an end-of-life spacecraft. All techniques aim to reduce the near-site altitude until the aerodynamic forces become large enough to eventually re-orbit. At this point, the aerodynamic heating and pressure applied to the spacecraft or satellite will increase and the spacecraft or satellite will be extensively destroyed in the atmosphere.
Today, the leading off-track strategy involves using small rocket motors, electric tethers, or pneumatic drag augments to force re-entry for the purpose of eliminating the targeted debris.
Small rocket motors may be used to propel the satellite toward the earth at a particular angle and speed to ensure destruction upon re-orbit. Rocket motors may be used to slow the rate at which a satellite descends and burns in the atmosphere. This development of technology makes use of missile technology which has reached commercial levels. The main advantage of this rocket is that the detachment process is controlled by a precise angular firing. Rocket technology, however, has the drawbacks of being extremely expensive, very heavy in mass, and complex in technology, including maintaining pressure on the rocket fuel for more than 10 years before its end of service life.
The electrically powered tether is an electrically conductive joint that extends between an off-orbit spacecraft and a spaced deployment end, possibly down a distance of several kilometers. Thus, the tether technique involves deploying and towing wires from a satellite through the earth's magnetic field. The interaction between the tether and the earth's magnetic field produces a propulsive force that can be used to raise and lower the altitude orbit of the satellite. Typically, the interaction between the tether and the earth's magnetic field generates a propulsive force such that the force is used to simultaneously raise and lower the satellite altitude orbit. When a derailment is required, the deployment unit of the tether system will remain mostly dormant for the useful life of the main spacecraft to which it is attached. Electric powertrain ropes have potential, but require a high degree of active control during the deployment and derailment process itself.
Pneumatic drag enhancement involves an increase in air resistance. The air resistance or drag decreases as the height increases and becomes progressively thinner. This off-track strategy is limited to LEO only. The satellites in this area experience a fairly limited aerodynamic drag and the reduction in satellite velocity due to the air drag is very small. Systems capable of increasing aerodynamic drag increase air drag, causing the speed of the satellite to decrease at the rate at which the satellite is being de-orbited in the desired time.
In drag augmentation systems, the towing sail is of particular interest. The concept proposed so far consists of compacting the towed sail transported by the spacecraft to a position close to the target fragment, then attaching the compacted towed sail to the target fragment, and finally expanding it to its final surface. This final surface will be responsible for creating a drag to remove the target debris from its initial position. The larger this drag surface, the more the device will pass over the target debris. In view of the limited space within the spacecraft, the towing sail must be loaded in its compacted version, which limits the maximum towing surface of the towing sail.
The advantage of the passive drag enhancement method is related to the simplicity of the task in the overall graph and the amount of payload required per fragment to be removed is also less. Although this technique has been studied to a great extent at present, no specific method has been developed to ensure the relationship between the surface area and the off-track time. As a main requirement for each task, the off-track time is a major factor, being fully related to the size of the sail. The difficulty of the towing sail size algorithm is: the decrease in track height at off-track phase is non-linear. In view of all the requirements of the task, it is necessary to develop a simple method that can be used to exactly optimize the relevant orbital elements of any particular fragment and its initial mass and cross-section.
Disclosure of Invention
The invention aims to provide a method for increasing the size of a towed sail from a towing area to a mass ratio towing area of a debris removal mission, aiming at developing a method for increasing the size of the towed sail from the area to the mass ratio towing area of the particular debris, which can ensure the required sail size required by any orbit time according to the mission requirements.
The core idea of the method is as follows: the relationship between the natural decay time of the debris and its initial mass is linked to the surface of the sail required for the final desired off-track time, and based on current debris clearance criteria, the towed sail designed by the method has been considered to drive the final equation; and the method does not generally affect the sail type, it can limit the design parameters of any towed sail to further optimize the design cycle; international standards for similar tasks of the world's prime space agency have been used so that tasks defined by any country can be calculated in this way.
The method is realized by the following technical scheme:
step A, deriving a relational expression of a calculated area-to-mass ratio parameter by using a power series data fitting method based on designed towing sail data;
b, extracting ideal off-orbit time to obtain a general coefficient expression of the final relation of the surface area and the quality;
step C, adopting the current fragment processing standard and the expression obtained in the step A and the step B, namely: obtaining an Ahmandoo inequality by a relational expression of the area-to-mass ratio parameter and a general coefficient expression of the final relation of the surface area and the mass;
from step a to step C, the drag area to mass ratio drag enhanced sizing method of the debris removal task is now complete.
Based on the steps A to C, aiming at a specific debris removal task, the parameter calculation process of the method from the dragging area to the mass ratio dragging enhancement size is as follows:
the method comprises the following steps of firstly, selecting fragments to be removed based on requirements;
step two, calculating the initial mass and the cross-sectional area of the fragments to be removed in the step one;
step three, imitating the natural decay time of the fragments to be removed selected in the step one on the basis of the calculated initial mass and cross sections;
step four, determining the required off-orbit time required by the task by utilizing the natural attenuation time and the required off-orbit time value through the steps A to C and the method;
step five, acquiring the size of the towing sail by using an Ahmaddoo inequality;
sixthly, checking based on the towing sail derailing time;
from step one to step six, the towing sail size, i.e. area and mass, is calculated by the towing area to mass ratio towing augmentation dimension method for performing the debris removal task according to the present invention.
Advantageous effects
Compared with the existing dragging enhancement size method, the method for enhancing the size from the dragging area to the mass ratio of the debris removal task has the following beneficial effects:
1. the method of the invention provides a very simple sail sizing method;
2. the method of the invention is applicable to any debris size and is independent of the type of towing sail;
3. the method of the invention is the only method which can calculate the section and mass of the towing sail for specific off-orbit time;
4. the method according to the invention can be further optimized for the specific type of towing sail.
Drawings
The following figures are used to visualize the drag-area-to-mass-ratio drag-enhanced sizing method that expresses the debris removal task described in this invention and to demonstrate the accuracy of the method.
FIG. 1 shows the area to mass ratio of the recently designed towing sail in Table 1;
FIG. 2 shows the fitting curve remaining with the data based on the selected towing sail;
FIG. 3 illustrates the use of the method according to the invention in steps;
FIG. 4 shows the natural decay time of the SCOUT G-1 DEB;
FIG. 5 shows the natural decay time of METEOR 2-5 DEB;
FIG. 6 shows a simulation of the dimensions of the towed sail for-1 DEB and METEOR 2-5DEB using the present method.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and embodiments, and technical problems and advantages solved by the technical solutions of the present invention will be described, wherein the described embodiments are only intended to facilitate understanding of the present invention, and do not limit the present invention in any way.
Example 1
The U.S. space agency technical standard 8719.14 and the U.S. aerospace restricted orbital fragmentation program requirements (NPR8715.6A) set forth a set of requirements and standards for operating the space fragmentation mitigation and EOL disposal phases of satellites. This standard is related to the LEO environment and is the only benefit of this patent due to the environment and nature of the towing sail operation required. NASA technical standard 8719.14 states that LEO satellites should be deleted within 25 years after EOL and not more than 30 years after launch. Objects with a short-distance altitude of less than 600 km do not require orbit clearance according to atmospheric pressure below this altitude. Debris high above 700(km) has been a major problem for centuries.
To formulate the final equation, a set of similar tasks of the design is considered. In 2010, NASA has proposed a 3UNanoSAil-D2 cube with a total mass of 4kg, with a 9 square meter tow sail deployed over a 640 km circular orbit.
The european space agency designed and analyzed gobicomm fragments from a 25 year off-orbit phase, with a tow sail mass of 2.5 kg and a surface of 12 square meters. The performance of the gossamer deorberter compared to the single and dual propellants was 55-70% and 14-39%, respectively. The derorbitsailfp 7 was developed by the sai space center, university of sai, as a task for the technical demonstration of Cubesat, and by means of hairspring structural studies using DLR, a size of 16 square meters with a total weight of 3.4 kg could be reached. TechDemosat-1 is a technical demonstration satellite funded by the United kingdom using an off-orbit wind EOL processing stage with a mass ratio of 0.7(m 2/kg). CanX-7 (advanced Nano satellite test in Canada 7) was developed to demonstrate the feasibility of a lightweight and low cost deployable towing sail. The conceptual design is based on the inter-agency space debris coordination Commission (IADC) requirements with sail size attributes of 0.9(kg) to 4.2 (square meters). InflateSail is a 3U cube, which is introduced in the QB50 project to demonstrate the feasibility of inflatable sails in space. By using a 3 meter diameter inflated torus frame, the total area is designed to be 10 square meters. The technical institute of distributed spacecraft systems at the university of beijing has designed a towed sail with dimensions such that it can target multiple debris in a single mission on different orbits, using a telescoping arm and a telescoping membrane, and a parent spacecraft can carry up to 5 different towed sails to remove 5 debris in a single mission. The detailed area and mass of all the above-mentioned towing sails are given in table 1 below and in fig. 1.
Table1.Selected designed drag sails information
As can be seen from FIG. 1, by using power progression, the towing sail area and mass relationship can generally be extracted. The second term of the infinite power series has been used for data fitting, and the power series can be expressed as the following equation (1):
it can be further expressed as the following formula (2):
and b isn(x-a)kRepresenting the individual terms, a center of the power level value; for neighborhood values of data of a circle with radius r, the coefficient may be calculated according to the following equation (3):
where the definition of the r value is the convergence region of the fit data. This method is simple in practice, but converges slowly. Matlab data fitting kits have been used to obtain a final curve fit of the data. The mass area equation calculated in the format of the following equation (4) is:
f(x)＝axb+c (4)
the coefficients a, b and c (and their acceptable ranges), which are more important to calculate the area based on the towed sail dataset than the quality, yield prediction coefficients for the following coefficients a, b and c:
a＝4.355(-15.29，24)
b＝0.7731(-0.476，2.022)
c＝1.466(-30，32.93)
in order to better fit the exact parameters, it is used for prediction, i.e. to better fit the exact parameter values. The Root Mean Square Error (RMSE) of equation (3) is equal to 11.4, R squared, i.e.: the square of the correlation between the predicted value and the response value is 0.98.
Fig. 2 shows the fitted curve and the residual error for each data point. The fitting method depends on the data set that has been selected for the simulation and may be changed slightly to estimate the other set of data with greater accuracy.
Below, T1And T2Respectively the natural life time of the fragments without a towed sail and the off-track time with a towed sail. According to the above requirements, also taking into account the maximum weight for the towing sail, only 30% of the target fragment mass or 30% of the main spacecraft payload can be taken as the decided processing time, as follows:
T2≤30years&MDragSail≤0.3M1
and A is1，M1And A2，M2Are the initial area, mass and enhanced area of debris, the mass of debris including the attached towing sail. The key factor defined as the AtM delta ratio should remain below the inverse of the reduction time, as in equation (5):
the relationship between area and mass can be written as:
A2＝A1+ADragSail(6)
M2＝M1+MDragSail(7)
substituting equations (6) and (7) into equation (5) yields equation (8) as follows:
in equation (3), the relationship between the area and the mass of the towed sail becomes equation (9) below:
ADragSail＝a(MDragSall)b+c (9)
substituting equation (9) into equation (8) yields the final optimized AtM ratio, i.e.: amadore inequality, the following formula (10):
by selecting the initial fragment mass range, plus the tugboat mass, which may be up to one third of the total payload, an optimized towing sail area may be obtained. For a specific value of quality that makes the above inequality equal to zero, an optimal area size of the selected off-track time can be achieved.
The debris samples were taken by calculating the towing sail size according to the inequality of ehamadoro. The same mentioned steps have also been followed for these fragments and for fig. 3. As can be seen from FIG. 3, after selecting the debris to be removed and simulating its natural decay time, the Amader's Roche inequality can calculate the appropriate sail size for any off-track time and the 2-5DEB based on orbit simulations.
The two selected fragments are METEOR 2-5DEB and SCOUT G-1 DEB. Table 2 below is a simulation of two selected patches.
Table 2 two selected patches of simulation
First, the natural decay time is calculated based on the Encke method of ENTEOR 2-5DEB and SCOUT G-1DEB (FIGS. 4 and 5).
As can be seen from FIG. 4, the time variation of the semi-major axis of SCOUT G-1DEB with a natural decay time of 48643 days; as can be seen from fig. 5, the natural decay time based on METEOR 2-5DEB was an orbital simulation of 60124 days.
Then, sail size was calculated to demonstrate the accuracy of the method based on the 25 year orbital time inequality of Ahmadloo, as shown in table 3 below:
TABLE 3 Sail size calculated from Ahmadglo inequality
| Off track time | ADragSail(m2) | MDragSail(kg) |
| 25 years (SCOUT G-1) | 11.371 | 2.8947 |
| 25 years (METEOR 2-5) | 15.520 | 4.551 |
Table 3 shows the towed sail area and mass for a 25 year off-track cycle calculated based on the patented method of METEOR 2-5 and SCOUT G-1 patches.
And (4) according to the calculation parameters of the towing sail at each off-orbit time, repeatedly connecting the towing sail with the orbit simulation of the fragments as an accuracy proof of the method. The final results demonstrate that the required off-track time is met by calculating the size from towing the sail (fig. 6), as shown in table 4 below.
TABLE 4 off-track time by calculation of size from towing sail
| Time to leave orbit (year) of preliminary plan | SCOUT G-1DEB (year) | METEOR 2-5DEB (year) |
| 25 | 21.89 | 23.31 |
As can be seen in FIG. 6, SCOUT G-1 has a track run time of 21.89 years and METEOR 2-5 has a track run time of 23.31 years (8488 days) (the last portion of the curve shows the final track run time). These off-track values are parameters that show the accuracy of the method, as they are all less than 25 years old. As long as the off-track time is less than the initial planning time, this means that the method proposed by this patent is accurate.
The above detailed description is intended to illustrate the objects, aspects and advantages of the present invention, and it should be understood that the above detailed description is only exemplary of the present invention and is not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (1)
1. The method for enhancing the size from the dragging area to the mass ratio dragging of the debris removal task is characterized by comprising the following steps of: the method comprises the following steps:
step A, deriving a relational expression of a calculated area-to-mass ratio parameter by using a power series data fitting method based on designed towing sail data;
b, extracting ideal off-orbit time to obtain a general coefficient expression of the final relation of the surface area and the quality;
step C, adopting the current fragment processing standard and the expression obtained in the step A and the step B, namely: obtaining an Ahmandoo inequality by a relational expression of the area-to-mass ratio parameter and a general coefficient expression of the final relation of the surface area and the mass;
from step A to step C, the method for enhancing the size from the dragging area to the mass ratio dragging of the debris removal task is completed;
based on the steps A to C, aiming at a specific debris removal task, the parameter calculation process of the method from the dragging area to the mass ratio dragging enhancement size is as follows:
the method comprises the following steps of firstly, selecting fragments to be removed based on requirements;
step two, calculating the initial mass and the cross-sectional area of the fragments to be removed in the step one;
step three, calculating the natural attenuation time of the initial mass and the cross section imitating the fragment based on the fragment to be removed selected in the step one;
step four, determining the required off-orbit time required by the task by using the natural attenuation time and the required off-orbit time value through the steps A to C;
step five, acquiring the size of the towing sail by using an Ahmaddoo inequality;
sixthly, checking based on the towing sail derailing time;
from step one to step six, the towing area to mass ratio towing augmentation dimension method for completing the debris removal task calculates the towing sail size, i.e., area and mass.
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| CN105910583A (en) * | 2016-04-25 | 2016-08-31 | 北京理工大学 | Space debris fast detection and positioning method based on space-borne visible camera |
| CN106114919A (en) * | 2016-08-01 | 2016-11-16 | 北京理工大学 | A kind of space junk rope system pulls racemization and method for cleaning |
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| CN105910583A (en) * | 2016-04-25 | 2016-08-31 | 北京理工大学 | Space debris fast detection and positioning method based on space-borne visible camera |
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