CN106777638B

CN106777638B - Zero-trim layout design method for propulsion cabin of eccentric spacecraft

Info

Publication number: CN106777638B
Application number: CN201611119197.6A
Authority: CN
Inventors: 张振峰; 曹俊生; 孙小珠; 崔赞红; 朱俊杰; 常立平; 常世杰; 段君毅; 冯宇; 何俊彦; 洪亚军; 李传吟; 李立春; 刘国林; 楼俏; 毛国斌; 欧阳文; 吴金花; 徐博; 徐磊
Original assignee: Shanghai Aerospace System Engineering Institute
Current assignee: Shanghai Aerospace System Engineering Institute
Priority date: 2016-12-08
Filing date: 2016-12-08
Publication date: 2020-06-26
Anticipated expiration: 2036-12-08
Also published as: CN106777638A

Abstract

The invention provides a zero trim layout design method for an eccentric spacecraft propulsion cabin, which comprises the following steps of: step 1, defining layout requirements; step 2, symmetrically distributing power system equipment; step 3, eccentrically arranging the solar wings; step 4, performing eccentric layout and subsequent iterative layout on the antenna, the sensor and other extravehicular equipment; step 5, carrying out eccentric layout and subsequent iterative layout on equipment in the cabin; step 6, eccentric layout and subsequent iterative layout of the pipeline; and 7, performing eccentric layout and subsequent iterative layout of the cables. The method reasonably utilizes the self mass distribution characteristic of the single-machine equipment through repeated layout iterative design, fully utilizes the functional requirements of the subsystems, and effectively mobilizes all factors capable of adjusting the mass center, such as pipeline layout, cable layout and the like so as to achieve the goal of zero trim of the propulsion cabin.

Description

Zero-trim layout design method for propulsion cabin of eccentric spacecraft

Technical Field

The invention relates to a spacecraft layout design method, in particular to a zero trim layout design method for an eccentric spacecraft propulsion cabin.

Background

With the continuous development of human space industry, the configuration of the spacecraft tends to be complex, and more spacecrafts with two-cabin configuration, three-cabin configuration and even multi-cabin configuration are available. The quality characteristics of each cabin section forming the spacecraft are different due to different functional characteristics and different configurations. Along with the deepening of the complexity of the spacecraft, the design cost, the construction cost, the launching cost and the operation cost of the spacecraft are continuously improved. Improving the design efficiency of the spacecraft is an important means for reducing the cost of each item of the spacecraft and is an important requirement for space engineers. Zero trim layout design is an important feature of high efficiency layout design for spacecraft.

The actuating mechanisms of the spacecraft power control system are basically symmetrical in configuration, and the mass center of the spacecraft assembly is basically located on the thrust axis, namely the central axis, according to the quality characteristic requirements of the spacecraft assembly. In the various sections of the cabin that make up the spacecraft, there are different priorities. High priority deck section designs are constraints on low priority deck section designs. When the center of mass of the high-priority cabin section is eccentric, the position of the center of mass of the low-priority cabin section is reversely eccentric, which becomes an important constraint.

The requirement of the mass center position of the spacecraft is an important layout design index. Zero trim layout design is an important feature of high efficiency layout design. For the spacecraft with strict weight index requirement, the zero trim layout design is especially important. In the existing spacecraft, mass center position requirements are achieved by adopting a balancing mode, so that the design efficiency is low, the launching cost is improved, and the waste of space resources is avoided. At present, most spacecrafts are composed of a plurality of cabin sections, and the eccentricity requirement of the cabin sections is common.

Disclosure of Invention

The invention aims to realize high-efficiency layout design, solve the defects of the existing balancing mode and provide a zero-balancing layout design method for an eccentric spacecraft propulsion cabin.

In order to achieve the aim, the invention provides a zero trim layout design method of an eccentric spacecraft propulsion cabin, which comprises the following design steps:

step 1, defining layout requirements;

step 2, symmetrically distributing power system equipment;

step 3, eccentrically arranging the solar wings;

step 4, performing eccentric layout and subsequent iterative layout on the antenna, the sensor and other extravehicular equipment;

step 5, carrying out eccentric layout and subsequent iterative layout on equipment in the cabin;

step 6, eccentric layout and subsequent iterative layout of the pipeline;

and 7, performing eccentric layout and subsequent iterative layout of the cables.

The specific design method is as follows:

a) step 1, defining layout requirements:

the method needs to specify flight mission requirements, orbit and flight procedure requirements, overall index requirements, equipment matching, interface data lists, function requirements, overall data management design principles and thermal control overall design principles.

Flight mission requirements, orbit and flight program requirements define the overall use requirements of the spacecraft, including space position characteristics, postures and functional requirements of different mission stages, and are the primary and key requirements of layout design.

The overall index requirement defines the requirements of the envelope, the weight, the centroid position and the like of the spacecraft, and is the requirement of the performance of the spacecraft to be realized by the layout design;

equipment matching, an interface data sheet and functional requirements specify matching, performance and functional characteristics of a layout object, and the layout object is a layout specific design object;

the overall data management design principle defines the overall information management system requirements to be followed by layout design.

The overall thermal control design principle defines the overall thermal environment management requirements to be followed by layout design, and the equipment layout meets the temperature control requirements according to the temperature characteristics of different parts and the equipment thermal performance.

b) Step 2, symmetrical layout of power system equipment:

the power system equipment mainly comprises a thruster, a storage tank, a gas cylinder and the like. The thrust axis points to the overall mass center of the spacecraft, and the overall mass center is located on the central axis. The thrusters, the gas cylinders, the storage tanks and the like are symmetrically arranged.

c) Step 3, eccentric layout of solar wings:

the solar wing is usually the largest mechanism product on a spacecraft, and the center of mass in an unfolded state, particularly the center of mass in a folded state is deviated from the center of an installation surface due to the asymmetric structure of a tripod on the solar wing. By utilizing the characteristic, the sun wing tripod is arranged in the direction required by the eccentricity of the propulsion cabin, and has a great effect on the realization of the eccentricity of the propulsion cabin.

d) Step 4, eccentric layout and subsequent iteration layout of the antenna, the sensor and other extravehicular equipment:

according to the layout conditions of power system equipment and solar wings, the layout requirements of antennas, sensors and other extravehicular equipment, the extravehicular equipment is eccentrically arranged and is arranged in the direction of the eccentricity requirement as far as possible. Meanwhile, iterative layout with power system equipment and solar wings is required according to requirements of signal receiving angles, field angles and the like.

e) Step 5, carrying out eccentric layout and subsequent iterative layout on equipment in the cabin:

according to the layout requirements, the principles of nearby layout, regional layout and the like, on the basis of the layout of the equipment outside the cabin, the equipment inside the cabin is eccentrically arranged, and the influence of weight factors such as a mounting bracket and cable weight on the center of mass of the propulsion cabin is considered and estimated during layout. Iterative design is performed as necessary.

f) Step 6, eccentric layout and subsequent iterative layout of the pipeline:

the influence on the mass center needs to be considered during the layout of the pipeline system, and the mass center can be effectively adjusted through the layout position design of the valve and the sensor and the layout path design of the pipeline. Iterative design is performed as necessary.

g) Step 7, cable eccentric layout and subsequent iterative layout:

the influence on the mass center needs to be considered during cable layout, and the mass center can be effectively adjusted through layout position design and cable layout path design of the transition electric connector. Iterative design is performed as necessary.

The invention brings the following beneficial effects:

the invention provides a zero trim layout design method for an eccentric spacecraft propulsion cabin. Through repeated layout iterative design, the self mass distribution characteristic of the single-machine equipment is reasonably utilized, the functional requirements of the subsystems are fully utilized, and all factors capable of adjusting the mass center, such as pipeline layout, cable layout and the like, are effectively adjusted, so that the goal of zero trimming of the propulsion cabin is achieved.

Drawings

The invention provides a zero trim layout design method of an eccentric spacecraft propulsion cabin, which is given by the following embodiments and attached drawings.

FIG. 1 is a flow chart of a design of a zero trim layout of an eccentric spacecraft propulsion nacelle.

FIG. 2 is a symmetrical layout of a spacecraft propulsion bay power system device.

Fig. 3 is a drawing of the folding state of the solar wing of the spacecraft propulsion cabin.

Fig. 4 is a layout diagram of an extravehicular device of a spacecraft propulsion cabin.

FIG. 5 is a weight distribution diagram of a layout of equipment in a propulsion bay of a spacecraft.

Fig. 6 is a layout diagram of a spacecraft propulsion bay pipeline.

Fig. 7 is a layout diagram of a spacecraft propulsion bay cable.

Detailed Description

The method for designing the zero trim layout of the propulsion capsule of the eccentric spacecraft according to the embodiment of the invention will be described in further detail with reference to the accompanying drawings.

See fig. 1. The invention provides a zero trim layout design method for an eccentric spacecraft propulsion cabin, which comprises the following steps:

a) step 1, defining layout requirements

The method is characterized by comprising the following steps of determining flight task requirements, track and flight program requirements, overall index requirements, equipment matching, interface data lists, function requirements, overall data management design principles, thermal control overall design principles and the like. The spacecraft nominal centroid requirements and the propulsion pod nominal centroid requirements are zero trim layout design target points. Wherein the nominal mass center of the propulsion cabin is deviated from the I quadrant by 20mm, which is the eccentric design requirement.

b) Step 2, symmetrical layout of power system equipment

See fig. 2. The method comprises the steps of firstly, symmetrically arranging a power system storage box 1, a gas cylinder 2 and a thruster 3 relative to a nominal mass center of a spacecraft. With the continuous improvement of the layout of the propulsion cabin, the design mass center position of the spacecraft is gradually clear, the layout design of the thruster 3 needs to be iterated according to the design mass center position, and the thruster 3 is symmetrically arranged relative to the design mass center of the spacecraft.

c) Step 3, eccentric layout of solar wing 4

See fig. 3. The main structures of the solar wing 4 are a base plate 4A and a tripod 4B. The base plate 4A is generally a rectangular parallelepiped of symmetrical configuration and the spider 4B is generally offset to one side, which results in the centre of mass of the solar wing 4 being offset from the mounting surface.

See fig. 4. By utilizing the characteristic that the centroid of the solar wing 4 deviates from the installation surface, the two solar wings 4 are arranged in a mode that the tripod 4B faces towards the I quadrant. The sun wing 4 has a significant effect on the center of mass adjustment because it is generally heavier.

d) Step 4, the antenna 5, the sensor 6 and other extravehicular equipment 7 are eccentrically arranged and then are iteratively arranged

See fig. 4. The antenna 5, the sensor 6 and other extra-cabin equipment 7 are arranged to face the direction of the quadrant I as much as possible.

e) Step 5, eccentric layout and subsequent iterative layout of equipment in the cabin

See fig. 5. According to the layout requirements, the principles of nearby layout, regional layout and the like, on the basis of the layout of the equipment outside the cabin, the equipment inside the cabin is eccentrically arranged, and the influence of weight factors such as a mounting bracket, cable weight and the like on the center of mass of the propulsion cabin is considered and estimated during layout. After many iterations of the design, FIG. 5 is a layout weight distribution diagram for the equipment in the cabin. The cabin equipment contributes significantly to the centre of mass of the propulsion cabin.

f) Step 6, eccentric layout of pipeline and iterative layout

See fig. 6. By designing the layout positions of the valves and the sensors and designing the layout path of the pipeline, the layout of the pipeline system is locally deviated to an IV quadrant.

g) Step 7, eccentric layout of cable and iterative layout

See fig. 7. Through the layout position design and the cable layout path design of the transition electric connector 8, the center of mass of the cabin body is effectively adjusted, so that the center of mass of the cabin body shifts towards the I-quadrant direction and the II-quadrant direction, the eccentric influence of a pipeline system is eliminated, and the requirement of the eccentricity of the cabin body is further met.

By adopting the zero-trim layout design method for the propulsion cabin of the eccentric spacecraft, the self mass distribution characteristic of single-machine equipment is reasonably utilized through repeated layout iterative design, the functional requirements of subsystems are fully utilized, all factors capable of adjusting the mass center, such as pipeline layout, cable layout and the like, are effectively adjusted, and the goal of zero-trim of the propulsion cabin is achieved.

Claims

1. A design method for a zero trim layout of an eccentric spacecraft propulsion cabin is characterized by comprising the following steps:

step 1, defining layout requirements; step 1, defining layout requirements: defining flight task requirements, track and flight program requirements, overall index requirements, equipment matching, interface data lists, function requirements, overall data management design principles and thermal control overall design principles;

step 2, symmetrically distributing power system equipment, wherein the power system equipment mainly adopts a thruster, a storage tank and a gas cylinder, and the thruster, the storage tank and the gas cylinder are symmetrically distributed;

step 3, eccentric layout of solar wings, which is as follows: the solar wing tripod is arranged in the direction of the eccentricity requirement of the propulsion cabin by utilizing the asymmetric structure of the tripod on the solar wing, so that the great effect on the realization of the eccentricity of the propulsion cabin is achieved;

step 4, performing eccentric layout and subsequent iteration layout on the antenna, the sensor and other extravehicular equipment, and performing eccentric layout and subsequent iteration layout on the antenna, the sensor and other extravehicular equipment: according to the layout conditions of power system equipment and solar wings, the layout requirements of antennas, sensors and other extravehicular equipment, the extravehicular equipment is eccentrically arranged and is arranged in the direction of the eccentricity requirement as much as possible; meanwhile, iterative layout with power system equipment and solar wings is required according to the requirements of a signal receiving angle and a field angle;

step 5, carrying out eccentric layout and subsequent iterative layout on equipment in the cabin, wherein the eccentric layout and subsequent iterative layout of the equipment in the cabin are as follows: according to the layout requirement, the principle of nearby layout and regional layout, on the basis of the layout of the equipment outside the cabin, the equipment inside the cabin is eccentrically arranged, and the influence of the weight factors of a mounting bracket and a cable on the mass center of the propulsion cabin is considered and estimated during the layout;

step 6, eccentric layout and subsequent iterative layout of the pipeline;

2. The design method of zero trim layout of an eccentric spacecraft propulsion capsule as claimed in claim 1, wherein said step 6, eccentric layout of the pipeline and then iterative layout: the center of mass is adjusted by designing the layout positions of the valves and the sensors and designing the layout path of the pipeline.

3. The design method of zero trim layout for an eccentric spacecraft propulsion capsule as claimed in claim 1, wherein said step 7, cable eccentricity layout and then iterative layout: the center of mass is adjusted through layout position design and cable layout path design of the transition electric connector.