CN109974768B - Test frame and test method for performance test of whole satellite active load in normal sample stage - Google Patents
Test frame and test method for performance test of whole satellite active load in normal sample stage Download PDFInfo
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- CN109974768B CN109974768B CN201910278447.8A CN201910278447A CN109974768B CN 109974768 B CN109974768 B CN 109974768B CN 201910278447 A CN201910278447 A CN 201910278447A CN 109974768 B CN109974768 B CN 109974768B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G99/00—Subject matter not provided for in other groups of this subclass
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a test rack and a test method for testing the performance of a satellite payload whole-satellite sample stage. The target plate honeycomb plate structure is light in weight, the supporting rods are detachable, and the transportation is convenient; the device is suitable for all satellite use fields, avoids using radioactive sources, and is safe and easy to control.
Description
Technical Field
The invention relates to the technical field of satellite testing, in particular to a test frame and a test method for testing the performance of a satellite effective load whole satellite normal sample stage.
Background
In the whole-satellite normal sample stage test, the effective load needs to be tested with a ray source for performance and function. The radiation source has two options of a radiation source and an X-ray tube, no X-ray is generated after the X-ray tube is powered off, and the X-ray tube is used as the radiation source for performance test in the whole satellite normal sample stage test from the radiation protection safety consideration, and the radiation source is reserved. Under common thinking, the test is carried out by using a radioactive source, firstly, very professional testers are required to operate, and trained specially-assigned personnel are required to carry out the test each time, so that the limitation of the test is increased, secondly, a plurality of models of a common aerospace test site hall usually work simultaneously, and the examination and approval process is very complicated. When the X-ray tube replacing the radioactive source is used for directly irradiating equipment, the field of view and the light intensity of the X-ray tube are limited, so that the X-ray tube can be remotely moved within a certain height above the detector to cover the field of view of the detector, and the purpose of testing is realized.
Disclosure of Invention
The invention aims to provide a test frame and a test method for testing the performance of a satellite payload in a whole satellite normal sample stage, so as to solve the problems in the background technology.
In order to achieve the above object, the present invention provides a test jig for testing performance of a satellite payload in a whole satellite normal sample stage, the test jig including a target substrate, the test jig further including: the tin target is arranged on the high-energy area, and the high-energy area is arranged in the middle of the surface of the target substrate; the molybdenum target is arranged on the middle energy area, and the middle energy area is arranged on one side of the surface of the target substrate; the copper target is arranged on the low-energy area, and the low-energy area is arranged on the other side of the surface of the target substrate; the fixing hole is formed in the area of the tin target, the supporting rod is arranged in the fixing hole in an inserting mode, an eye bolt is fixedly arranged at one end of the supporting rod, an X light tube base is fixedly arranged at the other end of the supporting rod, and an X light tube is fixedly arranged on the inner side of the X light tube base.
In a preferred embodiment, the X-ray tube base comprises a sleeve for sleeving the X-ray tube base on the support rod, and the X-ray tube is connected to the sleeve through a support frame.
In a preferred embodiment, three support rods are provided, and the three support rods are distributed on the side of the target substrate where the metal target is provided.
In a preferred embodiment, the support bar is fixed to the target substrate by means of an eye bolt.
In a preferred embodiment, the target substrate has overall dimensions of about 1900mm by 1650mm and a thickness of 15 mm.
The invention also provides a test method for performing the performance test of the satellite effective load whole satellite normal sample stage by using the test frame, which comprises the following steps:
preparing a target substrate;
fixedly mounting an eyebolt on the target substrate;
connecting a lifting appliance with a lifting ring of a lifting ring bolt and lifting;
after the target substrate is lifted to a preset height, the supporting rod is connected to the target substrate;
connecting an X-ray tube debugger to an X-ray tube base at the lower end of the support rod to enable a light path to point to a preset cursor point on the target substrate;
after the positions of the X-ray tubes are adjusted, the X-ray tube debugger is disassembled;
connecting and hoisting the X-ray tube to the corresponding X-ray tube base;
connecting the concave flange to the top end of the telescope suspender;
hoisting the test frame above the telescope, and screwing the upper connecting piece and the lower connecting piece of the support rod;
the X-ray tube cables are respectively led out of the top plate of the load cabin, connected with the wiring board and the extension line and simply connected with the cable fixing frame on the cabin plate; and
the test is started.
In a preferred embodiment, the target substrate is provided with: the tin target is arranged on the high-energy area, and the high-energy area is arranged in the middle of the surface of the target substrate; the molybdenum target is arranged on the middle energy area, and the middle energy area is arranged on two sides of the surface of the target substrate; and the copper target is arranged on the low-energy area, and the low-energy area is arranged on two sides of the surface of the target substrate.
In a preferred embodiment, the support bar is pre-sleeved with the X-ray tube base before the support bar is connected to the target substrate.
Compared with the prior art, the test frame and the test method for the performance test of the satellite payload whole satellite normal sample stage have the following beneficial effects: the invention adopts a target plate honeycomb panel structure, the weight is light, the supporting rod is detachable, and the transportation is convenient; the device is suitable for all satellite use fields, avoids using radioactive sources, is safe and easy to control, and means that complicated procedures of picking, storing, transporting and using in an aerospace test field are avoided. The design is simple, saves the expense, compares the truss with the scheme that movable mechanism adds up several million, saves the expense.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a test rack of the present invention;
FIG. 2 is an enlarged view of the area A in FIG. 1;
FIG. 3 is a schematic plan view of a test rack of the present invention;
FIG. 4 is a schematic view of the installation orientation of the present invention;
FIG. 5 is a method flow diagram of a testing method of the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
the device comprises a 1-tin target, a 2-fixing hole, a 3-supporting rod, a 4-lifting bolt, a 5-molybdenum target, a 6-copper target, a 7-X light pipe base, an 8-X light pipe, a 9-sleeve and a 10-opening sliding chute.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 4, the present invention provides a testing jig for testing performance of a satellite payload in a whole satellite normal sample stage, the testing jig including a target substrate, the testing jig further including: the tin target 1, the tin target 1 is set up on the high energy area, the high energy area is set up in the middle part of surface of the base plate of the target; the molybdenum target 5 is arranged on the middle energy area, and the middle energy area is arranged on two sides of the surface of the target substrate; the copper target 6, the copper target 6 is set up on the low energy area, the low energy area is set up in the surface both sides of the base plate of the target; the fixing hole 2 is arranged in the area of the tin target 1, the supporting rod 3 is arranged in the fixing hole 2 in an inserting mode, an eye bolt 4 is fixedly arranged at one end of the supporting rod 3, an X-ray tube base 7 is fixedly arranged at the other end of the supporting rod 3, and an X-ray tube 8 is fixedly arranged on the inner side of the X-ray tube base 7.
In a preferred embodiment, the X-ray tube base 7 comprises a sleeve for sleeving the X-ray tube base 7 on the support rod 3, and the X-ray tube 8 is connected to the sleeve 9 through a support frame.
In a preferred embodiment, three support rods 3 are provided, and the three support rods 3 are uniformly and equidistantly distributed on the side of the target substrate on which the metal target is disposed.
In a preferred embodiment, the support bar 3 is fixed to the target substrate by means of an eye bolt.
In a preferred embodiment, the target substrate has overall dimensions of about 1900mm by 1650mm and a thickness of 15 mm.
FIG. 5 is a method flow diagram of a testing method of the present invention. As shown in the figure, the test method for the satellite payload whole satellite sampling phase performance test comprises the following steps:
step 101: preparing a target substrate;
step 102: fixedly mounting an eyebolt on the target substrate;
step 103: connecting a lifting appliance with a lifting ring of a lifting ring bolt and lifting;
step 104: after the target substrate is lifted to a preset height, the supporting rod is connected to the target substrate;
step 105: connecting an X-ray tube debugger to an X-ray tube base at the lower end of the support rod to enable a light path to point to a preset cursor point on the target substrate;
step 106: after the positions of the X-ray tubes are adjusted, the X-ray tube debugger is disassembled;
step 107: connecting and hoisting the X-ray tube to the corresponding X-ray tube base;
step 108: connecting the concave flange to the top end of the telescope suspender;
step 109: hoisting the test frame above the telescope, and screwing the upper connecting piece and the lower connecting piece of the support rod;
step 110: the X-ray tube cables are respectively led out of the top plate of the load cabin, connected with the wiring board and the extension line and simply connected with the cable fixing frame on the cabin plate; and
step 111: the test is started.
In a preferred embodiment, the target substrate is provided with: the tin target 1, the tin target 1 is set up on the high energy area, the high energy area is set up in the middle part of surface of the base plate of the target; the molybdenum target 5 is arranged on the middle energy area, and the middle energy area is arranged on two sides of the surface of the target substrate; and a copper target 6, the copper target 6 being disposed on a low energy region, the low energy region being disposed on both sides of a surface of the target substrate.
In a preferred embodiment, the support bar is pre-sleeved with the X-ray tube base before the support bar is connected to the target substrate.
One specific application of this embodiment is: a target plate is placed above a telescope, 3X-ray tubes irradiate simultaneously, generated X-rays cover a high-energy detector, a medium-energy detector and a low-energy detector, performance measurement can be performed simultaneously, a test frame mainly comprises the target plate, a support ring, a support rod and an X-ray tube assembly, the test frame comprises 3 aluminum alloy tubes, connectors are designed at the upper end and the lower end of the tubes, the X end of each connector is in threaded connection with a telescopic hanger rod hole, 3 lifting bolts are arranged on the + X surface of the test frame, and the positions of the lifting bolts and the positions of the support connecting rods are the.
The specific process of mounting and dismounting comprises the following steps: the method comprises the steps of unpacking a packing box → placing a target substrate component with the surface of X facing upwards → installing 3 lifting bolts of M16X25 in place → hoisting the target substrate component → installing a support connecting rod component (with an X light pipe) → adjusting the pointing direction of the X light pipe → hoisting the telescopic hanger rod above and screwing the telescopic hanger rod → plugging an X light pipe cable → enabling the cable to respectively extend from + Y to Y along the telescopic support rod to the ground → enabling the cable to be connected with a test computer together → clearing field personnel → starting up the test.
In the description herein, references to the description of "one embodiment," "an example," "a specific example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (7)
1. A test jig of whole star of satellite payload appearance stage capability test, the test jig includes the target base plate, the test jig still includes:
the tin target (1), the said tin target (1) is set up on the high energy area, the said high energy area is set up in the middle part of surface of the said target base plate;
the molybdenum target (5), the molybdenum target (5) is arranged on the middle energy region, and the middle energy region is arranged on one side of the surface of the target substrate;
a copper target (6), wherein the copper target (6) is arranged on a low-energy area which is arranged on the other side of the surface of the target substrate; and
fixed orifices (2), fixed orifices (2) are seted up in the region of tin target (1), and it is provided with bracing piece (3) to alternate in fixed orifices (2), the fixed eye bolt (4) that is provided with of one end of bracing piece (3), and the other end of bracing piece (3) is fixed and is provided with X light pipe base (7), the inboard of X light pipe base (7) is fixed and is provided with X light pipe (8), X light pipe base (7) including be used for with X light pipe base (7) cup joint sleeve on bracing piece (3), X light pipe (8) are connected through the support frame on the sleeve.
2. The test rack of claim 1, wherein: the number of the support rods (3) is three, and the three support rods (3) are distributed on the surface, provided with the metal target, of the target substrate.
3. The test rack of claim 2, wherein: the support rod (3) is fixed on the target base plate through a lifting bolt.
4. The test rack of claim 1, wherein: the external dimension of the target substrate is about 1900mm multiplied by 1650mm, and the thickness of the target substrate is 15 mm.
5. A test method for satellite payload whole-satellite proof-phase performance testing using a test rig according to any of claims 1-4, characterized by: the test method comprises the following steps:
preparing a target substrate;
fixedly mounting an eyebolt on the target substrate;
connecting a lifting appliance with a lifting ring of the lifting ring bolt and lifting;
after the target substrate is lifted to a preset height, connecting a support rod to the target substrate;
connecting an X-ray tube debugger to an X-ray tube base at the lower end of the supporting rod to enable a light path to point to a preset cursor point on the target substrate;
after the positions of the X-ray tubes are adjusted, the X-ray tube debugger is detached;
connecting and hoisting the X-ray tube to the corresponding X-ray tube base;
connecting the concave flange to the top end of the telescope suspender;
hoisting the test frame above the telescope, and screwing the upper connecting piece and the lower connecting piece of the support rod;
the X-ray tube cables are respectively led out of the top plate of the load cabin, connected with the wiring board and the extension line and simply connected with the cable fixing frame on the cabin plate; and
the test is started.
6. The test method of claim 5, wherein: the target substrate is provided with:
the tin target (1), the said tin target (1) is set up on the high energy area, the said high energy area is set up in the middle part of surface of the said target base plate;
the molybdenum target (5), the molybdenum target (5) is arranged on the middle energy region, and the middle energy region is arranged on two sides of the surface of the target substrate; and
a copper target (6), the copper target (6) being disposed on the low energy region, the low energy region being disposed on both sides of a surface of the target substrate.
7. The test method of claim 6, wherein: the support rod is sleeved with the X-ray tube base in advance before the support rod is connected to the target substrate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910278447.8A CN109974768B (en) | 2019-04-03 | 2019-04-03 | Test frame and test method for performance test of whole satellite active load in normal sample stage |
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| CN201910278447.8A CN109974768B (en) | 2019-04-03 | 2019-04-03 | Test frame and test method for performance test of whole satellite active load in normal sample stage |
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| CN109974768A CN109974768A (en) | 2019-07-05 |
| CN109974768B true CN109974768B (en) | 2020-12-08 |
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2019
- 2019-04-03 CN CN201910278447.8A patent/CN109974768B/en active Active
Patent Citations (7)
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| US4387467A (en) * | 1981-07-27 | 1983-06-07 | The United States Of America As Represented By The Secretary Of The Air Force | Satellite test chamber with electromagnetic reflection and resonance damping for simulating system generated electromagnetic pulses |
| JPS63228080A (en) * | 1987-03-17 | 1988-09-22 | Mitsubishi Electric Corp | Testing device |
| CN202710098U (en) * | 2012-07-20 | 2013-01-30 | 航天东方红卫星有限公司 | Special inspection equipment for whole satellite testing |
| CN104698509A (en) * | 2013-12-10 | 2015-06-10 | 上海卫星工程研究所 | Geostationary orbit meteorological satellite |
| CN104215859A (en) * | 2014-09-19 | 2014-12-17 | 航天东方红卫星有限公司 | Satellite electronic load testing method |
| CN105510734A (en) * | 2015-11-26 | 2016-04-20 | 中国空间技术研究院 | Satellite ground system grade electrical property verification platform |
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Non-Patent Citations (1)
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