CN111879544A - Satellite-borne laser communication terminal thermal test tool and test method - Google Patents

Abstract

The invention provides a thermal test tool and a test method for a spaceborne laser communication terminal, comprising: a first heat flow simulation module configured to directly apply heat flow to a bearing component of the spaceborne laser communication terminal; a second heat flow simulation module configured In order to indirectly apply heat flow to the filter of the spaceborne laser communication terminal; the support system is configured to support the spaceborne laser communication terminal and the second heat flow simulation module, and fix the first heat flow simulation module .

Description

Thermal test tool and test method for spaceborne laser communication terminal

technical field

The invention relates to the technical field of aerospace, in particular to a thermal test tool and a test method for a spaceborne laser communication terminal.

Background technique

Satellite laser communication technology is a powerful means to realize high-speed communication in space, which can meet the huge demand for information transmission in current military and civilian communication technology. Compared with traditional microwave communication technology, laser communication has the advantages of notification, confidentiality, anti-interference and miniaturization. However, due to the relatively small divergence angle of the laser beam, the long communication distance and the small receiving field of view of the target terminal, the accuracy of aiming, capturing and tracking has a great influence on the communication quality. Bit rate increased. The deformation caused by the uneven temperature of the optical components such as the primary mirror of the laser communication terminal will lead to large aiming errors and tracking errors.

Therefore, it is necessary to carry out a separate thermal control design for the laser communication terminal to ensure its temperature uniformity and stability during on-orbit operation. In order to evaluate the effectiveness of the thermal control design, the single-machine vacuum thermal test verification is particularly important. At present, most of the vacuum thermal tests on optical loads such as spaceborne laser communication terminals focus on the exploration of the two-dimensional turntable, and there are few experimental studies on the overall laser communication terminal.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a thermal test tool and a test method for a spaceborne laser communication terminal, so as to solve the problem that the existing laser communication terminal lacks accurate vacuum thermal test equipment.

In order to solve the above-mentioned technical problems, the present invention provides a thermal test tool for an on-board laser communication terminal, including:

a first heat flow simulation module, configured to directly apply heat flow to the bearing component of the spaceborne laser communication terminal;

a second heat flow simulation module configured to indirectly apply heat flow to the filter of the spaceborne laser communication terminal; and

A support system is configured to support the spaceborne laser communication terminal and the second heat flow simulation module, and to fix the first heat flow simulation module.

Optionally, in the thermal test tool for the spaceborne laser communication terminal, the support system includes a tool plate and a support structure, wherein:

The tooling plate is horizontally fixed on the guide rail through the support structure;

The spaceborne laser communication terminal is placed horizontally and fixed on the tooling board;

A leveling device is arranged between the tooling plate and the support structure for adjusting the levelness of the tooling plate.

Optionally, in the spaceborne laser communication terminal thermal test tool, the first heat flow simulation module includes a heating unit and a temperature measurement unit, wherein:

The heating unit is pasted on the bottom surface of the tooling plate facing the guide rail, and the temperature measuring unit and the heating unit are staggered;

Between the tooling plate and the support structure, there is a glass fiber reinforced plastic insulation block, which prevents the heat of the heating unit from leaking to the supporting structure through the tooling plate, and prevents the heating unit from leaking to the supporting structure through the tooling plate;

The heating unit and the temperature measuring unit maintain the interface temperature between the spaceborne laser communication terminal and the mounting surface of the tooling board.

Optionally, in the spaceborne laser communication terminal thermal test tool, the support system includes lateral adjustment mounting holes and support rods, wherein:

The lateral adjustment mounting hole is located on the tooling plate and corresponds to the position of the spaceborne laser communication terminal;

The support rod passes through the lateral adjustment mounting hole and is fixed at the connection with the lateral adjustment mounting hole.

Optionally, in the spaceborne laser communication terminal thermal test tool, the second heat flow simulation module includes an infrared cage and a heat flow meter, wherein:

The infrared cage is fixed on the end rod of the support rod, and faces the filter;

The heat flow meter is arranged on the side of the infrared cage facing away from the filter;

The end rod of the support rod has lateral and 360° rotation adjustment functions;

Both sides of the infrared cage resistance wire are coated with black paint to improve the infrared emissivity of the surface.

Optionally, in the spaceborne laser communication terminal thermal test tool, the support rod includes a longitudinal adjustment device, a heat flow meter adjustment device, and a lateral and rotational adjustment device, wherein:

The longitudinal adjustment device is used to adjust the support rod according to the height of the spaceborne laser communication terminal;

The lateral and rotational adjustment device is used to adjust the infrared cage to align with the infrared cage in the lateral position according to the direction of the lens barrel of the spaceborne laser communication terminal, and then rotate an appropriate angle to make the infrared cage parallel to the optical filter;

The heat flow meter adjusting device is used to adjust the position of the heat flow meter, so that the distance between the heat flow meter and the filter is consistent with the distance between the heat flow meter and the infrared cage.

The present invention also provides a test method based on the above-mentioned thermal test tool for the spaceborne laser communication terminal,

The main structure of the spaceborne laser communication terminal and the first heat flow simulation module perform contact heat flow simulation. The surface of the spaceborne laser communication terminal is wrapped with a multi-layer component, and a heating loop is pasted on the inner surface of the outermost layer of the multi-layer component to simulate the heat flow outside the space. Determine the analog power in conjunction with the simulation analysis.

Optionally, in the thermal test method of the spaceborne laser communication terminal, the filter of the spaceborne laser communication terminal and the second heat flow simulation module perform non-contact heat flow simulation, and the heat flow absorbed by the filter is determined in combination with the simulation analysis. density;

Determine the distance between the second heat flow simulation module and the filter according to the heat flux density absorbed by the filter;

The relationship between the heat flux density applied by the second heat flux simulation module and the temperature of the heat flow meter is determined according to the distance between the second heat flux simulation module and the filter.

Optionally, in the thermal test method of the spaceborne laser communication terminal, after the spaceborne laser communication terminal is fixed on the tooling board to adjust the pointing position, the vertical adjustment device and the lateral and rotational adjustment devices are adjusted to make the infrared cages parallel. Face the filter and adjust to the set distance;

Adjust the heat flow meter adjustment device so that the heat flow meters are arranged equidistantly on the back side of the infrared cage.

Optionally, in the spaceborne laser communication terminal thermal test method, after the space simulation equipment meets the test requirements, the infrared cage is calibrated when other heat flow simulation methods are not turned on, and the closed-loop control temperature of the heat flow meter is set according to the simulation results. , record the current applied to the infrared cage, and use a fixed current to control the infrared cage to apply the corresponding heat flow when the test is officially started, so as to avoid the deviation caused by the use of the closed-loop temperature control method of the heat flow meter to introduce the influence of the surrounding environment on the heat flow meter.

In the thermal test tool and test method of the spaceborne laser communication terminal provided by the present invention, the first heat flow simulation module directly applies heat flow to the bearing part of the spaceborne laser communication terminal, and the second heat flow simulation module filters the spaceborne laser communication terminal. The light sheet indirectly applies heat flow, and provides a simple, convenient and adaptable test tooling and heat flow simulation method for optical loads such as spaceborne laser communication terminals. Extensibility.

Specifically, the new design of the infrared cage structure solves the difficulty of simulating the heat flow absorbed by the filter, improves the accuracy of the heat flow simulation in the thermal test of the laser communication terminal, and also provides an idea for the simulation of the heat flow outside the lens of other optical loads.

Description of drawings

1 is a schematic diagram of a thermal test tool for a spaceborne laser communication terminal according to an embodiment of the present invention;

2 is a schematic diagram of an infrared cage and a support rod of a thermal test tool for an on-board laser communication terminal according to an embodiment of the present invention;

Shown in the picture:

100 - thermal test tooling;

110-rail;

120-infrared cage and support rod;

130-spaceborne laser communication terminal;

140 - Tooling board;

150-insulation pad;

160-level adjustment device;

170 - heating unit;

180 - temperature measurement unit;

190- Lateral adjustment mounting holes;

200-infrared cage and support rod;

210 - support rod;

220 - longitudinal adjustment device;

230 - heat flow meter;

240 - infrared cage;

250 - Lateral and Rotary Adjustments.

Detailed ways

The thermal test tool and test method of the spaceborne laser communication terminal proposed by the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of the present invention will become apparent from the following description and claims. It should be noted that, the accompanying drawings are all in a very simplified form and in inaccurate scales, and are only used to facilitate and clearly assist the purpose of explaining the embodiments of the present invention.

Furthermore, unless stated otherwise, features in different embodiments of the invention may be combined with each other. For example, a certain feature in the second embodiment can be used to replace the corresponding or functionally identical or similar feature in the first embodiment, and the resulting embodiment also falls within the scope of disclosure or description of the present application.

The core idea of the present invention is to provide a thermal test tool and a test method for a spaceborne laser communication terminal, so as to solve the problem that the existing laser communication terminal lacks accurate vacuum thermal test equipment.

The stand-alone vacuum thermal test is one of the most important environmental tests in the development of a stand-alone satellite. Single machine material, components and workmanship defects. The accuracy of the single-machine vacuum thermal test is closely related to the accuracy of the heat flow outside the space. The simulation software establishes a thermal model to determine the external heat flow method. The key lies in the method used for heat flow simulation. At present, the commonly used external heat flow simulation methods mainly include contact type and non-contact type. The first one is to paste the heating loop directly on the surface of the structure or on the inner side of the outermost layer of the surface-coated multi-layer component to simulate the heat flow. This method can directly The heating loop current is determined according to the calculated power, which is easy to apply; the second is to arrange an infrared lamp array or an infrared cage at a certain distance from the surface to simulate the heat flow. This method requires the introduction of a heat flow meter to measure the heat flow density absorbed by the surface, which needs to be simulated. After calculation, calibration correction is carried out in the space environment simulation equipment.

For the spaceborne laser communication terminal, the outermost side of the lens barrel is a filter, which requires extremely high cleanliness and is a translucent structure. It is impossible to paste a heater on its surface to simulate heat flow. Due to the limitation of size and structure of the infrared lamp array, the heat flow of the filter cannot meet the requirements of test uniformity, and the heat flow meter arranged under the infrared lamp will inevitably block part of the filter, and the simulation deviation is large. A similar problem exists with heat flow meters for infrared cages. In addition, the simulation analysis shows that the solar heat flow entering and absorbing through the lens filter cannot be ignored. Therefore, a thermal test tool and a heat flow simulation method that can adapt to optical loads such as laser communication terminals are required.

In order to realize the above-mentioned idea, the present invention provides a thermal test tool and a test method for a spaceborne laser communication terminal, including: a first heat flow simulation module configured to directly apply heat flow to the bearing part of the spaceborne laser communication terminal; a second heat flow a simulation module configured to indirectly apply heat flow to the optical filter of the spaceborne laser communication terminal; and a support system configured to support the spaceborne laser communication terminal and the second heat flow simulation module, and to support the first heat flow simulation module A heat flow simulation module is fixed.

The invention discloses a spaceborne laser communication terminal thermal test tool 100 and a test method, which are suitable for the vacuum thermal test of the spaceborne laser communication terminal 130 in a space environment simulator to check the rationality of its thermal design. It is mainly composed of a tooling board 140 , an infrared cage and a support rod 120 . The on-board laser communication terminal 130 is fixed on the horizontally adjustable tooling plate 140, and the horizontal adjustment mounting holes 190 are arranged on the tooling plate 140 for installing and adjusting the position of the infrared cage and the support rod 120 (including the infrared cage and the support rod). The rod is fixed at the end of the support rod, and the corresponding angle and distance can be adjusted according to the orientation of the lens barrel of the spaceborne laser communication terminal 130 . The present invention provides a simple, convenient and highly adaptable test tooling and heat flow simulation method for optical loads such as the spaceborne laser communication terminal 130, the tooling can be quickly disassembled, put into the tank and adjusted the level, and also has certain scalability; The new design of the infrared cage structure solves the difficulty of simulating the heat flow absorbed by the filter, improves the accuracy of the heat flow simulation in the thermal test of the spaceborne laser communication terminal 130, and also provides an idea for the simulation of the heat flow outside the lens of other optical payloads.

As shown in FIG. 1 , the thermal test tooling 100 of the spaceborne laser communication terminal provided by the present invention is mainly composed of a tooling plate 140 , an infrared cage and a support rod 120 . The satellite-borne laser communication terminal 130 is installed on the tooling board 140, and the tooling board 140 is fixed on the guide rail 110 through the support structure. The support structure and the tooling board 140 are directly provided with glass fiber reinforced plastic heat insulation pads 150 to ensure thermal insulation and thermal insulation between the two. insulating properties. The leveling device 160 is used to adjust the levelness of the tooling plate 140 to be better than 1 mm/m. The infrared cage and the support rod 120 are fixed to the lateral adjustment mounting holes 190 of the tooling plate 140 according to the position of the spaceborne laser communication terminal 130 . The heating unit 170 and the temperature measuring unit 180 are arranged on the bottom surface of the tooling board 140 to control the interface temperature between the spaceborne laser communication terminal 130 and the mounting surface of the tooling board 140 .

The main structure of the tooling plate 140: a support structure is installed at the bottom of the tooling plate 140, the heating unit 170 and the temperature measuring unit 180 are arranged on the bottom surface of the tooling plate 140 and are used to set the interface temperature of the tooling plate 140; the infrared cage and the support rod: the infrared cage support rod is fixed on the The horizontal adjustment hole of the tooling plate 140 has the function of adjusting the position in the horizontal and vertical directions; the support structure has the horizontal adjustment function to ensure that the tooling plate 140 carries the tested spaceborne laser communication terminal 130 The plane level is excellent at 1mm/m. The tooling plate 140 is insulated and insulated from the support structure. A glass fiber reinforced plastic insulation pad 150 is provided on the contact surface between the support structure and the tooling plate 140 . A lateral adjustment mounting hole 190 is provided on one side of the tooling plate 140 . A heating and temperature measuring unit 180 is arranged on the bottom surface of the tooling plate 140 , and has the function of closed-loop controlling the interface temperature of the tooling plate 140 . The infrared cage and the support rod 120 have a longitudinal adjustment function. The end rod of the support rod has lateral and 360° rotation adjustment functions. In order to achieve a better temperature control effect, multiple temperature measurement sensors are arranged at the installation position of the spaceborne laser communication terminal 130 .

FIG. 2 is an infrared cage and a support rod 200 in the thermal test tool 100 provided by the present invention. The support rod 210 can be installed in a suitable laterally adjusted mounting hole according to the position of the spaceborne laser communication terminal 130 , and the vertical adjustment device 220 can adjust the position of the support rod according to the height of the spaceborne laser communication terminal 130 . The lateral and rotational adjustment device 250 firstly adjusts the lateral position alignment of the infrared cage 240 according to the direction of the lens barrel of the spaceborne laser communication terminal 130, and then rotates to an appropriate angle to make it parallel to the lens barrel filter. The infrared heat flow meter 230 is arranged on the back side of the infrared cage 240, and is adjusted to a position consistent with the distance between the filter and the infrared cage.

The infrared cage heat flow meter 230 is arranged on the back side and has a longitudinal adjustment function. In order to ensure the measurement accuracy of the heat flow meter 230, the surfaces on both sides of the infrared cage resistance wire are coated with black paint, and are equipped with an analog spaceborne laser communication terminal 130 lens barrel Function of heat flow outside space. An infrared heat flow meter 230 is arranged on the back side of the infrared cage, and the distance between the heat flow meter 230 and the infrared cage can be adjusted. The distance between the infrared heat flow meter 230 and the infrared cage can be adjusted. The infrared cage is fixed on the end rod of the support rod, with lateral and 360° rotation adjustment functions.

The main structure of the spaceborne laser communication terminal 130 uses a contact heat flow simulation method, and a heating circuit is pasted on the inner surface of the outermost layer of the multi-layer component to simulate the heat flow outside the space. The simulation power can be determined in combination with the simulation analysis. The film is combined with 15 layers of polyester mesh at intervals. The outermost layer of the multi-layer component is a layer of F46, and the heater is pasted on the inner surface of this layer.

The filter at the front of the lens barrel of the spaceborne laser communication terminal 130 cannot use the contact method to simulate the heat flow, and the non-contact infrared cage is used for the simulation. Combined with the simulation analysis, determine the heat flux density absorbed by the filter, and then determine the distance between the infrared cage and the filter, and the relationship between the heat flux density applied by the infrared cage and the temperature of the heat flux meter 230 at this distance, including: simulation analysis and calculation to obtain each of the orbital laser terminals. The sum of the solar radiation heat flow at the surface, the Earth's albedo heat flow, and the Earth's infrared radiation heat flow:

Q=Q ₁ +Q ₂ +Q ₃

Q is the external heat flow received by the surface of the spaceborne laser communication terminal, Q ₁ is the direct solar radiation, Q ₂ is the earth's albedo external heat flow, and Q ₃ is the earth's infrared radiation heat flow;

S is the solar constant, a is the average albedo, A is the surface area, α is the surface solar absorptivity, ε is the surface infrared emissivity, φ1 is the solar radiation angle coefficient, φ2 is the earth albedo coefficient, φ3 is the earth’s infrared angle coefficient ;

For medium and high orbit satellites, the last two items can be ignored. In particular, for the filter with translucent properties, the heat flow through the filter will also be absorbed by the blackened surface with high absorption rate inside the lens barrel, and this part of the heat flow should be considered in the calculation formula. So the formula can be simplified to

Q=S(α+τ)Aφ ₁

τ is the filter transmittance;

After the on-board laser communication terminal 130 is fixed on the tooling plate 140 and the pointing position is adjusted, the vertical and horizontal positions and angles of the infrared cage support rods are adjusted so that the infrared cage is parallel to the filter and adjusted to the set distance; the heat flow meter 230 Equidistantly arranged on the back side of the infrared cage to reduce the blocking effect on the front filter;

After the space simulation equipment meets the test requirements, calibrate the infrared cage when other heat flow simulation methods are not turned on, set the closed-loop control temperature of the heat flow meter 230 according to the simulation results, record the current applied to the infrared cage, and use a fixed current control when the test is officially started. The infrared cage applies the corresponding heat flow, so as to avoid the deviation caused by using the closed-loop temperature control method of the heat flow meter 230 to introduce the influence of the surrounding environment on the heat flow meter 230 . The control method of applying heat flow to the infrared cage is to set the target temperature of the heat flow meter to achieve closed-loop control. After calibration, the current can be directly applied to avoid the deviation caused by the influence of the surrounding environment on the temperature of the heat flow meter.

To sum up, the above embodiments describe in detail the different configurations of the thermal test tool and test method for the spaceborne laser communication terminal. Of course, the present invention includes but is not limited to the configurations listed in the above implementation. Contents that are transformed on the basis of the provided configuration all belong to the protection scope of the present invention. Those skilled in the art can draw inferences from the contents of the foregoing embodiments.

The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments can be referred to each other. For the system disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant part can be referred to the description of the method.

The above description is only a description of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention. Any changes and modifications made by those of ordinary skill in the field of the present invention based on the above disclosure all belong to the protection scope of the claims.

Claims (10)

1. The utility model provides a satellite-borne laser communication terminal thermal test frock which characterized in that includes:

the first heat flow simulation module is configured to directly apply heat flow to a bearing part of the satellite-borne laser communication terminal;

the second heat flow simulation module is configured to indirectly apply heat flow to the optical filter of the satellite-borne laser communication terminal; and

the supporting system is configured to support the satellite-borne laser communication terminal and the second heat flow simulation module and fix the first heat flow simulation module.

2. The satellite-borne laser communication terminal thermal test tool according to claim 1, wherein the supporting system comprises a tool plate and a supporting structure, wherein:

the tooling plate is horizontally fixed on the guide rail through a supporting structure;

the satellite-borne laser communication terminal is horizontally placed and fixed on the tooling plate;

the tool plate and the supporting structure are provided with a horizontal adjusting device therebetween for adjusting the levelness of the tool plate.

3. The satellite-borne laser communication terminal thermal test tool according to claim 2, wherein the first heat flow simulation module comprises a heating unit and a temperature measuring unit, wherein:

the heating unit is adhered to the bottom surface of the tooling plate facing the guide rail, and the temperature measuring units and the heating unit are arranged in a staggered manner;

a glass fiber reinforced plastic heat insulation cushion block is arranged between the tooling plate and the supporting structure, so that heat of the heating unit is prevented from leaking to the supporting structure through the tooling plate, and the heating unit is prevented from leaking to the supporting structure through the tooling plate;

the heating unit and the temperature measuring unit keep the interface temperature of the satellite-borne laser communication terminal and the installation surface of the tooling plate.

4. The satellite-borne laser communication terminal thermal test tool according to claim 3, wherein the supporting system comprises a transverse adjusting mounting hole and a supporting rod, wherein:

the transverse adjusting mounting hole is positioned on the tooling plate and corresponds to the position of the satellite-borne laser communication terminal;

the supporting rod penetrates through the transverse adjusting mounting hole and is fixed at the joint of the supporting rod and the transverse adjusting mounting hole.

5. The satellite-borne laser communication terminal thermal test tool according to claim 4, wherein the second heat flow simulation module comprises an infrared cage and a heat flow meter, wherein:

the infrared cage is fixed on a tail end rod piece of the supporting rod, and the front side of the infrared cage faces the optical filter;

the heat flow meter is arranged on one side of the infrared cage back to the optical filter;

the tail end rod piece of the supporting rod has the functions of transverse and 360-degree rotation adjustment;

the surfaces of the two sides of the infrared cage resistance wire are both black paint coatings so as to improve the surface infrared emissivity.

6. The satellite-borne laser communication terminal thermal test tool according to claim 5, wherein the supporting rod comprises a longitudinal adjusting device, a heat flow meter adjusting device and a transverse and rotary adjusting device, wherein:

the longitudinal adjusting device is used for adjusting the supporting rod according to the height of the satellite-borne laser communication terminal;

the transverse and rotary adjusting device is used for adjusting the transverse position of the infrared cage to be aligned with the lens barrel according to the lens barrel direction of the satellite-borne laser communication terminal, and then rotating the infrared cage by a proper angle to enable the infrared cage to be parallel and opposite to the optical filter;

and the heat flow meter adjusting device is used for adjusting the position of the heat flow meter so that the distance between the heat flow meter and the optical filter is consistent with the distance between the heat flow meter and the infrared cage.

7. A test method based on the satellite-borne laser communication terminal thermal test tool as claimed in claim 1,

the satellite-borne laser communication terminal main structure and the first heat flow simulation module perform contact type heat flow simulation, the surface of the satellite-borne laser communication terminal is wrapped by a multi-layer assembly, the inner surface of the outermost layer of the multi-layer assembly is pasted with the heat flow outside the simulation space of a heating loop, and simulation analysis is combined to determine the simulation power.

8. The satellite-borne laser communication terminal thermal test method according to claim 7, wherein the optical filter of the satellite-borne laser communication terminal and the second heat flow simulation module perform non-contact heat flow simulation, and the heat flow density absorbed by the optical filter is determined by combining simulation analysis;

determining the distance between the second heat flow simulation module and the optical filter according to the heat flow density absorbed by the optical filter;

and determining the relationship between the heat flow density applied by the second heat flow simulation module and the temperature of the heat flow meter according to the distance between the second heat flow simulation module and the optical filter.

9. The satellite-borne laser communication terminal thermal test method according to claim 8, wherein after the satellite-borne laser communication terminal is fixed on the tooling plate and the pointing position is adjusted, the infrared cage is enabled to be parallel and opposite to the optical filter and adjusted to a set distance by adjusting the longitudinal adjusting device and the transverse and rotary adjusting devices;

and adjusting the heat flow meter adjusting device to enable the heat flow meters to be arranged on the back side of the infrared cage at equal intervals.

10. The satellite-borne laser communication terminal thermal test method as claimed in claim 7, wherein after the space simulation equipment meets the test requirements, the infrared cage is calibrated when other heat flow simulation modes are not started, the heat flow meter closed-loop control temperature is set in combination with the simulation result, the infrared cage applied current is recorded, the infrared cage is controlled by the fixed current to apply the corresponding heat flow when the test formally starts, and the deviation caused by the influence of the surrounding environment on the heat flow meter due to the heat flow meter introduced by the heat flow meter closed-loop temperature control method is avoided.

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