CN111090908B - Group umbrella system design parameter selection method - Google Patents
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Abstract
In a single parachute airdrop test, according to a height and speed change curve in the parachute strength airdrop test, ballistic reconstruction fitting is carried out on resistance areas of all levels of parachutes and main parachutes, and all levels of closing resistance areas of a single parachute and a single main parachute during working are obtained to serve as initial parameter values. In ballistic reconstruction fitting of the parachute, a parachute efficiency factor parameter is introduced, the aerial drop test data of the parachute is taken as an optimization target, the parachute efficiency factor of the parachute is taken as a target parameter, ballistic reconstruction fitting is carried out on the parachute efficiency factors of all stages of parachute opening, the fitting result and the optimization target are used for judging the fitting optimal value of the parachute efficiency factor through a certain criterion, and the parachute efficiency factors of all stages of parachute opening are obtained, so that the resistance area of a single parachute at each stage in the parachute opening system is obtained. The method can quantitatively describe the resistance loss condition of the group umbrella based on the air drop test data in the real use environment, and guide the design of the group umbrella system.
Description
Technical Field
The invention belongs to the field of spacecraft return deceleration landing design, and relates to a design parameter selection method of a parachute system for spacecraft return, which is suitable for parachute design of a large-load recovery landing system.
Background
With the further development of manned space technology, china breaks through and grasps manned space meeting docking technology, and starts to develop into the era of autonomous construction of space stations. Meanwhile, people-carrying airships of new generation with stronger development function and performance are developed in China such as Mei Ruo, and the like, and are aimed at a plurality of fields such as space station service, people-carrying deep space exploration, deep space residence and the like, so that people-carrying flying capability is expected to be provided in the next few years. For this reason, new generation manned airships are also developed in China.
The new generation manned spacecraft has large load mass, and the traditional single parachute landing technology can not meet the deceleration requirement of the new generation manned spacecraft, so that the recovery subsystem of the new generation manned spacecraft adopts the parachute landing technology of the parachute system for deceleration.
The resistance area is the most important technical index of the parachute system, in the parachute system, the phenomenon of resistance loss occurs to the parachute, the resistance area of the parachute is not the superposition of all the resistance areas of the parachute, and in the research design of the parachute, the quantitative description of the resistance loss is needed. How to determine the relationship between the drag area of a swarm umbrella and the drag area of a single parachute constituting the swarm umbrella is a key problem faced by the design of the swarm umbrella.
In the text of numerical simulation of the stable fall phase of the parachute based on the ALE method by the Nanjing aviation aerospace university Lianliang et al, the numerical simulation method is adopted to calculate the condition of the resistance loss of the parachute in the stable fall phase, the numerical calculation method is based on various ideal assumptions of a flow field, has a gap from a real use environment, and the calculation result is not verified, and is only limited to the resistance loss description of the stable fall phase, but cannot be applied to the parachute design of the whole process of a new airship.
Disclosure of Invention
The invention solves the technical problems that: the method for selecting the design parameters of the spacecraft return deceleration landing parachute system is provided, and based on the airdrop test data in the real use environment, the parachute drag loss condition of the working state of each stage in the whole process can be quantitatively described, so that the design of the parachute system is guided.
The technical scheme of the invention is as follows: a method for selecting design parameters of a group umbrella system comprises the following steps:
(1) Selecting a top ring sail parachute as a main parachute, selecting a top strip parachute as a speed reducing parachute, and constructing a single parachute system;
(2) In the single parachute airdrop test by utilizing the single parachute system, ballistic reconstruction fitting is carried out on the resistance areas of all levels of parachutes and main parachutes according to the height and speed change curves in the single parachute airdrop test along with time, so as to obtain all levels of closing resistance areas of the single parachute and the single main parachute during working, and the closing resistance areas are recorded as JA 0i ,i＝1,2…N J ，ZA 0j ,j＝1,2…N Z ，N J 、N Z The closing-up stages of the speed reducing umbrella and the main umbrella are respectively carried out;
(3) Selecting a P1 top ring sail umbrella as a main umbrella, selecting a P2 top strip umbrella as a speed reducing umbrella, and constructing a group umbrella system, wherein P1 and P2 are positive integers larger than 1;
(4) Carrying out a group parachute air drop test by using the group parachute system to obtain a change curve V of the speed measured by the group parachute air drop test along with time 0 (t) the height over time curve H 0 (t) as an objective function;
(5) Ballistic reconstruction fitting is carried out on the group umbrella efficiency factors of all stages of umbrella opening, in particular to
Wherein eta Ji ＝1-m i Δη is the efficiency factor of the ith stage of the parachute, η Zj ＝1-n j Δη is the efficiency factor of the j-th stage closing stage of the main umbrella, m i =1, 2, 3 … …, fitting steps for the drogue efficiency factor, n j =1, 2, 3 … … is the number of main umbrella efficiency factor fitting steps, Δη is the group umbrella efficiency factor fitting step;
(6) Comprehensively consider V 0 (t)、H 0 (t) two optimization targets, formulating an efficiency factor criterion parameter obj and a criterion function f obj (η Ji ，η Zj )，
Find the equivalent f obj (η Ji ，η Zj ) Independent variable η when=obj Zj 、η Ji The value of (A) is recorded as eta Jj_obj 、η Zj_obj The method comprises the steps of carrying out a first treatment on the surface of the Wherein T is the process time, and Deltat is the time step;
(7) The total resistance area of each parachute and main parachute required by each stage in the design of the parachute system is recorded as S Total Ji ,S Total Zj
(8) Using the formula
Calculating to obtain the resistance area S of single parachute at each stage in the parachute group system Single Ji 、S Single Zi 。
Preferably, p1=2 and p2=3. Said 1-m i Δη＞0、1-n j Δη＞0。
Compared with the prior art, the invention has the advantages that: the method provided by the invention can obtain the parachute efficiency factor of each level of parachute opening process of the parachute verified by experiments, and is further used for determining the resistance area in the parachute design, and the method is specific:
1) The air drop test data under the real use environment is utilized, so that various assumptions of numerical simulation on fluid-solid coupling calculation are eliminated, the calculation result is more in line with the real working state of the group umbrella, and the result is accurate and reliable;
2) The resistance loss condition of the state of each stage in the whole process of the operation of the group umbrella is obtained, and the limitation that the efficiency factor of the group umbrella only considers the stable descending stage is overcome.
Drawings
FIG. 1 is a flow chart of the method of the present invention;
FIG. 2 is a schematic diagram of the invention in a parachute working process, illustrating a parachute system comprising 2 parachutes and 3 main parachutes;
FIG. 3 is a graph showing the comparison of the actual and theoretical calculated height curves in the ballistic reconstruction of the parachute efficiency factor of the present invention;
FIG. 4 is a graph showing the comparison of the actual and theoretical calculated sky speed curves in the ballistic reconstruction of the parachute efficiency factor of the present invention.
Detailed Description
The recovery subsystem of the new generation manned spacecraft adopts the parachute landing technology of a group parachute system to carry out speed reduction, wherein a speed reduction parachute assembly consists of 2 strap parachutes (with long hanging strips), and a main parachute assembly consists of 3 annular sail parachutes.
The invention is mainly based on a numerical analysis method of air drop test data, and quantitatively describes the resistance area loss of the group umbrella by using an efficiency factor. The group umbrella efficiency factor is defined as the ratio of the group umbrella resistance characteristic to the single umbrella resistance characteristic multiplied by the number of umbrellas, and the efficiency factor in the group umbrella system is calculated and obtained, so that the design parameters of the group umbrella system are obtained.
Specifically, in the air drop test of a single parachute, ballistic reconstruction fitting is performed on the resistance areas of all levels of parachutes and main parachutes according to the change curve of the height and the speed in the air drop test of the strength of the parachute along with time, so that all levels of closing resistance areas of the single parachute and the single main parachute during working can be obtained, and the resistance areas are used as initial parameter values. In the airdrop test of the group parachute, a GPS measuring device is arranged in the test model, a curve of the model height and speed changing along with time can be obtained according to GPS data analysis, the curve of the change along with time of the airdrop test of the group parachute is used as an optimization target 1, and the curve of the change along with time of the airdrop test of the group parachute is used as an optimization target 2. In ballistic reconstruction fitting of the swarm umbrellas, the swarm umbrella efficiency factor parameters are introduced into a ballistic calculation program, the resistance area of a single umbrella is used as an initial parameter, air drop test data of the swarm umbrellas are used as optimization targets (two optimization targets are used for judging the fitting optimal value of the swarm umbrella efficiency factor), and the efficiency factor of the swarm umbrellas is used as a target parameter. Ballistic reconstruction fitting is carried out on the group umbrella efficiency factors of all levels of umbrella opening, and the fitting result and the optimization target are used for judging the fitting optimal value of the group umbrella efficiency factors through a certain criterion, so that the group umbrella efficiency factors of all levels of umbrella opening are obtained. The obtained efficiency factors can be used for guiding the design analysis of the parachute group to obtain the single parachute area and the number of the parachutes required by the parachute group design.
In the ballistic fitting process, the following principle is followed:
A. in the vertical velocity profile, the curvature is kept as consistent as possible where it varies;
B. in the altitude curve, if the altitude curve cannot be completely overlapped, 2 curves (one is GPS data and one is trajectory calculation data) should be kept parallel as soon as possible.
As shown in fig. 1, which is a flow chart of the method of the present invention, the main steps are as follows:
1) In the single parachute airdrop test, a main parachute of the parachute system is a 1-top ring sail parachute, a speed reducer is a 1-top strip parachute, ballistic reconstruction fitting is carried out on resistance areas of each level of parachute opening of the speed reducer and the main parachute according to a height and speed change curve in the single parachute airdrop test, and each level of closing resistance areas of the single speed reducer and the single main parachute during working are obtained and serve as initial parameter values.
The obtained resistance areas of the various stages of the drogue and the main drogue are recorded as JA 0i (i＝1,2…N J )，ZA 0j (j＝1,2…N Z ). Wherein N is J 、N Z The closing-up stages of the speed reducing umbrella and the main umbrella are respectively adopted.
Ballistic reconstruction fits can be obtained using six degree of freedom dynamics calculations. The parachute adopts a multistage closing technology, is a conventional method for inhibiting the overinflation of canopy, and is used for controlling the resistance characteristic of the parachute in a period of time, reducing the dynamic load of opening the parachute and the like. The number of stages is determined by the designer himself.
2) In the group parachute system used in the group parachute air-drop test, the main parachute consists of a P1 top ring sail parachute, and the speed reducing parachute consists of a P2 top strap parachute (the ring sail parachute and the strap parachute used in the group parachute air-drop test are respectively consistent with the ring sail parachute and the strap parachute used in the single parachute air-drop test), as shown in fig. 2. Obtaining a time-dependent speed change curve V measured by a group parachute airdrop test 0 (t) the height over time curve H 0 (t) (GPS data curves in fig. 3 and 4) as an objective function. In the group parachute system shown in fig. 3 and 4, the main parachute consists of a 2-top ring sail parachute, and the speed reducing parachute consists of a 3-top strip parachuteComposition, p1=2, p2=3.
In the group umbrella system, P1 and P2 are positive integers greater than 1 and can be freely combined according to design.
3) And carrying out ballistic reconstruction fitting on the umbrella group efficiency factors of all stages of umbrellas, wherein the ballistic reconstruction fitting process comprises a straightening process, an umbrella opening process, an inflation process and a stable descending process. The fitting method adopts a ballistic reconstruction fitting method of a single umbrella, and a group umbrella efficiency factor is introduced on the basis. In the ballistics reconstruction fitting of the umbrella-shaped efficiency factors, the speed and the height are functions of time, the closing-up resistance area of each stage, the closing-up stage number and the efficiency factors of each stage, namely
Specific f V And f H The expression of (2) is as follows:
wherein; θ is the track angle; m is the system weight; g is gravity acceleration;
wherein eta Ji ＝1-m i Δη is an efficiency factor of the ith stage of the drogue;
η Zj ＝1-n j Δη is an efficiency factor of the j-th stage closing stage of the main umbrella;
m i ＝1、2、3……(1-m i Δη > 0), is the number of steps fitted to the drogue efficiency factor;
n j ＝1、2、3……(1-n j Δη > 0), is the number of steps of fitting the main umbrella efficiency factor;
Δη is the fitting step length of the group umbrella efficiency factors;
3) Comprehensively consider V 0 (t)、H 0 (t) two optimization targets, judging a group umbrella efficiency factor fitting optimal value, and judging an efficiency factor criterion parameter obj:
where T is the process time, Δt is the time step,
criterion function
When f obj (η Ji ，η Zj ) When =obj, η is the argument at this time Zj 、η Ji The obtained umbrella efficiency factor of each group is denoted as eta Jj_obj 、η Zj_obj 。
At the optimal value, the target curve fitting value is
V _obj (t)＝f V (t,JA 0i ，N J ，ZA 0j ，N Z ,η Jj_obj ,η Zj_obj ,P 1 ,P 2 )
H _obj (t)＝f H (t,JA 0i ，N J ，ZA 0j ，N Z ,η Jj_obj ,η Zj_obj, P 1 ,P 2 )
As shown by the ballistic calculation data curves in fig. 3 and 4.
4) In the parachute system to be designed, the total resistance area of the parachute required in each stage is recorded as S according to the design requirement Total Ji ,S Total Zj 。
Then in group umbrella systemResistance area S of single parachute at each stage Single Ji 、S Single Zi The number P1 and P2 of the parachute meet
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (4)
1. The method for selecting the design parameters of the group umbrella system is characterized by comprising the following steps:
(1) Selecting a top ring sail parachute as a main parachute, selecting a top strip parachute as a speed reducing parachute, and constructing a single parachute system;
(2) In the single parachute airdrop test by utilizing the single parachute system, ballistic reconstruction fitting is carried out on the resistance areas of all levels of parachutes and main parachutes according to the height and speed change curves in the single parachute airdrop test along with time, so as to obtain all levels of closing resistance areas of the single parachute and the single main parachute during working, and the closing resistance areas are recorded as JA 0i ,i＝1,2…N J ，ZA 0j ,j＝1,2…N Z ，N J 、N Z The closing-up stages of the speed reducing umbrella and the main umbrella are respectively carried out;
(3) Selecting a P1 top ring sail umbrella as a main umbrella, selecting a P2 top strip umbrella as a speed reducing umbrella, and constructing a group umbrella system, wherein P1 and P2 are positive integers larger than 1;
(4) Carrying out a group parachute air drop test by using the group parachute system to obtain a change curve V of the speed measured by the group parachute air drop test along with time 0 (t) the height over time curve H 0 (t) as an objective function;
(5) Ballistic reconstruction fitting is carried out on the group umbrella efficiency factors of all stages of umbrella opening, in particular to
Wherein eta Ji ＝1-m i Δη is the efficiency factor of the ith stage of the parachute, η Zj ＝1-n j Δη isEfficiency factor, m of j-th stage closing stage of main umbrella i =1, 2, 3 … …, fitting steps for the drogue efficiency factor, n j =1, 2, 3 … … is the number of main umbrella efficiency factor fitting steps, Δη is the group umbrella efficiency factor fitting step;
(6) Comprehensively consider V 0 (t)、H 0 (t) two optimization targets, formulating an efficiency factor criterion parameter obj and a criterion function f obj (η Ji ，η Zj )，
Find the equivalent f obj (η Ji ，η Zj ) Independent variable η when=obj Zj 、η Ji The value of (A) is recorded as eta Jj_obj 、η Zj_obj The method comprises the steps of carrying out a first treatment on the surface of the Wherein T is the process time, and Deltat is the time step;
(7) The total resistance area of each parachute and main parachute required by each stage in the design of the parachute system is recorded as S Total Ji ,S Total Zj
(8) Using the formula
Calculating to obtain the resistance area S of single parachute at each stage in the parachute group system Single Ji 、S Single Zi 。
2. The method for selecting the design parameters of the umbrella group system according to claim 1, wherein the method comprises the following steps: p1=2 and p2=3.
3. The method for selecting the design parameters of the umbrella group system according to claim 1, wherein the method comprises the following steps: said 1-m i Δη＞0。
4. The method for selecting the design parameters of the umbrella group system according to claim 1, wherein the method comprises the following steps: said 1-n j Δη＞0。
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