JP2715617B2 - Flying object - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Object of the invention]

(Industrial application field) The present invention relates to an observation bay road or the like which is housed in a projectile storage unit such as a nose fairing of a rocket and used for weather observation while descending separately from the projectile storage unit. About the flying object. (Prior Art) Conventionally, as the above-mentioned flying object, for example, there has been an observation payload for weather observation shown in FIG. As shown in FIG. 7 (a), this observation payload 101
Is a rocket shape in its entirety, and has a sound section 102 on its head, and an observation device behind the sound section 102 that analyzes data obtained by the sound section 102 and transmits the data to a ground station. A parachute container 105 having a built-in parachute 104 indicated by an imaginary line is provided on the rear side of the observation instrument section 103. The observation payload 101 is to be stored in the nose fairing 110 and the trunk case 111 that are the rocket projectile storage units.
At a predetermined altitude, the nose fairing 110 is extruded from the trunk case 111 by a payload pressing body 114 which moves by gas pressure when the nose fairing 110 is separated from the trunk case 111 by igniting the separating agent 112 provided in the trunk case 111, and The nose fairing 110 is released forward by the repulsive force of the separation spring 113 provided on the fairing 110. Then, the observation payload 101 separates from the nose fairing 110 and the trunk case 111 and then flies to the observation altitude. When the observation payload 101 reaches the observation altitude, as shown in FIG. Restraint band
By releasing the restraint by 106, the parachute container 105 is separated and the parachute 104 connected to the tail of the observation device unit 103 is opened, and weather observation is performed during the descent. In order to improve the storage rate of the observation payload 101 in the nose fairing 110 and the trunk case 111,
The center of gravity is set almost at the center of the whole, and accordingly, the observation payload 101 is designed to obtain aerodynamic stability during its flight. (Problems to be solved by the invention) However, in the observation payload 101, the observation equipment unit 1
When the specification of 03 and the sonde unit 102 is changed and the aerodynamic center is located on the front side in the flight direction from the center of gravity,
As the aerodynamic moment increases, the observation payload 101 rotates during the flight and the sonde unit 102 faces in the direction opposite to the flight direction as shown in FIG. 8, and the parachute 104 is opened in this state. In this case, the parachute 104 rushes from the tail side of the observation device unit 103, and as a result, it may hinder the descent of the observation payload 101 and may not be able to perform the observation satisfactorily. There was a problem. In order to avoid such a situation, the observation payload
It is possible to achieve aerodynamic stability by using aerodynamic stabilizing wings that can be folded in the circumferential direction of the 101 or housed inside, but it is difficult to reduce the size structurally in any case Therefore, there is no space between the observation payload 101 and the nose fairing 110 to accommodate the inside of the observation payload 101, so that these aerodynamic wings cannot be adopted. Therefore, it has been a conventional problem to solve these problems. (Object of the Invention) The present invention has been made in view of the above-mentioned conventional problems, and has no effect on the storage efficiency of a rocket in a flying object storage portion, and enables stable flight. For example, when a parachute is provided, an object of the present invention is to provide a flying object that can surely open the parachute on the rear side in the flight direction.

Configuration of the Invention

(Means for Solving the Problems) The present invention is directed to a flying object separated from a flying object storage portion of a rocket (including a missile), wherein a front end portion is fixed to an outer peripheral surface of a tail portion of the flying object and the rocket flies. When the flying object separated from the body storage part, the trailing end was elastically biased to be displaceable in the radial direction and folded between the leading edge of the wing and the outer peripheral surface at the tail of the flying object A plurality of aerodynamic stabilizing wings are provided in the circumferential direction, the aerodynamic stabilizing wings being provided in a state and being deployed when the trailing end portion of the wing leading edge portion is radially displaced and forming a wing surface. The configuration of such a flying object is a means for solving the above-mentioned conventional problems. In one embodiment, a foldable aerodynamic stabilizing wing storage portion for storing the wing surface portion of the aerodynamic wing in a folded state is provided on the outer peripheral surface of the tail of the flying object. The flying object according to the present invention can be used for an observation payload for weather observation and a warhead released from a missile, and is adopted for an observation payload that is designed to fly in an environment where air density is low. This is particularly preferred. (Effect of the Invention) In the flying object according to the present invention, while being stored in the flying object storage portion of the rocket, the aerodynamic stabilizing wing adjusts the wing surface so that the leading edge of the wing follows the outer peripheral surface of the flying object. Since it is folded, it does not affect the storage efficiency of the flying object. Also, when the flying object separates from the projectile storage section of the rocket, the center of the aerodynamic force flies by expanding the folded wing surface of the aerodynamic stability wing by the elasticity of the leading edge of the aerodynamic stability wing located at the tail of the flying object. As you move to the back of your body,
For example, aerodynamic stability will be ensured even when specifications change in the observation equipment section and the sonde section, and if a parachute is provided, this parachute will be securely opened behind the flight direction. It will be. Hereinafter, the present invention will be described with reference to the drawings. FIGS. 1 to 4 show an embodiment of a flying object according to the present invention. In this embodiment, a case where the flying object is an observation payload for weather observation is illustrated. That is, as shown in FIG. 1, the observation payload 1 forms a rocket as a whole, and has a sonde part 2 for collecting weather data at its head, and a tail part on the tail side of the sonde part 2 shown in FIG. As shown in (b), an observation equipment unit 5 is provided in a frame 4 and has an observation equipment 3 for analyzing the weather data and transmitting the data to the ground station. A certain tail is provided with a parachute container 8 having a built-in parachute 7 connected via a hook 6 provided at the rear end of the observation instrument section 5. The observation payload 1 is accommodated in a nose fairing 21 and a trunk case 22 as a flying object accommodation portion located on the tip side of the observation rocket 20 shown in FIG. 4 (a). In this case, the nose fairing 21 and the torso case 22
As shown in FIG. 4 (b), the nose fairing 21 is detachably connected by a plurality of connecting means 23 provided in the circumferential direction.
A separation spring 24 fitted in a compressed state on the outer peripheral portion of the sound section 2 is provided between the front end of the observation device section 5 and the front end of the observation instrument section 5.
And a payload pressing body fitted to the rear end of the parachute container 8 of the observation payload 1 and moved to the front end side of the trunk case 22 by high-pressure gas generated by the ignition of the separating agent 22a.
22b, and a separation timer 22c indicated by a virtual line for igniting the separation medicine 22a. When the nose fairing 21 and the body case 22 are separated from each other, the separation medicine 22a is ignited by the separation timer 22c, and the high pressure gas generated at this time causes the payload pressing body 22b to be moved to the front end side of the body case 22 together with the observation payload 1. By moving the nose fairing by the coupling means 23
The coupling between the observation payload 1 and the nose fairing 21 is released while the connection between the
At this time, the observation payload 1 is pushed out of the body case 22 by the high-pressure gas and the nose fairing 21 is repelled by the separation spring 24 as shown in FIG. 4 (c). Release by force. This observation payload 1 is a nose fairing
An aerodynamic stabilizing wing 10 is provided which is deployed when separated from the body 21 and the trunk case 22. A plurality of the aerodynamic stabilizing wings 10 are provided on the parachute container 8 located at the tail part in the circumferential direction. In this embodiment, as shown in FIG. In this case, as shown in FIG. 3, the aerodynamic stabilizing wing 10 has a front end portion 11a formed by screwing a front end portion 11a to an outer peripheral surface of a portion near the front end of the parachute container 8 via a holding plate 12 as shown in FIG. A thin film provided in a state of being folded in a bellows shape as shown by a solid line in FIG. 3 between the wing leading edge portion 11 fixed by 13, 13 and the wing leading edge portion 11 and the outer peripheral surface of the parachute container 8. Wing surface 14
And The wing leading edge 11 of the aerodynamic stabilizing wing 10 is made of a leaf spring in this embodiment. Due to the elasticity of the leaf spring, the trailing end portion 11b moves from the outer peripheral surface of the parachute container 8 to an imaginary line in FIG. In the state where the observation payload 1 is stored in the nose fairing 21 and the torso case 22, the front end of the torso case 22 is By part
The trailing end portion 11b of the wing leading edge 11 is arranged along the outer peripheral surface of the observation payload 1 against the repulsion due to its elasticity. In this embodiment, the wing surface portion 14 of the aerodynamic stabilizing wing 10 is made of a polyimide material, which is formed into a film shape, and is formed into a folded shape so as to be deployable. When the trailing end portion 11b of the blade leading edge 11 is displaced in the radial direction, the blade is unfolded to form a wing surface as shown by a virtual line in FIG. Further, in this embodiment, the parachute container 8
The aerodynamic stabilizing wing in which the wing surface portion 14 is folded
The provision of the folding aerodynamic stabilizing wing storage section 15 for storing the aerodynamic stabilizing wing 10 prevents the aerodynamic stabilizing wing 10 from moving in the circumferential direction when receiving an impact force such as when the observation rocket 20 is launched. That is, as shown in FIG. 4 (b), when the observation payload 1 is stored in the nose fairing 21 and the trunk case 22, the aerodynamic stabilizer 10 is compactly stored in the folded aerodynamic stabilizer storage unit 15. Because it can be folded and stored,
The storage efficiency of the observation payload 1 in the nose fairing 21 and the torso case 22 is not reduced,
As shown in FIG. 4 (c), when the observation payload 1 separates from the nose fairing 21 and the trunk case 22,
The aerodynamic stabilization wing 10 located at the tail of the fuselage deploys instantaneously in a dilute atmosphere, resulting in the observation payload 1
By moving the center of aerodynamic force toward the rear side in the flight direction, that is, toward the tail of the fuselage, aerodynamic stability can be ensured. Furthermore, the observation payload 1 is provided with a container restraining band 16 for restraining the parachute container 8 on the side of the observation equipment unit 5, and the observation payload 1 separated from the nose fairing 21 and the trunk case 22 flies and measures the observation altitude. At this point, the band release means 17 provided at the front end of the observation device section 5 is operated to release the restraint of the parachute container 8 by the container restraint band 16 as shown in FIG. The parachute container 8 is separated from the observation equipment unit 5 so that the parachute 7 can be opened. Next, a situation in which the observation payload 1 described above is separated from the nose fairing 21 and the trunk case 22 to perform observation will be described. First, as shown in FIG. 4 (b), when the nose fairing 21 and the trunk case 22 separated from the thrust generating unit 30 of the observation rocket 20 reach a predetermined altitude, the separation timer
The separation agent 22a is ignited by 22c, and the separation agent 22a burns. By the high pressure gas generated by the combustion of the separating agent 22a, the payload pressing body 22b moves in the trunk case 22 together with the observation payload 1 toward the front end thereof, so that the nose fairing 21 and the trunk case 22 are coupled by the coupling means 23. The state is released, and the pin 21b provided between the observation payload 1 and the nose fairing 21 is released.
Is cut off, and the observation payload 1 is moved by the movement of the payload pressing body 22b as shown in FIG. 4 (c).
The nose fairing 21 is pushed out of the nose 2 and is released in the flying direction by the repulsive force of the separation spring 24. At this point, the aerodynamic stabilizer 10 located at the tail
The aerodynamic stabilization wing 10 is formed in six places in the circumferential direction with good balance by the wing leading edge 11 being instantaneously displaced in the radial direction instantaneously by its elasticity and the folded wing surface part 14 being expanded, so that The aerodynamic center of the observation payload 1 was moved to the rear in the flight direction, and the aerodynamic
, The observation payload 1 flies to the observation altitude in an aerodynamically stable state. Then, when the observation payload 1 reaches the observation altitude, the band release means 17 is operated by a command from a control means (not shown), and as shown in FIG. Is released from the observation device unit 5. Subsequently, the parachute container 8 is separated from the observation device unit 5, the parachute 7 built in the parachute container 8 is led out and opened, and the sonde unit 2 and the observation device unit 5 collect and analyze weather data while descending. I do. (Evaluation Example) Next, the observation payload 1 in which the sweepback angle θ of the aerodynamic stabilizer 10 was set to 13 ° and the observation payload 1 in which the sweepback angle θ of the aerodynamic stabilizer 10 was 26 ° were each shown in FIG. Mach number
When the aerodynamic center position when placed in the uniform flow U∞ of φ = 90 ° in the uniform flow U∞ of φ = 0 ° which is 0.8, 0.9, and 1.0 was examined, the result shown in FIG. 5 was obtained. I got The reference line in FIG. 5 is the test result of the observation payload (1) without the aerodynamic stabilizer 10. As is clear from FIG. 5, the sweepback angle θ of the aerodynamic stabilizer 10
Is 13 ° and the sweep angle θ of the aerodynamic wing 10 is 26 ° in both cases, although the aerodynamic center is slightly different from the direction of the uniform flow U∞, It has been demonstrated that the robot moves about 70% from the tip to the rear in the flight direction. When the static stability coefficient C _L α in the direction was measured under the same conditions as described above, the results shown in FIG. 6 were obtained. Note that the reference line in FIG. 6 is the test result of the observation payload (1) without the aerodynamic stabilizer 10. As is clear from FIG. 6, since the value of the static stability coefficient C _N α was 5 or more in each case, it was proved that each observation payload 1 had sufficient static stability in the direction. Was. In this embodiment, the leading edge 11 of the aerodynamic stabilizer 10 is made of a leaf spring, and the rear end portion 11b can be displaced in the radial direction by the elasticity of the leaf spring. However, the present invention is not limited to this. Instead, for example, by providing an elastic body such as a coil spring between the wing leading edge and the parachute container, the rear end portion of the wing leading edge 11 can be provided.
It is also possible to make 11b radially displaceable.

【The invention's effect】

As described above, since the present invention has the above-described configuration, it is possible to perform aerodynamically stable flight without reducing the storage efficiency of the projectile in the projectile storage section of the rocket, and If the body is, for example, an observation payload for meteorological observation with a parachute, when the parachute is opened, the aerodynamic center has already moved to the tail side of the flying object due to the deployment of the aerodynamic stabilizer wing located at the tail. Therefore, the parachute can be reliably opened on the rear side in the flight direction, and as a result, there is an extremely excellent effect that normal observation can always be performed.

[Brief description of the drawings]

1 to 4 show an observation payload according to an embodiment of the flying object according to the present invention. FIG. 1 is an overall explanatory view showing a state where an aerodynamic stabilizer wing of the observation payload is deployed.
FIG. 3 is an explanatory view showing the observation payload shown in FIG. 1 as viewed from the rear, FIG. 3 is a partial perspective explanatory view showing the aerodynamic stabilizing wing in detail, and FIG. 4 (a) is an observation payload shown in FIG. 4 (b) is a cross-sectional view showing the observation payload shown in FIG. 1 stored in a nose fairing and a trunk case, and FIG. 4 (c) is a nose fair. Operation explanatory view showing a state immediately after the observation payload is separated from the ring and the trunk case, FIG.
Figure (d) is an operation explanatory diagram showing a state when the parachute of the observation payload is opened, and Figs. 5 and 6 show Mach numbers when a wind tunnel test is performed on the observation payload shown in Fig. 1. A graph showing the relationship between the Mach number and the static stability in the direction,
FIG. 7 (a) is an operation explanatory view showing a state immediately after the conventional observation payload is separated from the nozzle fairing and the trunk case, and FIG. 7 (b) shows a state when the parachute of the conventional observation payload is opened. FIG. 8 is an explanatory view showing the operation, and FIG. 8 is a view showing a situation where the conventional observation payload rotates and projects to the parachute. 1 ... Observation payload (flying vehicle), 10 ... aerodynamic wing, 11 ... wing leading edge of aerodynamic wing, 11a ... front end of wing leading edge, 11b ... ... trailing end of wing leading edge Part, 14: Aerodynamic stabilizing wing surface, 15: Folding aerodynamic stable wing storage unit, 20: Observation rocket, 21: Nose fairing (flying object storage unit), 22 ... Torso case (flying object storage) Department).

Claims (2)

(57) [Claims] 1. A flying object separated from a flying object storage portion of a rocket, wherein a front end portion is fixed to an outer peripheral surface of a tail portion of the flying object, and a rear end of the flying object is separated from the flying object storage portion of the rocket. A wing leading edge portion which is elastically biased so as to be displaceable in a radial direction, and a rear end of the wing leading edge portion which is provided in a folded state between the wing leading edge and the outer peripheral surface of the tail of the flying object. A flying object comprising: a plurality of aerodynamic stabilizing wings having a wing surface portion that expands when a portion is displaced in a radial direction to form a wing surface in a circumferential direction. 2. A flying object according to claim 1, further comprising a folded aerodynamic stabilizing wing housing portion for accommodating the wing surface of the aerodynamic stabilizing wing in a folded state on an outer peripheral surface at a tail portion of the flying object.