CN107391813A - A kind of energetic optimum moon based on the moon high ladder ground transfer orbit design method - Google Patents
A kind of energetic optimum moon based on the moon high ladder ground transfer orbit design method Download PDFInfo
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Abstract
Transfer orbit design method, its method and step are as follows with providing a kind of energetic optimum moon based on moon high ladder by the present invention：One：With designing the moon based on moon high ladder transfer scheme；Two：Establish transfer scheme model of energy；Three：Establish transfer scheme energy optimizing model；Four：Transfer scheme is energy-optimised；Pass through above step, a kind of present invention with establishing brand-new moon based on moon high ladder transfer scheme, realize simultaneously to the energy-optimised of transfer orbit, with reducing the moon energy expenditure of transfer process, solve the problems, such as that traditional transfer scheme power consumption is big, cost is high.
Description
Technical field
Transfer orbit design method, can solve tradition the present invention relates to a kind of energetic optimum moon based on moon high ladder
The problem of moon ground transfer scheme power consumption is big, cost is high, belongs to space technology field.
Background technology
As the mankind explore deepening continuously for space, existing delivery technology can not increasingly meet to require.The world at present
On into the main delivery vehicle of space be carrier rocket, the scale of carrier rocket and horizontal support enter the ability in space.
But the efficiency of carrier rocket is very low, for the quality of payload less than the 10% of rocket total quality, propellant account for 90%
Quality above.Delivery technology based on high ladder technology is shown one's talent with its novel theory and powerful advantage.
High ladder, space elevator is called, its main body is a hawser, and one end is fixedly connected on ground surface platform, and the other end leads to
Space is connected with counterweight, and whole hawser keeps tightening.For the ease of application, space station can be set on hawser.Climbing device edge
Hawser is run, and goods and personnel can be transported between ground and space station.Because the gravitation of the moon is small, moon high ladder is to hawser
The requirement of intensity is smaller；And the moon does not have air and magnetic field, spacecraft and space trash are also few, the stabilization of moon high ladder and
Safety has ensured.
The mankind in moon exploration activity, the moon surface sample return to task and manned moon exploration task and be required for spacecraft
Launch from moonscape and return to the earth.Manned at present and unmanned spacecraft returns to the earth from lunar surface will use chemical propulsion,
The energy of consumption is big, and cost is high, and it is therefore necessary to design the optimal energy transfer scheme from the lunar surface return earth.
In order to solve the above problems, transfer orbit is set the present invention with proposing a kind of energetic optimum moon based on moon high ladder
Meter method.The present invention can reduce lunar surface to the transfer energy of the earth in terms of two.First, propose the moon based on moon high ladder
Ground transfer scheme, this scheme is compared to the little energy that tradition is consumed using the transfer scheme of carrier rocket；Second, it is based on this scheme
Energetic optimum rail design method is proposed, is shifted while the moon based on moon high ladder of energetic optimum can be designed using the method
Track.
The content of the invention
1st, purpose
Transfer orbit design method, utilize it is an object of the invention to provide a kind of energetic optimum moon based on moon high ladder
Moon high ladder with designing moon transfer orbit, and design is optimized to track, obtains the transfer scheme of energetic optimum.
2nd, technical scheme
To achieve these goals, the present invention uses following technical scheme.
A kind of present invention energetic optimum moon based on the moon high ladder ground transfer orbit design method, it includes following step
Suddenly：
Step 1：With designing the moon based on moon high ladder transfer scheme
The moon based on moon high ladder transfer scheme be divided into four-stage：Climb section, moon heart elliptic orbit section, the moon heart
Hyperbolic orbit section and the earth's core elliptic orbit section；The relation of this four-stage is ordinal relation in time；
It is somebody's turn to do " climbing section " and refers to a certain height that climbing device delivers to payload within lunar effect ball；
It is somebody's turn to do " moon heart elliptic orbit section " and refers to that airship enters moon heart elliptic orbit, is flown from apocynthion to perilune；
It is somebody's turn to do " moon heart hyperbolic orbit section " and refers to that airship enters moon heart hyperbolic orbit, is flown from perilune to lunar effect
Ball edge；
It is somebody's turn to do " the earth's core elliptic orbit section " and refers to that airship enters the earth's core elliptic orbit, is flown from lunar effect ball edge to near-earth
Point；
Step 2：Establish transfer scheme model of energy
" the transfer model of energy " is by climbing section energy spectrometer submodel and Orbit Transformation section energy spectrometer
Model two parts form, and the two is coordination；
Should " climbing section energy spectrometer submodel " be used to analyzing climbing device that payload is transported into moon heart elliptic orbit be remote
The moon puts consumed energy；
Should the energy of " Orbit Transformation section energy spectrometer submodel " for analyzing airship progress Orbit Transformation consumption.
Step 3：Establish transfer scheme energy optimizing model
" the transfer scheme energy optimizing model " is made up of two parts：The energy-optimised target of transfer scheme and transfer side
The energy-optimised constraint of case；
" the energy-optimised target of transfer scheme " is somebody's turn to do to refer to find the minimum transfer scheme of energy；
It is somebody's turn to do " the energy-optimised constraint of transfer scheme " and includes three constraints：Month heart elliptic orbit perilune is highly constrained, the earth's core
Elliptic orbit perigee altitude constrains, single maximal rate increment；
It " moon heart elliptic orbit perilune highly constrained " should refer to that perilune was highly more than certain value, and prevent airship because of the nearly moon
Point is highly too low and hits the moon；
Being somebody's turn to do " constraint of the earth's core elliptic orbit perigee altitude " refers to perigee altitude within the specific limits so that airship can
Safety returns to the earth；
Step 4：Transfer scheme is energy-optimised
" transfer scheme is energy-optimised " refers to be combined optimization using genetic algorithm and quasi-Newton method；Should " heredity
Algorithm " is a kind of optimized algorithm with ability of searching optimum, and it is a kind of classical gradient optimal method to be somebody's turn to do " quasi-Newton method ", excellent
Change result is influenceed by initial value；Independent variable of the present invention is more, if directly using gradient optimal method, is easy to fall into
Enter locally optimal solution, optimal transfer orbit can not be obtained；Global search first can be carried out using genetic algorithm, by genetic algorithm
Initial value of the optimum results as quasi-Newton method, then optimized with quasi-Newton method；The characteristics of this Combinatorial Optimization is to be not easy
Locally optimal solution is absorbed in, and optimum results are often more preferable than genetic algorithm is used alone.
Wherein, " with designing the moon based on the moon high ladder transfer scheme " described in step 1, its practice is as follows：
The height h of climbing section is determined first, then the speed increment Δ v to climb the height h of section and become rail for the first time1
For input parameter, it is determined that moon heart elliptic orbit；Again with perilune height, the perilune speed and second of moon heart elliptic orbit section
The secondary speed increment Δ v for becoming rail2For input parameter, it is determined that moon heart hyperbolic orbit；Finally with moon heart hyperbolic orbit at the end of
Position, speed and third time become rail speed increment Δ v3For input parameter, the earth's core elliptic orbit is determined；
Wherein, " establishing transfer scheme model of energy " described in step 2, the process that it is established are as follows：
Energy of the climbing device in climbing section consumption is tried to achieve according to force analysis first, climbing device is during climbing by ground
The effect of ball gravitation, lunar gravitation, centrifugal force and tractive force；Then the energy for becoming rail three times and consuming is tried to achieve according to change rail speed increment
Amount.
Wherein, " establishing transfer scheme energy optimizing model " described in step 3, the process that it is established are as follows：
Optimization aim is determined first, and optimization aim of the invention is that the energy of transfer scheme is minimum；It is then determined that constraint bar
Part, constraints of the invention include the constraint of highly constrained and speed increment.
Wherein, " transfer scheme is energy-optimised " described in step 4, the method that it optimizes are as follows：
First with genetic algorithm progress global search, the initial value using the optimum results of genetic algorithm as quasi-Newton method, then
Optimized with quasi-Newton method.The characteristics of this Combinatorial Optimization is to be not easy to be absorbed in locally optimal solution, and optimum results are often
It is more preferable than genetic algorithm is used alone.
By above step, a kind of with establishing brand-new moon based on moon high ladder transfer scheme, while realize pair
Energy-optimised, with reducing the moon energy expenditure of transfer process of transfer orbit, solves that traditional transfer scheme power consumption is big, cost
The problem of high.
3rd, advantage and effect
Transfer orbit design method, its major advantage the invention provides a kind of energetic optimum moon based on moon high ladder
It is：A kind of with proposing new moon transfer scheme, i.e., the moon based on the moon high ladder ground transfer scheme, from the aspect of transfer scheme
Shift energy with saving the moon；With proposing the energetic optimum moon based on moon high ladder transfer orbit design method, further reduce
Transfer energy from lunar surface to the earth, greatly reduce cost and energy that moon surface sample returns to task and manned moon exploration task
Amount consumption.
Brief description of the drawings
Fig. 1 is the ground transfer orbit design method flow chart of the energetic optimum moon based on moon high ladder.
Fig. 2 is the ground transfer scheme of the moon based on moon high ladder.
Specific label declaration is as follows in figure：
Ⅰ：Climb section II：Heart elliptic orbit section
Ⅲ：Month heart hyperbolic orbit section IV：The earth's core elliptic orbit section
Ⅴ：Lunar effect ball
h：Climbing device climbing height Δ v1：Become rail speed increment for the first time
Δv2：Second of change rail speed increment Δ v3：Third time becomes rail speed increment
Embodiment
Below in conjunction with accompanying drawing and example, the invention will be further described, but the present embodiment is not intended to limit the invention,
Every similarity method using the present invention and its similar change, the protection category of the present invention all should be included in.
A kind of energetic optimum moon based on moon high ladder is provided transfer orbit design side of the invention as seen from Figure 1
Method, it includes following four step：
Step 1：With designing the moon based on moon high ladder transfer scheme
As shown in Fig. 2 the moon based on moon high ladder transfer scheme be divided into four-stage：Climb section, moon heart ellipse
Orbital segment, moon heart hyperbolic orbit section and the earth's core elliptic orbit section.The relation of this four-stage is ordinal relation in time.
The climbing section refers to a certain height h that climbing device delivers to payload within lunar effect ball.
The moon heart elliptic orbit section refers to that airship applies first velocity pulse Δ v1, airship enters moon heart ellipse rail
Road, when airship is run to perilune the stage terminate.
The moon heart hyperbolic orbit section refers to that airship applies second velocity pulse Δ v in perilune2, airship enters the moon
Heart hyperbolic orbit, when airship is run to lunar effect ball edge the stage terminate.
When the earth's core elliptic orbit section refers to that airship reaches lunar effect ball edge, apply the 3rd velocity pulse Δ
v3, airship enters the earth's core elliptic orbit, when airship is run to perigee the stage terminate.
Solving the motion dynamics equations that each mission phase is used is
H=r × v=const2
In formula, E represents orbital energy, and v is aircraft speed, and r represents position of the aircraft with respect to central body, and G is represented
Gravitational constant, M represent central body quality, and const1 and const2 represent two different constants.
Step 2：Establish transfer scheme model of energy
The transfer model of energy is by climbing section energy spectrometer submodel and Orbit Transformation section energy spectrometer submodel
Two parts form, and the two is coordination.
The climbing section energy spectrometer submodel is used to analyzing climbing device, and that payload is transported into moon heart elliptic orbit is remote
The moon puts consumed energy.Calculation formula is
In formula, WclimbRepresent the total work that climbing device is done, msRepresent airship dry weight, mcRepresent climbing device quality, VeRepresent to promote
Agent specific impulse；ramRepresent the distance between launch point of the airship on high ladder and the moon heart, RmFor the moon radius of a ball, μmRepresent lunar gravitation
Constant, μeRepresent Gravitational coefficient of the Earth, remRepresent ground moon distance, rcRepresent the distance between climbing device and the moon heart, ωmFor the moon
Revolve round the sun angular speed.
The Orbit Transformation section energy spectrometer submodel is used to analyze the energy that airship carries out Orbit Transformation consumption.Calculate public
Formula is
In formula, WtransferRepresent the total work that airship is done.
Thus, it is possible to the energy of transfer scheme unit mass airship dry weight consumption is with obtaining the moon based on moon high ladder：
Step 3：Establish transfer scheme energy optimizing model
Optimized model is as follows：
In formula, p1Represent the semi-latus rectum of moon heart elliptic orbit, e1Represent the eccentricity of moon heart elliptic orbit, ReRepresent the earth
Radius, p3Represent the semi-latus rectum of the earth's core elliptic orbit, e3Represent the eccentricity of the earth's core elliptic orbit.
The optimization aim of the Optimized model is the energy of unit mass airship dry weight consumption, and first is constrained to a moon heart ellipse
Track perilune constrains, and second is constrained to the constraint of the earth's core elliptic orbit perigee, the 3rd speed for being constrained to single application
Increment restriction.
Step 4：Transfer scheme is energy-optimised
The present invention is combined optimization using genetic algorithm and quasi-Newton method.Genetic algorithm is that one kind has global search energy
The optimized algorithm of power, quasi-Newton method are a kind of classical gradient optimal methods, and optimum results are influenceed by initial value.The present invention relates to
Independent variable it is more, if directly using gradient optimal method, be easily ensnared into locally optimal solution, optimal turn can not be obtained
Move track.Can be first using genetic algorithm progress global search, the initial value using the optimum results of genetic algorithm as quasi-Newton method,
Optimized again with quasi-Newton method.The characteristics of this Combinatorial Optimization is to be not easy to be absorbed in locally optimal solution, and optimum results are past
It is past more preferable than genetic algorithm is used alone.
By above step, a kind of with establishing brand-new moon based on moon high ladder transfer scheme, while realize pair
Energy-optimised, with reducing the moon energy expenditure of transfer process of transfer orbit, solves that traditional transfer scheme power consumption is big, cost
The problem of high.By example calculation, compared with transfer scheme with traditional moon, using the moon provided by the invention transfer scheme with
And rail design method, it can at most save energy 30%.
Claims (5)
- A kind of 1. ground transfer orbit design method of energetic optimum moon based on moon high ladder, it is characterised in that：It includes following several Individual step：Step 1：With designing the moon based on moon high ladder transfer schemeThe moon based on moon high ladder transfer scheme be divided into four-stage：Climb section, moon heart elliptic orbit section, moon heart hyperbolic Trajectory section and the earth's core elliptic orbit section；This four-stage is ordinal relation in time；It is somebody's turn to do " climbing section " and refers to a certain height that climbing device delivers to payload within lunar effect ball；It is somebody's turn to do " moon heart elliptic orbit section " and refers to that airship enters moon heart elliptic orbit, is flown from apocynthion to perilune；It is somebody's turn to do " moon heart hyperbolic orbit section " and refers to that airship enters moon heart hyperbolic orbit, is flown from perilune to lunar effect ball side Edge；It is somebody's turn to do " the earth's core elliptic orbit section " and refers to that airship enters the earth's core elliptic orbit, is flown from lunar effect ball edge to perigee；Step 2：Establish transfer scheme model of energy" the transfer model of energy " is by climbing section energy spectrometer submodel and Orbit Transformation section energy spectrometer submodel Two parts form, and the two is coordination；It is that payload is transported into a moon heart elliptic orbit remote moon for analyzing climbing device that " should climb section energy spectrometer submodel " The consumed energy of point；It is the energy that Orbit Transformation consumption is carried out for analyzing airship to be somebody's turn to do " Orbit Transformation section energy spectrometer submodel "；Step 3：Establish transfer scheme energy optimizing model" the transfer scheme energy optimizing model " is made up of two parts：The energy-optimised target of transfer scheme and transfer scheme energy Amount optimization constraint；" the energy-optimised target of transfer scheme " is somebody's turn to do to refer to find the minimum transfer scheme of energy；It is somebody's turn to do " the energy-optimised constraint of transfer scheme " and includes three constraints：The moon, heart elliptic orbit perilune was highly constrained, and the earth's core is oval Perigee of orbit is highly constrained, single maximal rate increment；It " moon heart elliptic orbit perilune highly constrained " should refer to that perilune was highly more than predetermined value, and prevent airship because of perilune height Spend low and hit the moon；Being somebody's turn to do " constraint of the earth's core elliptic orbit perigee altitude " refers to perigee altitude within a predetermined range so that airship can be safe Return to the earth；Step 4：Transfer scheme is energy-optimised" transfer scheme is energy-optimised " refers to be combined optimization using genetic algorithm and quasi-Newton method；It is somebody's turn to do " genetic algorithm " It is a kind of optimized algorithm with ability of searching optimum, it is a kind of classical gradient optimal method to be somebody's turn to do " quasi-Newton method ", optimization knot Fruit is influenceed by initial value；Independent variable of the present invention is more, if directly using gradient optimal method, is easily ensnared into office Portion's optimal solution, optimal transfer orbit can not be obtained；Global search is first carried out using genetic algorithm, by the optimization knot of genetic algorithm Initial value of the fruit as quasi-Newton method, then optimized with quasi-Newton method；The characteristics of this Combinatorial Optimization is to be not easy to be absorbed in part Optimal solution, and optimum results are often more preferable than genetic algorithm is used alone；Pass through above step, with establishing a kind of brand-new moon based on the moon high ladder transfer scheme, while realize to transfer Energy-optimised, with reducing the moon energy expenditure of transfer process of track, solves that traditional transfer scheme power consumption is big, cost is high Problem.
- 2. a kind of ground transfer orbit design method of energetic optimum moon based on moon high ladder according to claim 1, it is special Sign is：" with designing the moon based on moon high ladder transfer scheme " described in step 1, its practice is as follows：The height h of climbing section is determined first, then the speed increment Δ v to climb the height h of section and become rail for the first time1To be defeated Enter parameter, it is determined that moon heart elliptic orbit；Again with the perilune height, perilune speed and second of change of moon heart elliptic orbit section The speed increment Δ v of rail2For input parameter, it is determined that moon heart hyperbolic orbit；Finally with the position at the end of moon heart hyperbolic orbit Put, speed and third time become rail speed increment Δ v3For input parameter, the earth's core elliptic orbit is determined.
- 3. a kind of ground transfer orbit design method of energetic optimum moon based on moon high ladder according to claim 1, it is special Sign is：" establishing transfer scheme model of energy " described in step 2, the process that it is established are as follows：Energy of the climbing device in climbing section consumption is tried to achieve according to force analysis first, climbing device is drawn during climbing by the earth The effect of power, lunar gravitation, centrifugal force and tractive force；Then the energy for becoming rail three times and consuming is tried to achieve according to change rail speed increment.
- 4. a kind of ground transfer orbit design method of energetic optimum moon based on moon high ladder according to claim 1, it is special Sign is：" establishing transfer scheme energy optimizing model " described in step 3, the process that it is established are as follows：Optimization aim is determined first, and optimization aim of the invention is that the energy of transfer scheme is minimum；It is then determined that constraints, this The constraints of invention includes the constraint of highly constrained and speed increment.
- 5. a kind of ground transfer orbit design method of energetic optimum moon based on moon high ladder according to claim 1, it is special Sign is：" transfer scheme is energy-optimised " described in step 4, the method that it optimizes are as follows：First with genetic algorithm carry out global search, the initial value using the optimum results of genetic algorithm as quasi-Newton method, then with plan Newton method optimizes；The characteristics of this Combinatorial Optimization is to be not easy to be absorbed in locally optimal solution, and optimum results are often than list It is solely more preferable using genetic algorithm.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108408084A (en) * | 2018-02-28 | 2018-08-17 | 北京控制工程研究所 | Objects outside Earth capture braking orbit changing method, device and storage medium |
| CN109375648A (en) * | 2018-12-07 | 2019-02-22 | 北京理工大学 | Elliptical orbit satellite Formation Configuration initial method under a kind of multi-constraint condition |
| CN111382876A (en) * | 2020-02-28 | 2020-07-07 | 上海航天控制技术研究所 | Method and system for acquiring initial value of ground fire transfer orbit design based on evolutionary algorithm |
| CN112307611A (en) * | 2020-10-23 | 2021-02-02 | 中国运载火箭技术研究院 | Method for optimizing quantity and speed of scramblers of wide-area overhead ladder system |
| CN113310496A (en) * | 2021-05-08 | 2021-08-27 | 北京航天飞行控制中心 | Method and device for determining lunar-ground transfer orbit |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104527651A (en) * | 2015-01-14 | 2015-04-22 | 张峰 | Vertical traffic device using three-level relay cableway high ladder for completing ground-sky butt joint |
| CN104709477A (en) * | 2015-04-03 | 2015-06-17 | 张峰 | Method for acquiring operation power of space vehicle by virtue of linear velocities of stars and galaxies |
| CN105631095A (en) * | 2015-12-18 | 2016-06-01 | 中国人民解放军国防科学技术大学 | Search method for multi-constrained earth-moon transfer orbit cluster with equal launch intervals |
-
2017
- 2017-07-03 CN CN201710531380.5A patent/CN107391813A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104527651A (en) * | 2015-01-14 | 2015-04-22 | 张峰 | Vertical traffic device using three-level relay cableway high ladder for completing ground-sky butt joint |
| CN104709477A (en) * | 2015-04-03 | 2015-06-17 | 张峰 | Method for acquiring operation power of space vehicle by virtue of linear velocities of stars and galaxies |
| CN105631095A (en) * | 2015-12-18 | 2016-06-01 | 中国人民解放军国防科学技术大学 | Search method for multi-constrained earth-moon transfer orbit cluster with equal launch intervals |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108408084A (en) * | 2018-02-28 | 2018-08-17 | 北京控制工程研究所 | Objects outside Earth capture braking orbit changing method, device and storage medium |
| CN108408084B (en) * | 2018-02-28 | 2020-06-09 | 北京控制工程研究所 | Extraterrestrial celestial body capturing, braking and track changing method and device and storage medium |
| CN109375648A (en) * | 2018-12-07 | 2019-02-22 | 北京理工大学 | Elliptical orbit satellite Formation Configuration initial method under a kind of multi-constraint condition |
| CN109375648B (en) * | 2018-12-07 | 2020-04-10 | 北京理工大学 | Elliptical orbit satellite formation configuration initialization method under multi-constraint condition |
| CN111382876A (en) * | 2020-02-28 | 2020-07-07 | 上海航天控制技术研究所 | Method and system for acquiring initial value of ground fire transfer orbit design based on evolutionary algorithm |
| CN111382876B (en) * | 2020-02-28 | 2023-09-29 | 上海航天控制技术研究所 | Ground fire transfer orbit design initial value acquisition method and system based on evolutionary algorithm |
| CN112307611A (en) * | 2020-10-23 | 2021-02-02 | 中国运载火箭技术研究院 | Method for optimizing quantity and speed of scramblers of wide-area overhead ladder system |
| CN112307611B (en) * | 2020-10-23 | 2024-03-15 | 中国运载火箭技术研究院 | Method for optimizing number and speed of climbing devices of wide area ladder system |
| CN113310496A (en) * | 2021-05-08 | 2021-08-27 | 北京航天飞行控制中心 | Method and device for determining lunar-ground transfer orbit |
| CN113310496B (en) * | 2021-05-08 | 2024-01-09 | 北京航天飞行控制中心 | Method and device for determining moon-earth transfer track |
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