CN114323713A - Reusable flight test scattering platform system - Google Patents
Reusable flight test scattering platform system Download PDFInfo
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- CN114323713A CN114323713A CN202111363321.4A CN202111363321A CN114323713A CN 114323713 A CN114323713 A CN 114323713A CN 202111363321 A CN202111363321 A CN 202111363321A CN 114323713 A CN114323713 A CN 114323713A
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Abstract
The application relates to a platform system is shed in repeatedly usable flight test includes: the power curve outer shape part is internally provided with a balancing weight with freely adjustable weight, and the cylindrical outer shape part is internally provided with an parachute descending device for recovering the platform system by parachute opening in the flight process; the side wall of the equipment cabin is provided with an antenna window for mounting a telemetering antenna and a navigation antenna, and the equipment cabin is internally provided with electrical equipment; the load cabin comprises a cabin body framework and a shell sheet, the shell sheet is laid on the outer surface of the cabin body framework to form a cylindrical load cabin, a load, a release device and an opening device are installed in the load cabin, and power of the release device is derived from fuel gas; the system comprises a power system cabin, a tail cabin and a rudder wing combination for controlling the flight attitude of the platform system. The application has the following expected technical effects: better coverage, more resources and low use cost.
Description
Technical Field
The application relates to the technical field of aerospace tests, in particular to a reusable flight test scattering platform system.
Background
The existing cabin opening scattering test mainly comprises carrier carrying scattering, wherein the carrier carrying scattering is implemented by simulating a flight platform by using a carrier, and partial dynamic scattering technology can be verified.
With respect to the related art among the above, the inventors consider that the following drawbacks exist:
1. with the development of the existing aircraft, particularly a hypersonic aircraft, the flight indexes of the aircraft, such as aerodynamic appearance, speed, flight altitude, angular velocity, overload, attitude angle, load capacity and the like, are greatly different from the aircraft, so that the actual simulated flight of the aircraft is difficult to carry out, and the purpose of test verification cannot be achieved, so that the problem of poor coverage of the aircraft generally exists;
2. because the price of the carrier is high, the price of a single carrier is 3000 ten thousand to 2 hundred million, the suitable carrier resources in China are short, the journey is full, and the scattering test is difficult to be matched with, generally, in order to achieve the real throwing simulation effect, the structure of the carrier needs to be modified, the carrier is difficult to meet the requirements, and the problem of less carrier resources generally exists;
3. the carrier is used for carrying out a throwing test, the cost of a single time is in the millions of orders, the price is high, the carrier generally needs to be planned and declared in advance by 6 months to 12 months, and due to the fact that a delay event frequently occurs, the development time and the economic cost are greatly improved, and the problem that the use cost of the carrier is high generally exists.
Disclosure of Invention
In order to solve the problems of poor coverage, few resources and high use cost of a common carrier, the application provides a reusable flight test scattering platform system.
The application provides a platform system is shed in repeatedly usable flight test adopts following technical scheme:
a reusable flight test dispersal platform system, comprising:
the power curve outer shape part is internally provided with a balancing weight with freely adjustable weight, and the cylindrical outer shape part is internally provided with an parachute descending device for recovering the platform system by parachute opening in the flight process;
the equipment cabin is fixedly connected with one end, far away from the power curve appearance part, of the cylindrical appearance part, an antenna window for mounting a telemetering antenna and a navigation antenna is formed in the side wall of the equipment cabin, and electrical equipment is mounted in the equipment cabin;
the load cabin is fixedly connected with one end, far away from the nose cone cabin, of the equipment cabin and comprises a cabin body framework and a shell piece, the shell piece is laid on the outer surface of the cabin body framework to form the cylindrical load cabin, a load, a release device for pushing the load away from the platform system at a certain relative speed and a cabin opening device for separating the shell piece from the cabin body framework in the flying process are installed in the load cabin, and power of the release device is derived from gas;
the power system cabin is fixedly connected with one end, far away from the equipment cabin, of the load cabin, and an engine is arranged in the power system cabin;
the tail cabin is fixedly connected with one end, far away from the load cabin, of the power system cabin, and a tail conical spray pipe of the engine extends into the tail cabin;
and the rudder wing assembly is used for controlling the flight attitude of the platform system and is arranged on the tail cabin and the power system cabin.
Furthermore, the shells of the nose cone cabin, the equipment cabin and the tail cabin are cast from high-performance aluminum alloy, the portion of the nose cone cabin at the stagnation point of the nose cone is treated by external application of aerogel, and the outer surfaces of the shells of the nose cone cabin and the equipment cabin are coated with heat-insulating coatings.
Furthermore, the electrical equipment comprises, but is not limited to, an integrated computer, a telemetry all-in-one machine, a satellite navigation receiving and sending device and a battery, a first sensor is fixed on the inner bulkhead of the equipment cabin close to the load cabin, and the first sensor is used for detecting impact and vibration.
Furthermore, the loads are provided with two groups, the release device is located between the two groups of loads, the cabin opening device is arranged at one end, close to the equipment cabin, of the load cabin, and a second sensor is fixed on an inner side cabin wall, close to the power system cabin, of the load cabin and used for detecting impact and vibration.
Furthermore, the cabin opening device comprises explosion bolts and spring thrust rods, the shell pieces are connected with the cabin body framework through a plurality of groups of explosion bolts, and the spring thrust rods are arranged in the middle of two ends of the shell pieces.
Further, the rudder wing combination includes two fin and four air rudders of group, two fin symmetrical arrangement in the casing periphery wall in driving system cabin, the fin is on a parallel with the length direction in driving system cabin, four groups air rudder symmetrical arrangement in on the tail cabin.
Furthermore, the air rudder comprises a steering engine, a rudder sheet and a rudder shaft, wherein the steering engine is installed between the tail conical spray pipe and the inner cabin wall of the tail cabin, an opening for the rudder shaft to pass through is formed in the cabin wall of the tail cabin, the rudder sheet is located outside the tail cabin and passes through the rudder shaft and the steering engine, the rudder sheet is distributed in an X shape, and the tail wing and the rudder sheet are arranged at a 45-degree included angle.
Furthermore, the main body of the platform system is a cylindrical structure with the diameter of D, the distance between the tail part of the empennage and the tail part of the rudder sheet is 0.75D, the rudder sheet is in an inclined trapezoid shape, the chord length of the rudder root of the rudder sheet is D, the length of the rudder sheet is 0.75D, the extension length of the rudder sheet is D, and the sweepback angle of the rudder sheet is 75 degrees; the empennage is in a right trapezoid shape, the chord length of the lower bottom edge of the empennage is 2D, the chord length of the upper bottom edge of the empennage is 1.5D, and the height of the empennage (6) is 0.375D.
Further, the loads include, but are not limited to, rockets and drones.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the situation of insufficient test caused by the fact that the original high-speed flying scattering is simulated by using the airplane scattering is changed, and the cost is greatly reduced;
2. according to the pneumatic appearance design, a layout design with large static stability is formed, then after the load is released, the attitude can be quickly returned to be stable by self-restoring moment, and the next release is carried out;
3. the mode of parachute recovery is designed, the parachute can be used for multiple times, and the test cost is reduced.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be 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 to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a reusable flight test dispensing platform system according to an embodiment of the present application.
Fig. 2 is a schematic view of an installation structure of a rudder sheet and a tail wing according to an embodiment of the present application.
FIG. 3 is a schematic structural diagram of a rudder sheet according to an embodiment of the present application.
Fig. 4 is a schematic structural view of a rear wing according to an embodiment of the present application.
Description of reference numerals:
1. a nose cone cabin; 11. a power curve profile portion; 12. a cylindrical outer shape portion; 13. a balancing weight; 14. an parachute landing device; 2. an equipment compartment; 21. a telemetry antenna; 22. a navigation antenna; 23. a computer is controlled comprehensively; 24. a telemetering integrated machine; 25. a satellite navigation receiving and sending device; 26. a battery; 27. a first sensor; 3. a load compartment; 31. loading; 32. a release device; 33. a cabin opening device; 34. a second sensor; 4. a power system bay; 41. a tail conical nozzle; 5. a tail cabin; 6. a tail wing; 7. an air rudder; 71. a steering engine; 72. a rudder sheet; 73. a rudder shaft.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects to be solved by the present application clearer, the present application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.
It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings that is solely for the purpose of facilitating the description and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be considered as limiting the present application.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.
The present application is described in further detail below with reference to fig. 1 to 4.
The embodiment of the application discloses a reusable flight test scattering platform system. Referring to fig. 1 and 2, a reusable flight test dispersal platform system comprises: the nose cone cabin 1, the equipment cabin 2, the load cabin 3, the power system cabin 4, the tail cabin 5 and a rudder wing combination for controlling the flight attitude of the platform system.
Nose cone cabin 1 includes power curve appearance portion 11 and cylinder appearance portion 12, be provided with the balancing weight 13 that weight can freely be adjusted in the power curve appearance portion 11, balancing weight 13 can be steel billet or lead, balancing weight 13 mainly is responsible for carrying out the focus position adjustment of this platform system, be provided with in the cylinder appearance portion 12 and fall the device 14 through the parachute-opening with this platform system recovery in the flight process, the parachuting device 14 is the technique that technical personnel in the field are comparatively familiar and ripe, this embodiment is not being repeated its theory of operation and structure again.
The equipment compartment 2 is fixedly connected with one end, far away from the power curve shape part 11, of the cylindrical shape part 12 through screws, an antenna window for mounting a telemetering antenna 21 and a navigation antenna 22 is formed in the side wall of the equipment compartment 2, electrical equipment is mounted in the equipment compartment 2, the electrical equipment comprises but is not limited to a comprehensive control computer 23, a telemetering integrated machine 24, a satellite navigation receiving and sending device 25 and a battery 26, a first sensor 27 is fixed on the inner side bulkhead of the equipment compartment 2, close to the load compartment 3, and the first sensor 27 is used for detecting impact and vibration.
The integrated control computer 23 is equivalent to the brain of the whole platform and is mainly used for performing functions of instruction issuing, power supply and distribution management, data processing, detection management and the like on the whole platform; the telemetering integrated machine 24 is connected with the integrated control computer 23 through a communication cable, and transmits important data back to the ground transmitting station through the telemetering antenna 21; the satellite navigation receiver-transmitter 25 mainly receives satellite positioning signals, and can receive the satellite positioning signals of GPS/GNSS/BD; the battery 26 is mainly used for supplying power to the integrated control machine, the telemetry all-in-one machine 24, the satellite navigation receiver-transmitter device 25 and the first sensor 27.
The load cabin 3 is fixedly connected with one end of the equipment cabin 2 far away from the nose cone cabin 1, the load cabin 3 comprises a cabin body framework and a shell piece, the shell piece is laid on the outer surface of the cabin body framework to form the cylindrical load cabin 3, a load 31, a release device 32 for pushing the load 31 away from the platform system at a certain relative speed and a cabin opening device 33 for separating the shell piece from the cabin body framework in the flying process are installed in the load cabin 3, and the power of the release device 32 comes from gas.
In the present embodiment, two sets of loads 31 are provided, the loads 31 include, but are not limited to, rockets and drones, the releasing device 32 is located between the two sets of loads 31, the cabin opening device 33 is provided at one end of the load cabin 3 close to the equipment cabin 2, the inner cabin wall of the load cabin 3 close to the power system cabin 4 is fixed with a second sensor 34, and the second sensor 34 is used for detecting impact and vibration.
In this embodiment, the cabin opening device 33 includes explosive bolts and spring thrust rods, the shell pieces are connected with the cabin body framework through a plurality of groups of explosive bolts, and the spring thrust rods are arranged in the middle of the two ends of the shell pieces.
The power system cabin 4 is fixedly connected with one end, far away from the equipment cabin 2, of the load cabin 3, an engine is arranged in the power system cabin 4, the power system cabin 4 is used as flying power of the platform system to ensure that the platform system flies to a specified height and ensures that the platform system flies in a specified speed range, the tail cabin 5 is fixedly connected with one end, far away from the load cabin 3, of the power system cabin 4, a tail conical nozzle 41 of the engine extends into the tail cabin 5, and the rudder wing combination is installed on the tail cabin 5 and the power system cabin 4.
In this embodiment, the casings of the nose cone cabin 1, the equipment cabin 2 and the tail cabin 5 are cast from high-performance aluminum alloy, the nose cone cabin 1 is treated by external application of aerogel at the part of the stagnation point of the nose cone, the outer surfaces of the casings of the nose cone cabin 1 and the equipment cabin 2 are coated with heat-insulating coatings, and then the nose cone cabin 1, the equipment cabin 2 and the tail cabin 5 all have very high structural strength, are not easy to damage, and have good sealing performance, and meanwhile, the heat-insulating coatings can avoid the equipment in the nose cone cabin 1 and the equipment cabin 2 from being influenced by high temperature.
In the embodiment, the rudder wing combination comprises two tail wings 6 and four groups of air rudders 7, wherein the two tail wings 6 are symmetrically arranged on the peripheral wall of the shell of the power system cabin 4, the tail wings 6 are parallel to the length direction of the power system cabin 4, and the four groups of air rudders 7 are symmetrically arranged on the tail cabin 5.
The air rudder 7 comprises a steering engine 71, rudder pieces 72 and rudder shafts 73, the steering engine 71 is installed between the tail conical nozzle 41 and the inner cabin wall of the tail cabin 5, openings for the rudder shafts 73 to penetrate through are formed in the cabin wall of the tail cabin 5, the rudder pieces 72 are located outside the tail cabin 5 and connected with the steering engine 71 through the rudder shafts 73, the four rudder pieces 72 are distributed in an X shape, and the tail wing 6 and the rudder pieces 72 are arranged at an included angle of 45 degrees.
The shape design of the rudder sheet 72 and the empennage 6 needs to be comprehensively considered by combining the aerodynamic performance of the platform system, the longitudinal pressure center of the whole platform system is moved backwards by increasing the area of the rudder wing combination, and the longitudinal pressure center of the platform system is moved forwards by the counterweight of the nose cone cabin 1, so that the static stability of the platform system is about 30 percent, and a large static stability layout is formed; according to the stability operating performance of the platform system, the control effect of the rudder piece 72 is not shielded by the wing surface of the empennage 6 under the whole flight enveloping condition (attack angle enveloping, speed enveloping, sideslip angle enveloping, height enveloping and the like), the characteristic values of the shapes, the areas, the extension lengths, the sweepback angles, the relative distances and the like of the control surface of the rudder piece 72 and the wing surface of the empennage 6 are optimized under the constraint conditions that the stability operating ratio is in proper areas and the like, and the proper shapes of the control surface of the rudder piece 72 and the wing surface of the empennage 6 are finally obtained by trying various different combinations.
In the embodiment, referring to fig. 2 to 4, a main body of the whole reusable flight test scattering platform system is of a cylindrical structure and has a diameter D, the value of D in the embodiment is about 400mm, the obtained appearance is as follows, the distance between the tail of the tail 6 and the tail of the rudder sheet 72 is 300mm, the rudder sheet 72 is in an inclined trapezoid shape, the chord length of the rudder root of the rudder sheet 72 is 400mm, the rudder of the rudder sheet 72 is slightly longer than 300mm, the extension length of the rudder sheet 72 is 400mm, and the sweep angle of the rudder sheet 72 is 75 degrees; the tail wing 6 is in a right trapezoid shape, the chord length of the lower bottom edge of the tail wing 6 is 800mm, the chord length of the upper bottom edge of the tail wing 6 is 600mm, and the height of the tail wing 6 is 150 mm. Of course, the corners of the tail fin 6 and the rudder sheet 72 are rounded.
Through the structural design, the tail wing 6 has little influence on the rudder deflection of the air rudder 7 within 10 degrees, and the center of pressure of the platform system moves backwards, and then the center of gravity of the platform system moves forwards by adding the balancing weight 13 to the head. Under the condition that the gravity center moves forwards and the pressure center moves backwards, the large static stability is achieved, about 30%, strong restoring moment is provided for external airflow impact and impact release, the aircraft can quickly return to the stable attitude, and good flight test conditions are kept.
The working process of the reusable flight test scattering platform system in the embodiment of the application is approximately as follows:
1) the platform system is loaded on the launcher according to a preset launching angle;
2) the power system is ignited, the platform system leaves the launcher, and after a specific speed is reached, the platform system controls the flying attitude of the platform system by controlling the rudder deflection of the air rudder 7;
3) after the ignition of the engine is finished, the platform system enters a climbing section, the platform system controls the flying attitude of the platform system by controlling the rudder deflection of an air rudder 7 and enters a release window condition (generally comprising speed, height and attitude angle);
4) the platform system pushes away the shell pieces by using a spring thrust rod by controlling the detonation of the explosive bolt; then releasing the first load 31 by the releasing device 32 according to the releasing requirement of the load 31;
5) after the load 31 is released, the platform system jumps suddenly on the attitude angle, the attitude is adjusted quickly by turning the rudder through the tail air rudder 7 and restoring torque of the platform system, and after the attitude requirement meeting the release is restored, the platform system releases the second batch of load 31;
6) repeating the step of the fifth step until all the loads 31 are released;
7) the platform system continuously and stably flies for a section and flies out of a release area, and the posture of the platform system is quickly adjusted by using a tail air rudder 7 until the preset posture angle for opening the umbrella is met;
8) the platform system flies to the parachute opening height, the nose cone cabin 1 parachute system works, and the parachute device 14 is opened;
9) the platform system reduces the flying speed under the action of the parachute landing device 14 until the platform system falls into a specified recovery area, and the recovery of the device is realized;
10) the device is dragged back to a maintenance workshop, the initiating explosive devices and the engine are replaced, the shell system is supplemented, and after comprehensive inspection is carried out, the device is reused.
The reusable flight test scattering platform system provided by the embodiment of the application has the following expectable technical effects:
the platform system is based on the development requirements of the existing micro ammunition technology and bee colony battle, a set of real and comprehensive flight verification platform system for simulating the aircraft throwing and releasing process is established, and verification means are added; the platform system is developed based on the characteristics of the aircraft, can cover the scattering requirement of the aircraft on various flight indexes and environments, and can realize full verification; the platform system has the advantages of low cost, high matching degree, repeated use and high safety and reliability, and the single flight price is dozens to millions.
The platform system changes the situation of insufficient test caused by the fact that the original high-speed flying scattering is simulated by using the airplane scattering, and greatly reduces the cost; the platform system is designed according to the pneumatic appearance, forms a layout design with large static stability, can quickly return to the stable posture by self-restoring moment after releasing the load 31, and enters the next release; the platform system is designed with a parachute recovery mode, can be used for multiple times, and reduces the test cost.
In general, the reusable flight test scattering platform system has the advantages of good coverage, more resources and low use cost.
The present invention is not intended to be limited to the particular embodiments shown and described, but is to be accorded the widest scope consistent with the principles and novel features herein disclosed.
Claims (9)
1. A reusable flight test dispersal platform system, comprising:
the nose cone cabin (1), the nose cone cabin (1) includes power curve shape portion (11) and column shape portion (12), the power curve shape portion (11) is provided with a balancing weight (13) whose weight can be freely adjusted, the column shape portion (12) is provided with an parachute landing device (14) which recovers the platform system by opening the parachute in the flight process;
the equipment compartment (2) is fixedly connected with one end, far away from the power curve outline part (11), of the cylindrical outline part (12), an antenna window for mounting a telemetering antenna (21) and a navigation antenna (22) is formed in the side wall of the equipment compartment (2), and electrical equipment is mounted in the equipment compartment (2);
the load cabin (3) is fixedly connected with one end, far away from the nose cone cabin (1), of the equipment cabin (2), the load cabin (3) comprises a cabin body framework and shell pieces, the shell pieces are laid on the outer surface of the cabin body framework to form the cylindrical load cabin (3), a load (31), a releasing device (32) for pushing the load (31) away from the platform system at a certain relative speed and a cabin opening device (33) for separating the shell pieces from the cabin body framework in the flying process are installed in the load cabin (3), and power of the releasing device (32) is derived from gas;
the power system cabin (4), the power system cabin (4) is fixedly connected with one end, far away from the equipment cabin (2), of the load cabin (3), and an engine is arranged in the power system cabin (4);
the tail cabin (5), the tail cabin (5) is fixedly connected with one end, far away from the load cabin (3), of the power system cabin (4), and a tail conical nozzle (41) of the engine extends into the tail cabin (5);
and a rudder wing assembly used for controlling the flight attitude of the platform system, wherein the rudder wing assembly is arranged on the tail cabin (5) and the power system cabin (4).
2. The reusable flight test spreading platform system of claim 1, wherein: the shell of the nose cone cabin (1), the equipment cabin (2) and the tail cabin (5) is formed by casting high-performance aluminum alloy, the nose cone cabin (1) is externally coated with aerogel at a nose cone stagnation part, and the outer surface of the shell of the nose cone cabin (1) and the equipment cabin (2) is coated with a heat insulation coating.
3. The reusable flight test spreading platform system of claim 1, wherein: the electrical equipment comprises but is not limited to a comprehensive control computer (23), a telemetering integrated machine (24), a satellite navigation receiving and sending device (25) and a battery (26), a first sensor (27) is fixed on the inner side bulkhead of the equipment cabin (2) close to the load cabin (3), and the first sensor (27) is used for detecting impact and vibration.
4. The reusable flight test spreading platform system of claim 1, wherein: the load (31) is provided with two sets, release gear (32) are located two sets between load (31), open cabin device (33) are located load cabin (3) are close to the one end of equipment cabin (2), load cabin (3) are close to be fixed with second sensor (34) on the inboard bulkhead of power system cabin (4), second sensor (34) are used for detecting impact and vibrations.
5. The reusable flight test spreading platform system of claim 4, wherein: the cabin opening device (33) comprises explosion bolts and spring thrust rods, the shell pieces are connected with the cabin body framework through a plurality of groups of the explosion bolts, and the spring thrust rods are arranged in the middle of two ends of the shell pieces.
6. The reusable flight test spreading platform system of claim 1, wherein: the rudder wing combination includes two fin (6) and four air rudder of group (7), two fin (6) symmetrical arrangement in the casing periphery wall of driving system cabin (4), fin (6) are on a parallel with the length direction of driving system cabin (4), four groups air rudder (7) symmetrical arrangement in on tail cabin (5).
7. The reusable flight test spreading platform system of claim 6, wherein: air rudder (7) are including steering wheel (71), rudder piece (72) and rudder axle (73), steering wheel (71) are installed conical spray tube of afterbody (41) with between the interior bulkhead of tail cabin (5), be equipped with the publication on the bulkhead of tail cabin (5) the trompil that rudder axle (73) passed, rudder piece (72) are located the outside of tail cabin (5) is passed through rudder axle (73) with steering wheel (71) are connected, four rudder piece (72) are "X" type and distribute, fin (6) with be 45 degrees contained angles between rudder piece (72) and arrange.
8. The reusable flight test spreading platform system of claim 7, wherein: the main body of the platform system is a cylindrical structure with the diameter of D, the distance between the tail of the tail wing (6) and the tail of the rudder sheet (72) is 0.75D, the rudder sheet (72) is in an inclined trapezoid shape, the rudder root chord length of the rudder sheet (72) is D, the rudder of the rudder sheet (72) is slightly longer than 0.75D, the extension length of the rudder sheet (72) is D, and the sweepback angle of the rudder sheet (72) is 75 degrees; the tail wing (6) is in a right trapezoid shape, the chord length of the lower bottom edge of the tail wing (6) is 2D, the chord length of the upper bottom edge of the tail wing (6) is 1.5D, and the height of the tail wing (6) is 0.375D.
9. The reusable flight test spreading platform system of claim 1, wherein: the load (31) includes, but is not limited to, rockets and drones.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111363321.4A CN114323713A (en) | 2021-11-17 | 2021-11-17 | Reusable flight test scattering platform system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111363321.4A CN114323713A (en) | 2021-11-17 | 2021-11-17 | Reusable flight test scattering platform system |
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| CN114323713A true CN114323713A (en) | 2022-04-12 |
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| CN202111363321.4A Pending CN114323713A (en) | 2021-11-17 | 2021-11-17 | Reusable flight test scattering platform system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115127401A (en) * | 2022-07-13 | 2022-09-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for reusing ballistic target free flight model |
| CN117073965A (en) * | 2023-10-16 | 2023-11-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Gas-driven model free flight test mass block scattering device and scattering method |
-
2021
- 2021-11-17 CN CN202111363321.4A patent/CN114323713A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115127401A (en) * | 2022-07-13 | 2022-09-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for reusing ballistic target free flight model |
| CN115127401B (en) * | 2022-07-13 | 2024-04-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Reuse method of ballistic target free flight model |
| CN117073965A (en) * | 2023-10-16 | 2023-11-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Gas-driven model free flight test mass block scattering device and scattering method |
| CN117073965B (en) * | 2023-10-16 | 2023-12-15 | 中国空气动力研究与发展中心超高速空气动力研究所 | Gas-driven model free flight test mass block scattering device and scattering method |
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